• 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 invention relates to a fin precipitation mechanism (10, 20) for a rotation-stabilized projectile (1) comprising at least one fin (2, 15) and at least one actuator where the fin (2, 15) is foldable and foldably arranged on the projectile (1) and that the fin ( 2, 15) and at least one balance weight (3, 17) are mechanically arranged so that when the fin (2, 15) is folded out of the actuator, the balance weight (3, 17) moves towards the center (6) of the projectile (1) and when the fin (2, 15) is folded in by the actuator, the balance weight (3, 17) moves out from the center (6) of the projectile (1). The invention also relates to a method for energy-efficient precipitation and indentation of fins (2, 15) on a rotating projectile where at least one fin (2, 15) is fold-out and collapsibly arranged on the projectile and that the fin (2, 15) is arranged to at least one balance weight (3, 17) according to; (a) when the fin (2, 15) is moved out of the center of the projectile, upon precipitation of the fin (2, 15), the balance weight (3, 17) is moved towards the center of the projectile, (b) when the fin (2, 15) is moved towards the center of the projectile, when the fin is folded in, the balance weight (3, 17) is moved out of the center of the projectile.Fig. 1.
    公开号:SE1330122A1
    申请号:SE1330122
    申请日:2013-10-10
    公开日:2015-04-11
    发明作者:Lars-Åke Carlqvist；Pär Eriksson
    申请人:Bae Systems Bofors Ab；
    IPC主号:
    专利说明:

    and PggilIPININSVerkei 2013 -10- 1.0 1 FEN DEPOSIT MECHANISM WITH IMPROVED ENERGY EFFICIENCY AND PROCEDURE FOR FEN FALL OUT WITH INCREASED ENERGY EFFICIENCY 5 TECHNICAL FIELD The present invention relates to a fin failure mechanism for at least one root failure mechanism. The invention also relates to a method for energy-efficient precipitation and incident of fins on a rotating projectile. BACKGROUND OF THE INVENTION, TROUBLESHOOTING AND KNOWLEDGE TECHNOLOGY Rotation-stabilized projectiles are corrected in the trajectory, from the launching device to the target, for example through aft guide fins and / or brake flaps falling out and in under the projectile Lard in the trajectory. One problem is the large energy input that arises when the fins (brake and rotary fins or other fins) often need to fall out and in under the projectile's Lard from the launching device to the target.
    The template precision of a projectile in an artillery system is largely controlled by meteorological aspects and how the actual launch velocity, VO, corresponds to the calculated launch speed saint alien of factors that depend on the launch device such as the design of the electric gear and the accuracy of the target system. Before steerable projectiles began to be used in artillery applications, there was no possibility of affecting the projectile's firing trajectory after the projectile fired the barrel.
    By inserting controls, such as rudders, flaps or fins / wings, the projectile's steering shape can be checked. Depending on the design, location and size of the fins / wings, different degrees of control can be achieved. Different control shapes are required depending on the projectile design, VO, firing range, range and target precision. Reliable techniques have been developed for calculating the current position of a projectile based on inertial navigation and / or satellite navigation via a GNSS system such as GPS. Projectiles are also challenging with a GNC system and the GNSS system can be said to be part of the GNC system. GNC, which stands for Guidance, Navigation and Control, ensures that the projectile is steered against the target for which the projectile is intended.
    Eft specifically controlled for projectiles presupposes fins, such as brake flaps and rotary fins, frequently during the projectile's movement from launching device to food, falling out and in from the projectile. With now known design solutions, the energy consumption will be very high, especially when the fins fall in from the failure! Age when a large, created by centrifugal force, must be overcome.
    GB 2,121,147 A describes a fin ejection mechanism for a missile in which fins are mounted with hand heaters and pivots on a rotatably concentric, relative to the cylindrical missile, arranged inner part. The device is loaded with feathers and the fins fall out after a welding frees the inner part which falls out of the fins by a rotational movement. No radial movement for precipitation of the fins is described, nor is the occurrence of phenomena or that the inner part is adapted to constitute a counterweight or otherwise reduce the energy input in the event of precipitation.
    A problem with known embodiments of fin failure mechanisms is due to the large energy required to fill in and the Ma-5111st Ma in the fins is large.
    Another problem with cancel designs on fin failure mechanisms is that a powerful motor or powerful servo act to fall in or out of the fins. A powerful motor / servo consumes large amounts of energy and takes up a lot of space in the projectile.
    A further problem with the aforementioned projectile embodiments is that energy sources in the form of batteries or other energy storage techniques are sluggish, age or for other reasons are unsuitable for integration on projectiles. Thus, there is a desire to reduce the size of the energy particles or completely avoid energy particles.
    Further problems which the invention intends to solve appear in connection with the following detailed description of the various embodiments. OBJECT OF THE INVENTION AND ITS FEATURES An object of the present invention is a fin precipitation mechanism with improved energy efficiency.
    A further object of the present invention is an improved process for fin precipitation with four improved energy efficiency.
    Thus, according to the present invention, an improved fin drop mechanism has been provided for a rotationally stabilized projectile comprising at least one fin and at least a stable device where the projectile can be characterized in that the fin is foldable and incidentally arranged on the projectile and that the fin and at least one balance weight are mechanically arranged. out of the stable, the balance weight moves towards the center of the projectile and when the fin falls in from the stable, the balance weight moves out of the center of the projectile.
    According to further aspects of the fin precipitation mechanism of the invention apply; that the displacement of the fin is a displacement in the radial direction of the projectile and the opposite displacement of a balance weight is a displacement in the radial direction of the projectile. that the total mass of the balance weight increases as the number of balance weights increases as the balance weights are moved towards the center of the projectile at the same time as the fin falls out of the projectile. that the total mass of the balance weight decreases as the number of balance weights decreases as the balance weights are moved out from the center of the projectile at the same time as the fin falls into the projectile. a t t the number of balance weights is three ddr a balance weight is fixedly mounted against the slide and ddr another first a balance weight and then another balance weight is moved as the slide is moved towards the center of the projectile. that the fin and the balance weight are arranged in a rotatable disk, ddr rotation of disk in a first direction causes the fin to fall out of the projectile and that the balance weight is moved towards the center of the projectile and rotation of disk in a second direction, ddr the other direction is opposite direction towards the first direction. causes the fin to fall into the projectile and the balance weight to be moved out of the center of the projectile. 4 Furthermore, according to the present invention, an improved method for energy efficient precipitation and incident of fins on a rotating projectile has been achieved.
    The method can be characterized in that at least one fin is foldable and incidentally arranged on the projectile and the fin is arranged to at least a balance weight according to; (a) when the fin is moved out of the center of the projectile, when the fin falls out, the balance weight is moved towards the center of the projectile, (b) when the fin is moved towards the center of the projectile, when the fin falls, the balance weight is moved out of the center of the projectile.
    According to further aspects of the riding method, the grille according to the invention; that the displacement of the fin is a displacement in the radial direction of the projectile and the opposite displacement of a balance weight is a displacement in the radial direction of the projectile. that the incident force acting on the fin, F1, is compensated by an equal and equally directed radial force acting on the balance weight, F2, by increasing the mass of the balance weight as the balance weight is moved towards the center of the projectile and the mass weight decreases as the balance weight is moved out center of the projectile. that fins and balance weights are arranged in a rotatable disk challenge with spares, where the spares move fins and balance weights when the disk is rotated, and where the projecting force acting on the fin, F1, is compensated with an equal and equally directed radial force acting on the balance weight , F2, by the torque contribution on the rotatable disk from fins and balance weights, when the projectile is subjected to centrifugal acceleration, is balanced by the execution of the groove which moves the balance weights and the grooves which move the fins. ADVANTAGES AND EFFECTS OF THE INVENTION The invention solves the problem of high energy consumption when fins and flaps fall out and fall into a rotation-stabilized projectile through the use of balanced counterweights.
    LIST OF FIGURES The invention will be described in more detail below with reference to the accompanying figures: Figure 1 shows a side view of a projectile according to an embodiment of the invention.
    Figure 2 shows a view, in section of a projectile, of a fin precipitation mechanism with phenomena incident according to a first embodiment of the invention.
    Figure 3 shows a view, in skimming of a projectile, of a fin precipitation mechanism with the fins unfolded according to a first embodiment of the invention.
    Figure 4a shows a view of an exploded view of a fin counting mechanism with phenomena incident according to a second embodiment of the invention.
    Figure 4b shows a view of a fin precipitation mechanism with phenomena incident according to a second embodiment of the invention.
    Figure 5a shows a view of an exploded view of a fin precipitation mechanism with phenomena precipitated according to a second embodiment of the invention.
    Figure 5b shows a view of a fin precipitation mechanism with phenomena precipitated according to a second embodiment of the invention.
    DETAILED DESCRIPTION OF THE EMBODIMENT The invention relates to an energy-saving fin precipitation mechanism for precipitation and precipitation of fins. The fin precipitation mechanism has, through sift execution, with balance weights, an improved energy efficiency compared to traditional precipitation methods without balance weights.
    The fins, and thus the fin precipitation mechanism, are preferably lamped for a rotation-stabilized projectile. The fin precipitation mechanism can be used for all types of fins, flaps, baffles, rudders or other controls further referred to as fins, where phenomena are mainly regulated by a radial maneuvering. The principle of balance weights can also be used for axial fin failure. The fins can be saval steering as well as 6 braking. The fin deflection mechanism is applicable to both fixed fins and fins that are steerable, rotatable or adjustable.
    The fins are maneuvered radially by the fin precipitation mechanism with one or more movably arranged balance weights, or counterweights, which move synchronously in the opposite direction to the fin falling out of the projectile. The method also means that the forces that the centrifugal acceleration causes on phenomena during precipitation and / or precipitation can be completely or partially balanced away, which meant that a much smaller amount of energy is used for maneuvering phenomena and that a smaller motor, for precipitation and precipitation of phenomena , can be used. Phenomena AA] as the balance weights are affected by a control device or stable device arranged in the projectile which can be constituted by a motor or a servo or other mechanical, electrical or electromechanical device.
    Figure 1 shows a projectile 1 constructed with an energy-saving fin precipitation mechanism 15 with both guide fins and brake fins arranged. The number of fins 2 may vary depending on the purpose and purpose of the projectile 1. For example, fins 2 may be arranged to steer the projectile 1 but also to brake the projectile 1. Fins 2 may also be arranged to act as wings to give lift to a projectile 1 or to reduce or increase the rotation of a projectile 1 or a part of a projectile 1 rotation, such as a rotating center section. The embodiment of projectile 1 shown in Figure 1 has a total of 8 fins, of which four are brake flaps and four are guide fins / rotary fins. The projectile 1 can be challenged with a & part 4 which, during the projectile's launching process, acts on the rudder of the electric tube and clamed rotates the projectile 1. The belt 4 has awn purpose to protect the fin precipitation mechanism from gunpowder gases during the launching process. the belt seen from the stern of the projectile.
    A first embodiment of a projectile 1 in perforation with a fin precipitation mechanism 10 is shown in Figure 2. The fin precipitation mechanism 10 comprises a gear driven balance weight / counterweight 3, in the form of a slide 5. Datil11 shows a slide, not shown in the figure, which is arranged to a fin 2 for radial maneuvering of a fin 2 when falling out and falling in. When the slide 5 is moved, the slide, which is not shown to which the fin 2 is arranged, will move in the opposite direction. The slide, to which the fin 2 is arranged, is in figure 2 placed behind and hidden by slide 5.
    The balance weights 3 can consist of a balance weight or a number of cooperating balance weights. The slide 5 is in an embodiment, shown in figure 2, challenged with three balance weights 3a, 3b, 3c 7 and 3c ', which are connected to the slide 5, where the balance weights 3 rotate linearly and synchronously in the opposite direction to the fin 2 when falls out or in from the projectile 1. The balance weights 3c and 3c 'are interconnected in a common structure but may awn, if the construction so requires, be separated. In the center 6, or other center, of the projectile is arranged the motor which drives the slide 5 and the slide to which the fin 2 is arranged. As the motor shaft, according to Figure 2, is rotated counterclockwise, the balance weights 3 will move towards the center 6 of the projectile and the fin 2 will fall out of the projectile. The motor shaft located in the center 6 of the projectile 1 can be directly connected to a motor or a servo. Furthermore, a gearbox or other gearing device can be arranged between the motor and the motor shaft shown. The motor shaft is preferably arranged against the slide 5 by gears, alternatively the motor shaft can be arranged against the slide with a friction clutch or other clutch.
    Figure 3 shows the fin deposition mechanism 10 when the fin 2 is unfolded. When the stable unit, based on figure 3, is rotated clockwise, the slide 5 and with it the balance weights 3 move out from the center 6 of the projectile 1 and the fin 2 will be called into the projectile 1.
    Due to the construction of the fin precipitation mechanism, the fin 2 can be placed in the intermediate layer between fully collapsed and fully collapsed, i.e. the fin 2 can be placed in an Idge when the fin is partially folded out.
    In a second embodiment of the invention, shown in Figure 4a, the fin unfolding mechanism 20 comprises a rotatable disk 21 formed by fins 15 rotating in a screw or rotational movement in and out of which the fins 15 are arranged on mounted shaft pins 12 which rotate in semicircular grooves 23 chamfered on one side of the rotatable disk 21. The shaft pins 12 are then arranged to run in grooves 27 on a lower mounting disk 26. On the corresponding salt there are arranged semicircular chamfered grooves 22 on the other side of the rotatable disk 21, where shaft pins 13 are arranged to balance weights 17 rotate in the opposite radial direction towards the fins 15. The shaft pins 13 are awn arranged aft loop in grooves 25 in an upper mounting counter 24. In figure 4a the fins 15 are recessed. The lower mounting disk 26 and the upper mounting disk 24 are challenged to control the movement of the shaft journals 12, 13 as the rotatable disk 21 moves the fins 15 and balance weights 17 between the output and infant length. Recess 22, which is formed on the rotatable disk 21, is preferably challenged in the form of a circular segment. In one embodiment, the groove 22 is formed in the form of a quarter circle, other conceivable embodiments are different forms of exponential, elliptical or other shapes of grooves that allow equal force distribution between the forces acting on the fins 15 and the forces acting on the 8 balance weights 17. . Recess 23, which is not clearly shown in the figures, is mirror-smooth with ridge 22 but otherwise identical to ridge 22.
    Figure 4a shows an exploded view of the fin precipitation mechanism 20. An assembled fin precipitation mechanism 20 of the second embodiment with the fins recessed is shown in Figure 4b.
    Figure 5a shows the fin precipitation mechanism 20 after fin precipitation according to the second embodiment of the fin precipitation mechanism 20. The rotatable disk 21 has been rotated counterclockwise by approximately 90 degrees, the direction the disk 21 is rotated and the angle at which the disk 21 is rotated can be freely varied and adapted for the projectile. After the rotation, the bearing shaft pins 12 for phenomena 15 have rapidly collapsed from a layer of phenomena to a layer where the fins 15 have precipitated. The balance weights 17 have been moved, with the mounted shaft journals 13, towards the center 6 of the projectile. The grooves 23 for the mounted shaft journals 12 for phenomena and the grooves 22 for the mounted shaft pins 13 for the balance weights 17 are cured to balance the forces in case of incident and failure of phenomena 15, respectively.
    Figure 5a shows an exploded view of the fin precipitation mechanism 20. A mounted fin precipitation mechanism 20 of the second embodiment with the fins unfolded is shown in Figure 5b.
    FUNCTIONAL DESCRIPTION When the projectile 1 is fired from a rocket, the projectile 1 leaves the rocket mouth rotating. The projectile 1 is rotationally stabilized in the trajectory from the launching device to May. Through the belt 4, phenomena 2, 15 have been protected from gunpowder gases and gunpowder particles during the firing phase. At the appropriate time or distance in the projectile 1's trajectory, phenomena 2, 15 fall out of the projectile 1. The GNC system included in the projectile emits from the projectile 1's current position and speed and the position of the target how the projectile 1 should be controlled to hit the target. Depending on the deviation of the projectile 1 from an unsteady course or direction to hit the target, the projectile 1 can be controlled to varying degrees to ensure that the projectile 1 hits the target.
    According to the first embodiment, when phenomenon 2 falls out, at least one balance weight 3 will move towards the direction of phenomenon 2, i.e. the balance weights 3 move radially or on another sail towards the center 6 on the projectile when the fins 2 rotate out from center 6. 9 Upon precipitation, centrifugal forces will act on the fins 2 with a precipitating force. The centrifugal force acts on the balance weight 3 and thus constitutes an opposite force to that of the engine, in the center 6 on the projectile, on the force 5 acting on the slide 5, which moves the balance weight 3 towards the center 6 of the projectile. in the same way if the fins fall in, at least one balance weight 3 will move towards the direction of the phenomena 2, it will be said that the balance weights 3 move radially out from the center 6 on the projectile 1 then the fin 2 moves towards the center 6 on the projectile 1. centrifugal forces will act on the fins 2 with a force out of the center 6 of the projectile 1. The centrifugal force acts on the balance weight 3 and is a claimed force in the same direction as that of the force acting on the slide 5, which moves the balance weight 3 out of the center 6 of the projectile 1. In the event of a fallout, there is a force acting on the fin 2 on the centrifugal force which contributes to the fallout of the fin 2. Similarly, when the centrifugal force acts, there is a force on the balance weight 3 which helps to move the balance weight 3 out of the center 6. By balancing the force component generated by the centrifugal force acting on the fins 2 with the force component generated by the centrifugal force acting on the balance weights 3, a balanced fin precipitation mechanism 10, 20 can be provided. Balancing takes place on the basis that the mass and position of the balance weights 3 and that the design of the fin 2 and the balance weights 3 are selected on the basis of the design rules given by the speed of rotation and the fin construction. The force acting by the centrifugal force on the balance weights 3 as well as on the fins 2 is proportional to the distance from the center of mass of the balance weights / fins to the center 6 of the projectile 1. DA center of mass is closer to the center 6 of the projectile 1 mass is at a stone distance from the center 6. Thus, the force acting on the balance weight decreases as the balance weight 3 approaches the center 6 of the projectile. By increasing the mass of the balance weight as the balance weight 3 is moved towards the center, an counteracting force, F2, can be created / increased which is in the order of magnitude of the force Fi acting on the fin 2.
    In the illustrated first embodiment of the fin precipitation mechanism 10 of Figure 2 and Figure 3, when the fin 2 falls out, the balance weight 3a will initially move radially toward the center 6 of the projectile. DA the balance weight 3a, and thus the fin 2, at a certain predetermined point, the weight 3b will also be affected by the slide 5. In this case the balance weights consist of balance weights 3a and 3b. 1 further point closer to the center of the projectile when the balance weights 3a and 3b, and thus the fin 2, at a certain predetermined point, weights 3c and 3c 'will also be affected by the slide 5. In this ldge the balance weights 3 consist of balance weights 3a, 3b, 3c and 3c '. In this embodiment, there are thus three balance weights 3, as more and less balance weights 3 are conceivable for realizing a functional fin precipitation mechanism 10. In an advantageous embodiment, F2 is equal to or in the order of Fi, for example by the mass weight 3 mass continuously increasing the balance weight 3 approaches center 6 of the projectile. When the fin 2 is fully retracted, the counterweights 3b, 3c and 3c 'are in a resting hole as they abut a fixed structure in the projectile 1, dd. the slide 5 moves towards the center 6, first balance weight 3b and then balance weight 3c and 3c 'will be moved towards the center 6 by the projectile 1.
    In the proposed second embodiment of the fin precipitation mechanism 20 of Figures 4a, 4b and 5a, 5b, the balance weights 17 will move toward the center 6 of the projectile while the phenomenon 15 rotates out of the center 6 of the projectile 1 through a disk 21. . The grooves 22, 23 for the mounted shaft journals 12 for phenomenon 15 and the stored shaft journals 13 for the balance weights 17 should be made so that the forces F1 acting on the phenomena 15 and the forces F2 acting on the balance weights 17 are of equal magnitude during the precipitation procedure and the precipitation procedure. DA disk 21 is rotated so that grooves 22 cause the bearing energy of the fin 15 to change, by making grooves 23 so that the low energy of balance weight 17 is changed identically or change identically to how the bearing energy of the fin 15 is changed a balance of the force acting on the fin F1 and the force F2 acting on the balance weight is achieved. A motor or servo is connected to disk 21 and rotates disk 21. The phenomena 15 can be moved from fully collapsed to fully collapsed and all intermediate layers. The shaft journals 12 which are mounted or otherwise arranged to the fins 15 are controlled by grooves 27 made in a lower mounting counter 26. In the same way, grooves 25 arranged in an upper mounting disk 24 for controlling the shaft pins 13 arranged for the balance weights 17. 24 and the lower mounting disk 26 may also be provided for a shaft or other device for rotation of disk 21 may be provided to disk 21.
    The upper mounting disk 24 and the lower mounting disk 26 may also be designed to allow mounting of the fin precipitation mechanism 20 in the projectile 1.
    The incident radial force acting on the fin 15, F1, is compensated by an equal and equally directed radial force acting on the balance weight 17, F2, by increasing the torque contribution on the rotatable disk 21 from the fins 15 and balance weights 17, when the projectile 1 is exposed to centrifugal acceleration, is balanced by the design of the groove 22 which moves the shaft pins 13 which are arranged to the balance weights 17 and the groove 23 which moves the shaft pins 12 which are arranged to the fins 15. An advantageous embodiment of the groove 22 in a circle segment, preferably a quarter circle, groove 23, which is arranged on the opposite side of the rotatable disk 21, where the mirror is arranged parallel to groove 21 but otherwise identical. 11 EXAMPLE EXAMPLES An example where the fin precipitation mechanism can be used is for a rotationally stabilized projectile such as an artillery shell with an outer diameter of the projectile of 155 mm and with a length of the projectile in the order of 30-100 cm with a number of in and out fins where and precipitation of the fins during the movement of the projectile from the launching device to the target of the projectile.
    ALTERNATIVE EMBODIMENTS The invention is not limited to the embodiments shown but can be varied in various ways within the scope of the claims.
    It will be appreciated, for example, that the number, size, material and shape of the elements and details included in the projectile are adapted to the weapon system (s) and other design features which exist at the time.
    It will be appreciated that the projectile venting mechanism described above can be adapted for different dimensions and projectile types depending on the area of application and range of fire but also for missiles, rockets or other aircraft. 1. IOG.11 Reglitnpaverkat 2013 -10-
    权利要求:
    Claims (10)
    [1]
    A fin deflection mechanism (10, 20) for a rotation stabilized projectile (1) comprising at least one fin (2, 15) and at least one female jug characterized in that the fin (2, 15) is foldably and incidentally arranged on the projectile (1) and that the fin (2 , 15) and at least one balance weight (3, 17) which is mechanically arranged so that when the fin (2, 15) falls out of the stable, the balance weight (3, 17) moves towards the center (6) of the projectile (1) and then the fin (2, 15) falls in by the stable device and the balance weight (3, 17) moves out of the center (6) of the projectile (1).
    [2]
    A fin deflection mechanism (10, 20) for a rotation stabilized projectile (1) according to claim 1, characterized in that the movement of the fin (2, 15) is a movement in the radial direction of the projectile (1) and the opposite movement of a balance weight (3, 17) is a movement in the radial direction of the projectile (1).
    [3]
    A fin precipitation mechanism (10, 20) for a rotationally stabilized projectile (1) according to any one of claims 1-2 may be characterized in that the total mass of the balance weight (3) increases as the number of balance weights (3) increases as the balance weights (3) move towards the center (6) of the projectile (1) at the same time as the fin (2) falls out of the projectile (1).
    [4]
    Fencing mechanism (10, 20) for a rotationally stabilized projectile (1) according to any one of claims 1-2, characterized in that the total mass of the balance weight (3) decreases as the number of balance weights (3) decreases as the balance weights (3) are moved out of center (6) of the projectile (1) at the same time as the fin (2) falls into the projectile (1).
    [5]
    Phenom precipitation mechanism (10, 20) for a rotation-stabilized projectile (1) according to any one of the preceding claims, characterized in that the number of balance weights (3) where three ddr a balance weight (3a) is fixedly mounted to the slide (5) and ddr another first a balance weight (3b) and then another balance weight (3c) is moved as the slide (5) is moved towards the center of the projectile (1).
    [6]
    A fin deflection mechanism (10, 20) for a rotation stabilized projectile (1) according to any one of claims 1-2 may be characterized in that the fin (15) and the balance weight (17) are arranged on a rotatable disk (21), where rotation of disk (21) in a first direction, the fin (15) falls out of the projectile (1) and the balance weight (17) is moved towards the center (6) of the projectile (1) and rotation of the disk (21) in a second direction, where the second the direction is the opposite direction to the first direction, causing the fin (15) 1 2 to fall into the projectile (1) and the balance weight (17) to be moved out of the center (6) of the projectile (1).
    [7]
    7. A method for energy-efficient precipitation and incident of fins (2, 15) on a rotating projectile (1), characterized in that at least one fin (2, 15) is arranged and incidentably arranged on the projectile and that the fin (2, 15) is arranged to at least one balance weight (3, 17) according to; (a) cid the fin (2, 15) is moved out of the center of the projectile, in the event of a fin falling out, the balance weight (3, 17) is moved towards the center of the projectile, (b) when the fin (2, 15) is moved towards the center of the projectile, when the fin is incident, the balance weight (3, 17) is moved out of the center of the projectile.
    [8]
    Method according to claim 7 can be characterized by the fact that the movement of the fin (2, 15) is a movement in the radial direction of the projectile and the opposite movement of a balance weight (3, 17) is a displacement in the radial direction of the projectile.
    [9]
    Method for energy-efficient precipitation and precipitation of fins (2, 15) according to any one of claims 7-8k, characterized in that the precipitating force acting on the fin (2), F1, is compensated with an equal and equally directed radial force. acting on the balance weight (3), F2, by increasing the mass of the balance weight (3) as the balance weight (3) moves towards the center of the projectile and the mass of the balance weight (3) decreases as the balance weight (3) moves out of the center of the projectile.
    [10]
    A method for energy-efficient precipitation and indentation of fins according to any one of claims 7 to 8, characterized in that fins (15) and balance weights (17) arranged on a rotatable disk (21) challenge with spar (22, 23), or the spar. moves fins (15) and balance weights (17) when the disc (21) is rotated, and where the incident force acting on the fin (15), F1, is compensated by an equal and equally directed radial force acting on the balance weight (17), F2, in that the torque contribution on the rotatable disk from fins (15) and balance weights (17), when the projectile is subjected to centrifugal acceleration, is balanced by the design of the groove (22) which moves the balance weights and the grooves (23) which move the fins. Ink. 1. Patent. Bch mistrerionsverket 2013 2.4
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1302008A|1918-08-16|1919-04-29|William Cameron|Shell.|
    GB1523963A|1976-02-26|1978-09-06|Hawker Siddeley Dynamics Ltd|Method and means for auxiliary control of vehicle direction|
    GB2121147B|1982-06-02|1985-10-16|British Aerospace|Missile fin assemblies|
    GB8609166D0|1986-04-15|1986-09-17|British Aerospace|Deployment arrangement for spinning body|
    DE3712704C2|1987-04-14|1989-02-02|Diehl Gmbh & Co, 8500 Nuernberg, De|
    US5074493A|1990-12-21|1991-12-24|The United States Of America As Represented By The Secretary Of The Navy|Wing-extendible gliding store|
    US5816531A|1997-02-04|1998-10-06|The United States Of America As Represented By The Secretary Of The Army|Range correction module for a spin stabilized projectile|
    US7163176B1|2004-01-15|2007-01-16|Raytheon Company|2-D projectile trajectory correction system and method|
    WO2008143707A2|2006-12-07|2008-11-27|Pemery Corp.|Course correcting fuze|
    IL231186A|2014-02-26|2017-07-31|Israel Aerospace Ind Ltd|Fin deployment system|SE542272C2|2017-11-28|2020-03-31|Bae Systems Bofors Ab|Spark plug with reversible air brake|
    US10996032B2|2018-04-11|2021-05-04|Simmonds Precision Products, Inc.|Pre-slit membrane slot cover for a projectile|
    CN110065609A|2019-05-20|2019-07-30|中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所）|A kind of deep sea manned submersible synchronous folding formula horizontal stabilizer|
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