CN113548191A - Unmanned aerial vehicle locking device applied to large-scale unmanned aerial vehicle rocket boosting launching - Google Patents
Unmanned aerial vehicle locking device applied to large-scale unmanned aerial vehicle rocket boosting launching Download PDFInfo
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- CN113548191A CN113548191A CN202110653054.8A CN202110653054A CN113548191A CN 113548191 A CN113548191 A CN 113548191A CN 202110653054 A CN202110653054 A CN 202110653054A CN 113548191 A CN113548191 A CN 113548191A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses an unmanned aerial vehicle locking device applied to large-scale unmanned aerial vehicle rocket boosting launching, which comprises a main support assembly, a front support assembly, a limiting lock assembly and a pull rod limiting assembly, wherein the main support assembly comprises a support main body, a blocking mechanism, a locking mechanism and a rear support assembly; the front support assembly is rotatably connected with the front part of the support main body and comprises a left support frame, a right support frame and a support plate positioned between the left support frame and the right support frame, wherein the left support frame and the right support frame are in mirror symmetry, and one sides of the left support frame and the right support frame, which are far away from the support plate, are respectively provided with a limiting ejector rod mechanism which is matched with the blocking mechanism to fix the unmanned aerial vehicle; the limit lock assembly is arranged at the front part of the bracket main body; the pull rod limiting assembly is arranged at the bottom of the support main body. The invention replaces a shear pin or a breaking pin used in the prior art, can stably lock the unmanned aerial vehicle before launching by matching the limiting ejector rod mechanism with the blocking mechanism, and can quickly separate the pull rod limiting component by the locking mechanism during launching to ensure that the unmanned aerial vehicle launches normally.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle locking device applied to rocket-assisted launching of a large-scale unmanned aerial vehicle.
Background
At present, before a large unmanned aerial vehicle is launched and taken off by using a rocket-assisted launching mode, a shear pin or a breaking pin locking mechanism is generally used for fixing the unmanned aerial vehicle on a launching device. After the rocket booster is ignited and started, the shear pin or the breaking pin in the locking mechanism is cut off or broken under the combined action of the thrust of the unmanned aerial vehicle engine and the thrust of the rocket booster, so that the separation of the unmanned aerial vehicle and the launching device is realized. Because the launching process of the unmanned aerial vehicle requires high reliability, the machining and manufacturing requirements of the shear pin or the break pin as a key component are very high, however, the shear pin or the break pin is a disposable assembly and use consumable part in the launching process of the unmanned aerial vehicle every time, so that the operation of the locking mechanism is inconvenient and the cost for launching the unmanned aerial vehicle for many times is increased.
Disclosure of Invention
In order to solve the problems, the invention provides an unmanned aerial vehicle locking device applied to rocket-assisted launching of a large-scale unmanned aerial vehicle.
In order to achieve the purpose, the technical scheme of the invention is as follows:
be applied to unmanned aerial vehicle locking device of large-scale unmanned aerial vehicle rocket boosting transmission, include:
the main support assembly comprises a support main body, blocking mechanisms, locking mechanisms and a rear support assembly, wherein the blocking mechanisms are arranged on two sides of the front part of the support main body, the locking mechanisms are arranged at the bottom of the support main body, and the rear support assembly is arranged at the rear part of the support main body;
the front support assembly is rotationally connected with the front part of the bracket main body and comprises a left support frame, a right support frame and a support plate positioned between the left support frame and the right support frame, wherein the left support frame and the right support frame are in mirror symmetry, one sides of the left support frame and the right support frame, which are far away from the support plate, are respectively provided with a limiting ejector rod mechanism which is matched with the blocking mechanism to fix the unmanned aerial vehicle, and the front support assembly is configured to be matched with the rear support assembly to support and fix the unmanned aerial vehicle before launching;
the limiting lock assembly is arranged at the front part of the bracket main body and is configured to be matched with a bracket limiting piece at the bottom of the front supporting assembly to limit the rotation of the front supporting assembly after the unmanned aerial vehicle is launched;
the spacing subassembly of pull rod locates support main part bottom, and one end is articulated with preceding supporting component, and the other end and locking mechanism swing joint are configured as the hindrance preceding supporting component is rotatory around the support main part before unmanned aerial vehicle launches.
Furthermore, the blocking mechanism comprises a sleeve, a mandril top block, a sliding top block, a top block connecting rod and an adjusting screw, the sleeve is arranged at the front part of the bracket main body, and the axis of the sleeve is vertical to the bracket main body; the lower part of the ejector rod ejector block extends into the sleeve and moves along the axial direction of the sleeve, the upper part of the ejector rod ejector block extends out of the sleeve and is hinged with one end of the ejector block connecting rod, and the other end of the ejector block connecting rod is hinged with the sliding ejector block; the bottom of the sliding ejector block extends into the ejector block groove in the bracket main body and moves along the extending direction of the ejector block groove; adjusting screw passes through screw regulating plate movable mounting and keeps away from telescopic one side in slip kicking block, works as adjusting screw when removing to the slip kicking block, the slip kicking block is pushed by adjusting screw and is removed to the sleeve, simultaneously the ejector pin kicking block is driven by the kicking block connecting rod and is removed to the direction that promotes spacing ejector pin mechanism.
Furthermore, the part of the ejector rod ejector block close to the limiting ejector rod mechanism is provided with a semicircular arc surface.
Furthermore, the limiting ejector rod mechanism comprises a sliding pin stop hook, a stop hook ejector rod, a guide plate and an ejector rod compression spring, the sliding pin stop hook is hinged with the left support frame and the right support frame respectively, the stop hook ejector rod is positioned below the sliding pin stop hook and is driven by the blocking mechanism to force the sliding pin stop hook to rotate towards the direction of fixing the unmanned aerial vehicle; one side of the stop hook ejector rod is connected with a guide rod through a spring stop block, and the guide rod is parallel to the stop hook ejector rod; the guide plate is arranged along the moving direction of the stop hook ejector rod, the guide rod penetrates through the guide plate and moves along the extending direction of the guide plate, and the ejector rod compression spring is sleeved on the part of the guide rod, which is positioned in the guide plate, and is matched with the spring stop block to limit the movement of the guide rod; when the stop hook mandril moves towards the slide pin stop hook, the spring stop block compresses the mandril compression spring; the front support assembly is provided with a first guide piece, and the stop hook mandril passes through the first guide piece to move towards the direction close to or far away from the slide pin stop hook.
Furthermore, the top of the stop hook ejector rod is provided with a first inclined surface, and the first inclined surface is matched with the second inclined surface at the bottom of the sliding pin stop hook in position and shape.
Furthermore, a stop hook limiting part is arranged on one side, close to the slide pin stop hook, of the end part of the front support assembly and is configured to limit the rotation of the slide pin stop hook.
Furthermore, a baffle groove is formed in the top of the front support assembly, a sliding pin baffle is arranged in the baffle groove, and the sliding pin baffle is matched with a sliding pin stop hook to form a limiting structure for fixing a front sliding pin of the unmanned aerial vehicle; the end part of the front support assembly is provided with a first through hole extending into the groove of the baffle plate, and the sliding pin baffle plate is provided with a second through hole corresponding to the first through hole; after the sliding pin baffle is inserted into the baffle groove, the sliding pin baffle is fixed with the second through hole by sequentially extending the limiting rod into the first through hole.
Furthermore, the limiting lock assembly comprises a lock box, a lock body and a lock body pressure spring, through holes for the lock body to penetrate through are formed in two ends of the lock box, the lock body pressure spring is sleeved on the part, located inside the lock box, of the lock body, a lock tongue is arranged at one end, extending out of the lock box, of the lock body, a third inclined plane is arranged on one side of the end portion of the lock tongue, a pressure spring baffle is arranged at the position, close to the lock tongue, of the lock body, and the pressure spring baffle is in abutting connection with the lock body pressure spring; when the support limiting part rotates to the limiting lock assembly, the third inclined surface of the lock bolt is pushed by the support limiting part, so that the lock bolt moves towards the interior of the lock box, and meanwhile, the lock body pressure spring is driven by the pressure spring baffle to contract; be equipped with spacing through-hole on the support locating part, work as when spacing through-hole removes to the spring bolt tip, the spring bolt stretches into spacing through-hole under the effect of lock body pressure spring, the restriction the rotatory direction of support locating part.
Furthermore, the pull rod limiting assembly comprises a hook connecting rod and a hook pull rod, one end of the hook connecting rod is connected with the front support assembly, the other end of the hook connecting rod is connected with one end of the hook pull rod, and the other end of the hook pull rod penetrates through a second guide piece at the bottom of the support main body and is movably connected with the locking mechanism.
Further, the main support assembly further comprises a flame baffle, the flame baffle is located between the locking mechanism and the unmanned aerial vehicle, and the locking mechanism is an electromagnetic hook.
Compared with the prior art, the invention has the beneficial effects that:
the locking device of the unmanned aerial vehicle applied to large-scale unmanned aerial vehicle rocket boosting launching replaces a shear pin or a breaking pin used in the prior art, the unmanned aerial vehicle before launching can be stably locked through the matching of the limiting ejector rod mechanism and the blocking mechanism, and the locking mechanism can quickly separate the pull rod limiting component to enable the unmanned aerial vehicle to normally launch during launching.
The invention has the advantages of convenient operation, reliable use and repeated use.
Drawings
Fig. 1 is a schematic structural diagram of a locking device of an unmanned aerial vehicle according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of the locking device of the unmanned aerial vehicle before the unmanned aerial vehicle is launched in the embodiment of the present invention;
fig. 3 is a schematic structural diagram of the locking device of the unmanned aerial vehicle after the unmanned aerial vehicle is launched in the embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a blocking mechanism in an embodiment of the present invention;
FIG. 5 is a schematic structural view of a front support assembly in an embodiment of the present invention;
FIG. 6 is a schematic top view of a front support assembly in accordance with an embodiment of the present invention;
FIG. 7 is a schematic view of the assembly of the stop mechanism and the spacing mandril mechanism in the embodiment of the invention;
FIG. 8 is a schematic structural diagram of a limiting ejector rod mechanism when locking an unmanned aerial vehicle in the embodiment of the invention;
FIG. 9 is a schematic view of the assembly of the drawbar limiting assembly and the front support assembly in the embodiment of the present invention;
fig. 10 is an assembly schematic diagram of the pull rod limiting assembly and the front support assembly in the launching of the unmanned aerial vehicle in the embodiment of the present invention;
FIG. 11 is a schematic view of an embodiment of a limit lock assembly of the present invention;
FIG. 12 is a schematic view of the assembly of a position limiting lock assembly and a bracket position limiting member according to an embodiment of the present invention;
FIG. 13 is a schematic structural view of the rear slider in the rear support assembly in an embodiment of the present invention;
FIG. 14 is a schematic structural view of a locking mechanism in an embodiment of the present invention;
fig. 15 is a schematic structural diagram of the drone in an embodiment of the present invention;
in the figure: 100. a main support assembly; 110. a stent body; 111. A flame guard;
120. a blocking mechanism; 121. a sleeve; 122. a mandril jacking block; 123. sliding the ejector block; 124. a top block connecting rod; 125. an adjusting screw; 126. a screw adjusting plate; 127. a top block groove; 128. a top block clamping groove;
130. a locking mechanism;
140. a rear support assembly; 141. a concave chute;
200. a front support assembly; 201. a left support frame; 202. a right support frame; 203. a support plate; 204. a bracket limiting part;
210. a limit ejector rod mechanism; 211. a sliding pin catch hook; 212. a catch hook ejector rod; 213. a guide plate; 214. the mandril compresses the spring; 215. a spring stop; 216. a guide bar; 217. a first guide member; 218. a stop hook limiting member;
220. a baffle plate groove; 221. a sliding pin baffle; 222. a sliding pin support;
300. a limit lock assembly; 310. a lock case; 320. a lock body; 321. a latch bolt; 330. a lock body pressure spring; 331. a pressure spring baffle plate;
400. a pull rod limiting component; 401. a hook connecting rod; 402. a hook pull rod; 403. a second guide member;
500. an unmanned aerial vehicle; 501. a front slide pin; 502. and a rear slider.
Detailed Description
The following embodiments are provided to describe the embodiments of the present invention, and to explain in further detail the shapes and configurations of the components, the mutual positions and connection relationships among the components, the actions and working principles of the components, etc., so as to help those skilled in the art to more fully, accurately and deeply understand the inventive concept and technical solutions of the present invention.
Referring to fig. 1 to 15, an embodiment of the present invention discloses a locking device for a large unmanned aerial vehicle 500 for rocket-assisted launching, comprising a main support assembly 100, a front support assembly 200, a limiting lock assembly 300 and a pull rod limiting assembly 400, wherein,
the main support assembly 100 comprises a support main body 110, a blocking mechanism 120, a locking mechanism 130 and a rear support assembly 140, wherein the blocking mechanism 120 is arranged at two sides of the front part of the support main body 110, the locking mechanism 130 is arranged at the bottom of the support main body 110, and the rear support assembly 140 is arranged at the rear part of the support main body 110;
the front support assembly 200 is rotatably connected with the front part of the bracket main body 110 and comprises a left support frame 201, a right support frame 202 and a support plate 203 positioned between the left support frame 201 and the right support frame 202, wherein the left support frame 201 and the right support frame 202 are in mirror symmetry, one sides of the left support frame 201 and the right support frame 202, which are far away from the support plate 203, are respectively provided with a limiting ejector rod mechanism 210 which is matched with the blocking mechanism 120 to fix the unmanned aerial vehicle 500, and the front support assembly 200 is configured to be matched with the rear support assembly 140 to support and fix the unmanned aerial vehicle 500 before launching;
the limiting lock assembly 300 is arranged at the front part of the bracket main body 110 and is configured to be matched with the bracket limiting piece 204 at the bottom of the front support assembly 200 to limit the rotation of the front support assembly 200 after the unmanned aerial vehicle 500 is launched;
the pull rod limiting assembly 400 is arranged at the bottom of the support main body 110, one end of the pull rod limiting assembly is hinged to the front support assembly 200, the other end of the pull rod limiting assembly is movably connected with the locking mechanism 130, and the pull rod limiting assembly is configured to block the front support assembly 200 from rotating around the support main body 110 before the unmanned aerial vehicle 500 is launched.
Wherein, the bottom of the rear supporting assembly 140 is provided with a concave chute 141, and one side of the concave chute 141 is provided with a rear baffle.
Preferably, the blocking mechanism 120 includes a sleeve 121, a top rod block 122, a sliding block 123, a top block connecting rod 124 and an adjusting screw 125, the sleeve 121 is disposed at the front of the bracket body 110, and the axis of the sleeve 121 is perpendicular to the bracket body 110; the lower part of the ejector rod top block 122 extends into the sleeve 121 and moves along the axial direction of the sleeve 121, the upper part of the ejector rod top block 122 extends out of the sleeve 121 and is hinged with one end of a top block connecting rod 124, and the other end of the top block connecting rod 124 is hinged with a sliding top block 123; the bottom of the sliding top block 123 extends into the top block groove 127 on the bracket main body 110 and moves along the extending direction of the top block groove 127; the adjusting screw 125 is movably mounted on one side of the sliding top block 123 far away from the sleeve 121 through the screw adjusting plate 126, when the adjusting screw 125 moves towards the sliding top block 123, the sliding top block 123 is pushed by the adjusting screw 125 to move towards the sleeve 121, and meanwhile, the ejector rod top block 122 is driven by the ejector block connecting rod 124 to move towards the direction of pushing the limit ejector rod mechanism 210.
Wherein, sliding top piece 123 one side is equipped with kicking block draw-in groove 128, and kicking block draw-in groove 128 extends and restricts sliding top piece 123 and breaks away from kicking block recess 127 along sliding top piece 123 moving direction.
It is preferable for the embodiment of the present invention that the part of the ejector pin top block 122 near the limit ejector pin mechanism 210 has a semicircular arc surface.
Preferably, the limiting ejector rod mechanism 210 includes a slide pin stop hook 211, a stop hook ejector rod 212, a guide plate 213 and an ejector rod compression spring 214, the slide pin stop hook 211 is hinged to the left support frame 201 and the right support frame 202 respectively, the stop hook ejector rod 212 is located below the slide pin stop hook 211, and is driven by the blocking mechanism 120 to force the slide pin stop hook 211 to rotate in the direction of fixing the unmanned aerial vehicle 500; one side of the stop hook mandril 212 is connected with a guide rod 216 through a spring stop 215, and the guide rod 216 is parallel to the stop hook mandril 212; the guide plate 213 is arranged along the moving direction of the catch hook mandril 212, the guide rod 216 penetrates through the guide plate 213 and moves along the extending direction of the guide plate 213, and the mandril compression spring 214 is sleeved on the part of the guide rod 216 in the guide plate 213 and is matched with the spring stop block 215 to limit the movement of the guide rod 216; when the catch hook plunger 212 moves toward the slide pin catch hook 211, the spring stopper 215 compresses the plunger compression spring 214; the front support assembly 200 is provided with a first guide 217, and the hook lift rod 212 passes through the first guide 217 to move toward or away from the slide pin hook 211.
Further, preceding supporting component 200 tip is equipped with the sliding pin support 222 that extends along unmanned aerial vehicle 500 transmission direction to improve the area of contact of preceding supporting component 200 tip, the preceding sliding pin 501 of the unmanned aerial vehicle 500 of being convenient for is placed on preceding supporting component 200.
It is preferred for the present embodiment that the top of the catch mandril 212 has a first slope that matches in position and shape with a second slope of the bottom of the slide pin catch 211.
It is preferable for the embodiment of the present invention that a hook stopper 218 configured to limit the rotation of the slide pin hook 211 is provided at one side of the end of the front support assembly 200 adjacent to the slide pin hook 211.
Preferably, in the embodiment of the present invention, the top of the front support assembly 200 is provided with a baffle groove 220, a sliding pin baffle 221 is disposed in the baffle groove 220, and the sliding pin baffle 221 and the sliding pin baffle hook 211 are matched to form a limiting structure for fixing the front sliding pin 501 of the unmanned aerial vehicle 500; a first through hole extending into the baffle groove 220 is formed at the end part of the front support assembly 200, and a second through hole corresponding to the first through hole is formed on the sliding pin baffle 221; after the sliding pin baffle 221 is inserted into the baffle groove 220, the sliding pin baffle 221 is fixed with the second through hole by sequentially extending the limiting rod into the first through hole.
Preferably, the limiting lock assembly 300 includes a lock box 310, a lock body 320 and a lock body pressure spring 330, through holes for the lock body 320 to pass through are provided at two ends of the lock box 310, the lock body pressure spring 330 is sleeved on a portion of the lock body 320 located inside the lock box 310, a lock tongue 321 is provided at one end of the lock body 320 extending out of the lock box 310, a third inclined surface is provided at one side of an end portion of the lock tongue 321, a pressure spring baffle 331 is provided at a position of the lock body 320 close to the lock tongue 321, and the pressure spring baffle 331 is connected with the lock body pressure spring 330 in an abutting manner; when the bracket limiting piece 204 rotates to the limiting lock assembly 300, the third inclined surface of the lock tongue 321 is pushed by the bracket limiting piece 204, so that the lock tongue 321 moves towards the inside of the lock box 310, and meanwhile, the lock body pressure spring 330 is driven by the pressure spring baffle 331 to contract; the support limiting piece 204 is provided with a limiting through hole, and when the limiting through hole moves to the end of the lock tongue 321, the lock tongue 321 extends into the limiting through hole under the action of the lock body pressure spring 330 to limit the rotating direction of the support limiting piece 204.
Preferably, the pull rod limiting assembly 400 includes a hook connecting rod 401 and a hook pull rod 402, one end of the hook connecting rod 401 is connected to the front support assembly 200, the other end of the hook connecting rod 401 is connected to one end of the hook pull rod 402, and the other end of the hook pull rod 402 passes through a second guide 403 at the bottom of the support body 110 and is movably connected to the locking mechanism 130.
Preferably, the main support assembly 100 further comprises a flame guard 111, the flame guard 111 is located between the locking mechanism 130 and the drone 500, and the locking mechanism 130 is an electromagnetic hook.
The working principle of the invention is as follows:
the hook pull rod 402 is hooked by an electromagnetic hook, and the front support assembly 200 is fixed perpendicular to the support main body 110; then the adjusting screw 125 is rotated to prop the sliding top block 123 to slide; when the sliding top block 123 slides forwards, the semicircular arc surface of the top rod top block 122 is enabled to prop against the bottom of the stop hook top rod 212 through the action of the top block connecting rod 124, the stop hook top rod 212 moves upwards, the top rod compression spring 214 is compressed and shortened until a first inclined surface at the upper end of the stop hook top rod 212 is attached to a second inclined surface at the lower end of the sliding pin stop hook 211; while the slide pin stop hook 211 is prevented from further rotation by the stop hook stop 218.
Hoist unmanned aerial vehicle 500 to the support fixed position that preceding supporting component 200 and back supporting component 140 cooperation formed, when the preceding sliding pin 501 of unmanned aerial vehicle 500 is hooked by sliding pin stop hook 211, after the back slider 502 of unmanned aerial vehicle 500 slides in the spill spout 141 of back supporting component 140, insert the baffle recess 220 at preceding supporting component 200 top with sliding pin baffle 221 and keep off preceding sliding pin 501 in, thereby realize the locking of unmanned aerial vehicle 500 before launching take off.
When the rocket booster loaded on the unmanned aerial vehicle 500 and the electromagnetic hook are powered on to work simultaneously, the electromagnetic hook is rotated to be opened, the hook pull rod 402 is unlocked, under the combined action of the thrust of the engine of the unmanned aerial vehicle 500 and the thrust of the rocket booster, the front sliding pin 501 of the unmanned aerial vehicle 500 collides with the front supporting assembly 200, the front supporting assembly 200 rotates around the support main body 110, the baffle hook ejector rod 212 breaks away from the ejector rod top block 122 along the chamfer arc surface at the bottom of the baffle hook ejector rod 212, the baffle hook ejector rod 212 moves downwards under the restoring force action of the ejector rod compression spring 214, so that the second inclined surface at the lower end of the sliding pin baffle hook 211 breaks away from the first inclined surface of the baffle hook ejector rod 212, the sliding pin baffle hook 211 is ejected by the front sliding pin 501, the sliding block 502 slides out along the concave sliding groove 141 of the rear supporting assembly 140 after the unmanned aerial vehicle 500, and the unlocking and taking off of the large-scale unmanned aerial vehicle 500 are realized.
When the rocket booster sweeps the bracket main body 110, the flame baffle 111 blocks the high-temperature flame of the rocket booster to prevent the electromagnetic hook from being burnt out; when the front support assembly 200 rotates and falls down, the bracket limiting piece 204 collides with the third inclined surface of the lock tongue 321 of the limiting lock assembly 300, the lock tongue 321 is stressed and retracted into the lock box 310 until the limiting through hole on the bracket limiting piece 204 is exposed, and the lock tongue 321 rapidly extends out and is inserted into the limiting through hole on the bracket limiting piece 204 under the restoring force action of the lock body pressure spring 330, so that the front support assembly 200 is locked.
The above description is only illustrative of the present invention based on the limited embodiments and drawings, but the present invention is not limited thereto. Those skilled in the art to which the present invention pertains will appreciate that various modifications can be made without departing from the technical spirit of the present invention and the scope of the appended claims, and the scope of the present invention shall be deemed to fall within the scope of the present invention.
Claims (10)
1. Be applied to unmanned aerial vehicle locking device of large-scale unmanned aerial vehicle rocket boosting transmission, its characterized in that includes:
the main support assembly (100) comprises a support main body (110), blocking mechanisms (120), a locking mechanism (130) and a rear support assembly (140), wherein the blocking mechanisms (120) are arranged on two sides of the front part of the support main body (110), the locking mechanism (130) is arranged at the bottom of the support main body (110), and the rear support assembly (140) is arranged at the rear part of the support main body (110);
the front support assembly (200) is rotationally connected with the front part of the support main body (110) and comprises a mirror-symmetric left support frame (201), a mirror-symmetric right support frame (202) and a support plate (203) positioned between the mirror-symmetric left support frame and the mirror-symmetric right support frame, wherein a limiting ejector rod mechanism (210) which is matched with the blocking mechanism (120) to fix the unmanned aerial vehicle (500) is arranged on one side, away from the support plate (203), of each of the left support frame (201) and the right support frame (202), and the front support assembly (200) is configured to be matched with the rear support assembly (140) to support and fix the unmanned aerial vehicle (500) before launching;
the limiting lock assembly (300) is arranged at the front part of the bracket main body (110) and is configured to be matched with a bracket limiting piece (204) at the bottom of the front supporting assembly (200) to limit the rotation of the front supporting assembly (200) after the unmanned aerial vehicle (500) is launched;
the spacing subassembly of pull rod (400) is located support main part (110) bottom, and one end is articulated with preceding support subassembly (200), and the other end and locking mechanism (130) swing joint are configured to the hindrance preceding support subassembly (200) are rotatory around support main part (110) before unmanned aerial vehicle (500) transmission.
2. An unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 1, wherein: the blocking mechanism (120) comprises a sleeve (121), a mandril top block (122), a sliding top block (123), a top block connecting rod (124) and an adjusting screw (125), the sleeve (121) is arranged at the front part of the bracket main body (110), and the axis of the sleeve is vertical to the bracket main body (110); the lower part of the ejector rod top block (122) extends into the sleeve (121) and moves axially along the sleeve (121), the upper part of the ejector rod top block (122) extends out of the sleeve (121) and is hinged with one end of the top block connecting rod (124), and the other end of the top block connecting rod (124) is hinged with the sliding top block (123); the bottom of the sliding top block (123) extends into a top block groove (127) in the bracket main body (110) and moves along the extending direction of the top block groove (127); adjusting screw (125) are kept away from one side of sleeve (121) through screw regulating plate (126) movable mounting in slip kicking block (123), work as adjusting screw (125) are when sliding kicking block (123) and remove, slip kicking block (123) are promoted by adjusting screw (125) and are removed to sleeve (121), simultaneously ejector pin kicking block (122) are driven by kicking block connecting rod (124) and are removed to the direction that promotes spacing ejector pin mechanism (210).
3. Unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 2, characterized in that: the part of the ejector rod ejector block (122) close to the limiting ejector rod mechanism (210) is provided with a semicircular arc surface.
4. An unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 1, wherein: the limiting ejector rod mechanism (210) comprises a sliding pin stop hook (211), a stop hook ejector rod (212), a guide plate (213) and an ejector rod compression spring (214), the sliding pin stop hook (211) is hinged to the left support frame (201) and the right support frame (202) respectively, and the stop hook ejector rod (212) is located below the sliding pin stop hook (211) and is driven by the blocking mechanism (120) to force the sliding pin stop hook (211) to rotate towards the direction of fixing the unmanned aerial vehicle (500); one side of the stop hook ejector rod (212) is connected with a guide rod (216) through a spring stop block (215), and the guide rod (216) is parallel to the stop hook ejector rod (212); the guide plate (213) is arranged along the moving direction of the hook blocking ejector rod (212), the guide rod (216) penetrates through the guide plate (213) and moves along the extending direction of the guide plate (213), and the ejector rod compression spring (214) is sleeved on the part, located in the guide plate (213), of the guide rod (216) and is matched with the spring stop block (215) to limit the movement of the guide rod (216); when the catch hook mandril (212) moves towards the slide pin catch hook (211), the spring stop block (215) compresses the mandril compression spring (214); the front support assembly (200) is provided with a first guide piece (217), and the stop hook mandril (212) passes through the first guide piece (217) to move towards the direction close to or far away from the slide pin stop hook (211).
5. A locking device for a large unmanned aerial vehicle rocket-assisted launching device according to claim 4, wherein: the top of the stop hook ejector rod (212) is provided with a first inclined surface, and the first inclined surface is matched with a second inclined surface at the bottom of the sliding pin stop hook (211) in position and shape.
6. A locking device for a large unmanned aerial vehicle rocket-assisted launching device according to claim 4, wherein: one side of the end of the front support assembly (200) close to the sliding pin stop hook (211) is provided with a stop hook limiting part (218) which is configured to limit the rotation of the sliding pin stop hook (211).
7. A locking device for a large unmanned aerial vehicle rocket-assisted launching device according to claim 4, wherein: the top of the front support assembly (200) is provided with a baffle groove (220), a sliding pin baffle (221) is arranged in the baffle groove (220), and the sliding pin baffle (221) is matched with a sliding pin baffle hook (211) to form a limiting structure for fixing a front sliding pin (501) of the unmanned aerial vehicle (500); a first through hole extending into the baffle groove (220) is formed in the end part of the front support assembly (200), and a second through hole corresponding to the first through hole is formed in the sliding pin baffle (221); after the sliding pin baffle (221) is inserted into the baffle groove (220), the sliding pin baffle (221) is fixed with the second through hole by sequentially extending the limiting rod into the first through hole.
8. An unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 1, wherein: the limiting lock assembly (300) comprises a lock box (310), a lock body (320) and a lock body pressure spring (330), through holes for the lock body (320) to penetrate through are formed in the two ends of the lock box (310), the lock body pressure spring (330) is sleeved on the part, located inside the lock box (310), of the lock body (320), a lock tongue (321) is arranged at one end, extending out of the lock box (310), of the lock body (320), a third inclined plane is arranged on one side of the end portion of the lock tongue (321), a pressure spring baffle (331) is arranged at the position, close to the lock tongue (321), of the lock body (320), and the pressure spring baffle (331) is in abutting connection with the lock body pressure spring (330); when the bracket limiting piece (204) rotates to the limiting lock assembly (300), the third inclined surface of the lock bolt (321) is pushed by the bracket limiting piece (204), so that the lock bolt (321) moves towards the inside of the lock box (310), and meanwhile, the lock body pressure spring (330) is driven by the pressure spring baffle (331) to contract; be equipped with spacing through-hole on support locating part (204), when spacing through-hole removes to spring bolt (321) tip, spring bolt (321) stretch into spacing through-hole under the effect of lock body pressure spring (330), the restriction the rotatory direction of support locating part (204).
9. An unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 1, wherein: the pull rod limiting assembly (400) comprises a hook connecting rod (401) and a hook pull rod (402), one end of the hook connecting rod (401) is connected with the front support assembly (200), the other end of the hook connecting rod is connected with one end of the hook pull rod (402), and the other end of the hook pull rod (402) penetrates through a second guide piece (403) at the bottom of the support main body (110) to be movably connected with the locking mechanism (130).
10. An unmanned aerial vehicle locking device applied to large unmanned aerial vehicle rocket boosting launching according to claim 1, wherein: the main support assembly (100) further comprises a flame baffle (111), the flame baffle (111) is located between the locking mechanism (130) and the unmanned aerial vehicle (500), and the locking mechanism (130) is an electromagnetic hook.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110653054.8A CN113548191B (en) | 2021-06-11 | 2021-06-11 | Be applied to unmanned aerial vehicle locking device of large-scale unmanned aerial vehicle rocket boosting transmission |
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| CN202110653054.8A CN113548191B (en) | 2021-06-11 | 2021-06-11 | Be applied to unmanned aerial vehicle locking device of large-scale unmanned aerial vehicle rocket boosting transmission |
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| CN113548191B CN113548191B (en) | 2022-06-17 |
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| CN109094810A (en) * | 2018-09-30 | 2018-12-28 | 北京驰宇空天技术发展有限公司 | A kind of assisted unmanned plane launcher |
| CN110920923A (en) * | 2019-12-23 | 2020-03-27 | 中国人民解放军总参谋部第六十研究所 | Unmanned aerial vehicle launching device with double rocket boosters |
| CN111409847A (en) * | 2020-04-14 | 2020-07-14 | 奥瑞思智能科技(阜新)有限公司 | Medium-high speed fixed wing unmanned aerial vehicle launcher |
| CN112498727A (en) * | 2020-12-18 | 2021-03-16 | 成都航天万欣科技有限公司 | Unmanned aerial vehicle boosting launcher |
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| KR101013851B1 (en) * | 2010-10-21 | 2011-02-14 | (주)경안전선 | Shuttle device for unmanned aerial vehicle launcher |
| CN201907656U (en) * | 2010-12-28 | 2011-07-27 | 江西洪都航空工业集团有限责任公司 | Zero length launching device for pilotless planes |
| CN109094810A (en) * | 2018-09-30 | 2018-12-28 | 北京驰宇空天技术发展有限公司 | A kind of assisted unmanned plane launcher |
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| CN113548191B (en) | 2022-06-17 |
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