CN114229025B - A receive and release subassembly for fixed wing unmanned aerial vehicle - Google Patents
A receive and release subassembly for fixed wing unmanned aerial vehicle Download PDFInfo
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- CN114229025B CN114229025B CN202111567930.1A CN202111567930A CN114229025B CN 114229025 B CN114229025 B CN 114229025B CN 202111567930 A CN202111567930 A CN 202111567930A CN 114229025 B CN114229025 B CN 114229025B
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- 210000001503 joint Anatomy 0.000 claims abstract description 200
- 238000003032 molecular docking Methods 0.000 claims abstract description 85
- 241000309551 Arthraxon hispidus Species 0.000 claims abstract description 11
- 230000007246 mechanism Effects 0.000 claims description 5
- 238000011084 recovery Methods 0.000 abstract description 23
- 238000004064 recycling Methods 0.000 abstract description 7
- 238000005516 engineering process Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 16
- 230000008569 process Effects 0.000 description 13
- 230000005484 gravity Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 2
- 230000002146 bilateral effect Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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Classifications
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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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/007—Helicopter portable landing pads
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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
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The invention belongs to the field of launching and recycling of vertical take-off and landing fixed wing unmanned aerial vehicles, in particular to a retraction assembly for a fixed wing unmanned aerial vehicle, which is mainly used for docking the fixed wing unmanned aerial vehicle with an aerial docking platform below, and realizes take-off and landing of the fixed wing unmanned aerial vehicle on the aerial docking platform. The invention comprises a docking rod arranged at the lower end of an unmanned aerial vehicle and a docking groove arranged at the upper end of a docking platform; the lower end of the butt joint rod is provided with a butt joint head which is matched with the butt joint groove; the butt joint is characterized in that a fixing groove is formed in the butt joint, movable sliding blocks which can stretch towards the groove wall direction are arranged on the groove walls on two sides of the butt joint groove, and the movable sliding blocks are matched with the fixing groove and used for clamping the butt joint. The invention can bear the emission task and the recovery task, greatly lightens the structure weight, simplifies the circuit and improves the reliability without depending on the active control technology.
Description
Technical Field
The invention belongs to the field of launching and recycling of vertical take-off and landing fixed wing unmanned aerial vehicles, in particular to a retraction assembly for a fixed wing unmanned aerial vehicle, which is mainly used for docking the fixed wing unmanned aerial vehicle with an aerial docking platform below, and realizes take-off and landing of the fixed wing unmanned aerial vehicle on the aerial docking platform.
Background
The common unmanned aerial vehicle launching mode is rocket boosting, hydraulic pressure, pneumatic ejection, ground slideway take-off and the like. The large unmanned aerial vehicle generally utilizes a ground running take-off mode, and the small and medium unmanned aerial vehicle adopts an catapult take-off mode with extremely high cost and high safety measures. The traditional hydraulic ejection system and the pneumatic ejection system generally have the problems of large occupied area, difficult unfolding and withdrawing and the like. The recovery mode of the unmanned aerial vehicle can be classified into the types of wheel runway landing recovery, mesh collision recovery, parachute recovery, overhead hook recovery and the like, wherein the wheel landing, parachute recovery and mesh collision recovery are typical recovery modes.
The patent with publication number CN112829959A discloses a fixed wing unmanned aerial vehicle movable emission and recovery integrated platform, which comprises a hydraulic lifting emission bow, an emission rail frame, an unmanned aerial vehicle mounting base, a quick release device, an emission control device and a traction power cable mechanism; the hydraulic lifting transmitting bow consists of two connecting ends and a driving end; the driving ends of the hydraulic lifting launching bows are connected with a driving mechanism and are used for providing lifting force and launching angle for the unmanned aerial vehicle; the left side and the right side of the launching track frame are respectively provided with one launching track frame, and the launching track frame is connected with four connecting ends of the front and the rear hydraulic lifting launching bows; each launching rail frame is provided with a chute for movably mounting the unmanned aerial vehicle mounting base; the quick release device is arranged at the top end of the unmanned aerial vehicle mounting base and is used for fixing or releasing the unmanned aerial vehicle; the traction power cable mechanism is used for traction of the two unmanned aerial vehicle mounting bases to move along the launching rail frame; the emission control device is used for realizing emission control of the unmanned aerial vehicle. The integrated platform of this patent can accomplish the work of launching and descending recovery to unmanned aerial vehicle, but need to dispose actuating mechanism through hydraulic pressure lift launching bow and provide lift force and launch angle for unmanned aerial vehicle, need receive emission controlling means control simultaneously, rely on the master control technique to control, and the line connection that needs is comparatively complicated, and the reliability is lower, receives influence such as circuit interruption easily.
Disclosure of Invention
The invention aims to provide a retraction assembly for a fixed-wing unmanned aerial vehicle, which is mainly used for docking the fixed-wing unmanned aerial vehicle with an aerial docking platform below, and realizes take-off and landing of the fixed-wing unmanned aerial vehicle on the aerial docking platform.
In order to solve the technical problems, the application provides a retraction assembly for a fixed wing unmanned aerial vehicle, which comprises a docking rod arranged at the lower end of the unmanned aerial vehicle and a docking groove arranged at the upper end of a docking platform; the lower end of the butt joint rod is provided with a butt joint head which is matched with the butt joint groove; the butt joint is characterized in that a fixing groove is formed in the butt joint, movable sliding blocks which can stretch towards the groove wall direction are arranged on the groove walls on two sides of the butt joint groove, and the movable sliding blocks are matched with the fixing groove and used for clamping the butt joint.
In this application, this receive and release subassembly reaches the aerial operation of launching of fixed wing unmanned aerial vehicle and retrieving through pure mechanical manipulation mode completely, and when the transmission, the butt joint promotes under unmanned aerial vehicle lifting force and removes the slider, and when unmanned aerial vehicle's lift and gravity's difference reached a definite value, the butt joint promotes and makes and removes the slider to both sides removal so that butt joint and fixed slot separation, and unmanned aerial vehicle pops out the fixed slot, breaks away from docking platform, and then accomplishes the task of taking off. When the butt joint rod is recovered, the butt joint rod is sunk, the butt joint head moves downwards, the movable sliding blocks are pushed to move towards two sides, the butt joint head is extruded towards the butt joint bottom continuously, when the butt joint head moves downwards to be in contact with the butt joint bottom, the movable sliding blocks automatically recover to be clamped in the fixed groove along with the reduction of the pushing force of the butt joint head, the butt joint head is clamped, and the recovery of the unmanned aerial vehicle is completed. The receiving and releasing assembly can bear the transmitting task and the recovering task, so that the structural weight is greatly reduced, and in addition, the receiving and releasing assembly does not depend on an active control technology, the circuit is simplified, and the reliability is improved.
Preferably, the upper end of the movable slide block is provided with a butt joint limiting part, the bottom of the butt joint groove is provided with a butt joint bottom, and the butt joint bottom is arranged at the lower end of the movable slide block; the movable sliding blocks and the butt joint limiting parts of the side walls at two sides of the butt joint groove are symmetrically arranged.
Preferably, the end part of the movable sliding block, which is arranged towards the middle of the butt joint groove, is in a structure with a convex middle part and concave upper and lower ends; the side wall of the butt joint rod is recessed towards the center of the butt joint rod.
Preferably, the fixing groove is an annular groove arranged around the circumference of the docking rod.
Preferably, an elastic piece is arranged at one end of the movable sliding block, which is far away from the butt joint; the other end of the elastic piece is connected with a limiting table.
Preferably, the butt joint comprises a hemispherical piece arranged at the lower end of the butt joint groove; the upper end face of the butt joint bottom is matched with the hemispherical piece.
Preferably, the end part of the butt joint limiting part, which is arranged towards the butt joint groove, is close to the middle of the butt joint groove from top to bottom, so that the butt joint limiting parts on the two side walls of the butt joint groove are tapered.
Preferably, the docking slot is disposed along a length direction of the docking platform, and a cross section of an opening end of the docking slot is rectangular.
Preferably, the elastic member is provided in plurality along a length direction of the docking groove.
Preferably, two docking rods are arranged; a limiting pin for limiting the butt joint rod is arranged in the length direction of the butt joint groove; the limiting pin is positioned between the two abutting rods.
The invention has the following technical effects:
1. the butt joint groove is formed by butt joint bottom, butt joint spacing portion, removal slider, wherein, removes the slider setting and is in butt joint bottom and butt joint between spacing portion, because of butt joint head and fixed slot assorted, the fixed slot is also located the centre of butt joint head, and the diameter at both ends is greater than the diameter of butt joint groove department about the butt joint head, when unmanned aerial vehicle retrieves, removes the slider and is adapted to the position of the last fixed slot of butt joint, realizes that the butt joint is blocked by the removal slider of both sides in fixed slot department, realizes unmanned aerial vehicle recovery's stability.
2. In the process of sinking and rising of the butt joint of the unmanned aerial vehicle, the force applied to the movable sliding block is vertically downward or vertically upward, the end part of the movable sliding block, which is arranged towards the middle of the butt joint groove, is of a structure with a middle bulge and two concave upper and lower ends, namely, the two ends of the movable sliding block are inclined planes which face the middle direction of the butt joint groove, so that the movable sliding block can be pushed to move towards two sides along the inclined planes of the movable sliding block when being pushed by the butt joint. The movable sliding blocks are arranged at the upper end and the lower end of the butt joint body, the movable sliding blocks are arranged at the lower end of the butt joint body, the fixed grooves are annular grooves formed in a circle of the butt joint body, the movable sliding blocks are symmetrically arranged left and right, and the movable sliding blocks are matched with the annular grooves, so that the unmanned aerial vehicle can still ensure the range and the accuracy of landing on the butt joint platform under the condition of generating a deflection angle with the butt joint platform.
3. The elastic piece is arranged at one end of the movable sliding block, which is far away from the butt joint, and the elastic performance of the elastic piece can realize that the movable sliding block is pushed by the butt joint to push the elastic piece so that the elastic piece is compressed to move towards two sides, and when the pushing amplitude of the butt joint is reduced, the elastic piece is restored along with the movement of the movable sliding block, and then the movable sliding block is pushed to be gradually restored. Especially when docking, the elastic component can make and resume to the card between the movable slide block and go into the fixed slot to block the butt joint, realize unmanned aerial vehicle docking's stability.
4. The butt joint is including locating the hemisphere spare of butt joint groove lower extreme, and at unmanned aerial vehicle butt joint in-process, butt joint towards butt joint inslot butt joint, the structure of the hemisphere spare of the tip of butt joint reducible butt joint is to the frictional force of butt joint groove lateral wall. The upper end face of the butt joint bottom is matched with the hemispherical piece, the butt joint bottom is convenient to be embedded with the hemispherical piece in the butt joint process, and the accuracy of unmanned aerial vehicle butt joint is guaranteed.
5. The tip that the spacing portion of butt joint set up towards the butt joint groove is close to in the middle of the butt joint groove from top to bottom for be the toper between the spacing portion of butt joint on the butt joint groove both sides wall, and then make the opening of butt joint groove great, be convenient for increase the butt joint area, reduce the butt joint degree of difficulty.
6. The butt joint groove is arranged along the length direction of the connected platform, and the cross section of the opening end of the butt joint groove is rectangular. The unmanned aerial vehicle can land at any position of the runway, and the landing difficulty of the unmanned aerial vehicle is effectively reduced.
7. The elastic piece is provided with a plurality of along the length direction in butt joint groove for everywhere in the butt joint groove can realize moving the slider and receive the butt joint to remove towards both sides, and the thrust is little to the function that resumes the home position gradually again in-process when losing the thrust, the recovery function of the arbitrary position department on the butt joint groove of being convenient for unmanned aerial vehicle.
8. The butt joint rod is provided with two, and the centre of butt joint groove length direction is equipped with the limiting pin that is used for limiting the butt joint rod, and limiting pin is located between two butt joint rods, and the butt joint groove can run through whole butt joint platform in the length direction of butt joint platform, and restriction unmanned aerial vehicle slides in the butt joint groove, prevents to crossing the off-set to focus on the butt joint platform.
Drawings
Fig. 1 is a diagram of the whole structure of the retractable assembly of the unmanned aerial vehicle.
Fig. 2 is a detailed structural diagram of a retractable assembly of the unmanned aerial vehicle.
Fig. 3 is a cross-sectional view of the drone retraction assembly.
Fig. 4 is a schematic view of the recovery of the unmanned aerial vehicle retraction assembly.
Fig. 5 is a schematic view of the unmanned aerial vehicle retraction assembly ejection.
Wherein, 1-unmanned plane; 1-1-butt joint rod; 1-11-butt joint; 1-111-fixing grooves; 1-112-hemispherical members; 2-a docking platform; 2-1 of a butt joint groove; 2-11-moving the slide block; 2-12 parts of butt joint limiting parts; 2-13-butt bottom; 2-14-elastic members; 2-15-defining a stage; 2-16-limiting pins.
Detailed Description
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. Unless defined otherwise, all terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It will be further understood that the terms used in the specification should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and this disclosure. The present disclosure is to be considered as an exemplification of the invention and is not intended to limit the invention to the specific embodiments illustrated.
The embodiment provides a retraction assembly for a fixed wing unmanned aerial vehicle, which comprises a docking rod 1-1 arranged at the lower end of the unmanned aerial vehicle 1 and a docking groove 2-1 arranged at the upper end of a docking platform 2; the lower end of the butt joint rod 1-1 is provided with a butt joint 1-11, and the butt joint 1-11 is matched with the butt joint groove 2-1; the butt joint 1-11 is provided with a fixed groove 1-111, the groove walls at two sides of the butt joint groove 2-1 are provided with movable sliding blocks 2-11 which can stretch towards the groove wall direction, and the movable sliding blocks 2-11 are matched with the fixed groove 1-111 and used for clamping the butt joint 1-11.
In this embodiment, receive and release subassembly adopts receive and release integration setting, can realize unmanned aerial vehicle 1's transmission, also can realize unmanned aerial vehicle 1's recovery. As shown in fig. 1, 2 and 3, the retraction assembly realizes the emission and recovery through the cooperation of the butt joint 1-11 and the butt joint groove 2-1 at the lower end of the butt joint rod 1-1, specifically, when the unmanned aerial vehicle 1 is retracted on the butt joint platform 2, the movable sliding block 2-11 is clamped in the fixed groove 1-111 of the butt joint 1-11, namely, the butt joint 1-11 is clamped in the butt joint groove 2-1, and under the condition of no upward lifting force, the unmanned aerial vehicle 1 is tightly docked with the butt joint platform 2. In the launching process of the unmanned aerial vehicle 1, the movable sliding block 2-11 is enabled to move towards two sides under the action of the lifting force of the unmanned aerial vehicle 1, so that the movable sliding block 2-11 is not clamped on the butt joint 1-11 any more, the unmanned aerial vehicle 1 is ejected out of the butt joint platform 2, when the unmanned aerial vehicle 1 is launched from the butt joint platform 2, in the downward falling process of the unmanned aerial vehicle 1, the butt joint 1-11 applies downward force to the movable sliding block 2-11, so that the movable sliding block 2-11 moves towards two sides, and due to the fact that the fixed groove 1-111 is formed in the butt joint 1-11, the width of the butt joint 1-11 at the fixed groove 1-111 is smaller, the pushing force to the movable sliding block 2-11 is also reduced, the movable sliding block 2-11 is enabled to be restored to be clamped in the butt joint groove 2-1 in the direction of the butt joint 1-11, and the stability of the unmanned aerial vehicle 1 on the butt joint platform 2 is guaranteed under the condition that no lifting force is generated. In the embodiment, the aerial emission and recovery of the fixed wing unmanned aerial vehicle 1 are achieved through a purely mechanical control mode, so that redundant structures and weight can be reduced, and the lifting efficiency of the unmanned aerial vehicle 1 is improved.
In this embodiment, as shown in fig. 2 and 3, a docking limiting portion 2-12 is disposed at the upper end of the moving slide block 2-11, a docking bottom 2-13 is disposed at the bottom of the docking slot 2-1, and the docking bottom 2-13 is disposed at the lower end of the moving slide block 2-11; the movable sliding blocks 2-11 and the butt joint limiting parts 2-12 on the side walls on the two sides of the butt joint groove 2-1 are symmetrically arranged. The symmetrically arranged movable sliding blocks 2-11 clamp the butt joint 1-11 from two sides, so that the stability of the butt joint 1-11 in the butt joint groove 2-1 is ensured. The fixing groove 1-111 of the butt joint 1-11 is arranged towards the movable slide block 2-11, so that the movable slide block 2-11 is clamped in the fixing groove 1-111, and recovery of the unmanned aerial vehicle 1 is more stable. In this embodiment, the structure of the fixing groove 1-111 makes the diameters of the butt joints 1-11 at the upper and lower ends of the fixing groove 1-111 larger than the diameters of the butt joints 1-11 at the butt joint groove 2-1, and when the movable slide block 2-11 is clamped in the fixing groove 1-111, the butt joint 1-11 is fixed in the butt joint groove 2-1 without external force, so as to limit the positions in the up-down direction, and improve the recovery stability of the unmanned aerial vehicle 1. In the embodiment, when the unmanned aerial vehicle 1 is not recovered to the docking platform 2 in the air, the movable sliding block 2-11 protrudes towards the inside of the docking slot 2-1, and an elastic piece 2-14 is arranged at one end of the movable sliding block 2-11 away from the docking head 1-11; the other end of the elastic member 2-14 is connected with a limiting table 2-15. When the unmanned aerial vehicle 1 is recovered, as shown in fig. 4, the unmanned aerial vehicle 1 aligns with the docking groove 2-1 on the docking platform 2, sinks towards the inside of the docking groove 2-1, applies downward pushing force to the movable sliding block 2-11 at the lower end of the docking head 1-11, enables the movable sliding block 2-11 to move towards two sides under the pushing force, and due to the existence of the elastic piece 2-14, the movable sliding block 2-11 can move towards two sides, meanwhile, the movable sliding block 2-11 moving towards two sides enables the elastic piece 2-14 to be compressed, the position of the limiting table 2-15 is fixed, the elastic piece 2-14 is prevented from being displaced towards two sides, and only the elastic piece 2-14 can be compressed and deformed. In the sinking process of the butt joint 1-11, the fixed groove 1-111 is also gradually close to the movable slide block 2-11 downwards, the pushing force of the butt joint 1-11 to the movable slide block 2-11 at the fixed groove 1-111 is reduced, the extrusion force of the movable slide block 2-11 to the elastic piece 2-14 is reduced, the elastic piece 2-14 is gradually restored from a compressed state, the movable slide block 2-11 is pushed to move towards the fixed groove 1-111 until the butt joint 1-11 is sunk to the fixed groove 1-111 and the movable slide block 2-11 are positioned at the horizontal position, and the movable slide block 2-11 is just clamped into the fixed groove 1-111 under the action of the restoring force of the elastic piece 2-14, so that the butt joint 1-11 is clamped in the butt joint groove 2-1 to realize the recovery of the unmanned aerial vehicle 1. In the launching process of the unmanned aerial vehicle 1, as shown in fig. 5, the docking platform 2 carries the unmanned aerial vehicle 1 to fly flatly and accelerate, meanwhile, lift force is gradually provided for the unmanned aerial vehicle 1, the unmanned aerial vehicle 1 also has certain gravity, when the lift force of the unmanned aerial vehicle 1 is larger than the gravity, the docking head 1-11 applies upward pushing force to the movable sliding block 2-11 clamped in the docking groove 2-1, in the continuous lifting force increasing process, the pushing force received by the movable sliding block 2-11 is gradually increased, so that the movable sliding block 2-11 gradually moves towards two sides, when the difference value of the lift force of the unmanned aerial vehicle 1 and the gravity reaches a certain value, the lower end of the docking head 1-11 is separated from the middle of the movable sliding block 2-11 on two sides, namely, the unmanned aerial vehicle 1 is separated from the docking groove 2-1 of the docking platform 2, and the docking platform 2 is popped up, so that launching and take-off are realized.
In this embodiment, when the butt joint 1-11 is sunk during the recovery process of the unmanned aerial vehicle 1, the butt joint 1-11 applies a vertical downward force to the movable slider 2-11, and the movable slider 2-11 protrudes toward the inside of the butt joint groove 2-1 in the original state, and similarly, when the butt joint 1-11 is clamped in the fixed groove 1-111 during the emission process of the unmanned aerial vehicle 1, the movable slider 2-11 is also in a state of protruding toward the inside of the butt joint groove 2-1. In order to ensure that the movable slide blocks 2-11 can move towards two sides without being limited by the movable slide blocks 2-11 when the downward force is applied to the movable slide blocks 2-11 by the butt joint 1-11 during recycling or when the upward force is applied to the movable slide blocks 2-11 by the butt joint 1-11 during transmitting, in this embodiment, the movable slide blocks 2-11 are in a structure with a convex middle part and concave upper and lower ends towards the end part arranged in the middle of the butt joint groove 2-1; the side wall of the butt joint rod 1-1 is recessed towards the center of the butt joint rod 1-1. Namely, in terms of structure, the upper end face of the movable slide block 2-11 protruding from the inside of the butt joint groove 2-1 is inclined downward, and the lower end face is inclined upward. When the butt joint 1-11 sinks, the upper end surface of the part of the movable slide block 2-11 protruding out of the butt joint groove 2-1 is arranged in a downward inclined mode, so that the force applied by the butt joint 1-11 to the movable slide block 2-11 acts on the downward inclined surface, the butt joint 1-11 sinks along the inclined surface, and the component force applied to the inclined surface of the movable slide block 2-11 in the horizontal direction pushes the movable slide blocks 2-11 on two sides to move towards two sides, and further the butt joint 1-11 is prevented from being limited by the movable clamping blocks in the sinking process; similarly, in the launching process of the unmanned aerial vehicle 1, when the butt joint 1-11 ascends, the butt joint gradually ascends along the upward lower inclined surface of the movable sliding block 2-11 to push the movable sliding block 2-11 to move towards two sides.
In this embodiment, the fixing groove 1-111 is an annular groove disposed around the circumference of the docking rod 1-1. The movable sliding blocks 2-11 which are arranged in bilateral symmetry are matched with the annular grooves, and the annular grooves enable the movable sliding blocks 2-11 which are arranged in bilateral symmetry to be clamped in the fixed grooves 1-111 even if the unmanned aerial vehicle 1 and the docking platform 2 generate an offset angle, so that the recovery stability of the unmanned aerial vehicle 1 is guaranteed.
In this embodiment, the distance between the butt joint limiting parts 2-12 symmetrically arranged is gradually reduced from top to bottom. The end part of the butt joint limiting part 2-12 arranged towards the butt joint groove 2-1 is close to the middle of the butt joint groove 2-1 from top to bottom, so that the butt joint limiting parts 2-12 on the two side walls of the butt joint groove 2-1 are conical. The notch of the docking groove 2-1 is wider, the docking area is convenient to increase, the docking difficulty is reduced, meanwhile, the docking rod 1-1 of the unmanned aerial vehicle 1 can be guided to move at the docking bottom 2-13 when the unmanned aerial vehicle 1 is recycled, and the recycling accuracy is convenient to improve. In the recycling and docking process, in order to reduce the friction force between the docking rod 1-1 and the docking groove 2-1, the docking head 1-11 comprises a hemispherical piece 1-112 arranged at the lower end of the docking groove 2-1; the upper end surfaces of the butt joint bottoms 2-13 are matched with the hemispherical pieces 1-112. In the sinking process of the docking rod 1-1, the contact area of the hemispherical piece 1-112 at the lower end of the docking rod and the docking groove 2-1 is smaller, the friction force is smaller, the time required in the recycling docking process can be effectively reduced, and the recycling efficiency is improved. Meanwhile, the butt joint device is suitable for the special shape of the hemispherical piece 1-112, the upper end face of the butt joint bottom 2-13 in the embodiment is sunken downwards and is just matched with the hemispherical piece 1-112, and the butt joint stability of the butt joint rod 1-1 at the butt joint bottom 2-13 is ensured.
In addition, in this embodiment, as shown in fig. 2, the docking slot 2-1 is disposed along the length direction of the docking platform 2, and the cross section of the opening end of the docking slot 2-1 is rectangular. Namely, the runway is arranged on the docking platform 2, and the unmanned aerial vehicle 1 can land and dock with the docking platform 2 at any position along the length direction of the docking slot 2-1 when being recycled, so that the landing difficulty of the unmanned aerial vehicle 1 is greatly reduced, and the docking efficiency is improved. Wherein two docking rods 1-1 are arranged; a limiting pin 2-16 for limiting the docking rod 1-1 is arranged in the length direction of the docking groove 2-1; the limiting pin 2-16 is located between two of the docking rods 1-1. The limiting pin 2-16 restricts the longitudinal sliding of the docking rod 1-1 in the docking slot 2-1 so that the center of gravity of the docking platform 2 is not excessively affected even if the docking rod 1-1 slides back and forth. Meanwhile, in order to ensure that the stable docking function can be realized everywhere in the length direction of the docking slot 2-1, in this embodiment, a plurality of elastic members 2-14 are disposed along the length direction of the docking slot 2-1.
While embodiments of the present invention have been described, various modifications and adaptations may be made by one of ordinary skill in the art within the scope of the following claims.
Claims (4)
1. A receive and release subassembly for fixed wing unmanned aerial vehicle, its characterized in that:
the docking mechanism comprises a docking rod arranged at the lower end of the unmanned aerial vehicle and a docking groove arranged at the upper end of a docking platform;
the lower end of the butt joint rod is provided with a butt joint head which is matched with the butt joint groove;
the butt joint is provided with a fixed groove, the groove walls at two sides of the butt joint groove are provided with movable sliding blocks which can stretch towards the groove wall direction, and the movable sliding blocks are matched with the fixed groove and used for clamping the butt joint;
the upper end of the movable slide block is provided with a butt joint limiting part, the bottom of the butt joint groove is provided with a butt joint bottom, and the butt joint bottom is arranged at the lower end of the movable slide block;
the movable sliding blocks and the butt joint limiting parts on the side walls of the two sides of the butt joint groove are symmetrically arranged;
the butt joint rods are two;
the end part of the movable sliding block, which is arranged towards the middle of the butt joint groove, is in a structure with a convex middle part and concave upper and lower ends;
the fixing groove is recessed from the side wall of the butt joint rod towards the center of the butt joint rod;
the fixing groove is an annular groove arranged around the circumference of the docking rod;
an elastic piece is arranged at one end of the movable sliding block, which is far away from the butt joint;
the other end part of the elastic piece is connected with a limiting table;
the butt joint comprises a hemispherical piece arranged at the lower end of the butt joint groove;
the upper end surface of the butt joint bottom is matched with the hemispherical piece;
the end part of the butt joint limiting part, which is arranged towards the butt joint groove, is close to the middle of the butt joint groove from top to bottom, so that the butt joint limiting parts on the two side walls of the butt joint groove are conical.
2. A retraction assembly for a fixed wing unmanned aerial vehicle as claimed in claim 1, wherein:
the butt joint groove is arranged along the length direction of the butt joint platform, and the cross section of the opening end of the butt joint groove is rectangular.
3. A retraction assembly for a fixed wing unmanned aerial vehicle as claimed in claim 1, wherein:
the elastic piece is provided with a plurality of elastic pieces along the length direction of the butt joint groove.
4. A retraction assembly for a fixed wing unmanned aerial vehicle as claimed in claim 1, wherein:
a limiting pin for limiting the butt joint rod is arranged in the length direction of the butt joint groove;
the limiting pin is positioned between the two abutting rods.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111567930.1A CN114229025B (en) | 2021-12-21 | 2021-12-21 | A receive and release subassembly for fixed wing unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111567930.1A CN114229025B (en) | 2021-12-21 | 2021-12-21 | A receive and release subassembly for fixed wing unmanned aerial vehicle |
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| CN114229025A CN114229025A (en) | 2022-03-25 |
| CN114229025B true CN114229025B (en) | 2024-01-23 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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|---|---|
| CN114229025A (en) | 2022-03-25 |
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