• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The examples show rotorcraft multi-zone heater systems (100) and methods of operation thereof. An exemplary rotorcraft system (100) includes multiple blades (110, 112) coupled to a rotor (108) and multiple blade surfaces (110, 112) divided into sections. A given blade includes an inner and outer section. The system also includes a plurality of first heating systems on the respective outer sections of the multiple blades (110, 112), a plurality of second heating systems on the respective inner sections of the multiple blades (110, 112), and a control unit (102). coupled to the first and second heating systems. The respective systems of the multiple blade sections (110, 112) are fed in a sequence based on the outside temperature of the air.
    公开号:FR3028242A1
    申请号:FR1560776
    申请日:2015-11-10
    公开日:2016-05-13
    发明作者:Edward W Brouwers；Andrew A Peterson
    申请人:Boeing Co；
    IPC主号:
    专利说明:

    [0001] The present invention generally relates to an aircraft or rotorcraft system that provides anti-icing or de-icing. BACKGROUND OF THE INVENTION In other examples, methods and systems for de-icing single-rotor or multi-rotor vehicles are provided by concentrating power to the systems when necessary. Supercooled water droplets can freeze during an impact with a leading edge of a rotor blade or rotorcraft in the presence of a combination of near-freezing temperatures, high velocities and high cloud water. Helicopter and tilt-rotor blades or a rotorcraft operating at sub-freezing temperatures tend to accumulate ice along a large portion of the leading edge of the blades. As ice accumulation alters a geometry of the stagnation point of the blades, the performance of the vehicle decreases. Irregularly distributed rotor ice adhesion can create raster increases, separation of air streams, and high vibration levels. The increase in the screen generated by the accumulated ice increases the torque necessary to maintain the lift conditions of the vehicle. Transmission or engine limits may be reached as the ice thickness increases, making it difficult to maintain a given flight condition for a pilot.
    [0002] Ice shedding is another problem caused by ice accumulation on rotating blades. The shear stresses created by centrifugal forces at an interface between the ice and the leading edge of a bearing surface increase linearly with the thickness of the ice. When the shear stresses exceed a maximum shear adhesive strength of the ice, ice chips are released. The impact of the unloaded ice could cause damage to the aircraft. As the ice breaks off unevenly, an imbalance in the rotor mass generates unwanted vibrations and changes in the maneuvering of the vehicle. To avoid large amounts of ice formation on the rotor blades, the industry has adopted a standard de-icing system for a limited number of helicopter models. The industry standard defrost system uses thermal energy to melt accumulated ice. Electrothermal de-icing systems are the only ice protection systems certified by the Federal Aviation Administration (FAA) and accepted by the Department of Defense (DoD) for rotorcraft. The thermal defrosting mechanism operates only periodically to avoid excessive energy consumption or excessive heating of the leading edge blade. The ice thickness can reach up to 1 cm before the thermal system is turned on. Such a system requires large powers (for example 3.9 W / cm 2 or 25 W / in 2) and contributes to an undesirable increase in the weight and overall cost of the blade. The deicing system may not provide flight safety over the entire icing area, as the system may not be able to cope with critical ice accumulation rates. Because of these drawbacks, many helicopters do not use de-icing capabilities, limiting the operations of these vehicles in adverse conditions. For a rotorcraft using de-icing systems, because of the need for significant amounts of energy to operate such electrothermal de-icing systems, rotors of multi-rotor aircraft are typically de-iced in sequence. This reduces the peak power demanded on board the aircraft, but the power requirement still limits the use of the de-icing system. In addition, the alternating defrost is likely not to cope with critical ice accumulation rates and may ultimately limit the all-weather capability of the aircraft. In one example, a system for a rotorcraft is provided comprising multiple rotor-coupled blades and multiple blade surfaces divided into sections, and a given blade includes an inner section extending from the rotor outward and a section outer portion extending from the inner section to an end of the given blade. The system also includes a plurality of first span heating systems included on respective outer sections of the multiple blades, a plurality of second spanwise heating systems included on respective inner sections of the blades. multiple, and a control unit coupled to the plurality of first span heating systems and the plurality of second spanwise heating systems. The respective heating systems of the multiple blade sections are fed (in energy, for example by electric current) during a sequence based on the outside temperature of the air and the gravity of the icing.
    [0003] Another example provides a system comprising multiple blades coupled to a rotor and multiple blade surfaces divided into sections, and a given blade includes an inner section extending from the rotor outwardly and an outer section extending from the inner section to one end of the given blade. The system also includes a plurality of first span heating systems included on respective outer sections of the multiple blades, a plurality of second spanwise heating systems included on respective inner sections of the blades. multiple, and a control unit coupled to the plurality of first span heating systems and the plurality of second spanwise heating systems. The control unit is configured to cause the respective heating systems of the multiple blade sections to be powered (in energy, for example by electric current) during a sequence based on whether the sections are internal or external and on one or more icing conditions of a system environment.
    [0004] In another aspect, there is provided a method comprising detecting one or more icing conditions of a rotorcraft environment, and the rotorcraft includes multiple blades coupled to a rotor and the multiple blades include a first set of blades. and a second set of blades, and the surfaces of the multiple blades are divided into sections such that a given blade includes an inner section extending from the rotor outward and an outer section extending from the inner section to one end of the given blade. The method also includes providing, by a control unit, power (e.g., electrical current) to a plurality of first span heating systems included on respective outer sections of the first set of blades and the second set of blades, and supplying, by the control unit, energy to a plurality of second spanwise heating systems included on respective inner sections of the first set of blades. The method further includes supplying, by the control unit, energy to the plurality of first span heating systems included on respective outer sections of the first set of blades and the second set of blades. and providing, by the control unit, energy to a plurality of second spanwise heating systems included on respective inner sections of the second set of blades. The features, functions and advantages that have been analyzed can be achieved independently in various embodiments or can be combined in still other embodiments, where more details can be examined with reference to the following description and accompanying drawings. .
    [0005] The considered new features of the illustrative embodiments are set forth in the appended claims. Illustrative embodiments however, as well as a preferred mode of use, other objects and descriptions thereof, will become more apparent upon reading the following detailed description of an illustrative embodiment of the present invention. in connection with the accompanying drawings, in which: Figure 1 is a block diagram of an aircraft, according to one embodiment; FIG. 2 illustrates a block diagram of a computing device, according to one embodiment; FIG. 3A illustrates an example of a blade, according to one embodiment; Figure 3B illustrates a side view of a blade with heating systems, according to one embodiment; FIG. 4A is an example of a rotorcraft having a main single rotor and four blades, according to one embodiment; FIG. 4B illustrates the blades of the rotorcraft of FIG. 4A, according to one embodiment; FIGS. 5A-5D illustrate an example of a heating system operating sequence for a single rotor aircraft, according to one embodiment; FIG. 6A is an example of a multiple rotor rotorcraft and three blades for each rotor, according to one embodiment; Figure 6B illustrates the front rotor blades, and the rear rotor blades of the rotorcraft of Figure 6A, according to one embodiment; Figs. 7A-7D illustrate an example of a heating system operating sequence for a multi-rotor aircraft, according to one embodiment; and Figure 8 shows a flowchart of an exemplary method of operating heating systems on a rotorcraft, according to one embodiment. Embodiments are described in greater detail below with reference to the accompanying drawings, in which some embodiments are shown, but not all. Indeed, several different embodiments can be proposed and they should not be considered as limited to the embodiments set out below. On the contrary, these embodiments are provided so that the disclosure is detailed and complete and to convey the full scope of the invention to those skilled in the art. Examples provide de-icing systems and methods of operation for use on a rotorcraft. An example of a rotor de-icing system includes heaters installed in a leading edge of a blade, and the heaters may have a thickness of about 0.0025 "(about 0.0635 mm) to be integrated in an upper spar of a composite blade arrangement For the defrosting operation, one objective of the heaters is to rapidly raise the temperature of the ice / rotor interface above approximately 32 ° F (ie 0 ° C) A temperature above about 40 ° F (about 4.5 ° C) is usually required.The heating process melts an ice interface, allowing the centrifugal force inherent in the rotating blades to remove ice from a surface of the blade For this reason, a layer of ice is usually detected before activation of the heating element Heat applied too slowly or to thin ice accumulations may not eliminateice because the centrifugal forces may not be large enough to overcome the ice / rotor connection. In such cases, the ice may then melt locally and liquid water may flow to other parts of the blade and freeze again. This process, called runoff, can be problematic since a re-freezing location may be outside of an area protected by the heating elements and the ice can not be removed by additional pulses of the heating element.
    [0006] Depending on the structure of the blade, an electrothermal Icing protection system may require powers of the order of 25 WSI (Watt per square inch or about 3.9 Wcm-2) to achieve a desired surface temperature with number of minimum power-ups. This may require a high demand to the electrical system of the aircraft. In the examples, to reduce the peak power required, the heating elements are divided into surfaces or zones. These zones are fed in a specific sequence to defrost the blade, and this sequence can be adapted to icing conditions. Examples of areas on a blade include two zones in the sense of the span of an inner zone and an outer zone. Areas of the span configuration may range from a blade root to a blade tip. The heating elements on the multiple blades are defrosted in sequence using a three-phase AC system or a DC power source depending on the blade model. The cycle time between the heating elements is regulated so as to eliminate ice accumulation continuously on the blades and prevent the formation of ice. A root section of the blade may be able to tolerate longer durations between heater trips because this section accumulates ice at lower rates.
    [0007] Referring to the figures, FIG. 1 is a block diagram of an exemplary aircraft 100, according to one embodiment. The aircraft 100 comprises a control unit 102 coupled to a power source 104 and to a sensor (s) 106. The control unit 102 is furthermore coupled to a rotor 108 which is connected to blades 110. and 112. Each blade 110 and 112 may include an outdoor heater 114 and an indoor heater 116. In some examples, the aircraft 100 may include multiple rotors (e.g., such as a front and rear rotor) and, therefore, Fig. 1 illustrates a possible second rotor 118 coupled to the control unit 102, which also includes blades 120 and 122. Each blade 120 and 122 also includes an outdoor heater 124 and a system The aircraft 100 may thus be representative of a single rotor rotorcraft with an even number of multiple blades (e.g., four or more blades) or a multiple rotor rotorcraft. (for example, two rotors including a rotor with and a rear rotor, where each rotor may include three or more blades, a helicopter with two side rotors equipped with a left rotor and a right rotor, each rotor may include three or more blades or a coaxial helicopter equipped with an upper rotor and a lower rotor, each rotor may include three or more blades). The control unit 102 may be configured to operate the heating systems on the blades 110, 112, 120 and 122, and to provide current (energy) from the power source 104 for this purpose. The control unit 120 may receive outputs from the sensors 106 to determine when to initiate the operation of the heating systems. The sensors 106 may include temperature sensors for sensing the ambient air temperature, or moisture content sensors for sensing a humidity level in the air. The sensors 106 may more generally include sensors for determining the icing conditions of an environment of the aircraft 100.
    [0008] Each blade 110, 112, 120 and 122 includes an outdoor heating system and an indoor heating system. For example, blade surfaces may be divided into sections including an inner section extending from the rotor outwardly and an outer section extending from the inner section to an end of the given blade. Outdoor heating systems 114 and 124 and interior heating systems 116 and 126 may each be configured as spanwise heating systems, and the control unit 102 may control the operation of the heating systems. during a sequence based on the outside temperature of the air, the icing conditions detected from the environment, or in such a way that the operation is based on the fact that the sections are interior or exterior and on one or several icing conditions of the system environment. FIG. 2 illustrates a block diagram of an example of a computing device 200. The computing device 200 of FIG. 2 may represent the control unit 102 shown in FIG. 1. In some examples, certain components illustrated in FIG. Figure 2 may be distributed between multiple computing devices. However, by way of example, the components are shown and described as part of a device 200. The computing device 200 may include an interface 202, a wireless communication component 204, a sensor (s) 206 , a data storage 208 and a processor 210. The components illustrated in FIG. 2 can be linked together by a data link 212. The computing device 200 can also include hardware to enable communication within the computing device. 200 and between the computing device 200 and another computing device (not shown), such as a server entity. The equipment may include transceivers, receivers and antennas, for example. The interface 202 may be configured to allow the computing device 200 to communicate with another computing device (not shown), such as a server or device on the floor. Thus, the interface 202 may be configured to receive input data from one or more computing devices, and may also be configured to send output data to one or more computing devices. In some examples, the interface 202 may also store and manage databases received and sent by the computing device 200. The interface 202 may also include a receiver and a transceiver for receiving and sending data. The wireless communication component 204 may be a communication interface that is configured to facilitate wireless data communication for the computing device 200 in accordance with one or more wireless communication standards. For example, the wireless communication component 204 may include a Wi-Fi communication component, or a cellular communication component. Other examples are also possible, such as proprietary wireless communication devices. The sensor 206 may include one or more sensors, or may represent one or more sensors included in the computing device 200. Examples of sensors include air temperature sensors, moisture sensors (or water content sensors) ), etc., or all of the sensors shown in FIG. 1 can be integrated in the computing device 200. Additional sensors may also be included, such as a current monitoring sensor for controlling the power taken at the source of the sensor. supply, shown in Figure 1, for each heating system. The data storage 208 may store program logic 214 that is accessible and executable by the processor 210. The data storage 208 may also store data collected by the sensors or data relating to a heating sequence 216 to power the data storage systems. heating according to a desired sequence. Figure 3A illustrates a blade 300, according to one embodiment. A spanwise axis and an axis in the direction of the rope are illustrated, and a leading edge is located on one side of a stagnation line, while a trailing edge is opposite the edge attack. The heating systems can be placed on a surface or inside the blade. Figure 3B illustrates a side view of the example of blade 300 equipped with heating systems. An indoor heating system 302 is placed on an inner section which extends from a rotor outward, and an outer heating system 304 is placed on an outer section which extends from the inner section to an end of The blade 300. FIG. 4A is an example of a single rotor rotorcraft 402 and four blades 404, 406, 408 and 410, according to one embodiment. FIG. 4B illustrates the blades 404, 406, 408 and 410 of the rotorcraft 400 of FIG. 4A, according to one embodiment. In Fig. 4B, each of the blades is divided into an inner section 412 which extends outward from the rotor, and an outer section 414 which extends from the inner section 412 to one end of the blade 404. The section Inner 412 and the outer section 414 (of each blade) each include spanwise heating systems such that the heaters extend along a length of the blade. For example, as shown on the blade 404, the inner section 412 includes spanwise heating systems 416, 418 and 420, and the outer section 414 includes spanwise heating systems 422. , 424 and 426. All blades can be configured in the same way. In addition, although only three heating systems are shown for each section, more or less heating elements can be provided. Each heating system 416-426 is coupled to a control unit, as shown in Figure 1. Each heating system 416-426 can be individually controlled to limit energy consumed during deicing operations. The operation of the heating systems 416-426 on each of the blades 404-410 can be performed during a sequence based on a measured water content indicative of the severity of icing, and / or air temperatures. For example, based on an air temperature of less than 32 ° F (ie, about 0 ° C), (or about at a temperature corresponding to freeze conditions or below freezing conditions), the heating systems can be activated. The sequence of operations can be repeated until icing conditions are cleared for the system to deactivate. FIGS. 5A-5D illustrate an example of a sequence of heating operations for a single rotor airplane. The blades illustrated in FIGS. 5A-5D are the blades 404-410 as described in FIGS. 4A-4B. The multiple blades may include a first set of blades 404 and 408 (opposed to each other) and a second set of blades 406 and 410 (opposite each other). In a first step, as shown in Fig. 5A, the outer sections of the first set of blades 404 and 408, and the outer sections of the second set of blades 406 and 410 may be energized. Thus, all heating systems on the outer sections can be powered. In the examples, the respective heating systems are fed in the rope direction from a leading edge to a trailing edge of a respective blade. For example, as shown on the blade 404, inside the outer section 414, the heating element 426 can be fed first, followed by the heating element 424 and then followed by the heating element 422. The elements External heaters remaining on the blades 406, 408 and 410 may be fed in the order represented by the arrows shown in Figure 5A. In this way, less current (power) is needed to power all the heating elements simultaneously, and the leading edges of the blades can be fed first. In a second step, as shown in Figure 5B, the inner sections of a set of blades 406 and 410 may be energized. Thus, following the supply of all the outer sections, the respective inner sections of a set of blades can be powered. For example, the blade 410 is illustrated with an outer section 430 and an inner section 428, and the inner section 428 includes heating systems 432, 434 and 436. The interior heating systems 432, 434 and 436 can be powered in a such that the heating element 432 is energized first, followed by the heating element 434 and then by the heating element 436 so as to feed from a leading edge to a trailing edge when the rotor rotates the blades counterclockwise as shown in Figure 5B. In a third step, illustrated in Figure 5C, the outer sections of the first set of blades 404 and 408, and the outer sections of the second set of blades 406 and 410 are fed again. This is a repetition of step 1, as illustrated in Figure 5A. In a fourth step, as shown in Figure 5D, the inner sections of a set of blades 404 and 408 are energized. Thus, the remaining two interior sections that were not powered in the second stage are now energized to turn on all sections of all the blades. As illustrated in FIG. 5D, the inner section 412 may be energized such that the heating element 420 is energized first, followed by the heating element 418, and then the heating element 416. Using the As illustrated in FIGS. 5A-5D, the heating systems of the multiple blade sections are fed during a sequence based on the outside temperature of the air and the severity of the icing, and the sequence includes the heating of the sections. outer sections of the multiple blades more frequently than the heating of the inner sections of the multiple blades. The outer sections are heated twice more during the sequence. Following the heating of an interior section, all exterior sections are heated. The inner sections of each set of blades are heated only half-way through the sequence so as to reduce a heating amount of the inner sections, which allows for additional heating on the outer sections while using less space. of energy (and / or current) in total. Steps 1-4 as illustrated in Figures 5A-5D are repeated until the aircraft exits a freezing cloud, or until icing conditions are no longer present, for example. In some examples, based on the fact that an outside air temperature is above a threshold value, for example, 40 ° F (about 4.5 ° C), the respective heating systems of the Multiple blade sections may be fed during a sequence in which the heating systems included on the respective outer sections of the blades are removed from the sequence. In this example, called icing conditions in hot weather, heating the ends of the blades may not be necessary and energy can be saved. In other examples, based on the fact that the outside temperature of the air is below a threshold value, for example, 10 ° F (about -12 ° C), the respective heating zones of the sections multiple blades may be fed during a sequence in which the heating systems included on the respective outer sections of the blades are removed from the sequence. In this example, more attention can be paid to the outer sections due to extreme icing conditions. Deletion of one section of the sequence may occur during one (or more) cycle (s) during the sequence, and the section may be reintroduced into the sequence in subsequent cycles. FIG. 6A is an example of a rotorcraft 600 with multiple rotors 602 and 604 and three blades for each rotor, according to one embodiment. In FIG. 6A, the rotorcraft 600 includes a front rotor 602 and a rear rotor 604. As shown, the front rotor 602 can be placed near a forward end of the rotorcraft 600 and the rear rotor 604 can be placed near a Figure 6B illustrates examples of blades 606, 608 and 610 of the front rotor, and examples of blades 628, 630 and 632 of the tail rotor, according to one embodiment. Although FIG. 6A illustrates an aircraft equipped with a front and a rear rotor, the heating system described below may alternatively or additionally be implemented on a multiple rotor aircraft in which the rotors are configured as left and right rotor, or as upper and lower rotor, for example. In Fig. 6B, each of the blades is divided into an inner section 612 which extends from the rotor outward, and an outer section 614 which extends from the inner section 612 to one end of the blade 610. Each blade of each rotor (front and rear) can be configured in the same way. The inner section 612 and the outer section 614 (of each blade) each include spanwise heating systems such that the heaters extend along a length of the blade. For example, as shown on the blade 610, the inner section 612 includes spanwise heating systems 616, 618 and 620, and the outer section 614 includes spanwise heating systems 622. , 624 and 626. All blades can be configured in the same way. In addition, although only three heating systems are shown for each section, a larger or smaller number of heating elements can be provided. Each heating system 616-626 is coupled to a control unit, as shown in FIG. 1. Each heating system 616-626 of each blade and of each rotor can be controlled individually to limit the energy consumed during the deicing operations. The operation of the heating systems on each of the blades 606-610 and 628-632 can be performed during a sequence based on a measured moisture content (moisture content) indicative of the severity of the icing, and / or the air temperatures. For example, if we consider an air temperature below 32 ° F - that is, 0 ° C- (or approximately at a temperature corresponding to freezing conditions or below freezing conditions), the heating systems can be activated. The sequence of operations may be repeated until icing conditions have been removed for the system to stop.
    [0009] Figs. 7A-7D illustrate an example of a sequence of heating operations for a multi-rotor aircraft. The blades illustrated in FIGS. 7A-7D are the blades 606, 608, 610, 628, 630 and 632 as described in FIGS. 6A-6B. The front rotor and the rear rotor each include a set of blades. In a first step, as shown in Fig. 7A, the outer sections of the multiple blades on the front rotor and the rear rotor are energized. Thus, all heating systems on the outer sections can be powered. In the examples, the respective heating systems are fed in the rope direction from a leading edge to a trailing edge of a respective blade. For example, as shown on the blade 610, in the outer section 614, the heating element 622 can be fed first, followed by the heating element 624 and then followed by the heating element 626. The remaining external heating elements on the Other blades may be powered in the order indicated by the arrows shown in Figure 7A. In this way, less current (and less energy) is needed to power all the heating elements simultaneously, and the leading edges of the blades can be fed first. In addition, three cycles can be performed to perform the first step of this sequence, although more or fewer cycles can be used depending on the number of section heating systems.
    [0010] In a second step, as shown in Fig. 7B, the inner sections of the multiple blade set of the tail rotor are energized. Thus, following the supply of all the outer sections, the respective inner sections of the rotor are fed. For example, the blade 632 is illustrated with the outer section 634 and the inner section 636, and the inner section 636 includes heating systems 638, 640 and 642. The interior heating systems 638, 640 and 642 can be fed into a such that the heating element 642 is the first, followed by the heating element 640, then the heating element 638, and the remaining inner sections are fed in the order indicated by the arrows in FIG. 7B. Again, three cycles are used to perform the second step of this sequence because three heating systems are installed on the rear inner sections. In a third step, as shown in FIG. 7C, the outer sections of the set of multiple blades on the front rotor and on the rear rotor are fed again. This is a repetition of step 1 as shown in Figure 7A. In a fourth step, as shown in Fig. 7D, the inner sections of the set of multiple blades on the front rotor are energized. Thus, the remaining two interior sections that were not powered in the second stage are now energized to turn on all sections of all the blades. As shown in FIG. 7D, the inner section 612 of the front rotor can be powered so that the heating element 616 is fed first, followed by the heating element 618 and the heating element 620. The remaining inner sections of the blades on the front rotor are fed in the order indicated by the arrows in Figure 7D. Steps 1-4 as shown in Figs. 7A-7D are repeated until the aircraft exits an icing cloud or until the icing conditions are no longer present, for example. In some examples, a peak power reduction of up to 40% can be achieved (compared to systems without dual heating zones) with the concept of distribution zone described herein. Using the configuration as shown in FIGS. 7A-7D, the respective heating systems of the sections of the multiple blades are fed in the direction of the rope so that for the outer sections and inner sections of the multiple blade set on the front rotor, the sections are fed from a leading edge to a trailing edge of a respective blade, and, for the outer sections and inner sections of the multiple set of blades on the tail rotor, the sections are fed from a leading edge to a trailing edge of a respective blade, in a direction of rotation of the respective rotors. In some examples, such as during hot weather icing protection (for example, when air temperatures are close to 32 ° F (0 ° C), the outer sections of the blades (eg extremities) may not need to be heated due to kinetic heating, so current can be saved by not feeding such sections In such examples, the heating systems on the blades front and rear rotor can be fed during a sequence including the inner sections of the tail rotor (for example, three cycles to cover the three independent heaters), followed by the inner sections of the front rotor (for example, three cycles) to cover the three independent heating elements.) In other examples, the heating of the inner sections of the multiple blades is removed from the sequence, allowing the outer sections of the game multiple blades on the front rotor and rear rotor to be fed more frequently, such as when outside air temperatures are below a threshold and / or more severe icing conditions are present. In the examples, labeling of the sampling element is provided below in Table 1 in which the inner and outer sections of the front and rear rotors are divided into zones including areas labeled 1-6 (from the rotor and moving towards the end). More or less areas may be included in the root and end sections. Rotor Zone ID Rotor Area ID Rotor Area ID Front 1 1 Rear 1 11 Ends 1 21 forward / backward 2 2 2 12 2 22 3 3 3 13 3 23 4 4 4 4 5 5 5 15 6 6 6 16 Table 1 One Example of a feeding sequence g for an outside temperature of -20 ° C may include zones 2, 3, 4, 1, 5, 6 for the inner sections (to heat first inwards and the surfaces external zones), and the outer zones are triggered in a sequence 2, 3, 1, 4. The distribution zone system (inner and outer) allows the end heating elements to be triggered between each heating sequence forward or backward , now the ends of pale without ice. Higher pulse frequencies allow blade working sections to remain free of significant ice accumulation and therefore maintain their performance. As described above, in one example, if necessary, the back interior areas can be removed from the icing sequence. This increases the number of pulses on the blade tips, allowing the aircraft to return to more severe icing conditions by eliminating much of the ice formed. This could be tolerated for limited periods of time although ice duvets may eventually accumulate in the rear sections of the interior region and compromise performance, thus requiring an occasional full heating cycle. In other examples, the distribution area arrangement also has additional advantages. At lower temperatures, where ice accumulations are reduced in the outer portion of the blade, the end pulses may be reduced as needed so as to provide end deicing pulses only once per cycle. In other examples, the distribution area arrangement also has additional advantages. The system can tolerate erosion protection materials with low thermal conductivity and high specific heat on the inner sections of the blades. In one example of use, since the system is supposed to heat the ends of the rotor blades more frequently to maintain performance, the root section has more time to cool between cycles. Cooling the blades between defrost cycles can help prevent thermal creep in the blade's internal structure and ice runoff. In addition, erosion protection materials with low thermal conductivity and high specific heat may take longer to cool, and in use examples, the multizone heating system can adapt to cooling times. longer. In examples, the use of described trigger sequences allows the control unit to distribute the heating power of a respective blade between the heating systems in the span direction so as to reduce the power peaks. . The control unit can distribute the power between the outer heating systems in the span direction and the inner space heating systems in the span direction with a distribution of approximately two-thirds / one-third, respectively, by example. If the current is divided between the inner and outer zones in a distribution of 2/3, 1/3, respectively, the rotor ends on the two rotor hubs (for example, front and rear) can be activated together and not increase the peak power required. Reductions in the power peaks of electrothermal Icing protection systems can thus be achieved with the distribution zone arrangement, in which two sets of elements are installed in the blade and independently activated. By heating the outer surfaces of the blade more frequently, the ice thicknesses can be kept lower (on average), for example, in the working sections of the blade. When feeding the heating systems, the EOT may vary depending on the outside temperature of the air, so that for colder temperatures, the EOT may be longer . Figure 8 shows a flowchart of an exemplary method 800 for operating heating systems on a rotorcraft, according to one embodiment. The method 800 shown in FIG. 8 presents an embodiment of a method, which, for example, could be used with the system shown in FIG. 1, for example, and can be realized by a computing device (or the components of a computing device), or can be achieved by the components of the rotorcraft according to the instructions provided by the computing device. Thus, the examples of devices or systems may be used or configured to perform logic functions shown in FIG. 8. In some examples, the components of the devices and / or systems may be configured to perform the functions such that the components are actually configured and structured (with hardware and / or software) to enable such performance. In other examples, the components of the devices and / or systems may be arranged to be adapted to, capable of, or designed to perform the functions. Method 800 may include one or more operations, functions or actions as illustrated by one or more of boxes 802-810. Although the boxes are illustrated in sequential order, these boxes may also be made in parallel, and / or in a different order than those described herein. In addition, the various boxes can be combined into fewer boxes, divided into additional boxes, and / or deleted depending on the desired implementation. It should be understood that for this process and method and other processes and methods disclosed herein, the flow charts show the functionality and operation of a possible implementation of present embodiments. As such, each box may represent a module, a segment or a portion of program code, which includes one or more instructions executable by a processor for implementing specific functions or logic steps of the process. The program code may be stored on any type of computer-readable medium or data storage, for example such as a storage device including a disk or hard disk drive. The computer readable medium may include a computer readable medium or non-transitory memory, for example, such as a computer readable medium that stores data for short periods of time such as register memory, processor cache memory, and memory. Random Access (RAM). The computer readable medium may also include non-transient media, such as secondary or non-volatile long-term memory, such as read-only memory (ROM), optical or magnetic disks, CD-ROMs, example. The computer readable medium may also be any other volatile or nonvolatile storage system. The computer readable medium can be considered as a computer-readable storage medium, for example. In addition, each box in Figure 8 may represent circuits that are wired to perform the specific logic functions of the process. Alternative embodiments are included within the scope of the exemplary embodiments of the present disclosure in which functions may be performed in a different order than those shown or analyzed, including substantially a simultaneous or inverse order, depending on the feature concerned, as will be understood by those skilled in the ordinary art. In block 802, method 800 includes detecting one or more icing conditions of an environment of a rotorcraft. The rotorcraft may include multiple blades coupled to a rotor and the multiple blades include a first set of blades and a second set of blades, and the surfaces of the multiple blades are divided into sections such that a given blade includes an inner section extending from the rotor outward and an outer section extending from the inner section to an end of the given blade. At block 804, method 800 includes providing, by a controller, current to a plurality of first span heating systems included in respective outer sections of the first set of blades and the second set of blades. In block 806, method 800 includes providing, by the control unit, current (or energy) to a plurality of second span heating systems included on respective inner sections of the first blade game. In box 808, method 800 includes providing, by the control unit, current (or energy) to the plurality of first span heating systems included on respective outer sections of the first set of blades and the second set of blades. In box 810, method 800 includes providing, by the control unit, current (or energy) to a plurality of second span heating systems included on respective inner sections of the second blade game.
    [0011] In the examples, method 800 may be repeated by supplying power to the respective heating systems until the at least one icing condition of the environment is no longer present. In yet another example, in cases where the rotorcraft includes multiple rotors including a front rotor and a rear rotor, the front rotor includes the first set of blades and the rear rotor (or the second rotor of a left / right game). or upper / lower) includes the second set of blades. The method 800 may include supplying (power) power to the outer sections of the first set of blades on the front rotor and the second set of blades on the rear rotor, followed by supply of current (energy) to the sections the second set of blades on the rear rotor, followed by supplying power to the outer sections of the first set of blades on the front rotor and the second set of blades on the rear rotor, and finally the supply of current (d energy) to the inner sections of the first set of blades on the front rotor. The examples described herein enable a reduction in peak power demand for heating scenarios by reducing a quantity of actively heated rotor blade areas. The division of the zones between the inner and outer (end) regions limits the peak power required for the icing protection system, and lowers a size and / or weight of the aircraft generators. In addition, the examples described herein shorten an anti-icing sequence for the outer sections of the rotor blades and allow the power to be distributed between the rotors to minimize the defrost sequence.
    [0012] In addition, using the exemplary configurations described, since the ends of the rotor blades have combinations of sweep, warp, negative dihedral / dihedral angle and rope changes, the fabrication of the Heaters that can meet geometric requirements is performed by dividing the heaters into two sections that can be manufactured and installed in complex end sections. This allows for improved accuracy of the manufacturing process, in some cases. Further, the disclosure includes the embodiments according to the following clauses: Clause 1: System for a rotorcraft, the system comprising: multiple rotor-coupled blades and multiple blade areas divided into sections, wherein a given blade includes an inner section extending from the rotor outward and an outer section extending from the inner section to an end of the given blade; a plurality of first span heating systems included on respective outer sections of the multiple blades; a plurality of second span heating systems included on respective inner sections of the multiple blades; and a control unit coupled to the plurality of first span heating systems and the plurality of second span heating systems, wherein the respective heating systems of the multiple blade sections are fed during a sequence based on the outside temperature of the air.
    [0013] Clause 2: System according to clause 1, wherein the respective heating systems of the multiple blade sections are fed during a sequence further based on an output of a moisture content sensor indicative of the severity icing and the outside temperature of the air. Clause 3: System according to clauses 1 or 2, in which the sequence is repeated until the icing conditions are no longer present. Clause 4: System according to Clauses 1, 2 or 3, wherein the respective heating systems of the multiple blade sections are fed during the sequence based on the outside temperature of the air, and wherein the sequence includes the heating of outer sections of the multiple blades more frequently than the heating of the inner sections of the multiple blades. Clause 5: System according to clauses 1, 2, 3 or 4, wherein the control unit distributes the power to heat a respective blade between the plurality of first heating systems in the sense of the span and the plurality of second Scale heating systems to reduce a peak power requirement. Clause 6: A system according to clause 5, wherein the control unit distributes power between the plurality of first span heating systems and the plurality of second spanwise heating systems according to a breakdown of approximately two-thirds / one-third, respectively.
    [0014] Clause 7: System according to clauses 1, 2, 3, 4, 5 or 6, wherein the multiple blades include a first set of blades and a second set of blades, and wherein the respective heating systems of the sections of the multiple blades are fed during a sequence comprising: the outer sections of the first set of blades and the second set of blades; the inner sections of the first set of blades; the outer sections of the first set of blades and the second set of blades; and the inner sections of the second set of blades. Clause 8: System according to clauses 1, 2, 3, 4, 5, 6 or 7, wherein the respective heating systems of the sections of the multiple blades are fed in the direction of the rope from a leading edge to a trailing edge of a respective blade. Clause 9: A system according to clauses 1, 2, 3, 4, 5, 6, 7 or 8, further comprising multiple rotors including a front rotor and a rear rotor, wherein the front rotor includes a set of multiple blades and the tail rotor also includes a set of multiple blades. Clause 10: A system according to clause 9, wherein the respective heating systems of the sections of the multiple blades are fed during a sequence comprising: the outer sections of the set of multiple blades on the front rotor and on the rear rotor; the inner sections of the set of multiple blades on the tail rotor; the outer sections of the set of multiple blades on the front rotor and on the rear rotor; and the inner sections of the multiple blade set on the front rotor. Clause 11: System according to clauses 1, 2, 3, 4, 5, 6, 7, 8, 9 or 10, further comprising multiple rotors including a front rotor and a rear rotor, wherein the front rotor includes a set multiple blades and the tail rotor includes a set of multiple blades, and wherein the respective heating systems of the multiple blade sections are fed during a sequence in which the plurality of second heating systems in the direction of the included span on respective inner sections of the multiple blades of the tail rotor are removed from the sequence, allowing the outer sections of the multiple blade set on the front rotor and on the tail rotor to be fed more frequently. Clause 12: A system according to clauses 1, 2, 3, 4, 5, 6, 7, 8, 9, 10 or 11, further comprising multiple rotors including a first rotor and a second rotor, wherein the first rotor includes a set of multiple blades and the second rotor includes a set of multiple blades, and wherein the respective heating systems of the sections of the multiple blades are fed in the direction of the rope such that: for the outer sections and the inner sections of the set of multiple blades of the first rotor, the sections are fed from a leading edge to a trailing edge of a respective blade; and for the outer sections and inner sections of the multiple rotor set of the second rotor, the sections are fed from a leading edge to a trailing edge of a respective blade. Clause 13: System according to clauses 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11 or 12, in which, depending on the fact that the outside temperature of the air is above of a threshold value, the respective heating systems of the multiple blade sections are fed during a sequence in which: the plurality of first span heating systems included on the respective outer sections of the blades multiple or the plurality of second spanwise heating systems on respective inner sections of the multiple blades are removed from the sequence. Clause 14: A system comprising: multiple rotor-coupled blades and multiple blade surfaces divided into sections, wherein a given blade includes an inner section extending from the rotor outward and an outer section extending from the inner section to one end of the given blade; a plurality of first span heating systems included on respective outer sections of the multiple blades; a plurality of second span heating systems included on respective inner sections of the multiple blades; and a control unit coupled to the plurality of first span heating systems and the plurality of second spanwise heating systems, a control unit configured to bring the respective section heating systems multiple blades to be fed during a sequence based on whether the sections are indoor or outdoor and on one or more icing conditions of a system environment. Clause 15: A system according to clause 14, wherein the multiple blades include a first set of blades and a second set of blades, and wherein the respective heating systems of the sections of the multiple blades are fed during a sequence comprising: the outer sections of the first set of blades and the second set of blades; the inner sections of the first set of blades; the outer sections of the first set of blades and the second set of blades; and the inner sections of the second set of blades. Clause 16: A system according to clause 14 or 15, wherein the respective heating systems of the sections of the multiple blades are fed in the rope direction from a leading edge to a trailing edge of a respective blade. Clause 17: A system according to clauses 14, 15 or 16, further comprising multiple rotors including a front rotor and a rear rotor, wherein the front rotor includes a set of multiple blades and the rear rotor also includes a set of multiple blades and wherein the respective heating systems of the multiple blade sections are fed during a sequence comprising: the outer sections of the multiple blade assembly on the front rotor and the rear rotor; the inner sections of the set of multiple blades on the tail rotor; the outer sections of the set of multiple blades on the front rotor and on the rear rotor; and the inner sections of the multiple blade set on the front rotor. Clause 18: A method comprising: detecting one or more icing conditions of a rotorcraft environment, wherein the rotorcraft includes multiple blades coupled to a rotor and the multiple blades include a first set of blades and a second set of blades, and wherein the surfaces of the multiple blades are divided into sections such that a given blade includes an inner section extending from the rotor outward and an outer section extending from the inner section to an end of the given blade; supplying, by a control unit, power to a plurality of first span heating systems included on respective outer sections of the first set of blades and the second set of blades; supplying, by the control unit, current to a plurality of second spanwise heating systems included on respective inner sections of the first set of blades. ; supplying, by the control unit, current to the plurality of first spanwise heating systems included on respective outer sections of the first set of blades and the second set of blades; and supplying, by the control unit, current to a plurality of second spanwise heating systems included on respective inner sections of the second set of blades. Clause 19: A method according to clause 18, further comprising repeating a current supply sequence to the respective heating systems until the at least one icing condition of the environment is no longer present. Clause 20: A method according to clause 18 or 19, wherein the rotorcraft comprises multiple rotors including a front rotor and a rear rotor, wherein the front rotor includes the first set of blades and the rear rotor includes the second set of blades, and wherein: supplying power to the plurality of first spanwise heating systems included on the respective outer sections of the first set of blades and the second set of blades comprises supplying energy to the outer sections the first set of blades on the front rotor and the second set of blades on the rear rotor; supplying energy to the plurality of second spanwise heating systems included on the respective inner sections of the first set of blades comprises supplying power to the inner sections of the second set of vanes on the rear rotor; supplying energy to the plurality of first spanwise heating systems included on the respective outer sections of the first set of blades and the second set of blades comprises supplying energy to the outer sections of the first set of blades. blades on the front rotor and the second set of blades on the rear rotor; and supplying power to the plurality of second spanwise heating systems included on the respective inner sections of the second set of blades comprises supplying power to the inner sections of the first set of blades on the front rotor.
    [0015] The description of the various advantageous arrangements has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments in the disclosed form. Many modifications and variants will become clear to the skilled person. In addition, various advantageous embodiments may have different advantages over other advantageous embodiments. The embodiment or selected embodiments are selected and described to better explain the principles of the embodiments, the practical application, and to enable others skilled in the art to understand the disclosure for various embodiments including various modifications as adapted to the particular use envisaged.
    权利要求:
    Claims (4)
    [0001]
    REVENDICATIONS1. A system for a rotorcraft (100), the system comprising: multiple blades (110, 112) coupled to a rotor (108) and multiple blade surfaces (110, 112) divided into sections, wherein a given blade includes a section interior (412) extending outwardly from the rotor (108) and an outer section (414) extending from the inner section (412) to an end of the given blade; a plurality of first span heating systems (422, 424, 426) included on respective outer sections (414) of multiple blades; a plurality of second spanwise heating systems (416, 418, 420) included on respective inner sections (412) of the multiple blades; and a control unit (102) coupled to the plurality of first span heating systems (422, 424, 426) and the plurality of second span heating systems (416, 418, 420), wherein the respective heating systems of the multiple blade sections are excited during a sequence based on the outside temperature of the air.
    [0002]
    The system of claim 1, wherein the respective heating systems (114,116) of the multiple blade sections (411,414) (110,112) are fed during a sequence further based on an output of a water content sensor (106) indicative of the severity of the icing and the outside temperature of the air.
    [0003]
    3. System according to claims 1 or 2, wherein the sequence is repeated until the icing conditions are no longer present. 25
    [0004]
    The system of claims 1, 2 or 3, wherein the respective heating systems (114, 116) of the multiple blade sections (412, 414) (110, 112) are fed during the temperature-based sequence. wherein the sequence includes heating the outer sections (414) of multiple blades (110, 112) more frequently than heating the inner sections (412) of the multiple blades (110, 112). . The system of claims 1, 2, 3 or 4, wherein the control unit (102) distributes power to heat a respective blade (110, 112) between the plurality of first scale heating systems. (422, 424, 426) and the plurality of second spanwise heating systems (416, 418, 420) to reduce a required peak power. The system of claim 5, wherein the control unit (102) divides the current between the plurality of first span heating systems (422, 424, 426) and the plurality of second plurality of heating systems. span heating (416, 418, 420) in a split of about two-thirds / one-third, respectively. The system of claims 1, 2, 3, 4, 5 or 6, wherein the multiple blades (110, 112) include a first set of blades (404, 408) and a second set of blades (406, 410). , and wherein the respective heating systems of the sections of the multiple blades are excited during a sequence comprising: outer sections (414) of the first set of blades (404, 408) and the second set of blades (406, 410 ); inner sections (412) of the first set of blades (404, 408); the outer sections (414) of the first set of blades (404, 408) and the second set of blades (406, 410); and inner sections (412) of the second set of blades (406, 410). 8. System according to claims 1, 2, 3, 4, 5, 6 or 7, wherein the respective heating systems (114, 116) of the sections of the multiple blades (110, 112) are fed in the direction of the rope. from a leading edge to a trailing edge of a respective blade. The system of claims 1, 2, 3, 4, 5, 6, 7 or 8, further comprising multiple rotors (602, 604) including a front rotor (602) and a rear rotor (604), wherein the front rotor (602) includes a set of multiple blades (110, 112) and the rear rotor (604) also includes a set of multiple blades (120, 122). The system of claim 9 wherein the respective heating systems of the multiple blade sections are fed during a sequence comprising: outer sections (422, 424, 426) of the multiple blade set (120, 122) on the front rotor (602) and rear rotor (604); inner sections (612) of the multiple blade set on the tail rotor (604); the outer sections (614) of the multiple blade set on the front rotor (602) and the rear rotor (604); and inner sections (612) of the multiple blade set on the front rotor (602). The system of claims 1, 2, 3, 4, 5, 6, 7, 8, 9 or 10, further comprising multiple rotors (602, 604) including a front rotor (602) and a rear rotor (604). ), wherein the front rotor (602) includes a set of multiple blades and the rear rotor (604) also includes a set of multiple blades, and wherein the respective heating systems (612, 614) of the multiple blade sections are fed during a sequence in which the plurality of second spanwise heating systems (616, 618, 620) included on the respective inner sections (612) of the multiple blades (628, 630, 632) on the rear rotor (118, 604) are removed from the sequence allowing the outer sections (614) of the multiple blade set on the front rotor (108, 602) and on the rear rotor (118, 604) to be fed more frequently . The system of claims 1,2,3,4,5,6,7,8,9,10 or 11, further comprising multiple rotors 602) and a second rotor (118, 604), wherein the first rotor (108, 602) includes a set of multiple blades (110, 112) and the second rotor (118, 604) also includes a set of multiple blades ( 120, 122), and wherein the respective heating systems of the sections of the multiple blades are fed in the direction of the rope such that: for the outer sections (614) and the inner sections (612) of the multiple blade set on the first rotor (108, 602), the sections are fed from a leading edge to a trailing edge of a respective blade; andfor the outer sections (614) and the inner sections (612) of the multiple blade set on the second rotor (118, 604), the sections are fed from a leading edge to a trailing edge of a respective blade . 13. System according to claims 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11 or 12, wherein, depending on an outside temperature of the air greater than a threshold value. the respective heating systems of the multiple blade sections are fed during a sequence in which: the plurality of first span heating systems (622, 624, 10 626) included on the respective outer sections (614) multiple blades or the plurality of second spanwise heating systems (616, 618, 620) included on the respective inner sections (612) of the multiple blades are removed from the sequence. A method comprising: detecting one or more icing conditions of an environment of a rotorcraft (100), wherein the rotorcraft (100) includes multiple blades (110, 112) coupled to a rotor (108) and the multiple blades (110, 112) include a first set of blades (404, 408) and a second set of blades (406, 410), and wherein the surfaces of the multiple blades are divided into sections (412, 414) such that a given blade includes an inner section (412) extending outwardly from the rotor (108, 402) and an outer section (414) extending from the inner section to an end of the given blade ; providing, by a control unit (102), energy to a plurality of first span heating systems (422, 424, 426) included on respective outer sections (414) of the first set blades (404, 408) and the second set of blades (406, 410); supplying, by the control unit (102), energy to a plurality of second spanwise heating systems (416, 418, 420) included on respective inner sections (412) of the first blade set (404, 408); supplying, by the control unit (102), energy to the plurality of first span heating systems (422, 424, 426) included on the respective outer sections (414) of the first set blades (404, 408) and the second set of blades (406, 410); and supplying, by the control unit (102), energy to a plurality of second spanwise heating systems (416, 418, 420) included on respective inner sections (412) of the second blade set (406, 410). The method of claim 14, wherein the rotorcraft (100, 600) comprises multiple rotors (108, 118) including a front rotor (602) and a rear rotor (604), wherein the front rotor (602) includes the first set of blades (606, 608, 610) and the rear rotor (604) includes the second set of blades (628, 630, 632), and wherein: supplying power to the plurality of first heating systems in the span direction (622, 624, 626) included on the respective outer sections (614) of the first set of blades (606, 608, 610) and the second set of blades (628, 630, 632) includes the supplying power to the outer sections (614) of the first set of blades (606, 608, 610) on the front rotor (602) and the second set of blades (628, 630, 632) on the rear rotor (118, 604). ); supplying energy to the plurality of second spanwise heating systems (616, 618, 620) included on the respective inner sections (612) of the first set of blades (606, 608, 610) includes the supplying power to the inner sections (612) of the second set of blades (628, 630, 632) on the rear rotor (118, 604); supplying power to the plurality of first span heating systems (622, 624, 626) included on the respective outer sections (614) of the first set of blades (606, 608, 610) and the second set of blades (628, 630, 632) includes supplying power to the outer sections (614) of the first set of blades (606, 608, 610) on the front rotor (108, 602) and the second set of blades (628, 630, 632) on the rear rotor (118, 604); and supplying power to the plurality of second spanwise heating systems (616, 618, 620) included on the respective inner sections (612) of the second set of blades (628, 630, 632) comprises supplying power to the inner sections (612) of the first set of blades (606, 608, 610) on the front rotor (108, 602).
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    同族专利:
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    DE102015117640A1|2016-05-12|
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    JP6495150B2|2019-04-03|
    RU2015141769A|2017-04-06|
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    法律状态:
    2016-11-23| PLFP| Fee payment|Year of fee payment: 2 |
    2017-11-27| PLFP| Fee payment|Year of fee payment: 3 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 4 |
    2019-11-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-25| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-24| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/538,468|US9745070B2|2014-11-11|2014-11-11|Systems for multiple zone heaters for rotor craft and methods of operation|
    US14538468|2014-11-11|
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