A rocket support mechanism capable of automatically falling off

Abstract

The present application discloses an automatically detachable rocket support mechanism, which relates to the field of rocket launch and includes a small slider fixed to the rocket body; a large sliding shoe, one end of which is slidably connected to the small slider and the other end of which is slidably connected to a guide rail; a locking mechanism, which includes an elastic snap ring extending from the end of the large sliding shoe facing away from the small slider, passing through the large sliding shoe and inserting into the small slider to lock the small slider and the large sliding shoe; and an unlocking mechanism, one end of which is connected to the locking mechanism and the other end to one end of the guide rail, so that when the rocket body leaves the guide rail, the unlocking mechanism drives the locking mechanism to slide out of the small slider and release the lock. During launch, the mechanism can provide auxiliary support, sliding guidance, and position limiting for the rocket body while on track, reducing vibration. The mechanism can quickly detach upon leaving the track, eliminating the adverse effects of aerodynamic drag.

Description

Technical Field

[0001] The present invention relates to a rocket supporting mechanism which can be automatically detached and is installed on a rocket launching orienter body, belonging to the technical field of carrier rocket launching.

[0002] It is used to provide auxiliary support on the launch device after the rocket is loaded, axial and vertical sliding guidance and limitation during launch, and rapid fall-off at the moment of leaving orbit, and fall into the storage cabin, thereby ensuring the reliable launch of the rocket, restraining relevant parts of the rocket on the track, and reducing lateral vibration; it is thrown into the storage cabin during flight, reducing the wind resistance of the rocket and improving flight stability. Background Art

[0003] When designing a launch vehicle structure, the payload compartment diameter sometimes becomes significantly larger than the engine diameter, or the main stage diameter is significantly smaller than the booster stage diameter. To prevent interference between the rocket and the guide rails, the payload compartment requires protection to minimize axial and vertical vibrations during launch. Alternatively, a two-stage rocket's main stage diameter is significantly smaller than the booster stage diameter. When the rocket's center of mass is at a certain position on the main stage, a support mechanism, taller than typical rocket legs, is designed on the front slider. This mechanism assists in supporting the rocket in its horizontally parked state, guides and limits the rocket on the guide rails during on-orbit motion, and automatically drops off quickly upon de-orbit to prevent the asymmetric layout of the legs, which are larger and have a greater negative mass, from affecting the rocket's aerodynamic characteristics.

[0004] Traditional rocket auxiliary support uses explosive bolts to attach the rocket's taller, integral legs to the auxiliary support position on the bulkhead. These explosive bolts break and separate after launch. While this meets the requirements, the electrical operation sequence is complex and the cost is high. Furthermore, the structural installation is complex, and the testing process is lengthy. Another auxiliary support method utilizes a liftable arc seat mechanism. This mechanism utilizes the screw lifting principle to ensure effective contact between the rocket and the arc seat. However, due to the lack of a reliable connection to the guide rail during on-orbit motion, only pre-erect support is guaranteed. This mechanism needs to be removed before the rocket is ignited. Summary of the Invention

[0005] The technical problem solved by the present invention is: to overcome the shortcomings of the existing technology and provide a rocket support mechanism that can be automatically detached. The mechanism is efficient, simple and can be detached quickly, so as to provide sliding guidance and limitation during launch, provide auxiliary support, reduce the lateral vibration of the rocket, and detach quickly at the moment of leaving orbit, thereby reliably completing the rocket launch mission.

[0006] The technical solution of the present invention is:

[0007] A rocket supporting mechanism capable of automatically falling off, comprising:

[0008] A small slider, connected to the rocket body;

[0009] A large sliding shoe, one end of which is slidably connected to the small sliding block, and the other end of which is slidably connected to the guide rail;

[0010] The locking mechanism starts from the end of the large sliding shoe facing away from the small sliding shoe, passes through the large sliding shoe and is inserted into the small sliding shoe to lock the small sliding shoe and the large sliding shoe;

[0011] The unlocking mechanism has one end connected to the locking mechanism and the other end connected to one end of the guide rail, so that when the rocket body leaves the guide rail, the unlocking mechanism drives the locking mechanism to slide out of the small slider and release the lock.

[0012] The locking mechanism includes a pin shaft and an elastic snap ring. The small slider is provided with a second insertion hole, and the large slide shoe is provided with a first insertion hole. The first insertion hole is located on the side of the large slide shoe away from the direction of movement of the rocket. When the second insertion hole is opposite to the first insertion hole, the small slider and the large slide shoe are installed in place. The elastic snap ring is clamped at the interface position between the first insertion hole and the second insertion hole. The pin shaft is inserted into the first insertion hole and the second insertion hole, and into the elastic snap ring. The unlocking mechanism is connected to the pin shaft.

[0013] Along the direction pointing to the rocket body, the first insertion hole includes a first chamber and a second chamber, the inner diameter of the second chamber is smaller than that of the first chamber, and a first interface is formed between the first chamber and the second chamber. The second insertion hole includes a third chamber and a fourth chamber, the inner diameter of the fourth chamber is larger than that of the third chamber, and a second interface is formed between the third chamber and the fourth chamber; the outer wall of the elastic retaining ring is provided with a first positioning ring and a second positioning ring, the first positioning ring contacts the first interface, and the second positioning ring contacts the second interface.

[0014] The end of the elastic snap ring located in the second insertion hole is provided with a plurality of notches.

[0015] The notch extends along the radial direction of the rocket body to the interface position between the first insertion hole and the second insertion hole.

[0016] The locking mechanism further includes a stabilizing structure for stabilizing the pin in the second insertion hole;

[0017] The stabilization mechanism includes a reset spring and a retaining ring. A reset protrusion is provided on the outer wall of the pin shaft. The reset protrusion is located at the end of the elastic retaining ring away from the rocket body. The reset spring is sleeved outside the pin shaft. The retaining ring is threadedly connected to the large sliding shoe. One end of the reset spring abuts against the side of the reset protrusion away from the elastic retaining ring, and the other end abuts against the retaining ring.

[0018] The unlocking mechanism includes a storage cabin, a wire rope, a fixed pulley and a wire rope winding. One end of the storage cabin is arranged at the bottom of the guide rail end, and the other end extends from under the guide rail along the direction of rocket launch. The storage cabin is a box with an open top. The wire rope winding and the fixed pulley are connected in the storage cabin. The wire rope connected to the wire rope winding passes around from under the fixed pulley and is connected to the locking mechanism.

[0019] The top of the large sliding shoe is provided with a rectangular slot that mates with the small slider. The bottom of the large sliding shoe is provided with left and right legs. A guide rail is connected to the orienter body. The guide rail includes a left track and a right track. The left leg slides on the left track, while the right leg slides on the right track. A steel wire rope passes through a movement space between the left and right tracks.

[0020] The end of the small sliding block facing away from the rocket launching direction is provided with a protrusion, which is clamped on the end of the large sliding shoe for positioning and guiding the large sliding shoe.

[0021] The raised portion is arranged at an angle, and the raised portion gradually tilts upward along the launching direction of the rocket.

[0022] In summary, this application has at least the following beneficial technical effects:

[0023] (1) The mechanism adopts mechanical structure base hole clearance fit, reset spring and elastic snap ring, pin shaft combination to achieve the positioning fit of small slider and large slide shoe. The structure has good coordination and simple structure, which improves the working stability under the vibration environment of rocket off-orbit.

[0024] (2) By rationally designing the fixed pulley and wire rope winding mechanism, the pin shaft can be moved up and down and the elastic clamp can be locked and unlocked. By designing the wire rope length and the position of the fixed pulley, the large sliding shoe components can be completely detached and moved into the storage cabin. At the moment the rocket leaves the orbit, the center of mass of the large sliding shoe is designed to be biased to the front side, which facilitates reliable detachment in the box-shaped storage cabin. There will be no interference with the tail of the rocket on the guide rail;

[0025] (3) The mechanism is triggered when the rocket moves after ignition, and does not require any other external force to drive it. It will automatically detach from the rocket as the rocket leaves the orbit. It is lighter than the explosive bolt structure and has no electrical control risks. It also falls into the storage compartment at the front end of the launch mechanism director, without the risk of collision with the rocket. Adaptive adjustments can be made to the mechanism, and different large sliding shoe structures, fall-off times, and fall-off positions can be designed to meet the launch requirements of different types of rockets.

[0026] (4) The entire limiter and force transmission components are designed to be inside the mechanism and the orienter body. This ensures reliable movement and greater safety. There will be no splashing during rocket loading and test launches, or mechanical safety hazards caused by the wire rope mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the overall structure of the supporting mechanism and the elastic clamp structure of an embodiment of the present application;

[0028] Figure 2 A cross-sectional view of the support mechanism between the rocket body and the guide rail;

[0029] Figure 3 a is a structural diagram of the small slider, Figure 3 b is a schematic diagram of the structure of the large sliding shoe;

[0030] Figure 4 The overall external map of the support institution;

[0031] Figure 5 The connection diagram of the small slider guiding the large sliding shoe movement position;

[0032] Figure 6 It is a partial cross-sectional view of the support mechanism;

[0033] Explanation of reference numerals: 1. small slider; 2. large sliding shoe; 3. pin; 4. elastic snap ring; 5. return spring; 6. retaining ring; 7. guide rail; 8. storage compartment; 9. wire rope; 10. wire rope winding; 11. fixed pulley; 12. orienter body;

[0034] 13. Second insertion hole; 14. First insertion hole; 15. First interface; 16. Second interface; 17. First positioning ring; 18. Second positioning ring; 19. Notch; 20. Reset protrusion; 21. Rectangular groove; 22. Left support leg; 23. Right support leg; 24. Protrusion; 25. Rocket body. DETAILED DESCRIPTION

[0035] The present application is further described in detail below with reference to the accompanying drawings and specific embodiments:

[0036] The embodiment of the present application discloses a rocket support mechanism that can automatically fall off, such as Figure 1 and Figure 2 As shown, it includes a small slider 1, a large sliding shoe 2, a pin 3, an elastic snap ring 4, a return spring 5, a retaining ring 6, a guide rail 7, a storage compartment 8, a wire rope 9, a wire rope winding 10, a fixed pulley 11, and a director body 12. The rocket support mechanism is installed on the rocket and the launcher director guide rail to support the rocket during launch and then quickly fall off.

[0037] The small slider 1 is fixedly connected to the rocket body; one end of the large sliding shoe 2 is slidably connected to the small slider 1, and the other end is slidably connected to the guide rail 7. The top of the large sliding shoe 2 is provided with a rectangular slot 21 that mates with the small slider 1; the bottom of the large sliding shoe 2 is provided with a left support leg 22 and a right support leg 23. The guide rail 7 is connected to the orienter body 12. The guide rail 7 includes a left track and a right track. The left support leg 22 is slidably connected to the left track, and the right support leg 23 is slidably connected to the right track. There is a movement space between the left and right tracks, and the wire rope 9 passes through the movement space.

[0038] like Figure 1 As shown, the small slider 1 defines a second insertion hole 13, and the large sliding shoe 2 defines a first insertion hole 14. When the second insertion hole 13 is aligned with the first insertion hole 14, the small slider 1 and the large sliding shoe 2 are in place. An elastic snap ring 4 is positioned at the interface between the first and second insertion holes 14, 13. The pin 3 is inserted into the first and second insertion holes 14, 13, and into the elastic snap ring 4. A return protrusion 20 is provided on the outer wall of the pin 3, located on the end of the elastic snap ring 4 facing away from the rocket body. A return spring 5 is sleeved around the pin 3, and a retaining ring 6 is connected to the large sliding shoe 2. One end of the return spring 5 abuts against the side of the return protrusion 20 facing away from the elastic snap ring 4, and the other end abuts against the retaining ring 6. In its natural state, the return spring 5 is compressed, providing an upward force to the pin 3. During launch, the pin 3 will not fall out of the first insertion hole 14 due to vibration from the rocket body, thus improving the positional stability of the pin 3. Furthermore, the return spring 5 can be compressed and deformed, so when the pin 3 is subjected to a downward pulling force, it can slide downward and contact the locking between the small slider 1 and the large sliding shoe 2.

[0039] like Figure 2 and Figure 3 a. Figure 3 As shown in FIG. 2b, along the direction toward the rocket body, the first insertion hole 14 comprises a first chamber and a second chamber. The second chamber has a smaller inner diameter than the first chamber, forming a first interface 15 between the first and second chambers. The second insertion hole 13 comprises a third chamber and a fourth chamber. The fourth chamber has a larger inner diameter than the third chamber, forming a second interface 16 between the third and fourth chambers. The outer wall of the elastic snap ring 4 is provided with a first positioning ring 17 and a second positioning ring 18. The first positioning ring 17 contacts the first interface 15, and the second positioning ring 18 contacts the second interface 16. This ensures that the elastic snap ring 4 can be more stably secured between the small slider 1 and the large shoe 2 during installation. The end of the elastic snap ring 4 located within the second insertion hole 13 is provided with multiple notches 19. These notches 19 extend radially along the rocket body to the interface between the first and second insertion holes 14, 13. The provision of the notches 19 facilitates deformation and contact locking of the elastic snap ring 4 after the pin 3 is released from the second insertion hole 13.

[0040] like Figure 4 、 Figure 5 As shown, one end of the storage cabin 8 is arranged at the bottom of the end of the guide rail 7, and the other end extends from under the guide rail 7 along the direction of rocket launch. The storage cabin 8 is a box with an open top. The wire rope 9 winding and the fixed pulley 11 are connected in the storage cabin 8. The wire rope 9 connected to the wire rope winding passes around from under the fixed pulley 11 and is connected to the locking mechanism.

[0041] like Figure 6 As shown, the end of the small slider 1 facing away from the rocket launch direction is equipped with a raised portion 24. This raised portion 24 engages the end of the large slider 2 to position and guide the large slider 2. The raised portion 24 is tilted and gradually slopes upward along the direction of the rocket launch. When the pin 3 is pulled out of the second insertion hole 13 and the large slider 2 moves to the front end of the guide rail 7, the large slider 2 can be pulled over by the inclined surface of the raised portion 24 at the rear of the small slider 1, causing it to flip and fall into the storage compartment 8.

[0042] This mechanism utilizes the coordination of a small rocket slider 1 and a large slide shoe 2, secured by an elastic retaining ring 4, to ensure the rocket's on-orbit motion during launch, completing a short glide. At the moment of derailment, a wire rope 9 on a pulley pulls down a pin 3, deforming and unlocking the elastic retaining ring 4 between the small slider 1 and the large slide shoe 2. Driven by the small rocket slider 1, the large slide shoe 2 flips mid-air using its eccentric gravitational torque and inertia, ultimately sliding into a storage compartment 8. This prevents erosion by the combustion gas stream or collision with the rocket caused by ejection. This mechanism is primarily suitable for rapidly disengaging the front support mechanism during rocket launch, and the mechanical mechanism can be reused after launch.

[0043] The launch support mechanism is adapted to the special rocket structure and shape and is suitable for launches on the upper support rail 7. It is small in size and light in weight; it can be stored automatically after being detached and will not collide with the rocket tail or cabin.

[0044] The implementation principles of this application are:

[0045] Based on the actual rocket's structural shape and mass center of mass, the support mechanism's installation location and structural design are determined, the installation method is optimized, and the components are assembled rationally. First, place the rocket on the transfer bracket and install the small slider 1 and large slide shoe 2. Then, install the elastic retaining ring 4, assemble the pin 3 and return spring 5, and finally install and secure the retaining ring 6 in place. After the rocket is mounted, the rocket's front and rear legs and the front large slide shoe 2 slide within the grooves of the guide rail 7. When the rocket's rear leg contacts the rear baffle, the large slide shoe 2 is installed in the guide rail groove.

[0046] At this time, the wire rope 9 and the pin 3 are reliably connected on the launch director body 12, and the wire rope is connected to the wire rope winding 10 through the groove of the fixed pulley 11. The length of the wire rope 9 is adjusted to maintain a certain redundancy of the wire rope on the wire rope winding 10 so that the pin 3 is in a state of waiting for stress.

[0047] During operation, after the rocket ignites and begins to move, the small slider 1, fixed to the rocket, propels the large shoe 2 forward via its mating surfaces. When the wire rope 9, which has been routed around the fixed pulley 11, has sufficient length to allow for proper tension, it pulls down on the pin 3, causing it to move a certain distance downward along the inner cavity of the elastic retaining ring 4. At this point, the elastic retaining ring 4 loses its rigid support from the pin 3 and elastically deforms, disengaging from the inner cavity of the small slider 1, unlocking the small slider 1 and the large shoe 2.

[0048] After the small slider 1 and large slider 2 are unlocked, the large slider 2 moves to the front of the guide rail 7. Unconstrained at its base, it is pulled by the inclined surface of the raised portion at the rear of the small slider 1, causing it to flip over. Together with the wire rope 9, it falls into the storage compartment 8, effectively preventing the rocket's tail flame from eroding the mechanism itself and avoiding collisions with rocket components during launch.

[0049] The technologies not disclosed in the present invention are common knowledge to those skilled in the art.

[0050] Although the present invention is disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be based on the scope defined by the claims of the present invention.

Claims

1. A rocket support mechanism that can automatically fall off, characterized by: include A small slider (1) is fixedly connected to the rocket body; A large sliding shoe (2) is slidably connected to the small sliding block (1) at one end and slidably connected to the guide rail (7) at the other end; The locking mechanism starts from the end of the large sliding shoe (2) facing away from the small sliding block (1), the large sliding shoe (2) and the rectangular notch of the small sliding block (1) are matched, and then the elastic snap ring (4) passes through the large sliding shoe (2) and is inserted into the small sliding block (1) to achieve locking of the small sliding block (1) and the large sliding shoe (2); An unlocking mechanism, one end of which is connected to the locking mechanism and the other end of which is connected to one end of the guide rail (7), so that when the rocket body is separated from the guide rail (7), the unlocking mechanism drives the locking mechanism to slide out of the small slider (1) and release the lock; The locking mechanism comprises a pin (3) and an elastic snap ring (4); the small slider (1) is provided with a second insertion hole (13); the large slide shoe (2) is provided with a first insertion hole (14); when the second insertion hole (13) is aligned with the first insertion hole (14), the small slider (1) and the large slide shoe (2) are installed in place; the elastic snap ring (4) is clamped at the interface between the first insertion hole (14) and the second insertion hole (13); the pin (3) is inserted into the first insertion hole (14) and the second insertion hole (13), and is also inserted into the elastic snap ring (4); and the unlocking mechanism is connected to the pin (3); Along the direction pointing to the rocket body, the first insertion hole (14) includes a first chamber and a second chamber, the inner diameter of the second chamber is smaller than that of the first chamber, and a first interface (15) is formed between the first chamber and the second chamber; the second insertion hole (13) includes a third chamber and a fourth chamber, the inner diameter of the fourth chamber is larger than that of the third chamber, and a second interface (16) is formed between the third chamber and the fourth chamber; the outer wall of the elastic snap ring (4) is provided with a first positioning ring (17) and a second positioning ring (18), the first positioning ring (17) contacts the first interface (15), and the second positioning ring (18) contacts the second interface (16); The unlocking mechanism comprises a storage cabin (8), a steel wire rope (9), a fixed pulley (11) and a steel wire rope winding (10); one end of the storage cabin (8) is arranged at the bottom of the end of the guide rail (7), and the other end extends from below the guide rail (7) along the rocket launching direction; the storage cabin (8) is a box with an open top; the steel wire rope (9), the steel wire rope winding (10) and the fixed pulley (11) are connected in the storage cabin; the steel wire rope (9) connected to the steel wire rope winding (10) passes around from below the fixed pulley (11) and is connected to the locking mechanism.

2. The automatically detachable rocket support mechanism according to claim 1, characterized in that: The end of the elastic snap ring (4) located in the second insertion hole (13) is provided with a plurality of notches (19).

3. The automatically detachable rocket support mechanism according to claim 1, characterized in that: The locking mechanism further comprises a base hole clearance fit stabilizing structure for stabilizing the pin shaft (3) in the second insertion hole (13); The stabilizing mechanism comprises a reset spring (5) and a retaining ring (6); a reset protrusion (20) is provided on the outer wall of the pin shaft (3); the reset protrusion (20) is located at the end of the elastic retaining ring (4) away from the rocket body; the reset spring (5) is sleeved outside the pin shaft (3); the retaining ring (6) is connected to the large sliding shoe (2); one end of the reset spring (5) abuts against the side of the reset protrusion (20) away from the elastic retaining ring (4), and the other end abuts against the retaining ring (6).

4. The automatically detachable rocket support mechanism according to claim 1, characterized in that: The top of the large sliding shoe (2) is provided with a rectangular groove (21) that cooperates with the small sliding block (1); The bottom of the large sliding shoe (2) is provided with a left support leg (22) and a right support leg (23), the guide rail (7) is connected to the orienter body (12), the guide rail (7) includes a left rail and a right rail, the left support leg (22) is slidably connected to the left rail, and the right support leg (23) is slidably connected to the right rail, there is a gap between the left rail and the right rail, and the wire rope (9) passes through the gap.

5. The automatically detachable rocket support mechanism according to claim 1, characterized in that: The end of the small slider (1) facing away from the rocket launching direction is provided with a protrusion (24), and the protrusion (24) is provided at the end of the large sliding shoe (2) for positioning and guiding the movement of the large sliding shoe (2).

6. The automatically detachable rocket support mechanism according to claim 5, characterized in that: The raised portion (24) is arranged at an angle, and the raised portion (24) gradually tilts upward along the launch direction of the rocket to guide the movement of the large sliding shoe (2).

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