A reliable locking mechanism for the step-by-step deployment of a two-folding wing

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) and spacecraft technology, and discloses a reliable locking mechanism for the step-by-step deployment of a two-folding wing. The mechanism includes a first folding wing assembly, a locking assembly, a fixing plate, a second folding wing assembly, an unlocking assembly, and a cabin. The first folding wing assembly includes a first support, a first torsion spring, a first pin, a first shaft pin, a first compression spring, a first nut, a first pull pin, a first mounting lug, a first pivot pin, and a first wing shaft. The torsion spring is mounted on the first pin. The static arm is located on the boss of the first support, and the dynamic arm is located on the first wing shaft. The first pivot pin is inserted into the end of the first wing shaft. The first mounting lug slides along the inclined surface of the first wing shaft, while the first compression spring is compressed. When the first mounting lug disengages from the first wing shaft, the first mounting lug and the first pull pin rotate around the first pivot pin, and the first wing shaft rotates around the first pin. This invention is applicable to the field of UAVs and spacecraft with controlled two-folding actions, high synchronization and robustness, and limited storage space.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle and spacecraft technology, and in particular to a reliable locking mechanism for the step-by-step deployment of a two-folding wing. Background Technology

[0002] In modern aerospace fields such as unmanned aerial vehicles (UAVs) and spacecraft, aerodynamic control surfaces (such as missile control surfaces and UAV wings) are key components for attitude control and flight trajectory execution. To meet the urgent needs of high-density storage and transportation, universal launch platforms, and compact overall structures, folding designs have become one of the core means of miniaturizing these aircraft. By folding the wings during non-operational phases, the radial envelope space can be significantly reduced, ensuring that it does not affect the original launch and storage devices, and enabling efficient integration and multiple loading within a limited volume (such as within launch tubes, bomb bays, or carriers).

[0003] Currently, the folding wing deployment mechanisms widely used in domestic UAVs and aerospace vehicles largely rely on pyrotechnic-driven multi-path independent propulsion schemes, and are mostly single-folding mechanisms. This scheme equips each folding wing with an independent pyrotechnic device (such as an actuator) and a locking-unlocking mechanism. The pyrotechnic device actuates its corresponding push rod, unlocking and driving the deployment of all four wing surfaces. However, this traditional method has several inherent drawbacks: Poor synchronization and structural complexity: Due to the slight performance variations and actuation time differences among the four pyrotechnic components, the four push rods cannot achieve precise synchronization, resulting in inconsistent wing deployment timing and severely affecting the stability of the aircraft's initial attitude after exiting the cabin. Furthermore, the existence of four independent systems leads to a large number of mechanical parts, complex structural design, and increased manufacturing costs and failure rate.

[0004] System reliability bottleneck: Multiple sets of pyrotechnics and locking mechanisms constitute a series reliability model. Failure at any single point (such as a push rod not fully functioning) will cause the entire wing surface to malfunction or fail to deploy properly, which may lead to serious consequences such as instability in the missile's flight attitude.

[0005] Space reduction still has limitations: For applications with large wingspans or extremely demanding launch platform (such as vertical launch systems or fuselage bomb bays) space constraints, the radial envelope, which remains bulky after folding, limits the number of aircraft that can be carried and the versatility of the platform.

[0006] Therefore, existing single-folding schemes relying on pyrotechnics-driven, multi-path independent propulsion are insufficient to meet the stringent requirements of folding wings for precise action sequences, reliable two-stage locking, and high system integration. Developing a mechanism for the synchronized deployment and locking of a two-folding wing that can control both folding actions and possesses high synchronization and robustness has become an urgent technological need driving the development of next-generation compact aircraft. Summary of the Invention

[0007] The purpose of this invention is to provide a reliable locking mechanism for the step-by-step unfolding of a two-folding wing in order to solve the above-mentioned problems.

[0008] To achieve the above objectives, the present invention adopts the following technical solution: A reliable locking mechanism for the step-by-step deployment of a two-folding wing includes a first folding wing assembly, a locking assembly, a fixing plate, a second folding wing assembly, an unlocking assembly, and a cabin. The first folding wing assembly includes a first support, a first torsion spring, a first pin, a first shaft pin, a first compression spring, a first nut, a first pull pin, a first mounting lug, a first pivot pin, and a first wing shaft. The torsion spring is mounted on the first pin, the static arm is located on the boss of the first support, and the dynamic arm is located on the first wing shaft. The first pivot pin is inserted into the end of the first wing shaft. The first mounting lug slides along the inclined surface of the first wing shaft, while the first compression spring is compressed. When the first mounting lug disengages from the first wing shaft, the first mounting lug and the first pull pin rotate around the first pivot pin, and the first wing shaft rotates around the first shaft pin. The locking assembly includes a bracket, a spring pin, a compression spring, and a sleeve. The spring pin is inserted into the bracket and pressed by the compression spring and fixed by the sleeve. The spring pin slides along the built-in circular hole of the bracket against the spring force. The mounting plate is installed on the cabin body by screws, and the mounting plate has a built-in threaded hole. The second folding wing assembly includes a second support, a second torsion spring, a second pin, a second shaft pin, a second compression spring, a second nut, a second pull pin, a second mounting lug, a second pivot pin, and a second wing shaft. The second torsion spring is sleeved on the second pin. The static arm is located on the boss of the second support, and the dynamic arm is located on the second wing shaft. The second pivot pin is inserted into the end of the second wing shaft. The second mounting lug slides laterally along the second wing shaft, while the second compression spring is compressed. When the second mounting lug is disengaged from the second wing shaft, the second mounting lug and the second pull pin rotate around the second pivot pin, and the second wing shaft rotates around the second pin. The unlocking assembly includes a pyrotechnic component, a pyrotechnic support, a locking screw, a push rod, and a pawl. The push rod is fixedly connected to the pyrotechnic support by the locking screw, and the push rod slides axially along the inner hole of the pyrotechnic support.

[0009] Preferably, in the folded state, the first and second wing shafts overcome the spring forces of the first and second torsion springs respectively and rotate into the cabin. After they are in place, the claws enter the slots of the first and second wing shafts, and the locking screws fix the pyrotechnic support and the push rod, thus completing the wing surface locking in one folded state.

[0010] Preferably, in the folded state, the mounting ear plate 1 slides laterally along the wing shaft 1, the compression spring 1 is compressed, and after disengaging from the wing shaft 1, it rotates 135° around the pivot pin 1. The mounting ear plate 2 slides laterally along the wing shaft 2, the compression spring 2 is compressed, and after disengaging from the wing shaft 2, it rotates 135° around the pivot pin 2. It is then limited by the launch tube to complete the secondary folding.

[0011] Preferably, after the secondary folding wing unfolds and reliably locks out of the launch tube, the first compression spring releases its spring force, and the first mounting ear plate moves along the inclined surface of the wing shaft one around the pivot pin one under the spring pressure. After it is in place, the groove of the first mounting ear plate is inserted into the trapezoidal boss of the wing shaft one. The second compression spring releases its spring force, and the second mounting ear plate moves along the inclined surface of the wing shaft two around the pivot pin two under the spring pressure. After it is in place, the groove of the second mounting ear plate is inserted into the trapezoidal boss of the wing shaft two, thus completing the first stage of unfolding and locking.

[0012] Preferably, after the pyrotechnic device is ignited, the high-pressure gas shears off the locking screw and pushes the push rod and the pawl to move. The pawl disengages from the first and second wing shafts, completing the unlocking of the second-stage deployment.

[0013] Preferably, the first wing shaft and the second wing shaft rotate along the first pin shaft and the second pin shaft under the action of the first torsion spring and the second torsion spring, respectively, to complete the second-stage deployment action.

[0014] Preferably, after the first folding wing assembly and the second folding wing assembly are unfolded, the first wing shaft and the second wing shaft are pushed open by the force of the torsion spring. After they are in place, the spring pin is pushed into the positioning hole of the first wing shaft and the second wing shaft by the pressure of the compression spring, thus completing the locking of the second-stage unfolding.

[0015] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. This application inherits the advantages of the original mechanism, such as compact structure, good synchronization and reliable locking. By introducing the concept of secondary folding, it significantly improves the storage efficiency of the wings, making it particularly suitable for applications of UAVs and spacecraft where the inner diameter of the launch tube is strictly limited.

[0016] 2. This application features a simple structure, precise action sequence, reliable two-level locking, and high system integration. It is suitable for controlling two folding actions, has high synchronization and robustness, and is applicable to the field of drones and spacecraft with limited storage space. Attached Figure Description

[0017] Figure 1 The diagram shows the folding and locking state of a reliable locking mechanism for the step-by-step deployment of a two-folding wing provided according to an embodiment of the present invention. Figure 2 A diagram showing a folding wing assembly in a folded locked state according to an embodiment of the present invention is shown. Figure 3 A diagram showing the folded locking state of a locking component provided according to an embodiment of the present invention is shown. Figure 4 The diagram shows a folding wing assembly in a two-fold locked state according to an embodiment of the present invention. Figure 5 A diagram showing the folded and locked state of the unlocking component provided according to an embodiment of the present invention is shown.

[0018] Legend: 1. Folding Wing Assembly 1; 11. Support 1; 12. Torsion Spring 1; 13. Pin 1; 14. Shaft 1; 15. Compression Spring 1; 16. Nut 1; 17. Pull Pin 1; 18. Mounting Ear Plate 1; 19. Rotating Pin 1; 110. Wing Shaft 1; 2. Locking Assembly; 21. Bracket; 22. Spring Pin; 23. Compression Spring 3; 24. Sleeve; 3. Fixing Plate; 4. Folding Wing Assembly 2; 41. Support 2; 42. Torsion Spring 2; 43. Pin 2; 44. Shaft 2; 45. Compression Spring 2; 46. Nut 2; 47. Pull Pin 2; 48. Mounting Ear Plate 2; 49. Rotating Pin 2; 410. Wing Shaft 2; 5. Unlocking Assembly; 51. Pyrotechnic Device; 52. Pyrotechnic Support; 53. Locking Screw; 54. Push Rod; 55. Claw; 6. Cabin. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Please see Figures 1-5 The present invention provides a technical solution: A reliable locking mechanism for the step-by-step deployment of a two-folding wing includes a folding wing assembly 1, a locking assembly 2, a fixing plate 3, a second folding wing assembly 4, an unlocking assembly 5, and a cabin 6. The folding wing assembly 1 includes a support 11, a torsion spring 12, a pin 13, a shaft pin 14, a compression spring 15, a nut 16, a pull pin 17, a mounting lug 18, a pivot pin 19, and a wing shaft 110. The torsion spring 12 is sleeved on the pin 13. The static arm is located on the boss of the support 11, and the dynamic arm is located on the wing shaft 110. The pivot pin 19 is inserted into the end of the wing shaft 110. The mounting lug 18 slides along the inclined surface of the wing shaft 110, while the compression spring 15 is compressed. When the mounting lug 18 disengages from the wing shaft 110, the mounting lug 18 and the pull pin 17 rotate around the pivot pin 19, and the wing shaft 110 rotates around the shaft pin 14. The locking assembly 2 includes a bracket 21, a spring pin 22, a compression spring 23, and a sleeve 24. The spring pin 22 is inserted into the bracket 21 and pressed by the compression spring 23, and fixed by the sleeve 24. The spring pin 22 slides along the built-in round hole of the bracket 21 against the spring force. The mounting plate 3 is installed on the cabin 6 by screws, and the mounting plate 3 has a built-in threaded hole; The folding wing assembly 24 includes a support 241, a torsion spring 242, a pin 243, a shaft 244, a compression spring 245, a nut 246, a pull pin 247, a mounting lug 248, a pivot pin 249, and a wing shaft 2410. The torsion spring 242 is sleeved on the pin 243. The static arm is located on the boss of the support 241, and the dynamic arm is located on the wing shaft 2410. The pivot pin 249 is inserted into the end of the wing shaft 2410. The mounting lug 248 slides laterally along the wing shaft 2410, while the compression spring 245 is compressed. When the mounting lug 248 is disengaged from the wing shaft 2410, the mounting lug 248 and the pull pin 247 rotate around the pivot pin 249, and the wing shaft 2410 rotates around the shaft 244. The unlocking component 5 includes a pyrotechnic component 51, a pyrotechnic support 52, a locking screw 53, a push rod 54, and a pawl 55. The push rod 54 is fixedly connected to the pyrotechnic support 52 by the locking screw 53, and the push rod 54 slides axially along the inner hole of the pyrotechnic support 52.

[0021] Specifically, in the folded state, the wing shaft 110 and wing shaft 2 410 overcome the spring forces of torsion spring 12 and torsion spring 2 42 respectively and rotate into the cabin 6. After they are in place, the pawl 55 enters the slot of the wing shaft 110 and wing shaft 2 410, and the locking screw 53 fixes the pyrotechnic support 52 and the push rod 54, thus completing the wing surface locking in the folded state.

[0022] Specifically, in the folded state, mounting ear plate 18 slides laterally along wing shaft 110, compressing spring 15. After disengaging from wing shaft 110, it rotates 135° around pivot pin 19. Mounting ear plate 2 48 slides laterally along wing shaft 2 410, compressing spring 2 45. After disengaging from wing shaft 2 410, it rotates 135° around pivot pin 2 49. The launch tube provides a limiting position, completing the second fold.

[0023] Specifically, after the reliable locking mechanism of the secondary folding wing unfolds from the launch tube, the compression spring 15 releases its spring force, and the mounting ear plate 18 moves along the inclined surface of the wing shaft 110 around the pivot pin 19 under the spring pressure. After it is in place, the groove of the mounting ear plate 18 is inserted into the trapezoidal boss of the wing shaft 110. The compression spring 2 45 releases its spring force, and the mounting ear plate 2 48 moves along the inclined surface of the wing shaft 2 410 around the pivot pin 2 49 under the spring pressure. After it is in place, the groove of the mounting ear plate 2 48 is inserted into the trapezoidal boss of the wing shaft 2 410, completing the first stage of unfolding and locking.

[0024] Specifically, after the pyrotechnic device 51 is ignited, the high-pressure gas shears off the locking screw 53 and pushes the push rod 54 and the pawl 55 to move. The pawl 55 disengages from the first wing shaft 110 and the second wing shaft 410, completing the unlocking of the second stage of deployment.

[0025] Specifically, wing shaft 110 and wing shaft 2 410 rotate along pin 14 and pin 24 respectively under the action of torsion spring 12 and torsion spring 2 42, completing the second-stage deployment action.

[0026] Specifically, after the folding wing assembly 1 and the folding wing assembly 2 are unfolded, the wing shaft 110 and the wing shaft 2410 are pushed open by the force of the torsion spring, and after they are in place, the spring pin 22 is pushed in by the pressure of the compression spring 323, and the positioning holes of the wing shaft 110 and the wing shaft 2410 are locked to complete the second-stage unfolding.

[0027] In summary, the embodiment provides a reliable locking mechanism for the step-by-step deployment of a secondary folding wing. The locking component 2 is installed on the cabin 6 for locking during secondary deployment, the fixing plate 3 is installed on the cabin 6, and the folding wing component 1, the folding wing component 2, and the unlocking component 5 are installed on the fixing plate 3 for locking the folding wing and unlocking the deployment.

[0028] The entire working state is divided into: first fold and lock state, second fold and lock state, first unfold and lock state, second unfold state, and second unfold and lock state.

[0029] The specific folding and locking state is as follows: Fold the folding wing assembly 1 and folding wing assembly 2, pull down the push rod 54 and the pawl 55, and the pawl 55 enters the pawl slot of the control surface. Use the locking screw 53 to fix the push rod 54 and the pyrotechnic support 52 to complete one folding and locking of the wing.

[0030] The second fold locking state is as follows: When mounting lug 18 and mounting lug 2 48 are pulled outwards and completely detached from the rudder shaft, they fold 135° to the side. The secondary folding and locking of the wing is completed by limiting mounting lug 18 and mounting lug 2 48 through the launch tube.

[0031] The specific unfolding and locking states are as follows: After the reliable locking mechanism of the secondary folding wing unfolds through the launch tube, mounting lug 18 and mounting lug 2 48 slide along the inclined surfaces of wing shaft 110 and wing shaft 210 under the elastic force of compression spring 15 and compression spring 2 45, respectively. After mounting lug 18 and mounting lug 2 48 slide into place, they form a boss and groove fit with the rudder shaft. Through the pressure of compression spring 15 and compression spring 2 45, mounting lug 18 and mounting lug 2 48 are pressed tightly onto the rudder shaft, completing the first unfolding and locking of the wing.

[0032] The second unfolding state is as follows: After controlled ignition of the pyrotechnic device 51, gas enters the combustion chamber, pushing the push rod 54 and the pawl 55 upwards. First, the pawl 55 moves away from the rudder shaft slot, completing the unlocking. Under the spring force of torsion spring 12 and torsion spring 42, the folding wing assembly 1 and folding wing assembly 4 complete the secondary deployment of the wings.

[0033] The second-stage unfolding and locking state is as follows: Under the spring force of torsion spring 12 and torsion spring 24 respectively, folding wing assembly 1 and folding wing assembly 2 will squeeze open the spring pin 22 of locking assembly 2 during rotation. After folding wing assembly 1 and folding wing assembly 24 are in place, the spring pin 22, under the action of the internal compression spring 3 23 of locking assembly 2, will be positioned and locked through the positioning holes of folding wing assembly 1 and folding wing assembly 24, thus completing the secondary deployment and locking of the wings.

[0034] The above description of the embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A reliable locking mechanism for the step-by-step deployment of a secondary folding wing, comprising a first folding wing assembly (1), a locking assembly (2), a fixing plate (3), a second folding wing assembly (4), an unlocking assembly (5), and a cabin (6), characterized in that, The folding wing assembly (1) includes a support (11), a torsion spring (12), a pin (13), a shaft (14), a compression spring (15), a nut (16), a pull pin (17), a mounting lug (18), a pivot pin (19), and a wing shaft (110). The torsion spring (12) is sleeved on the pin (13). The static arm is located on the boss of the support (11), and the dynamic arm is located on the wing shaft (110). The pivot pin (19) is inserted into the end of the wing shaft (110). The mounting lug (18) slides along the inclined surface of the wing shaft (110), while the compression spring (15) is compressed. When the mounting lug (18) is disengaged from the wing shaft (110), the mounting lug (18) and the pull pin (17) rotate around the pivot pin (19), and the wing shaft (110) rotates around the shaft (14). The locking assembly (2) includes a bracket (21), a spring pin (22), a compression spring (23), and a sleeve (24). The spring pin (22) is inserted into the bracket (21) and pressed by the compression spring (23), and fixed by the sleeve (24). The spring pin (22) slides along the built-in round hole of the bracket (21) against the spring force. The fixing plate (3) is installed on the cabin (6) by screws, and the fixing plate (3) has a built-in threaded hole; The second folding wing assembly (4) includes a second support (41), a second torsion spring (42), a second pin (43), a second pin shaft (44), a second compression spring (45), a second nut (46), a second pull pin (47), a second mounting lug (48), a second pivot pin (49), and a second wing shaft (410). The second torsion spring (42) is sleeved on the second pin (43). The static arm is located on the boss of the second support (41), and the dynamic arm is located on the second wing shaft (410). The second pivot pin (49) is inserted into the end of the second wing shaft (410). The second mounting lug (48) slides laterally along the second wing shaft (410), while the second compression spring (45) is compressed. When the second mounting lug (48) is disengaged from the second wing shaft (410), the second mounting lug (48) and the second pull pin (47) rotate around the second pivot pin (49), and the second wing shaft (410) rotates around the second pin shaft (44). The unlocking component (5) includes a pyrotechnic component (51), a pyrotechnic support (52), a locking screw (53), a push rod (54), and a pawl (55). The push rod (54) is fixedly connected to the pyrotechnic support (52) by the locking screw (53), and the push rod (54) slides axially along the inner hole of the pyrotechnic support (52).

2. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 1, characterized in that, In the folded state, the first wing shaft (110) and the second wing shaft (410) overcome the spring force of the first torsion spring (12) and the second torsion spring (42) respectively, and rotate into the cabin (6). After they are in place, the claws (55) enter the slots of the first wing shaft (110) and the second wing shaft (410), and the locking screws (53) fix the pyrotechnic support (52) and the push rod (54) to complete the wing surface locking in the folded state.

3. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 2, characterized in that, In the folded state, the mounting ear plate (18) slides laterally along the wing shaft (110), the compression spring (15) is compressed, and after disengaging from the wing shaft (110), it rotates 135° around the pivot pin (19). The mounting ear plate (48) slides laterally along the wing shaft (410), the compression spring (45) is compressed, and after disengaging from the wing shaft (410), it rotates 135° around the pivot pin (49). The launch tube provides a limit, thus completing the second fold.

4. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 3, characterized in that, After the reliable locking mechanism of the secondary folding wing unfolds and is released from the launch tube constraint, the first compression spring (15) releases the spring force, and the first mounting ear plate (18) moves along the inclined surface of the first wing shaft (110) around the first pivot pin (19) under the spring pressure. After it is in place, the groove of the first mounting ear plate (18) is inserted into the trapezoidal boss of the first wing shaft (110). The second compression spring (45) releases the spring force, and the second mounting ear plate (48) moves along the inclined surface of the second wing shaft (410) around the second pivot pin (49) under the spring pressure. After it is in place, the groove of the second mounting ear plate (48) is inserted into the trapezoidal boss of the second wing shaft (410), thus completing the first stage of unfolding and locking.

5. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 4, characterized in that, After the pyrotechnic device (51) is ignited, the high-pressure gas shears off the locking screw (53) and pushes the push rod (54) and the pawl (55) to move. The pawl (55) disengages from the first wing shaft (110) and the second wing shaft (410), completing the unlocking of the second-stage deployment.

6. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 5, characterized in that, The first wing shaft (110) and the second wing shaft (410) rotate along the first pin shaft (14) and the second pin shaft (44) respectively under the action of the first torsion spring (12) and the second torsion spring (42) to complete the second-stage deployment action.

7. The reliable locking mechanism for the step-by-step deployment of a secondary folding wing according to claim 6, characterized in that, After the folding wing assembly one (1) and folding wing assembly two (4) are unfolded, the wing shaft one (110) and wing shaft two (410) are pushed open by the force of the torsion spring and the spring pin (22) is pushed into place by the pressure of the compression spring three (23) and the positioning hole of the wing shaft one (110) and wing shaft two (410) to complete the locking of the second-stage unfolding.

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