method for calculating a location on the liquid surface plane, method for simulating the behavior of

专利摘要:
CALCULATION OF LIQUID LEVELS IN CONTAINER RESERVOIRS WITH ARBITRARY FORMAT USING SOLID MODELING. The present invention relates to systems and methods for simulating the containment behavior of the liquid. The system comprises a solid modeler (26) and a non-linear equation solver (28). The nonlinear equation solver (28) takes as input the representation of the solid model (26) of the containment reservoir (22) from the solid modeler (26), a desired orientation (18) in space, the dynamic conditions (for example, lateral acceleration) and an amount of liquid. To find the liquid level (10) in the reservoir (22), the system solver iteratively performs the successive Boolean subtractions using an infinite horizontal half space (10) that represents the liquid level of the reservoir (18). The resulting cut solid model (26) is used to compute the volume of the liquid (12, 14, 16) at this level. The iterative system solver ends when the computed volume (12, 14, 16) of the cut-off containment reservoir (22) is compatible with the specified liquid volume (for example, fuel) at a given tolerance. To accommodate dynamic situations, for example, when acceleration is present, the horizontal plane of the liquid (10) is replaced by a plane (18) at an angle that corresponds to the total acceleration.
公开号:BR112013013946B1
申请号:R112013013946-3
申请日:2011-09-09
公开日:2020-12-29
发明作者:Sthephen L. Ray；Thomas A. Grandine；Jan H. Vandenbrande；Douglas A. Carr
申请人:The Boeing Company；
IPC主号:

专利说明:

BACKGROUND
[0001] The present invention relates to systems and methods for simulating containment reservoirs (hereinafter "containers") containing liquid. Such systems are useful, for example, in engineering simulations in the design phase of vehicles that carry liquid fuel. Such systems can also be used to reduce the number of sensors in a fuel tank to determine the fuel level, or to correlate liquid levels and volume amounts in geological formations such as water reservoirs and oil deposits.
[0002] It is known to compute fuel distributions on aircraft wings for different wing attitudes, different side and yaw angles and different wing deflections using rectangular cut-off approaches to the interior shape of the wing. This known solution has the following disadvantages: (1) it is linked to a specific geometric shape and topology (that is, a wing); (2) requires extensively formatted and reduced geometric representations of structural inputs to function; (3) uses approximate solution methods and therefore does not provide an accurate solution; (4) the existing software is written in FORTRAN, which is complex, difficult to maintain and difficult to improve; (5) the existing software is difficult to integrate with other solutions (for example, computing an airplane center of gravity subject to different flight angles); (6) the results of the analysis are exchanged through proprietary file formats that require custom encoding to read and write.
[0003] There is a need for improved systems and methods to appropriately compute liquid levels (also referred to herein as "locations on the plane on the surface of the liquid") for an arbitrarily shaped containment reservoir in different spatial orientations in static or dynamic (for example, the containment tank accelerates in a particular direction). BRIEF SUMMARY
[0004] The present invention is directed to systems and methods for calculating liquid levels in arbitrary full-shaped containers (for example, fuel tanks) using solid modeling techniques. Solid modeling encompasses a body of theories, techniques and systems focused on representations that allow the well-defined geometric properties of a represented solid to be calculated automatically. Many schemes for representing solids unambiguously are known. Limit representations are graphs whose nodes represent faces, edges and vertices, and whose links represent incidence and adjacency relationships. Most solid modelers provide support for Boolean operations on solid objects. Boolean operations are used in solid modeling to define solid objects through additions and subtractions of parameterized solid primitives such as cubes, cylinders and other limit representations.
[0005] To use solid modeling, application algorithms are required, which operate on representations of solids. Geometric algorithms manipulate the data (symbol structures) that represent the solids. In particular, the algorithms are well known for computing the volume, inertial moments, and other properties of geometrically complex solids.
[0006] The modalities disclosed in the present are limits for representing fuel tanks, but the present invention is not limited to using exclusively the representations of the fuel tank limit. The modalities disclosed in the present also use Boolean solid modeling operations to create a system for determining liquid levels in arbitrary full-shaped containers using exact computations in exact geometry. These modalities influence Boolean solid modeling operations to reduce the amount of code by an order of magnitude. These modalities do not rely on approximations. Given a volume of liquid and an arbitrarily shaped containment reservoir, the revealed modalities greatly simplify the computation of liquid levels and other properties such as the amount of usable and unusable liquid in different orientations of the reservoir, the accessibility of the liquid, area of exposed surface and wet surface area, height of the liquid at any location in the reservoir, and volume transfer with changes in orientation in the reservoir.
[0007] According to the modalities revealed in the present, the simulation system comprises a processor programmed with software that uses Boolean operations of solid modeling in combination with a nonlinear equation solver to compute the liquid level in a reservoir of arbitrarily shaped contention, for example, the fuel level in an aircraft wing.
[0008] More specifically, according to one modality, a solid modeler produces a representation of the limit of a containment reservoir for a non-linear equation solver. The solid model of the containment reservoir represents a shape by its limit, which consists of a set of faces that are joined at common edges to form a "waterproof" space envelope.
[0009] The nonlinear equation solver takes for granted the representation of the limit of the solid model of the containment reservoir, an orientation in the desired space, dynamic conditions (for example, lateral acceleration) and a quantity of liquid. To find the liquid level in the reservoir, the system solver iteratively performs successive Boolean subtractions using an infinite horizontal half space (or half space with another shape) that represents the liquid level of the reservoir. The resulting cut solid model is used to compute the volume of the liquid at that level.
[00010] The iterative system solver ends when the computed volume of the cut-off containment tank is compatible with the specified volume of liquid (for example, fuel) in a given tolerance. The result of the system solver is a representation of the limit of the liquid solid model that corresponds to the given volume. To accommodate dynamic situations, for example, when acceleration is present as in a curve or uphill, the horizontal plane of the liquid is replaced by a plane at an angle that corresponds to the total acceleration.
[00011] According to another modality, the simulation system is designed to accommodate the containment reservoirs with interior deflectors that form compartments or openings connected by narrow holes in the deflectors. The computation of the height of the liquid level (as previously described) is applied, first, in each individual compartment (ie, gap) to compute the initial height of the liquid. Then, the peak, which is the pressure produced by the differences in liquid levels between two switching reservoirs, is computed between each pair of connected spans. This information is then used to compute how the liquid flows between the gaps to level the liquid levels.
[00012] Representations of the liquid solid model and the containment reservoir can be used to greatly facilitate the derivation of reservoir properties, such as: (1) the exposed liquid area, which is simply the area of the top faces of the solid model (this property is important to estimate evaporation; (2) the wet area (the area that is touched by the liquid) when computing the areas of all faces of the representation of the solid model of the liquid that touches the faces of the reservoir ; (3) dipstick levels (the amount that a dipstick is submerged in the liquid) when intersecting a representation of the dipstick solid model with the representation of the liquid solid model (this is used to calibrate the dipsticks for indicate the volume of liquid); (4) the amount of liquid trapped by the compartments; (5) the amount of liquid transferred from one compartment to another when the orientation of the reservoir changes; and (6) distributes it weight of the fluid in the containment reservoir.
[00013] The functionality of the software disclosed in the present provides a general method for computing the liquid levels in arbitrarily shaped containers. Because the software is not tied to a specific format or topology (how things connect), it can be used in different applications, such as liquid levels in aircraft and automobile fuel tanks, water tanks and radiators, rocket propulsion levels, etc.
[00014] This software influences Boolean solid modeling operations to reduce the amount of code by an order of magnitude. This successively reduces the necessary maintenance of the software.
[00015] Furthermore, the liquid level calculation software does not have approximations. Due to the fact that the approximations are not carried out, the solutions are more accurate.
[00016] Also, the software can be incorporated into other software solutions. Due to the fact that the solution is embeddable, the need to transfer the results of the analysis in different formats is eliminated.
[00017] The software uses the actual CAD definition of the geometry of a containment reservoir instead of a discretized "linear FIG" approximation of the geometry. Because the software operates directly on the geometry, many data chat problems are eliminated.
[00018] Other aspects of the invention are disclosed and claimed below. BRIEF DESCRIPTION OF THE DRAWINGS
[00019] FIG. 1 is a representation of the solid model of a containment reservoir intersected by one face of another representation of the solid model, whose face represents the level of liquid in the containment reservoir as determined by an algorithm according to an embodiment. An angled point of view was chosen for the sake of clarity.
[00020] FIG. 2A is a representation of the solid model of an aircraft's conceptual wing.
[00021] FIG. 2B is a representation of the solid model of a 15% liquid fill in the wing represented in FIG. 2A, produced by the same algorithm used to produce FIG. 1.
[00022] FIG. 3A is a representation of the solid model of a conceptual wing with a 9 degree lateral tilt angle.
[00023] FIG. 3B is a representation of the solid model of a 15% liquid fill in the wing represented in FIG. 3A, produced by the same algorithm used to produce FIG. 1.
[00024] FIG. 4A is a representation of the solid model of a cylindrical containment reservoir.
[00025] FIG. 4B is a representation of the solid model of a 15% volume filling of liquid in the cylindrical containment reservoir shown in FIG. 4A, produced by the same algorithm used to produce FIG. 1.
[00026] FIG. 5 is a block diagram representing the components of a system for calculating the level of liquid in a containment reservoir according to an embodiment of the invention.
[00027] FIG. 6 is a flow chart showing an algorithm performed by the system depicted in FIG. 5.
[00028] FIG. 7 is a diagram of the top level model representing two subsystems of liquid volume (each representing a respective compartment or gap containing liquid) interfaced through a connection subsystem that performs liquid flow rate calculations according to a further embodiment of the invention.
[00029] FIG. 8 is a three-dimensional illustration showing the computations of the liquid level applied in two reservoirs that communicate at the beginning of a simulation.
[00030] FIG. 9 is a three-dimensional illustration showing the leveling of liquid between two reservoirs that communicate after the levels equalize.
[00031] FIG. 10 is a block diagram representing the calculations performed using commercially available software (ie, Simulink®, developed by MathWorks) to model, simulate and analyze the flow of liquid between the connected compartments or spans of a containment reservoir.
[00032] FIG. 11 is a three-dimensional illustration showing the multiple spans of a fuel tank in which the liquid becomes trapped by the inner deflectors.
[00033] Reference will be made hereinafter to drawings in which similar elements in different drawings have the same numerical references. DETAILED DESCRIPTION
[00034] Various modalities of a system for shaping and simulating the behavior of the liquid inside a fuel tank under dynamic conditions will now be described.
[00035] FIG. 1 is a representation of the solid model of a wing 2 comprising compartments 4, 6 and 8 for storing fuel. According to one embodiment of the invention, the representation of the solid model of the wing 2 is intersected by a face 18 of an infinite horizontal half space 10, whose face 18 represents the fuel level (that is, the level of the plane of the surface of the fuel) inside wing 2 given a 15% volume filling. An angled point of view was chosen for the sake of clarity.
[00036] As shown in FIG. 2A, compartment 4 of wing 2 is in fluid communication with compartment 6 through an orifice, and compartment 6 is in fluid communication with compartment 8 through an orifice. FIG. 2A shows wing 2 with a lateral tilt angle of 0 °. In contrast, FIG. 2B is a representation of the solid model of the fuel volumes within the wing 2 at a lateral tilt angle of 0 ° for a 15% volume fill. As seen in FIG. 2B, the fuel volume within the fuel tank compartments comprises the respective fuel volumes 12, 14 and 16. As best seen in FIG. 1, the fuel volume 12 is contained by compartment 4; the fuel volume 14 is contained by compartment 6; and the fuel volume 16 is contained by compartment 8.
[00037] As will be revealed in more detail later, a processor is programmed with the software that performs an algorithm to determine the location and orientation of the face 18 (representing the fuel level) as a function of the representation of the model of solid of the wing 2, the spatial orientation of wing 2, the amount of fuel contained within wing 2, and the dynamic conditions (for example, wing acceleration) that affect the fuel within wing 2.
[00038] For example, as the wing tilt angle of wing 2 changes, the position of the fuel within wing 2 changes. FIG. 3A is a representation of the solid model of the same wing 2 with an angle of lateral inclination of 9 degrees, while FIG. 3B is a solid model representation of the fuel volumes within wing 2 at a 9 ° side tilt angle for a 15% volume fill. As seen in FIG. 3B, the fuel volume within the fuel tank compartments 4 and 6 comprises the respective fuel volumes 12 'and 14'. There is no fuel in compartment 8 for the spatial orientation shown in FIG. 3A and with a 15% filling.
[00039] FIG. 4A is a representation of the solid model of a cylindrical containment container 22 oriented at an angle of 45 degrees. FIG. 4B is a representation of the solid model of a 15% volume filling of liquid 24 contained by the cylindrical containment reservoir 22 shown in FIG. 4A, produced by the same algorithm used to produce the images seen in Figures 1, 2A, 2B, 3A and 3B. This demonstrates the generic nature of the algorithm.
[00040] FIG. 5 is a block diagram representing the components of a system for calculating and displaying the level of liquid in a containment reservoir according to an embodiment of the invention. The system comprises a processor 20 programmed with solid shaper software 26 that uses Boolean solid shaping operations and a nonlinear equation solver 28 that computes the liquid level in an arbitrarily shaped containment reservoir, for example, the fuel level in an aircraft wing. The solid modeler 26 produces a representation of the limit of a containment reservoir for the nonlinear equation solver 28. The solid model of the containment reservoir represents a shape by its limits, which consists of a set of faces that are joined in common edges to form a "waterproof" space envelope. The nonlinear equation solver 28 takes the representation of the limit of the containment reservoir solid model, an orientation in the desired space (input A in FIG. 5), dynamic conditions (for example, lateral acceleration) (input B in the FIG. 5) and an amount (that is, volume) of liquid contained therein (entry C in FIG. 5). To find the liquid level in the containment tank, the system solver 28 performs iteratively, successive Boolean subtractions using an infinite horizontal half-space (for example, item 10 in FIG. 1) that represents the level of liquid within the reservoir. The resulting cut solid model is used to compute the volume corresponding to the liquid at that level. The iterative system solver 28 ends when the computed volume of the cut-off containment reservoir is compatible with the specified liquid volume (for example, fuel) within a given tolerance. The result of the system solver is a representation of the limit of the solid model of the computed volume of liquid. To accommodate dynamic situations, for example, when acceleration is present as in a curve or uphill, the horizontal surface plane of the liquid is replaced by a plane at an angle that corresponds to the total acceleration. This representation of the final liquid limit in dynamic conditions is then sent to a display device 30, which displays an image of the solid model of the containment container intersected by a horizontal liquid surface plane (for example, as shown in FIG. 1).
[00041] FIG. 6 is a flow chart showing an algorithm performed by the system depicted in FIG. 5. In step 32, the processor retrieves a representation of the solid model limit from the memory containment reservoir. In step 34, the processor retrieves the additional data from memory. According to a preferred embodiment, the additional data includes at least the following: the spatial orientation of the containment reservoir; the amount (that is, target volume) of liquid in the containment reservoir; and the magnitude and direction of acceleration (ie, vector of full acceleration) of the containment reservoir. In step 36, the processor determines the limits of a possible location on the liquid surface plane, the limits being a function of the spatial orientation, the target volume and the acceleration vector (that is, the acceleration vector is normal to the plane of the liquid's surface).
[00042] The tool can perform the methods to determine the limits of a solid, that is, the minimum and maximum x, y and z values of its limits. These limits can be thought of as two points that define the opposite corners of a "bounding box" that contains the solid. In conditions where only gravity acts on the liquid - that is, the total acceleration is perfectly aligned with the "inertial" z direction - the limits of the liquid are the z limits of the solid. In cases where the aircraft's additional accelerations cause the full acceleration vector to no longer align with the z direction, the container is first temporarily rotated until its full acceleration vector aligns with the z inertia direction. The tool then finds the boundaries of the rotated solid, defining a rotated "bounding box". The rotated solid is discarded, and the boundaries of its bounding box are rotated back to the original "inertial" coordinate system, in which a radius drawn between them contains a variation of location points for a plane of the liquid aligned with the vector acceleration.
[00043] More specifically, the limits are based on the computation of the bounding box of the solid model, with the bounding box oriented along the geometric axis of the current coordinate system (for example, the xy plane represents the "horizontal" plane, the component "z", the height in the "vertical" direction - with "vertical" meaning the direction of gravity plus any factor that is to accommodate other accelerations). How to compute the bounding box of a solid model is well known, although there are varying degrees of hardness in the "box" surrounding the solid model. The "z" component is the limit used by the modalities revealed in the present.
[00044] The revealed modalities compute a bounding box of a boundary representation when computing the bounding boxes of all underlying surfaces of the faces of the boundary representation, and then "combine" the boxes when computing the collective minima and maximums of the points extremities in each box in each direction of the coordinate. Consequently, the bounding box may be a little loose, but due to the computations performed, it does not matter.
[00045] So the problem is reduced to finding the bounding boxes of the surfaces, for which there is a variety of published methods. The revealed modalities use the tensor product splines to represent the surfaces and use the control polygon boundaries for the polynomial splines (the rational ones are more complex). However, this is just an exemplary modality and there are other published ways to compute the bounding boxes. Various methods of computing bounding boxes are revealed in the Handbook of Computer Aided Geometric Design, G. Farin et al. (editors), Elsevier B. V., Chapter 13 - Interrogation of Subdivision Surfaces, M. Sabin (2002).
[00046] In step 38, the processor makes a first guess (that is, a Nth guess, where N = 1) which refers to the location of the plane of the liquid's surface by means of linear interpolation, with such a first guess being locates between the limits previously determined in step 36. Then, the processor uses regularized solid modeling operations (ie, Boolean) to determine the volume of liquid below the location of the liquid surface plane according to the first guess (see step 40 in FIG. 6). The processor then compares the volume of liquid as determined in step 40 to the target volume (step 42) and determines whether the difference between them is acceptable (step 44). The test applied is whether the difference between the computed volume and the target volume is within a tolerance specified by the user (block 46 in FIG. 6). If the difference is not acceptable, a numerical method (for example, a method similar to Newton-Raphson) is used to make an improved guess as to the location of the plane of the liquid's surface (step 42). Using this improved guesswork, steps 42 and 44 are repeated. If the improved guesswork is unacceptable (step 42), then steps 48, 40 and 42 are repeated until the difference between the computed and target volumes is acceptable. If the difference is acceptable (step 44), the processor stores image data that represents the final guess as to the location of the liquid surface plane and / or a representation of the solid model limit of the computed volume of liquid in the reservoir, being that the upper face of the limit representation of the solid model is the plane of the surface of the liquid mentioned above (step 50). The processor also sends the image data to a display device (for example, a computer monitor) for display.
[00047] The numerical method for guessing the location of the liquid surface plane comprises finding successively better approximations to zero of a function equal to a difference between the volume of liquid below for the current guess for the location of the liquid surface plane and the liquid volume represented by said liquid volume data. The set of possible zero-finding methods includes both polynomial and derivative-based methods known in the art. Different applications can find benefit from any number of different approaches.
[00048] Referring further to FIG. 6, the iterations represented by steps 40, 42, 44 and 48 can be based on different, but fundamentally equivalent, approaches. For example, a first version of the source code subtracts a large block from a simulated wing to eliminate "empty space" using a regularized Boolean operator: cutsolid = solid - cutblock.Translate ([0,0, zrange * delta / 10.0]) where "-" is overloaded to mean regularized Boolean subtraction in solid BRep objects (representation of the limit). A second version uses a "Cut" command, which cuts a solid with an infinite plane and keeps only the part of the solid along the positive normal of the plane. Both versions achieve the same goal using different methods, and both are considered standard solid modeling operations.
[00049] The means of operation of the first version are a cutWing function (solid, height), which cuts an arbitrary solid in its given orientation with a large block at a given z value (that is, height), and a findwl function ( solid, volume), which uses a Newton-Raphson iteration to find the fuel level given a solid model of a containment tank and the fuel volume. In essence, it starts with a level guess and then iteratively refines the level by computing the volume of the cut solid model given a particular level.
[00050] The revealed modalities of the invention apply solid modeling techniques within a Newton method applied to find fuel levels. However, a Newton-Raphson method is only one possible way of solving this particular problem, that is, finding a height such that Volume (containment_solid - * big_block in z = height) - given_volume <ε where - * denotes the regularized Boolean subtraction, ε is defined for a small amount (due to the limited precision of oscillation point computations and limited computational resources), and big_block is a rectangular box with the bottom face parallel to the floor (conceptually) and sized such that it is larger than the containment reservoir represented by containment_solid. An infinitely large half space (as seen in FIG. 1) would also work. For some implementations, ε was set to 0.001 to 0.0001. Choosing too small a number leads to unstable Newton-Raphson behavior (or long computational times).
[00051] The cutWing function (solid, height) takes as input a solid model represented as a BRep ("solid") of a containment tank (fuel tank, bottle, septic tank, etc.) and a height parameter "hgt" represented as an actual value. The "hgt" height value represents the liquid level in the containment reservoir, which means that the solid and the height value both represent a common (and arbitrary) origin. It can also be assumed the presence of gravity (or an external force), which means that the direction of the force will be normal to the plane of the liquid surface in the containment reservoir. In this implementation, it is also assumed that the liquid is "at rest" and not splashing all over the place.
[00052] The cutWing routine uses the height value to return a solid model that represents the space occupied by the liquid in the containment reservoir. Conceptually, it does this by creating an infinite plane, cutting the solid with this plane and maintaining the part that is in the direction of positive gravitation. In one version, it is assumed that the containment reservoir is significantly smaller than the circumference of the planet, and the level of the liquid in the containment reservoir can be considered to be planar.
[00053] However, this can be trivially extended to cover reservoirs that are large in relation to the size of the planet by using a sphere (or other shapes) centered in the center of the body in vertical motion, and by adjusting the radius according to the relative position of the reservoir with respect to the common origin.
[00054] In the cutWing routine, this operation was implemented by creating a solid model representation of a large rectangular block, sized so that it is larger than the containment reservoir, and then, by positioning the block at a given height. Regularized Boolean operations were used to subtract the block from the containment reservoir to have a solid model representation of the liquid contained in the reservoir. It should be noted that, in some cases, there will be no return if the level is low in the containment reservoir, or it will return the entire containment reservoir if the level is above the reservoir.
[00055] The cutWing routine also implements a slight "delta" oscillation for the variable height in case the Boolean operation at the prescribed level fails. It basically swings the block up and down with small increases in "zrange" until a successful computation is returned. The zrange is defined as 1% of the maximum height of the reservoir. Typically, failures in Boolean operations are caused by problems that deal with the fact that the cutting surface is coincident with a face of a boundary representation. Boolean operations rely on the computation of many intersections between surfaces, and when two surfaces are partially coincident, the number of solutions reaches infinity (that is, instead of one or more curves, one reaches infinitely many curves, ie , a subset of the surfaces). The revealed system (and most CAD systems) has special code to detect the most common matches, but there are many cases where the Boolean operation will fail. Of course, there are many other reasons why a Boolean operation can fail (for example, errors), and the disturbance trick allows for recovery from those errors. It is also a very common technique used by most solid modeling systems internally.
[00056] The findwl function (solid, volume) uses the following parameters to find the fuel level: hlow, a variable to store the current lower height divider (hlow = zlower); vlow, a variable to store the current lower partition of the reservoir volume vlow = 0); hhigh, a variable to store the common upper height divider (hhigh = zupper); vhigh, a variable to store the current upper partition of the reservoir volume (vhigh = total); hmed, the mean of hlow and hhigh [hmed = abs (hhigh - hlow) * .5 + zlower]; vmed: the volume of the liquid in hmed [vmed = cutWing (solid, hmed) .Volume ()].
[00057] The Volume () function is a routine (defined in solid models) that computes the volume contained by the closed space by the faces of the solid model. A representation of the boundary of a volume is represented by a collection of faces that meet on common edges and create a "leak-proof" space envelope. The Area () function is a routine that computes this area of the part of the surface defined by "fit curves" that define a subset of the surface. Area () is used to compute the wet area of the reservoir, which represents this part of the total area of the reservoir that makes contact with the liquid, as well as the area of the "top" surface of the liquid (which is used to determine the rates of evaporation and such).
[00058] The previous algorithm uses the actual CAD definition of the geometry of a fuel tank instead of a discretized "linear FIG" approximation of the geometry. To compute the liquid level, the algorithm uses the exact solid modeling operations directly on the geometry of the original design. Boolean regularized solid operations perform the necessary intersections between the geometry followed by the classification to determine which parts of the intersecting surfaces to maintain.
[00059] As previously mentioned, many schemes for representing solids unambiguously are known. For example, the use of boundaries to represent a solid object is revealed by Requicha in "Representations for Rigid Solids: Theory, Methods, and Systems", ACM Computing Surveys, Vol. 12, No. 4, pages. 437 to 464 (December 1980). In addition, Boolean operations are used in solid modeling to define solid objects through additions and subtractions of parameterized solid primitives such as cubes, cylinders and other limit representations. For example, the use of Boolean subtractions to define solid objects is revealed by Requicha and Voelcker in "Boolean Operations in Solid Modeling: Boundary Evaluation and Merging Algorithms", Proceedings of the IEEE, Vol. 73, No. 1, pages. 30 to 44 (January 1985).
[00060] According to another modality, the simulation system is designed to accommodate the containment reservoirs with interior deflectors that form compartments or gaps connected by narrow holes in the deflectors. The computation of the height of the liquid level (as previously described) is applied, first, in each individual compartment (ie, gap) to compute the initial height of the liquid. Then, the peak, which is the pressure produced by the differences in liquid levels between two switching reservoirs, is computed between each pair of connected spans. This information is then used to compute how the liquid flows between the gaps to level the liquid levels.
[00061] An implementation of this modality uses Simulink® and MATLAB® software, commercially available from Mathworks, together with solid modeling software capable of representing solid objects as representations of the limit. MATLAB® is a numerical computing environment with a programming language. MATLAB® allows matrix manipulations, plotting functions and data, and implementations of algorithms. Simulink® is a tool for modeling, simulating and analyzing dynamic multi-domain systems. Simulink® is well integrated with the MATLAB® environment and can either trigger MATLAB® or be scripted from it.
[00062] In describing its physical modeling tools, MathWorks established that Simscape ™ extends Simulink® with tools for modeling systems that span mechanical, electrical, hydraulic and other physical domains such as physical networks. It provides fundamental building blocks for these domains to allow you to create custom component models. The Simscape ™ language based on MATLAB® enables text-based creation of components, domains and physical modeling libraries. The modalities of the invention revealed in the present use the physical modeling tools of Mathworks, but other physical modeling tools can be used.
[00063] In accordance with an embodiment of the invention to simulate the flow between a series of compartments or spans of a fuel tank that communicate through holes, the solver 28 (see FIG. 5) comprises multiple subsystems, which include a respective fuel volume subsystem to calculate the liquid level in each span and a respective connection subsystem (which uses blocks provided by the standard Mathworks) to calculate the flow rate through each orifice as a function of differentiating the liquid levels in every span. [These subsystems comprise respective sets of instructions executed by a processor.] It should be noted, however, that the invention is not limited to the case where the interconnecting element is an orifice. In real applications, there are numerous other types of interconnections between tanks, such as valve openings, tubes, tube slides that pass through pumps, valves and other devices, etc., which can be simulated.
[00064] For illustrative purposes, the exemplary subsystems for calculating the liquid levels in two fuel tank spans at least partially filled and the rate of liquid flow through an orifice connecting these spans will now be described. These calculations can be extended to cover a simulated fuel tank equipped with a sequence of at least three communicating spans, each span being at least partially filled with liquid fuel. The same procedures can be carried out between any multiple of solid objects, with any multiple of interconnecting elements.
[00065] FIG. 7 is a top-level simulation model diagram representing two fuel volume subsystems 52 and 54 (corresponding to the respective compartments or gaps that contain liquid connected through an orifice) interfaced through a third subsystem 56 that contains the information of connection. Each fuel volume subsystem 52, 54 represents the liquid fuel contained in a respective span or compartment and is interfaced with a respective single solid object (started using solid modeling software) that represents that same span or compartment in a tank of fuel. Connecting subsystem 56 performs liquid flow rate calculations that simulate the flow of liquid from one span to the other through the orifice. According to an implementation, connection subsystem 56 connects only blocks provided by Mathworks.
[00066] According to the implementation that is described, each fuel volume subsystem interacts with a solid object that represents a tank or a single span in a fuel tank. These objects must be loaded into the Simulink® workspace as an arrangement with names "Spans". The initial conditions for each fuel volume subsystem can be entered by the simulation operator using an instant window on a computer monitor. This pop-up window has two parameter fields respectively called "Span Number" and "Initial Volume". If there are multiple gaps in the arrangement, each gap must be configured in a respective initial volume of liquid. The span number for the span that is configured is inserted in the field called "Span Number". If there is only one object, the "Span Number" must be set to 1. The "Initial Volume" parameter defines the initial fuel volume for the simulation in the units [lenA3], where "len" is the unit used to define the solid. For example, if the solid was defined in inches, the initial fuel volume is defined in inA3. Also the same units are used to define the flow rate in the gap at the "dV [lenA3 / s]" port.
[00067] Still referring to FIG. 7, each fuel volume subsystem 52, 54 receives the data from the acceleration vector 58 which represents a vector of an acceleration of the containment reservoir that is simulated and the data from the rotation vector 60 which represent a vector of a spatial orientation ( that is, rotation relative to a frame of reference) of the containment reservoir that is simulated. The fuel volume subsystem 52 additionally receives data from an output port Out1 of the connection subsystem 56, while the fuel volume subsystem 54 receives data from the output port Out2 of the connection subsystem 56. The data output Out1 is the liquid flow rate dV (in volume units per second) for Gap 1 or out of it as calculated by connection subsystem 56 during the simulation of the liquid flow from one of Gaps 1 and 2 to the other span through a circular orifice with a specified diameter, while the Out2 data output is the liquid flow rate dV for the Gap 2 or out of it as calculated by the connection subsystem 56 during the same simulation. If the initial volume of liquid in Gap 1 is greater than the initial volume of liquid in Gap 2, then the liquid will flow from Gap 1 to Gap 2; alternatively, if the initial volume of liquid in gap 1 is less than the initial volume of liquid in gap 2, then the liquid will flow from gap 2 to gap 1. In any case, the flow rates for gap 1 and 2 will be equal in magnitude and opposite in direction. In the specific example shown in FIG. 7, the initial volume within Gap 1 is 6,000 while the initial volume within Gap 2 is 1,000.
[00068] Each of the fuel volume subsystem routes introduces a "S-Function" block in Simulink®. This provides the interface for the corresponding solid object when executing the custom embedded code. This S-Function code comprises a definition file named sFun_tanque.m which is implemented in a standard Mathworks model. The relevant bit of the custom code calls a "findFuelPlane" function that operates on a solid object. A line in sFun_tank.m is: block.OutputPort (1) .Data = findFuelPlane (rot, volume, 1, ... normal) findFuelPlane is the key operation. The entry "rot" is an indicator for a solid object with a specified spatial orientation. "volume" is a numerical double that represents the current volume of liquid within "rot". "normal" is a three-dimensional vector of numerical doubles that represent the vector of total acceleration that acts on the liquid. The findFuelPlane function returns a three-dimensional vector of numeric doubles that are a location point for the plane of the liquid's surface, that is, a plane defined by [oint, normal].
[00069] Referring again to FIG. 7, the flow through a circular orifice (of a specified diameter and at a specified height) in the division between Spans 1 and 2 is simulated using the standard Simulink® components. The "volume" entries in the findFuelPlane function are changed as liquid flows from one to the other. During the simulation, the liquid level determined by the solid modeling software is used to determine the "peak" pressure of the liquid above the orifice on each side of the room. Differential pressure due to non-uniform fuel levels triggers the flow through the orifice until the levels are equal.
[00070] At the start of the simulation system, the fuel volume subsystem 52 calculates the initial location of the liquid surface plane within Gap 1 as a function of the solid model object representing Gap 1, the initial volume of liquid in Gap 1, and the acceleration and rotation vectors, and produces those data for the input port In1 of the connection subsystem 56; and the fuel volume subsystem 54 calculates the initial location of the liquid surface plane within Gap 2 as a function of the solid model object representing Gap 2, the initial liquid volume in Gap 2, and the same vectors acceleration and rotation, and produces that data for the In2 input port of connection subsystem 56. At the same time, the solid model representations of the threshold solid and initial liquid levels in Spans 1 and 2 can be displayed in a display device.
[00071] FIG. 8 is a static image of the two solid objects and their volumes of liquid contained. The image represents the initial conditions of the simulation. The lines in bold represent limits of the volumes of liquid in the respective spans, while the lines without bold represent the solid walls of the respective spans that delimit the respective interior volumes that contain liquid. Not shown is a small circular hole between the gaps that allows the liquid to pass from one gap to the other.
[00072] Based on the objects in the solid model that represent Spans 1 and 2, the initial liquid levels in Spans 1 and 2, and the area of the orifice through which Spans 1 and 2 communicate, the connection 56 calculates the peak, which is the pressure produced by the differences in liquid levels between Spans 1 and 2. This information is then used to compute the rate at which the liquid flows between the spans to level the liquid levels. As the difference in liquid levels decreases, so does the flow rate, until, finally, the flow rate equals zero when the simulated liquid levels in Spans 1 and 2 become equal, as pictured in FIG. 9.
[00073] Although FIG. 8 depicts the display of the different liquid levels initially simulated on a computer monitor and FIG. 9 depict the display of the simulated liquid levels finally simulated on the same computer monitor, it should be noted that the display device preferably also continuously displays the simulated liquid levels as they transition from the levels depicted in FIG. 8 for those depicted in FIG. 9.
[00074] In response to any change in the acceleration or rotation vector subsequent to the equalization of the liquid level, the fuel volume subsystems 52 and 54 will calculate new locations for the liquid surface planes in Spans 1 and 2, respectively . In response to those new inputs on ports In1 and In2, the connection subsystem will recalculate and produce (on ports Out1 and Out2) the initial flow rate from one span to the other under these changed conditions. The connection subsystem 56 will then continue to calculate the flow rate until the liquid levels have equalized again.
[00075] The previous implementation allows dozens of mainframe Fortran programs to be replaced with a platform-independent toolkit designed to fit perfectly into the MATLAB® computing environment. The two spans with initial non-uniform fuel levels are connected by an orifice. The solid modeling software is used to calculate the respective heights (in relation to the elevation of the orifice) of the fuel in each span and Simulink® handles the flow from one span to the other. Figures 8 and 9 show a simulation for the first two spans of an external wing tank on the 747-8. Units are in inches in the wing reference plane coordinate system.
[00076] The fuel height information is calculated by passing the fuel volume to the solid object for each span and is returned as a three-dimensional location vector for the fuel surface plane (the normal of the plane in the case shown in FIG 7 is just [0 0 1]). For now, the aircraft remains static, so the third element is extracted from this vector and used as the height of the fuel plane, from which the z-location of the orifice is subtracted to obtain the relative height of the fuel to calculate the peak pressure. The conversion to peak is achieved by a series of gain blocks that represent the appropriate conversions, that is, P = rho * g * h.
[00077] Up to this point, everything is achieved either by calls to the solid modeling software or by using Simulink® signals, which are purely mathematical; it is after the peak is determined that the signal is converted to "Physical Signals" used by Simscape ™. The converted pressure signal is used to drive the Hydraulic Pressure Source which is connected at one end to an Atmospheric Reference and at the other end to an orifice. The hole is then connected to a mirror configuration in the second span. An exemplary fuel volume subsystem is depicted symbolically in FIG. 10. The Flow Rate Sensor is used to determine the resulting flow through the physical system, which is then converted back to a regular Simulink® signal in inA3 / s and integrated to provide volume updates for the solid object that represents the partially filled span.
[00078] Simulations can be conducted in which, the next refueling, the volume of fuel is preserved while the conditions of the aircraft change. To approximate a starting bearing, the "normal" input for the .slice or .cut methods is a full acceleration vector defined in MATLAB® as [-accel 0 1], where "accel" is the forward acceleration (direction x) in g's. A standardized MATLAB® function called "findFuelPlane" is used to determine the location point for the fuel plane.
[00079] In addition, the simulation may include changing the plane's pitch (up / down). In this case, the orientation of the fuel tank with respect to gravity varies in time as does the full acceleration vector. This is achieved using the "rotate" method of the solid object; the MATLAB® function "angle2dcm" (tool box in airspace) was useful to quickly generate the required directional cosine matrix input.
[00080] The various methods for integrating solid model objects into Simulink® have been tried successfully. In the method revealed above, a "Level-2 M-File S-Function" block was used. Other methods used an "Embedded Matlab Function" block or a "Matlab Fcn" block. All three blocks subsequently call the "findFuelPlane" function, which successively locates the fuel plane for an incoming fuel volume and the dynamic conditions that use a solid model object.
[00081] Because of the Java nature of objects, all three of these methods basically do the same thing - that is, they perform the findFuelPlane function on the regular MATLAB® instrument. Simulink® does not digest Java on its own, which limits the type of acceleration options that can be applied to streamline a simulation later on. Even in the Built-in MATLAB® Function, which pre-compiles the C code in m equivalent for faster execution, the findFuelPlane function is declared as "extrinsic", which means it is delivered to the regular MATLAB® instrument at run time instead of trying to precompile it.
[00082] FIG. 10 is a block diagram representing the calculations performed using Simulink® to model, simulate and analyze the flow of liquid between the compartments or spans of a containment reservoir.
[00083] Block 62 labeled "Vol 1" in FIG. 10 is a "Goto" block, which directs the signal to a corresponding "From" block. The From and Goto blocks allow you to pass a signal from one block to another without actually connecting them. In this case, the signal is simply routed to a data capture section to be plotted.
[00084] Block 64 labeled "Constant" is a Constant block, in this case set to 0.0, which is providing the "Fwd Acc" or forward acceleration component of a full acceleration vector for the tank model.
[00085] Block 66 labeled "Level-2 M-file S-Function" is exactly this. This S function provides the interface for the solid modeling software, and is an old version of the previously described block.
[00086] Block 68 labeled "h1" in FIG. 10 is a "For the workspace" block; it stores data in the program's memory in the MATLAB® workspace for use after the simulation ends.
[00087] The dark bar 70 directly to the right of block 66 is a Demux block. The Demux 70 block extracts the components from an input signal and sends the components as separate signals. The output signals are ordered from the top to the bottom output port. The "Fuel Plane" output of the S function is a three-dimensional array (representing the location point x, y, z of the fuel plane), and in the particular simulation depicted in FIG. 10, only the third element was of interest, the z value or the height of the liquid. Thus, the two upper signals that leave the end of the Demux block in the "Finisher" 72 blocks, while the third proceeds to the other operations. A "Finisher" block terminates an unconnected output port.
[00088] Block 74 labeled "Goto", with the inner label "h1" is a Goto block that leads to a graphical representation and data capture section, not shown.
[00089] Block 76 labeled "orifice height reference" is a Constant block, which in this case provides a z value (height) for the orifice through which the liquid flow is calculated. The output of block 76 is subtracted from the z value of the fuel plane using a circular block "Sum" 78, generating a product that represents the height of the liquid above the orifice, also called "peak height". In this case, the peak height sign represents a height in inches.
[00090] The peak height signal is then executed through a series of conversion multipliers that use the "Gain" blocks, multiply an input by a constant value (gain). Block 80 labeled "in2m" is a unit conversion from inches to meters; block 82 labeled "rho" is a multiplier for the density of the liquid; and block 84 labeled "g" is a multiplier for acceleration due to gravity in m / sA2. The product of these multipliers is the "peak pressure" in Pascals.
[00091] Block 86 labeled "HEAD 1" is a Goto block that directs peak pressure to the graphing and data capture section.
[00092] Block 88 with the internal labeling "S PS" is a "Simulink to Physical Signal" conversion block. It converts a regular Simulink® signal, the units of which are implied, to a SimscapeTM Physical Signal, the units of which are explicit. In this case, the Physical sign is declared in Pascals. Simulink® blocks represent basic mathematical operations. SimscapeTM technology makes it possible to create a representation of the system network under design, based on the Physical Network approach. According to this approach, a system can be represented as functional elements that interact with each other when exchanging energy through its doors.
[00093] Still referring to FIG. 10, the pressure signal output from the S-PS 88 block enters a "Hydraulic Pressure Source" 90 block. A Hydraulic Pressure Source block represents an ideal source of hydraulic energy that is powerful enough to maintain the pressure specified in its output regardless of the flow rate consumed by the system. Block connections T and P correspond to the hydraulic input and output ports, respectively, and connection S represents a control signal port. The hydraulic pressure source 90 provides an ideal pressure differential between ports P and T that is directly proportional to the input signal S. Block 90 implements the calculated peak pressure of the fuel above the orifice in the fluid network.
[00094] Pressure source T port 90 is defined as the "bottom" side of the pressure source. It is connected to a block 92 labeled "Output Area [inA2]". This is an orifice block that models the pressure and flow rate effects of a hydraulic orifice with a constant cross-sectional area. The Exit Area 92 block is connected to an "Exit Port" 94 that connects it to another diagram which is a mirror image of it, and calculates the peak pressure in Gap 2 instead of Gap 1.
[00095] Block 96 labeled "Ideal Hydraulic Flow Rate Sensor" simulates an ideal flow meter, that is, a device that converts the volumetric flow rate through a hydraulic line into a control signal proportional to this rate. flow. The sensor is ideal because it is responsible for inertia, friction, delay, pressure loss, etc. Block 96 measures the flow rate of the physical network as it crosses from port A to port B. The ports are connected to a hydraulic reference 97 on one side and to the peak pressure source 90 on the other. This sequence can be thought of as starting at atmospheric pressure above the liquid (the hydraulic reference), then adding the peak pressure (weight of the liquid above the orifice), before passing through an orifice. The higher the peak pressure, the greater the flow induced through the orifice. The Q connection is a physical signal port that outputs the flow rate value.
[00096] Block 98 labeled "inA3 / s" is a "Physical Signal to Simulink" converter block. In this case, it is emitting a Simulink® signal (that is, the units of which it is implied) that represents the flow rate in cubic inches per second. This flow rate enters a "Discrete Time Integrator" block 100 that integrates the flow rate in Gap 1 to keep track of the total volume of the liquid from within. Block 102 represents the entry of the initial fuel volume in Span 1 in block 100.
[00097] The final block 104 in the loop is a "Unit Delay", the function of which is to delay the output of the integrator 100 one step before it inserts the volume input of the S 66 tank calculator function. breaks what would otherwise be an algebraic loop, in which the block's output is used to define its input at the same time step.
[00098] In short, the loop calculates the peak pressure of the liquid above an orifice. This pressure then determines the flow rate through this orifice, and this flow rate adds or subtracts the volume of the liquid in the container, which successively affects the height of the liquid in the container, and then the peak pressure. In practice, any difference in the height of the liquid between the two compartments on either side of the orifice will induce a flow through the orifice until the heights are equal.
[00099] As previously revealed, the previous calculations can be extended to cover a simulated fuel tank equipped with a sequence of at least three communicating spans, each span being at least partially filled with liquid fuel. FIG. 11 shows an image representing fuel 108 in a 747 106 wing tank. This fuel tank has multiple communicating spans that can be simulated using the techniques disclosed at present.
[000100] A proof of concept was implemented in the solid modeling software using Jython and MATLAB®. Jython is an implementation of the Python programming language written in Java. A subsequent embodiment of the invention used MATLAB® to drive solid modeling software through its Java API to compute liquid levels.
[000101] Solid modeling software provides the ability to represent solid models as representations of the boundary and perform regularized Boolean operations on solid models such as subtracting, adding and intersecting, and the ability to compute the exact integral properties in models solid when implementing the divergence theorem. In particular, the solid model representation of the containment reservoir can be used to facilitate the derivation of the reservoir properties.
[000102] For example, the representations of the liquid solid model and the containment reservoir can be used to trigger the exposed liquid area within the containment reservoir, which is simply the top face area of the representation of the solid model of the liquid. This property is important for estimating evaporation. Fuel evaporation is calculated using Antoine's equation and the ideal gas law: Antoine's equation is a vapor pressure equation and describes the relationship between vapor pressure and temperature for the pure components:
where the steam pressure is, T the temperature and A, B and C are component specific constants. August's equation assumes heat of vaporization regardless of temperature. The evaporation (more technically "evolution") of atmospheric gases dissolved in a liquid is estimated using Ostwald's solubility coefficients and the ideal gas law. Should both effects be considered when analyzing the fuel tank's flammability, that is, when vapors are at risk of ignition in a fuel tank Flammability analysis is required to certify and effectiveness of a fuel tank Flammability Reduction System (FRS). Federal aviation regulation FAR 25,981 explains the mandate for an FRS.
[000103] Representations of the liquid solid model and the containment reservoir can also be used to trigger the wet area (the area that is touched by the liquid) when computing the areas of all faces of the representation of the liquid solid model that touches the faces of the reservoir. The wet area of the reservoir is used primarily in heat transfer calculations to predict fuel tank temperatures.
[000104] Many commercial aircraft have a set of "dipstick" indicators that provide a backup copy for the Electronic Fuel Quantity Indication System (FQIS). In the event that the amount of fuel cannot be determined by FQIS, aircraft operators can manually read the fuel height information in various parts of the tank from these "dipstick" type indicators, and then use this information with a set of pre-stored tables (provided by the aircraft manufacturer) to determine the amount of fuel in the tank. Representations of the liquid solid model and the containment reservoir can be used to derive the levels of the dipstick (the portion that a dipstick is submerged in the liquid) by intersecting a representation of the solid model of the dipstick with the representation of the liquid solid model (this is used to calibrate the dipsticks to indicate the volume of liquid). The calibration process is a process of fine-tuning and checking the tables to ensure accurate volume prediction based on the "dipstick" readings. Computer models, based on the invention disclosed in the present, can be used to generate the tables.
[000105] Furthermore, representations of the liquid solid model and the containment reservoir can be used to derive the amount of liquid trapped. When designing a fuel tank and aircraft system, it is essential to minimize the locations where the liquid becomes trapped (that is, it is not drained during normal operation). The locations of the trapped fuel are not only dead weight that cannot be used by the instruments, but they also provide the potential for collecting water (becoming a potential corrosion problem) and, in certain circumstances, freezing to form ice. Solid ice can present a blocking hazard that can prevent fuel from reaching the engines.
[000106] As revealed above with reference to Figures 7 to 10, representations of the liquid solid model and the containment reservoir can be used to derive the amount of liquid transferred from one compartment to another when the orientation of the reservoir changes. The throughput must be shown to be suitably fast to prevent fuel from accumulating on one side of a tank split during normal operations, especially during refueling when a large volume of fuel is being rapidly deposited in one part of the tank. tank and must flow freely to the others. Excessive fuel "not leveling" through a tank deflector can create undesirable structural stresses. On the other hand, deflectors must be restrictive enough to prevent all fuel from simultaneously falling into the primary structure in a high acceleration drop scenario.
[000107] Representations of the liquid solid model and the containment reservoir can be used to derive the weight distribution of the liquid in the containment reservoir. In an aircraft, center of gravity management is an important component of the performance, efficiency and manipulation of the aircraft's qualities. A full fuel tank represents a scalable proportion of the vehicle's entire weight, and small deviations in the distribution of this weight can have significant impacts on the factors mentioned above. It is important to make sure that the fuel's center of gravity remains within safe limitations in all operating conditions, and ideally that it is optimized so that the aircraft can achieve peak efficiency.
[000108] The algorithms for computing volume, moments of inertia, and other properties of geometrically complex solids are well known. For example, algorithms for computing the volume and other integral properties of solid objects are revealed by Lee and Requicha in Technical Memo 35a of Production Automation Project at the University of Rochester (March 1981); in "Algorithms for Computing the Volume and Other Integral Properties of Solids. I. Known Methods and Open Issues", Communications of the ACM, Vol. 25, No. 9, pgs. 635 to 641 (September 1982); and in "Algorithms for Computing the Volume and Other Integral Properties of Solids. II. A Family of Algorithms Based on Representation Conversion and Cellular Approximation", Communications of the ACM, Vol. 25, No. 9, pgs. 642 to 650 (September 1982). Computing the integral properties of solid objects that have curved faces is more difficult, but they have also been solved. See, for example, pages 603 to 622 of Handbook of Computer Aided Geometric Design, G. Farin et al. (editors), Elsevier B. V., Chapter 24 - Geometry Processing, Thomas A. Grandine (2002).
[000109] The invention has application in any situation that requires the accurate computation of fluid levels in full-format containment reservoirs and reservoirs that change orientations or that are subjected to dynamic forces. This includes domestic and international airlines and space companies, car and truck companies, ships and boats (for example, oil tankers), and possibly anyone interested in correlating fluid levels and volume quantities in geological formations such as water reservoirs. water and oil deposits.
[000110] The savings will be driven by increased accuracy to determine fluid levels in the aircraft's wings. Any discrepancy between the computed and actual values detected during physical calibration costs several orders of magnitude more to correct than when found early in the project.
[000111] The direct use of solid models (for example, imported from CATIA) will save weeks of work per model currently spent making those solids in highly formatted and very small arrays of point data to provide to the current tool.
[000112] The improved architecture (Jython / Java API and solid modeling software) will greatly improve the integration of analysis computing processes. This currently requires a significant amount of laborious and error-prone manual intervention between about two dozen applications.
[000113] The revealed modalities provide clear benefits when there is a need to simulate liquid-containing behavior, that is, when a physical system is not available, which includes analysis software, system test equipment and flight simulators . For example, the application revealed: (1) improving the accuracy of analysis tools and reduces the need for testing and post-test documentation calibration (for example, in new airplane programs); (2) produces a common enterprise module for computing liquid levels to facilitate the communication of results between business units (for example, this tool can be used for more accurate load computations); (3) can be applied in addition to the computations of the wing volume; (4) eliminates the time spent on data transfers and reduces errors due to data transfers; and (5) reduces legacy code maintenance efforts.
[000114] The revealed modalities can also be used to reduce cycle times in the calibration of fuel gauges and improves the estimation of unusable fuel. Greater confidence in the accuracy of these analyzes will reduce testing dependency, shorten development time by reducing post-test calibration of certification data, and reduce the risk of redoing the potential project. The shortened reorganization of the analysis results during the aircraft design will capture design problems sooner, and allow for more efficient exploration of alternative designs.
[000115] In the figures and the text, in one aspect, a method is revealed to calculate a surface location of the liquid in a containment reservoir 22, which comprises: a) storing a first data set comprising a representation of the solid model 26) of said containment reservoir 22; b) storing a second set of data representing a spatial orientation of said containment reservoir 22; c) storing a third set of data representing a quantity and the acceleration direction of said containment reservoir 22; d) storing the liquid volume data representing a liquid volume 12, 14, 16 in said containment reservoir 22; e) derive a first image data set representing a surface plane of said liquid in said containment reservoir 22, said first image data set being a function of at least said first to the third data sets and the said liquid volume data; and f) displaying said first image data set in intersection relation with a second image data set representing said containment reservoir 22 having said spatial orientation.
[000116] In a variant, the method includes in which said step of derivation comprises: i) selecting a current divination for the location of said surface plane of the liquid; ii) determine the liquid volume 12, 14, 16 below the current guess for the location of the liquid's surface plane using regularized solid modeling operations; iii) compare the volume of liquid 12, 14, 16 below the current guess for the location of the liquid surface plane to the volume of liquid 12, 14, 16 represented by said liquid volume data; iv) if the liquid volume 12, 14, 16 below the current guess for the location of the liquid surface plane is not close enough to the liquid volume 12, 14, 16 represented by said liquid volume data, use a method numeric to select a different current guess for the location of the liquid's surface plane; and v) repeat steps ii) to iv) until the volume of liquid 12, 14, 16 below the current guess for the location of the liquid's surface plane is sufficiently close to the volume of liquid 12, 14, 16 represented by said data volume of the liquid.
[000117] In another variant, the method includes in which said numerical method comprises finding successively better approximations of zero to a function equal to a difference between the volume of liquid 12, 14, 16 below the current guess for the location of the plane of liquid surface and liquid volume 12, 14, 16 represented by said liquid volume data. In yet another variant, the method additionally includes: storing a fourth set of data representing an area and an elevation of a door connected to said containment reservoir 22; and calculating a rate of liquid flow into or out of said containment reservoir 22 via said port, said calculated flow rate being a function of said first to fourth data sets and said volume data of the liquid, wherein said first set of image data is also a function of said fourth set of data. In yet another variant, the method additionally includes deriving a reservoir property 22 selected from the following group: the exposed liquid area; the wet area of said containment reservoir 22; and the weight distribution of the liquid in said containment reservoir 22. On one occasion, the method additionally includes intersecting a representation of the solid model 26 of a dipstick with a representation of the solid model 26 of said liquid in said containment reservoir 22.
[000118] In one aspect, a method is revealed to simulate the behavior of the liquid in a containment reservoir 22 that includes first and second compartments 4, 6, 8 that communicate through an interconnection, which includes: a) storing a first data set comprising a representation of the solid model 26 of said first compartment 4, 6, 8; b) storing a second data set comprising a representation of the solid model 26 of said second compartment 4, 6, 8; c) storing a third set of data representing a spatial orientation of said containment reservoir 22; d) storing a fourth set of data representing an area and an elevation of said interconnection between said first and second compartments 4, 6, 8; e) storing the first liquid volume data representing an initial liquid volume 12, 14, 16 in said first compartment 4, 6, 8; f) storing the second liquid volume data representing an initial liquid volume 12, 14, 16 in said second compartment 4, 6, 8; g) deriving a first image data set representing at least one initial surface plane of the liquid in said first compartment 4, 6, 8, said first image data set being a function of at least said first and third data sets and said first liquid volume data; h) derive a second set of image data representing at least one initial surface plane of the liquid in said second compartment 4, 6, 8, said second set of image data being a function of at least said second and third sets of data and said second liquid volume data; i) after steps g) and h), calculate changes in pressure due to differences in liquid levels 12, 14, 16 in said first and second compartments 4, 6, 8; j) for each change in pressure calculated in step i), calculate a liquid flow rate from one of the said first and second compartments 4, 6, 8 to the other, the said flow rate being a function of at least minus a respective change in pressure and said fourth data set; k) after steps i) and j), derive a third set of image data representing a later level of liquid 10 in said first compartment 4, 6, 8; l) after steps i) and j), derive a fourth set of image data representing a later level of liquid 10 in said second compartment 4, 6, 8; em) after steps k) and l), display said third and fourth sets of image data in relation to intersection with a fifth set of image data representing said first and second compartments 4, 6, 8 of said reservoir of containment 22 that has the said spatial orientation.
[000119] In a variant, the method additionally includes the step, performed after steps g) and h), of displaying said first and second sets of image data in relation to the intersection with said fifth set of image data. In another variant, the method additionally includes the step of storing a fifth data set representing a quantity and the direction of acceleration of said containment reservoir 22, in which said first and second image data sets are also a function of said fifth data set. In yet another variant, the method additionally includes the step, performed during step i), of displaying the image data representing the changing liquid levels in said first and second compartments 4, 6, 8. In yet another variant, the method includes in which step g) includes: i) selecting a current guess for the location of said surface plane of the liquid in said first compartment 4, 6, 8; ii) determining the volume of the liquid below the current guess for the location of the liquid's surface plane in said first compartment 4, 6, 8 using regularized solid modeling operations; iii) comparing the liquid volume below the current guess for the location of the liquid's surface plane in said first compartment 4, 6, 8 to the liquid volume 12, 14, 16 represented by said first liquid volume data; iv) if the liquid volume below the current guess for the location of the liquid's surface plane is not close enough to the liquid volume 12, 14, 16 represented by said first liquid volume data, use a numerical method to select a different current guessing for the location of the liquid's surface plane; and v) repeat steps ii) to iv) until the volume of the liquid below the current guess for the location of the liquid's surface plane is sufficiently close to the volume of the liquid 12, 14, 16 represented by the first dittos of liquid volume .
[000120] On one occasion, the method includes in which said numerical method comprises finding successively better approximations of zero for a function equal to a different one between the volume of liquid 12, 14, 16 below the current guess for the location of the plane of liquid surface and the liquid volume 12, 14, 16 represented by said liquid volume data. On another occasion, the method additionally includes deriving a reservoir property selected from the following group: the areas of the liquid exposed in said first and second compartments 4, 6, 8; the wet areas of said first and second compartments 4, 6, 8; the distribution of the weight of the liquid in said containment reservoir 22; the amount of liquid trapped by said first and second compartments 4, 6, 8; and the amount of liquid transferred from one of said first and second compartments 4, 6, 8 to the other when the orientation of said containment reservoir 22 changes.
[000121] In one aspect, a system is revealed to calculate a location on the liquid's surface plane in a containment reservoir 22 which includes: a processor 20 programmed to derive a first set of image data representing a surface plane of the said liquid in said containment reservoir 22, said first set of image data being a function of at least a first data set comprising a representation of the solid model 26 of said containment reservoir 22, a second set of data representing a spatial orientation of said containment reservoir 22, a third set of data representing a quantity and the acceleration direction of said containment reservoir 22, and liquid volume data representing a volume of liquid 12, 14, 16 in said containment reservoir 22; and a display device 30 for displaying said first image data set in said intersecting relationship with a second image data set representing said containment reservoir 22 having said spatial orientation.
[000122] In a variant, the system includes in which said drift operation comprises: i) selecting a current divination for the location of said liquid surface plan; ii) determine the liquid volume 12, 14, 16 below the current guess for the location of the liquid's surface plane using regularized solid modeling operations; iii) compare the volume of liquid 12, 14, 16 below the current guess for the location of the liquid surface plane with the volume of liquid 12, 14, 16 represented by said liquid volume data; iv) if the liquid volume below the current divination for the location of the liquid surface plane is not close enough to the liquid volume 12, 14, 16 represented by said liquid volume data, use a numerical method to select a divination different current for the location of the liquid's surface plane; and v) repeat steps ii) to iv) until the liquid volume 12, 14, 16 below the current guess for the location of the liquid surface plane is sufficiently close to the liquid volume 12, 14, 16 represented by said data volume of the liquid.
[000123] In another variant, the system includes in which said numerical method comprises finding successively better approximations of zero for a function equal to a difference between the volume of the liquid below the current guess for the location of the liquid's surface plane and the liquid volume 12, 14, 16 represented by said liquid volume data. In yet another variant, the system according to claim 14, wherein said processor 20 is additionally programmed to calculate a liquid flow rate into or out of said containment reservoir 22 by means of a door, being that said flow rate is a function of said first to third data sets, said liquid volume data, and a fourth data set represent an area and elevation of said port, wherein said first data set imaging is also a function of said fourth data set.
[000124] In yet another variant, the system includes in which said processor 20 is additionally programmed to derive a reservoir property selected from the following group: the exposed liquid area; the wet area of said containment reservoir 22; and the weight distribution of the liquid in said containment reservoir 22. On one occasion, the system includes wherein said processor 20 is additionally programmed to intersect a representation of the solid model 26 of a dipstick with a representation of the solid model 26 of said liquid in said containment reservoir 22.
[000125] In one aspect, a system is revealed to simulate the behavior of the liquid in a containment reservoir 22 comprising first and second compartments 4, 6, 8 communicating via an interconnect, comprising: a programmed processor 20 to perform the following operations: a) derive a first set of image data representing at least one initial surface plane of the liquid in said first compartment 4, 6, 8, said first image data set being a function of at least a first data set comprising a representation of the solid model 26 of said first compartment 4, 6, 8, a second data set representing a spatial orientation of said containment reservoir 22, and first volume data of the liquid representing an initial volume of liquid 12, 14, 16 in said first compartment 4, 6, 8; b) deriving a second image data set representing at least one initial surface plane of the liquid 18 in said second compartment 4, 6, 8, said second image data set being a function of at least a third data set comprising a representation of the solid model 26 of said second compartment 4, 6, 8, said second data set represents said spatial orientation of said containment reservoir 22, and second liquid volume data representing a initial volume of liquid 12, 14, 16 in said second compartment 4, 6, 8, c) calculating changes in pressure due to differences in liquid levels in said first and second compartments 4, 6, 8; d) for each calculated change in pressure, calculate a liquid flow rate from one of said first and second compartments 4, 6, 8 to the other, said flow rate being a function of at least one respective change pressure and said fourth data set; e) deriving a third set of image data representing a later level of liquid 10 in said first compartment 4, 6, 8; and f) deriving a fourth set of image data representing a posterior level of liquid 10 in said second compartment 4, 6, 8; and a display device 30 for displaying said third and fourth image data sets in intersection relation with a fifth image data set representing said first and second compartments 4, 6, 8 of said containment reservoir 22 which has said spatial orientation. In a variant, the system includes in which said third and fourth image data sets are a function of at least a fifth data set representing a quantity and the acceleration direction of said containment reservoir 22.
[000126] Although the invention has been described with reference to the various modalities, it will be understood by those skilled in the art that various changes can be made and the equivalents can be replaced by elements of them without departing from the scope of the invention. In addition, many modifications can be made to adapt a particular situation to the teachings of the invention without departing from its essential scope. Therefore, it is intended that the invention is not limited to the particular modality revealed as the best method contemplated for carrying out this invention.
[000127] The claims of the method established hereinafter should not be interpreted to require that the steps cited are performed in the order cited. In particular, no inference should be drawn from any alphabetical listing of the steps.

权利要求:
Claims (9)
[0001]
1. Computer-implemented method to calculate a location on the plane of the liquid surface (18) in a containment reservoir (22), comprising: (a) storing a first set of data comprising a representation of the solid model (26) of said containment reservoir (22); (b) storing a second set of data representing a spatial orientation (18) of said containment reservoir (22); (c) storing a third set of data representing a quantity and the direction of acceleration of said containment reservoir (22); (d) storing the liquid volume data that represents a liquid volume (12, 14, 16) in said containment reservoir (22); (e) derive a first set of image data representing a surface plane of said liquid (18) in said containment reservoir (22), said first set of image data being a function of at least said first to third data sets and said liquid volume data; and (f) displaying said first image data set in intersection relation with a second image data set representing said containment reservoir (22) having said spatial orientation (18); characterized by the fact that the said derivation stage comprises: (i) selecting a current divination for the location of said plane of the liquid surface (18); (j)) determining the volume of liquid (12, 14, 16) below the current guess for the location of the liquid surface plane (18) using regularized solid modeling operations; (k) i) compare the volume of liquid (12, 14, 16) below the current guess for the location of the plane of the liquid surface (18) to the volume of liquid (12, 14, 16) represented by said data of volume of the liquid; (l)) if the volume of liquid (12, 14, 16) below the current guess for the location of the plane of the liquid surface (18) does not correspond, within a given tolerance, to the volume of liquid (12, 14, 16 ) represented by said liquid volume data, use a numerical method to improve a current guess for the location of the liquid surface plane (18); and (v) repeat steps (ii) to (iv) until the volume of liquid (12, 14, 16) below the current guess for the location of the liquid surface plane (18) matches, within a tolerance, the liquid volume (12, 14, 16) represented by said liquid volume data; wherein said numerical method comprises successively finding better approximations to the zero of a function equal to a difference between the volume of liquid (12, 14, 16) below the current guess for the location of the plane of the liquid's surface (18) and for the liquid volume (12, 14, 16) represented by said liquid volume data.
[0002]
2. Method, according to claim 1, characterized by the fact that it additionally comprises: storing a fourth set of data representing an area and an elevation of a door connected to said containment reservoir (22); and calculating a rate of liquid flow into or out of said containment reservoir (22) by means of said port, said flow rate calculated being a function of said first to fourth data sets and said volume data liquid, wherein said first set of image data is also a function of said fourth set of data.
[0003]
3. Method according to claim 1, characterized by the fact that it additionally comprises at least one of: deriving a reservoir property (22) selected from the following group: an exposed liquid area; a wet area of said containment reservoir (22); and a weight distribution of the liquid in said containment reservoir (22); and intersecting a solid model representation (26) of a dipstick with a solid model representation (26) of said liquid in said containment reservoir (22).
[0004]
4. Method implemented by computer to simulate the behavior of the liquid in a containment reservoir (22) that comprises the first and second compartments (4, 6, 8) that communicate through an interconnection, which includes: (a) storing a first data set comprising a representation of the solid model (26) of said first compartment (4, 6, 8); (b) storing a second data set comprising a representation of the solid model (26) of said second compartment (4, 6, 8); (c) storing a third set of data representing a spatial orientation (18) of said containment reservoir (22); (d) storing a fourth data set representing an area and an elevation of said interconnection between said first and said second compartments (4, 6, 8); (e) storing the first liquid volume data representing an initial liquid volume (12, 14, 16) in said first compartment (4, 6, 8); (f) storing the second liquid volume data representing an initial volume of liquid (12, 14, 16) in said second compartment (4, 6, 8); (g) deriving a first image data set representing at least one initial liquid surface plane (18) in said first compartment (4, 6, 8), said first image data set being a function of at least minus said first and third data sets and said first liquid volume data; (h) deriving a second image data set representing at least one initial liquid surface plane (18) in said second compartment (4, 6, 8), said second image data set being a function of at least minus said second and third data sets and said second liquid volume data; (i) after steps (g) and (h), calculate changes in pressure due to differences in liquid levels (12, 14, 16) in said first and second compartments (4, 6, 8); (j) for each change in pressure calculated in step (i), calculate a liquid flow rate from one of said first and second compartments (4, 6, 8) to the other, said flow rate being calculated as a function at least one respective change in pressure and said fourth data set; (k) after steps (i) and (j), derive a third set of image data representing a later level of liquid (10) in said first compartment (4, 6, 8); (l) after steps (i) and (j), derive a fourth set of image data representing a later level of liquid (10) in said second compartment (4, 6, 8); and (m) after steps (k) and (l), display said third and fourth sets of image data in relation to the intersection with a fifth set of image data representing said first and second compartments (4, 6 , 8) of said containment reservoir (22) which has said spatial orientation (18); characterized by the fact that step (g) comprises: (i) selecting a current guess for the location of said liquid surface plane in said first compartment (4, 6, 8); (ii) determining the volume of liquid below the current guess for the location of the liquid surface plane (18) in said first compartment (4, 6, 8) using the regularized solid modeling operations; (iii) comparing the volume of liquid below the current guess for the location of the plane of the liquid surface (18) in said first compartment (4, 6, 8) to the volume of liquid (12, 14, 16) represented by said first liquid volume data; (iv) if the volume of liquid below the current guess for the location of the liquid surface plane (18) does not correspond, within a determined tolerance, to the volume of liquid (12, 14, 16) represented by said first data of volume of liquid, use a numerical method to improve a current guess for the location of the plane of the liquid's surface (18); and (v) repeat steps (ii) to (iv) until the volume of liquid (12, 14, 16) below the current guess for the location of the plane of the liquid's surface (18) matches, within a given tolerance , to the liquid volume (12, 14, 16) represented by said first liquid volume data; wherein said numerical method comprises finding successively better approximations to the zero of a function equal to a difference between the volume of liquid (12, 14, 16) below the current guess for the location of the plane of the liquid's surface (18) and of the liquid volume (12, 14, 16) represented by said liquid volume data.
[0005]
5. Method according to claim 4, characterized by the fact that it additionally comprises at least one of the following: the step performed after steps (g) and (h), of displaying said first and second sets of image data in relation to the intersection with said fifth image data set; the step of storing a fifth data set representing a quantity and the direction of acceleration of said containment reservoir (22), wherein said first and second image data sets are also a function of said fifth data set; and the step carried out during step (i), of displaying the image data representing the change in liquid levels in said first and second compartments (4, 6, 8); and deriving a reservoir property selected from the following group: the areas of the liquid exposed in said first and second compartments (4,6,8); the wet areas of said first and second compartments (4,6,8); a weight distribution of the liquid in said containment reservoir (22); the amount of liquid trapped by said first and second compartments (4,6,8); and the amount of liquid transferred from one of said first and second compartments (4,6,8) to the other when the orientation (18) of said containment reservoir (22) changes.
[0006]
6. System for calculating a location on the liquid surface plane (18) in a containment reservoir (22), comprising: a processor (20) programmed to derive a first set of image data representing a surface plane ( 18) of said liquid in said containment reservoir (22), said first image data set being a function of at least a first data set comprising a representation of the solid model (26) of said containment reservoir ( 22), a second set of data representing a spatial orientation (18) of said containment reservoir (22), a third set of data representing a quantity and the acceleration direction of said containment reservoir (22), and the liquid volume data representing a liquid volume (12, 14, 16) in said containment reservoir (22); and a display device (30) for displaying said first set of image data in said intersecting relationship with a second set of image data representing said containment reservoir (22) having said spatial orientation (18) ; characterized by the fact that the said drift operation comprises: (i) selecting a current divination for the location of said plane of the liquid surface (18); (ii) determine the volume of liquid (12, 14, 16) below the current guess for the location of the liquid surface plane (18) using regularized solid modeling operations; (iii) compare the volume of liquid (12, 14, 16) below the current guess for the location of the liquid surface plane (18) to the volume of liquid (12, 14, 16) represented by said volume data liquid; (iv) if the liquid volume below the current guess for the location of the liquid surface plane (18) does not correspond, within a determined tolerance, to the liquid volume (12, 14, 16) represented by said volume data of liquid, use a numerical method to improve the current divination for the location of the plane of the liquid's surface (18); and (v) repeat steps (ii) to (iv) until the volume of liquid (12, 14, 16) below the current guess for the location of the liquid surface plane (18) matches, within a given tolerance , to the liquid volume (12, 14, 16) represented by said liquid volume data; wherein said numerical method comprises finding successively better approximations to the zero of a function equal to a difference between the volume of liquid below the current guess for the location of the plane of the liquid's surface (18) and the volume of liquid (12, 14, 16) represented by said liquid volume data.
[0007]
7. System according to claim 6, characterized by the fact that it includes at least one of: wherein said processor (20) is additionally programmed to calculate a liquid flow rate into or out of said reservoir of contention (22) by means of a door, said flow rate being a function of said first to third data sets, said liquid volume data, and a fourth data set representing an area and an elevation of said door, wherein said first image data set is also a function of said fourth data set; wherein said processor (20) is additionally programmed to derive a reservoir property selected from the following group: the exposed liquid area; a wet area of said containment reservoir (22); and a weight distribution of the liquid in said containment reservoir (22); and wherein said processor (20) is further programmed to intersect a representation of the solid model (26) of a measuring rod with a representation of the solid model (26) of said liquid in said containment reservoir (22).
[0008]
8. System according to claim 6, characterized by the fact that the system is used to simulate the behavior of the liquid in a containment reservoir (22) comprising the first and second compartments (4, 6, 8) that communicate through an interconnection, comprising: a processor (20) programmed to perform the following operations: (a) derive the first set of image data that represents at least one plane of the initial surface of the liquid (18) in said first compartment (4, 6, 8), said first image data set being a function of at least the first data set comprising a representation of the solid model (26) of said first compartment (4, 6, 8 ), the second data set represents a spatial orientation (18) of said containment reservoir (22), and the first data of liquid volume (12, 14, 16) represent an initial volume of liquid in said first compartment (4 , 6, 8); (b) deriving a second set of image data that represents at least one plane of the initial liquid surface (18) in said second compartment (4,6,8), said second set of image data being a function of at least minus a third data set comprising a representation of the solid model (26) of said second compartment (4,6,8), said second data set represents said spatial orientation (18) of said containment reservoir (22 ), and the second liquid volume data represents an initial liquid volume (12, 14, 16) in said second compartment (4, 6, 8), (c) calculating changes in pressure due to differences in liquid levels in said first and second compartments (4, 6, 8); (d) for each calculated change in pressure, calculate a liquid flow rate from one of said first and second compartments (4, 6, 8) to the other, said flow rate being a function of at least one respective change in pressure and a fourth set of data representing an area and an elevation of said interconnection between first and second compartments; (e) deriving a third set of image data representing a later level of liquid (10) in said first compartment (4, 6, 8); and (f) deriving a fourth set of image data representing a later level of liquid (10, 12, 14) in said second compartment (4, 6, 8); and a display device (30) for displaying said third and fourth image data sets in relation to intersection with a fifth image data set representing said first and second compartments (4, 6, 8) of said reservoir containment (22) which has the said spatial orientation (18);
[0009]
9. The system according to claim 8, characterized by the fact that said third and fourth image data sets are a function of at least a fifth data set representing a quantity and the direction of acceleration of said reservoir of image containment (22).

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