Missile air rudder deflection device

Abstract

The present invention provides a missile air rudder deflection device, comprising an air rudder, a base, a pull rod, a tension spring, a pin puller actuator, and an elastic plunger. A stepped shaft is connected below the trapezoidal rudder surface of the air rudder, the lower end of which is movably mounted on the base. One end of the pull rod is tightly connected to the stepped shaft, and the other end is tightly connected to one end of the tension spring, the other end of which is tightly mounted on the base. The pin puller actuator is mounted on the base, and the pin of the pin puller actuator is pluggably engaged with the stepped shaft. The elastic plunger is mounted on the base, and the elastic rod of the elastic plunger is pressed against the stepped shaft. The present invention applies a deflection torque to the air rudder, combining the unlocking action of the pin puller actuator with the locking action of the elastic plunger, thereby avoiding the use of a full-state servo cabin, significantly improving the cost-effectiveness and significantly reducing development costs.

Description

Technical Field

[0001] The present invention relates to the field of missile control technology, in particular to a missile air rudder deflection device. Background Art

[0002] During the flight of a missile with a booster stage, when the booster stage finishes working, the booster stage and the main stage are structurally separated. Generally, the air rudder in the booster stage servo cabin is delayed in deflection to change the attitude of the booster stage, increase the wind resistance load on the booster stage, quickly reduce the speed of the booster stage, increase the safe distance from the main stage, avoid collision between the booster stage and the main stage, and ensure the structural safety of the main stage.

[0003] However, sometimes a missile development flight test only requires pushing the missile to a designated location along its trajectory to separate the booster and main stage structures. During this process, the air rudders in the booster stage's rudder compartment remain at their initial zero position, requiring only a delayed deflection after the separation of the booster and main stage structures. Using a full-state rudder compartment and a complete rudder control system to control the air rudder deflection in this situation would be significantly ineffective and detrimental to reducing development costs.

[0004] Therefore, the inventors believe that it is necessary to provide a missile air rudder deflection device, which, through a simple structure, can meet the requirements of delayed deflection only after the separation of the booster stage and the main stage body structure in missile special development flight tests, thereby improving the cost-effectiveness and reducing development costs. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a missile air rudder deflection device.

[0006] According to the present invention, a missile air rudder deflection device includes: an air rudder, a base, a pull rod, a tension spring, a pin puller actuator and an elastic plunger; a stepped shaft is connected below the trapezoidal rudder surface of the air rudder, the lower end of the stepped shaft is movably mounted on the base, one end of the pull rod is tightly connected to the stepped shaft, and the other end is tightly connected to one end of the tension spring, the other end of the tension spring is tightly mounted on the base; the pin puller actuator is mounted on the base, and the pin of the pin puller actuator is plugged into and engaged with the stepped shaft; the elastic plunger is mounted on the base, and the elastic rod of the elastic plunger is pressed against the stepped shaft.

[0007] Preferably, the stepped shaft is composed of a small shaft, a middle shaft and a large shaft from bottom to top, the small shaft is a threaded shaft section, the middle shaft is a polished rod shaft section, and the large shaft is provided with a cylindrical hole, a rectangular hole, a round through hole and a waist-shaped hole; the rectangular hole is coaxial with the round through hole, and the axis is at an angle to the symmetrical surface of the rudder surface; the cylindrical hole and the waist-shaped hole are at the same height, both are located below the rectangular hole, and the cylindrical hole is located on the symmetrical surface of the rudder surface.

[0008] Preferably, the pin pulling actuator is connected to an external power source, and the pin pulling is plug-fitted into the cylindrical hole.

[0009] Preferably, the end of the elastic rod rests on the large shaft under the action of elastic force, and when the stepped shaft rotates, the elastic rod can be inserted into the waist-shaped hole.

[0010] Preferably, the base includes a bottom plate and two vertical plates, the two vertical plates are perpendicular to each other and wrap around a corner of the bottom plate, and both vertical plates are provided with vertical plate mounting holes; bottom plate screw holes and bottom plate through holes are diagonally provided on the bottom plate, and the bottom plate through holes are located at a corner of the bottom plate wrapped by the two vertical plates.

[0011] Preferably, the stepped shaft passes through the through hole of the base plate, and the lower end of the middle shaft extends to below the bottom surface of the base, and the middle shaft rotates with the base plate through the through hole of the base plate; a third fixing device is installed on the small shaft, and the third fixing device includes a third nut, a third flat washer and a third elastic washer.

[0012] Preferably, the pull rod is an L-shaped rod, which includes a threaded section, a rectangular section and a cylindrical section connected in sequence. The cylindrical section extends vertically downward from one end of the rectangular section, and the cylindrical section cooperates with the rectangular section to form the corner of the L-shaped rod; the cylindrical section is fastened to one end of the tension spring.

[0013] Preferably, the rectangular segment is plugged into the rectangular hole, and the threaded segment passes through the rectangular hole and the round through hole. A first fixing device is installed on the threaded segment, and the first fixing device includes a first nut, a first flat washer and a first elastic washer.

[0014] Preferably, the tension spring is in a stretched state, and one end of the tension spring away from the pull rod is fastened to the base through a screw, and the screw is fastened to the screw hole of the bottom plate by threaded fit.

[0015] Preferably, the pin pulling actuator and the elastic plunger are respectively fastened to the two vertical plates by a second fixing device, and the second fixing device includes a screw, a second flat washer and a second elastic washer.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] 1. The present invention inserts a pin on a pin puller actuator into a stepped shaft to restrict the air rudder from rotating freely. After activation, the pin is completely withdrawn from the air rudder. Under the action of the deflection torque applied by the tension spring, the pull rod pulls the air rudder to rotate, and the elastic rod of the elastic plunger is inserted into the stepped shaft, stopping the air rudder from rotating, completing the delayed deflection action after the booster stage and main stage body structures are separated. By applying a deflection torque to the air rudder, combined with the unlocking action of the pin puller actuator and the locking action of the elastic plunger, the use of a full-state servo cabin is avoided, greatly improving the cost-effectiveness and significantly reducing development costs.

[0018] 2. The present invention provides four holes, namely a cylindrical hole, a rectangular hole, a round through hole and a waist-shaped hole, on the stepped shaft of the air rudder. Through the cooperation of the rectangular hole and the round through hole, the threaded section of the pull rod is fixed on the outside of the round through hole, and the rectangular section cannot pass through the round through hole, so that the pull rod and the air rudder form a firm connection relationship; through the plug-in cooperation of the pull pin and the cylindrical hole, in the initial state, the pull pin can limit the air rudder 1, and in the starting state, the pull pin can be completely withdrawn from the cylindrical hole, releasing the rotation restriction of the air rudder; when the air rudder rotates, the elastic rod can be inserted into the waist-shaped hole, so that the air rudder 1 stops rotating; through the simple hole design, multiple limit positions of the air rudder are completed, the operation is simple, the installation is convenient, and it helps to improve the test efficiency.

[0019] 3. The present invention uses a tension spring in conjunction with a pull rod. The tension spring in a stretched state actively pulls the pull rod under elastic action, thereby applying a deflection torque to the air rudder. Through a simple structural design, the rotation requirements of the air rudder can be met, greatly reducing the test cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0021] Figure 1 This is a front view of a missile air rudder deflection device mainly embodied in the present invention;

[0022] Figure 2 This is a right side view of a missile air rudder deflection device mainly embodied in the present invention;

[0023] Figure 3 This is a left side view of a missile air rudder deflection device mainly embodied in the present invention;

[0024] Figure 4 This is a top view of a missile air rudder deflection device mainly embodied in the present invention;

[0025] Figure 5 The present invention mainly embodies Figure 2 Top view along section BB;

[0026] Figure 6 The present invention mainly embodies Figure 1 Top view along section AA;

[0027] Figure 7 This is a side view of the air rudder that is mainly embodied in the present invention;

[0028] Figure 8 This is a rear view of the air rudder that is mainly embodied in the present invention;

[0029] Figure 9 This is a front view of the air rudder mainly embodied in the present invention;

[0030] Figure 10 The present invention mainly embodies Figure 7 Cross-section along CC;

[0031] Figure 11 The present invention mainly embodies Figure 7 Cross-section along DD;

[0032] Figure 12 This is a top view of the base that mainly embodies the present invention;

[0033] Figure 13 This is a front view of the base that mainly embodies the present invention;

[0034] Figure 14 This is a side view of the base that mainly embodies the present invention;

[0035] Figure 15 This is a front view of the pull rod mainly embodying the present invention;

[0036] Figure 16 This is a side view of the pull rod that is mainly embodied in the present invention;

[0037] Figure 17 This is a front view of the missile air rudder deflection device in the activated state, which mainly reflects the present invention;

[0038] Figure 18 This is a right side view of the missile air rudder deflection device in the activated state, which mainly embodies the present invention;

[0039] Figure 19 This is a left side view of the missile air rudder deflection device in the activated state, which mainly reflects the present invention;

[0040] Figure 20 This is a top view of the missile air rudder deflection device in the activated state, which mainly reflects the present invention;

[0041] Figure 21 The present invention mainly embodies Figure 17 Top view along section AA.

[0042] As shown in the figure:

[0043] Air rudder 1 base 2 pull rod 3

[0044] Extension spring 4 Pin puller actuator 5 Elastic plunger 6

[0045] Screw 7 First fixing device 8 Pull pin 11

[0046] Elastic rod 12 Second fixing device 13 Third fixing device 16

[0047] Cylindrical hole 101 Rectangular hole 102 Round hole 103

[0048] Waist-shaped hole 104 bottom plate 201 vertical plate 202

[0049] Bottom plate through hole 203 Bottom plate screw hole 204 Vertical plate mounting hole 205

[0050] Threaded segment 301 Rectangular segment 302 Cylindrical segment 303 DETAILED DESCRIPTION

[0051] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, without departing from the scope of the present invention, a number of variations and improvements may be made by those skilled in the art. These all fall within the scope of protection of the present invention.

[0052] like Figure 1-6 As shown, a missile air rudder deflection device provided by the present invention includes: an air rudder 1, a base 2, a pull rod 3, a tension spring 4, a pin puller actuator 5 and an elastic plunger 6; a stepped shaft is connected below the trapezoidal rudder surface of the air rudder 1, and the lower end of the stepped shaft is movably mounted on the base 2; one end of the pull rod 3 is tightly connected to the stepped shaft, and the other end is tightly connected to one end of the tension spring 4, and the other end of the tension spring 4 is tightly mounted on the base 2; the pin puller actuator 5 is mounted on the base 2, and the pin puller 11 of the pin puller actuator 5 is plugged into and engaged with the stepped shaft; the elastic plunger 6 is mounted on the base 2, and the elastic rod 12 of the elastic plunger 6 is pressed against the stepped shaft.

[0053] After the assembly of the present application is completed, the pin 11 on the pin-pulling actuator 5 is inserted into the stepped shaft, restricting the air rudder 1 from rotating freely. After the present application is started, the pin 11 is completely withdrawn from the air rudder 1. Under the deflection torque applied by the tension spring 4, the pull rod 3 pulls the air rudder 1 to rotate. Then, the elastic rod 12 of the elastic plunger 6 is inserted into the stepped shaft, and the air rudder 1 stops rotating, completing the delayed deflection action after the booster stage and main stage body structures are separated. The present application applies a deflection torque to the air rudder 1, combines the unlocking action of the pin-pulling actuator 5 with the locking action of the elastic plunger 6, avoids the use of a full-state servo cabin, greatly improves the cost-effectiveness, and significantly reduces the development cost.

[0054] like Figure 7-11 As shown, the stepped shaft consists of a small shaft, a middle shaft, and a large shaft from bottom to top. The small shaft is a threaded shaft section, the middle shaft is a polished shaft section, and the large shaft is provided with a cylindrical hole 101, a rectangular hole 102, a round hole 103, and a waist-shaped hole 104. The rectangular hole 102 and the round hole 103 are coaxial, and their axes are at an angle to the symmetric plane of the rudder. The cylindrical hole 101 and the waist-shaped hole 104 are located at the same height and staggered, both located below the rectangular hole 102, and the cylindrical hole 101 is located on the symmetric plane of the rudder. In actual application, the position of each hole can be adjusted, and this application only introduces the optimal position scheme.

[0055] The pin 11 engages with the cylindrical hole 101 and, in its initial state, secures the air rudder 1. The pin actuator 5 is connected to an external power source. When powered on, the internal explosive device detonates, pushing the pin 11 completely out of the cylindrical hole 101 of the air rudder 1, releasing the rotation restriction on the air rudder 1.

[0056] The end of the elastic rod 12 rests on the main shaft under the action of elastic force. When the air rudder 1 rotates with the stepped shaft, the elastic rod 12 can be inserted into the waist-shaped hole 104, thereby restricting the air rudder 1 and stopping the rotation of the air rudder 1.

[0057] like Figure 12-14 As shown, the base 2 includes a bottom plate 201 and two vertical plates 202. The two vertical plates 202 are perpendicular to each other and wrap around a corner of the bottom plate 201. Both vertical plates 202 are provided with vertical plate mounting holes 205; bottom plate screw holes 204 and bottom plate through holes 203 are diagonally provided on the bottom plate 201, and the bottom plate through holes 203 are located at a corner of the bottom plate 201 wrapped by the two vertical plates 202.

[0058] The stepped shaft passes through the bottom plate through-hole 203, and the lower end of the middle shaft extends below the bottom surface of the base 2. The middle shaft rotates with the bottom plate 201 through the bottom plate through-hole 203. A third fixing device 16 is installed on the small shaft. The third fixing device 16 includes a third nut, a third flat washer, and a third elastic washer. This ensures that the middle shaft can stably rotate within the bottom plate through-hole 203 under the pull of the pull rod 3.

[0059] like Figure 15 and 16 As shown, the pull rod 3 is an L-shaped rod, comprising a threaded section 301, a rectangular section 302, and a cylindrical section 303, which are sequentially connected. The cylindrical section 303 extends vertically downward from one end of the rectangular section 302, and the cylindrical section 303 and the rectangular section 302 cooperate to form the corner of the L-shaped rod. The cylindrical section 303 is tightly connected to one end of the tension spring 4.

[0060] The rectangular section 302 is inserted into the rectangular hole 102, and the threaded section 301 passes through the rectangular hole 102 and the circular hole 103. A first fixing device 8 is mounted on the threaded section 301. The first fixing device 8 comprises a first nut, a first flat washer, and a first elastic washer. The threaded section 301 is secured to the outside of the circular hole 103 by the threaded section 301. Neither the rectangular section 302 nor the first fixing device 8 can pass through the circular hole 103. This creates a secure connection between the tie rod 3 and the air rudder 1, allowing the tie rod 3 to fully drive the air rudder 1 in rotation.

[0061] In the initial state after assembly, the tension spring 4 is in a stretched state, and one end of the tension spring 4 away from the pull rod 3 is fastened to the base 2 via a screw 7 , which is threadedly engaged with the screw hole 204 of the base plate for fastening.

[0062] The pin puller actuator 5 and the elastic plunger 6 are secured to the two vertical plates 202, respectively, by a second securing device 13. The second securing device 13 is secured to the vertical plate mounting holes 205 and comprises a screw, a second flat washer, and a second elastic washer. Preferably, the air rudder 1 rotates from the waist-shaped hole 104 toward the cylindrical hole 101, so that the pin puller actuator 5 is mounted on the vertical plate 202 closest to the tension spring 4. Similarly, the pin puller actuator 5 and the elastic plunger 6 can be interchanged by simply swapping the positions of the waist-shaped hole 104 and the cylindrical hole 101.

[0063] When assembling the missile air rudder deflection device, screw 7 is installed in screw hole 204 on the base plate of base 2. The rectangular section 302 of tie rod 3 is inserted into the rectangular hole 102 of air rudder 1 until the threaded section 301 emerges. Then, the first fixture 8 is used to secure the tie rod 3, with the cylindrical section 303 facing downward. The stepped shaft of air rudder 1 is passed through base 2's base plate through-hole 203 until the central axis fits into the through-hole 203 and the lower end of the central axis slightly protrudes from the bottom surface of base 2. Then, the third fixture 16 is installed on the small shaft, close to the lower end of the central axis. Now, air rudder 1 can rotate freely around base 2's base plate through-hole 203. The pin puller actuator 5 is installed on the outside of the vertical plate 202 and secured with the second fixture 13. The pin 11 on the pin puller actuator 5 is inserted into the cylindrical hole 101 of air rudder 1, restricting the air rudder 1 from rotating freely. The elastic plunger 6 is mounted on the outside of the other vertical plate 202 and secured by the second fixing device 13. The end of the elastic rod 12, under the action of elastic force, now rests against the main shaft of the air rudder 1, locating on the same cross-section as and adjacent to the waist-shaped hole 104 on the main shaft of the air rudder 1. Finally, the tension spring 4 is stretched to hook onto the screw 7 and the cylindrical section 303 of the tie rod 3, respectively, thereby applying a deflecting torque to the air rudder 1 through the tie rod 3. The missile air rudder deflection device is now fully assembled and in its pre-activation state.

[0064] like Figure 17-21 As shown, when the pin puller actuator 5 is connected to an external power source, the internal explosive device detonates, pushing the pin puller 11 completely out of the cylindrical hole 101 of the air rudder 1, releasing the rotation restriction of the air rudder 1. At the same time, under the deflection torque applied by the tension spring 4, the air rudder 1 rotates, causing the elastic rod 12 of the elastic plunger 6 to slide into the waist-shaped hole 104 on the main shaft of the air rudder 1. When the elastic rod 12 contacts the side wall of the waist-shaped hole 104, the air rudder 1 stops rotating. At this point, the missile's air rudder deflection device is in the activated state.

[0065] The present application has a simple structure and is easy to install, and can meet the requirements of missile special development flight tests in which only delayed deflection is required after the booster stage and main stage body structures are separated, thereby greatly improving the cost-effectiveness and significantly reducing development costs.

[0066] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0067] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A missile air rudder deflection device, characterized in that: include: An air rudder (1), a base (2), a pull rod (3), a tension spring (4), a pin-pulling actuator (5), and an elastic plunger (6); A stepped shaft is connected below the trapezoidal rudder surface of the air rudder (1), and the lower end of the stepped shaft is movably mounted on the base (2); one end of the pull rod (3) is tightly connected to the stepped shaft, and the other end is tightly connected to one end of the tension spring (4); the other end of the tension spring (4) is tightly mounted on the base (2); The pin pulling actuator (5) is installed on the base (2), and the pin pulling actuator (5) has a pin pulling pin (11) that is plug-fitted to the stepped shaft; The elastic plunger (6) is mounted on the base (2), and the elastic rod (12) of the elastic plunger (6) is pressed against the stepped shaft; The base (2) comprises a bottom plate (201) and two vertical plates (202); The pin-pulling actuator (5) is mounted on the outer side of the vertical plate (202) and fixed by the second fixing device (13). At this time, the pin (11) on the pin-pulling actuator (5) is inserted into the cylindrical hole (101) of the air rudder (1), restricting the air rudder (1) from rotating freely. When the pin-pulling actuator (5) is connected to an external power source, the internal pyrotechnics explode, pushing the pin-pulling actuator (11) to completely withdraw from the cylindrical hole (101) of the air rudder (1), thereby releasing the rotation restriction on the air rudder (1).

2. The missile air rudder deflection device according to claim 1, characterized in that: The stepped shaft is composed of a small shaft, a middle shaft and a large shaft from bottom to top, the small shaft is a threaded shaft section, the middle shaft is a polished rod shaft section, and the large shaft is provided with a cylindrical hole (101), a rectangular hole (102), a round through hole (103) and a waist-shaped hole (104); The rectangular hole (102) and the circular through hole (103) are coaxial, and the axis forms an angle relationship with the symmetric surface of the rudder surface; The cylindrical hole (101) and the waist-shaped hole (104) are located at the same height, both located below the rectangular hole (102), and the cylindrical hole (101) is located on the symmetrical surface of the rudder surface.

3. The missile air rudder deflection device according to claim 2, characterized in that: The pin pulling actuator (5) is connected to an external power source, and the pin pulling (11) is plugged into and fitted with the cylindrical hole (101).

4. The missile air rudder deflection device according to claim 2, characterized in that: The end of the elastic rod (12) rests against the large shaft under the action of elastic force, and when the stepped shaft rotates, the elastic rod (12) can be inserted into the waist-shaped hole (104).

5. The missile air rudder deflection device according to claim 2, characterized in that: The two vertical plates (202) are perpendicular to each other and wrap around a corner of the bottom plate (201), and both vertical plates (202) are provided with vertical plate mounting holes (205); The bottom plate (201) is provided with a bottom plate screw hole (204) and a bottom plate through hole (203) at opposite corners, and the bottom plate through hole (203) is located at a corner of the bottom plate (201) wrapped by the two vertical plates (202).

6. The missile air rudder deflection device according to claim 5, characterized in that: The stepped shaft passes through the bottom plate through hole (203), and the lower end of the middle shaft extends to below the bottom surface of the base (2), and the middle shaft rotates with the bottom plate (201) through the bottom plate through hole (203); A third fixing device (16) is installed on the small shaft, and the third fixing device (16) comprises a third nut, a third flat washer and a third elastic washer.

7. The missile air rudder deflection device according to claim 2, characterized in that: The pull rod (3) is an L-shaped rod, and the pull rod (3) comprises a threaded section (301), a rectangular section (302), and a cylindrical section (303) connected in sequence. The cylindrical section (303) extends vertically downward from one end of the rectangular section (302). The cylindrical section (303) cooperates with the rectangular section (302) to form a corner of the L-shaped rod. The cylindrical section (303) is tightly connected to one end of the tension spring (4).

8. The missile air rudder deflection device according to claim 7, characterized in that: The rectangular section (302) is plugged into the rectangular hole (102), and the threaded section (301) passes through the rectangular hole (102) and the round through hole (103). A first fixing device (8) is installed on the threaded section (301), and the first fixing device (8) includes a first nut, a first flat washer, and a first elastic washer.

9. The missile air rudder deflection device according to claim 5, characterized in that: The tension spring (4) is in a stretched state, and one end of the tension spring (4) away from the pull rod (3) is fastened to the base (2) via a screw rod (7), and the screw rod (7) is threadedly matched and fastened to the bottom plate screw hole (204).

10. The missile air rudder deflection device according to claim 5, characterized in that: The pin pulling actuator (5) and the elastic plunger (6) are respectively fixedly mounted on the two vertical plates (202) via a second fixing device (13), wherein the second fixing device (13) comprises a screw, a second flat washer and a second elastic washer.

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