CN114701642A - Unmanned aerial vehicle and catapult thereof - Google Patents
Unmanned aerial vehicle and catapult thereof Download PDFInfo
- Publication number
- CN114701642A CN114701642A CN202210377139.2A CN202210377139A CN114701642A CN 114701642 A CN114701642 A CN 114701642A CN 202210377139 A CN202210377139 A CN 202210377139A CN 114701642 A CN114701642 A CN 114701642A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- track
- catapult
- rail
- aerial vehicle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 135
- 239000010985 leather Substances 0.000 claims description 3
- 230000001681 protective effect Effects 0.000 claims 1
- 230000001133 acceleration Effects 0.000 abstract description 3
- 230000035899 viability Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 10
- 230000009471 action Effects 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000005096 rolling process Methods 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000032258 transport Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- 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
- B64F1/005—Protective coverings for aircraft not in use
-
- 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—Ground or aircraft-carrier-deck installations for launching aircraft
- B64F1/06—Ground or aircraft-carrier-deck installations for launching aircraft using catapults
-
- 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
- B64F1/22—Ground or aircraft-carrier-deck installations for handling aircraft
- B64F1/223—Ground or aircraft-carrier-deck installations for handling aircraft for towing aircraft
- B64F1/225—Vehicles specially adapted therefor, e.g. aircraft tow tractors
- B64F1/227—Vehicles specially adapted therefor, e.g. aircraft tow tractors for direct connection to aircraft, e.g. tow tractors without towing bars
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and an ejector thereof, and the unmanned aerial vehicle comprises a flight mechanism, wherein an ejection mechanism is arranged on the flight mechanism, a folding mechanism is arranged on the ejection mechanism, a power mechanism is arranged between the folding mechanism and the ejection mechanism, the power mechanism drives the ejection mechanism, a mounting mechanism is rotatably arranged on the folding mechanism, and a shielding mechanism is mounted on the mounting mechanism; the wings of the unmanned aerial vehicle can be conveniently folded and stored through the arrangement of the flight mechanism, the unmanned aerial vehicle can be conveniently transported by the arrangement mechanism, and the occupied space of the unmanned aerial vehicle is reduced; the folding mechanism and the flying mechanism are convenient to carry and move and to support the unfolded folding mechanism through the arrangement of the arrangement mechanism, and the flying track is convenient to extend through the arrangement of the folding mechanism, so that the flying mechanism obtains enough acceleration; through the setting that shelters from the mechanism and then be convenient for shelter from the protection to the flying mechanism machine auxiliary member, improve the outdoor viability of unmanned aerial vehicle and transmitter.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle and a catapult thereof.
Background
An unmanned aircraft, referred to as "drone", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either fully or intermittently, by an onboard computer. Unmanned aircraft tend to be more suitable for tasks that are too "fool, messy or dangerous" than manned aircraft, where the unmanned aircraft is required to obtain a flyable velocity during the initial flight, and for this reason an accelerated catapult is required to perform the flight task.
However, the conventional fixed-wing unmanned aerial vehicle occupies a large space, is inconvenient to transport, and a conventional ejection rack for executing an ejection task generally needs to be arranged on the ground for the ejection task, an ejection part needs to be lifted to the ground separately for arrangement and expansion, so that the flight preparation time is prolonged, and the ejection task can be executed only by selecting a flat ground, so that the flight condition of the unmanned aerial vehicle is strictly limited; unmanned aerial vehicle ejection rack generally all exposes outside at the in-process of transporting, and unmanned aerial vehicle and catapult expose to the corruption very easily at long-time insolate or wind and rain, can't play the protection to unmanned aerial vehicle and ejection part and shelter from the effect to reduced the service ability of dealing with emergency unmanned aerial vehicle, and not set up any guard plate that shelters from on the current ejection rack, reduced the life of catapult.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides an unmanned aerial vehicle and a catapult thereof.
The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides an unmanned aerial vehicle, includes flight mechanism, flight mechanism includes the organism, be provided with the backup pad on the organism, install a plurality of gyro wheels in the backup pad, install three fin on the organism, just it has two wings to rotate on the organism, it has the second gear to settle on the wing, two the second gear rotates to be connected in the organism and intermeshing, two it has first telescopic link and second telescopic link to rotate between the second gear, first telescopic link and second telescopic link sliding fit, it has the spring to contradict between second telescopic link and the first telescopic link, first telescopic link of spring drive and second telescopic link.
The technical scheme adopted by the invention for solving the technical problems is as follows: the utility model provides an unmanned aerial vehicle's catapult, be equipped with ejection mechanism on the organism, be provided with folding mechanism on the ejection mechanism, install power unit between folding mechanism and the ejection mechanism, power unit drive ejection mechanism, the last arrangement mechanism that has rotated of folding mechanism, it shelters from the mechanism to settle on the arrangement mechanism.
Preferably, the placing mechanism comprises a vehicle body, the vehicle body is arranged on the machine body, a bracket is arranged on the vehicle body, a placing plate is installed on the vehicle body, the placing plate rotates on the vehicle body, and a fixing frame is fixed on the placing plate.
Preferably, the folding mechanism comprises a first rail, the fixing frame is provided with the first rail in a rotating mode, the first rail is provided with a second rail, a first rotating shaft is arranged between the second rail and the first rail in a rotating mode, a hydraulic telescopic rod is arranged between the first rail and the second rail in a rotating mode, and the hydraulic telescopic rod drives the first rail and the second rail.
Preferably, the power mechanism comprises reciprocating wheels, the reciprocating wheels are respectively arranged between the first rail and the second rail in a rotating mode, a connecting band is wound between the two reciprocating wheels, a protection ring is arranged on each reciprocating wheel, and the two reciprocating wheels are assembled together through the connecting band.
Preferably, a high-speed motor is installed on the first track, first gears are respectively fixed on the high-speed motor and the reciprocating wheel, a chain is meshed between the two first gears, and the high-speed motor drives the reciprocating wheel through the chain.
Preferably, the ejection mechanism includes the fixed block, install a plurality of fixed blocks on the connecting band, it is a plurality of be connected with the bow between the fixed block, it has the removal seat to settle on the bow, it is equipped with the lug to remove between seat and the bow, the lug block is to removing on the seat, the lug will remove seat and bow and assemble together, the gyro wheel contact removes the seat, it has a plurality of balls to roll between seat and the first track to remove.
Preferably, the shielding mechanism comprises a guide rail, the guide rail is arranged on the vehicle body, a plurality of first sliding blocks and second sliding blocks are arranged in the guide rail in a sliding fit mode, a connecting rod is arranged between the first sliding blocks and the second sliding blocks in a rotating mode, and the first sliding blocks and the second sliding blocks are matched together through the connecting rod.
Preferably, be equipped with third pivot and lead screw on the guide rail, third pivot and lead screw fixed connection, lead screw threaded connection is in the second slider, install driving motor on the guide rail, driving motor is fixed in the lead screw, driving motor passes through lead screw drive second slider.
Preferably, a support rod is arranged between the first sliding block and the second sliding block, and a folding leather is arranged between the support rods.
The invention has the beneficial effects that:
(1) according to the unmanned aerial vehicle and the catapult thereof, the wings of the unmanned aerial vehicle can be conveniently folded and stored through the arrangement of the flight mechanism, the unmanned aerial vehicle can be conveniently transported by the arrangement mechanism, the occupied space of the unmanned aerial vehicle is reduced, and the unmanned aerial vehicle can play a role in protecting and shielding the emergent weather conditions encountered when the unmanned aerial vehicle is launched; namely: when the flying wing needs to be ejected to fly, firstly, the vehicle body needs to be started, the vehicle body is transferred to an open area through the vehicle body to fly, the driving motor is started to drive the plurality of support rods to be stored and folded to expose the vehicle body, the flying wings are operated to enable the two second gears to be meshed with each other and rotate, the two flying wings synchronously deflect to the outer side of the vehicle body due to the arrangement of the two second gears, the occupied space of the unmanned aerial vehicle is reduced due to the arrangement of the foldable flying wings, the vehicle body can be conveniently transferred by the vehicle body, the two first telescopic rods and the second telescopic rods are driven by the second gears during deflection to be in sliding fit, when the flying wings rotate to the flying position, the springs abut against the first telescopic rods and the second telescopic rods to enable the two second gears to keep the deflecting position, the two flying wings are driven to the unfolding position, the lifting force required by flying wings can be conveniently obtained, and the vehicle body is arranged on the moving seat through the plurality of rollers, thereby being convenient for flying by quickly separating from the movable seat during ejection.
(2) According to the unmanned aerial vehicle and the catapult thereof, the folding mechanism is provided with the mounting mechanism in a rotating manner, the mounting mechanism is provided with the shielding mechanism, the mounting mechanism is convenient to carry the folding mechanism and the flying mechanism to move and is convenient to support the unfolded folding mechanism, the arrangement of the folding mechanism is further convenient to prolong the flying track, so that the flying mechanism obtains enough acceleration, and the catapult effect is ensured, namely: when unmanned aerial vehicle and accessory equipment remove need to be carried, the accessible is driven the automobile body and is shifted to it, the setting board rotates and connects the automobile body, thereby be convenient for deflect first track and second track regulation and launch the angle, first track and second track rotate through first pivot and connect, and first track and second track pass through hydraulic telescoping rod and realize folding, and then be convenient for launch orbital the convenient receipts and release in the extension, further improvement the space utilization of supplementary flight part, the second track can hold in the palm the groove of putting on the automobile body after launching, thereby can reduce the load after the second track expandes, first track and second orbital result of use have been guaranteed.
(3) The invention relates to an unmanned aerial vehicle and a catapult thereof.A catapult mechanism is arranged on a body, a folding mechanism is arranged on the catapult mechanism, a power mechanism is arranged between the folding mechanism and the catapult mechanism, and the catapult mechanism can conveniently obtain a fast moving speed through the power mechanism, namely: when needing the drive to remove the seat and carry unmanned aerial vehicle fast and remove, at first will remove the seat and settle to two lugs on, make the lug can carry and remove seat quick travel, it has a plurality of balls to remove roll connection between seat and first track and the second track, and then be convenient for reduce the frictional force between seat and first track and the second track, power loss when reducing the removal, start high-speed motor, high-speed motor passes through the chain and drives the reciprocating wheel rotation, winding connecting band between two reciprocating wheels, the connecting band passes through fixed block and bow-shaped frame and drives the lug and remove, the connection removes the seat can be dismantled to the lug, and then be convenient for the block to remove seat quick slip, the lug breaks away from and removes the seat after removing the orbital tip of second, and then is driven the inside of first track by the connecting band, remove the seat and make preparation work for the block next time.
(4) According to the unmanned aerial vehicle and the catapult thereof, the shielding mechanism is arranged on the arrangement mechanism, and the shielding mechanism is arranged to further facilitate shielding and protecting the auxiliary parts of the flying mechanism machine and avoid wind and sunshine, namely: when needs play the guard action to unmanned aerial vehicle and ejection part, at first start the inside driving motor of two guide rails, driving motor drive lead screw rotates, lead screw and second slider threaded connection, then lead screw drive second slider moves along the guide rail, through the connecting rod linkage between first slider and the second slider, thereby conveniently drive the synchronous even removal of a plurality of first sliders to the guide rail on, realize the displacement effect, first slider and second slider drive the bracing piece that is the U word form and remove, the bracing piece supports folding skin, thereby can shelter from unmanned aerial vehicle and ejection part in the transfer transportation, unmanned aerial vehicle blowing rain has been avoided idle, the maintenance effect of spare part has been improved.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic structural view of an overall structure provided by the present invention;
FIG. 2 is a schematic view of the shielding mechanism shown in FIG. 1;
FIG. 3 is a schematic structural view of the flying mechanism shown in FIG. 1;
FIG. 4 is a schematic view of the connection of the folding mechanism and the ejection mechanism of FIG. 1;
FIG. 5 is an enlarged view of the part A shown in FIG. 1;
FIG. 6 is an enlarged view of the portion B shown in FIG. 1;
FIG. 7 is an enlarged view of the portion C shown in FIG. 1;
FIG. 8 is an enlarged view of the portion D shown in FIG. 3;
fig. 9 is an enlarged schematic view of the part E shown in fig. 4.
In the figure: 1. a placement mechanism, 11, a vehicle body, 12, a placement plate, 13, a fixed frame, 14, a bracket, 2, a folding mechanism, 21, a first rail, 22, a second rail, 23, a first rotating shaft, 24, a hydraulic telescopic rod, 3, a power mechanism, 31, a reciprocating wheel, 32, a second rotating shaft, 33, a high-speed motor, 34, a first gear, 35, a chain, 36, a connecting belt, 37, a guard ring, 4, an ejection mechanism, 41, a fixed block, 42, a bow-shaped frame, 43, a bump, 44, a moving seat, 45, a ball, 5, a flight mechanism, 51, a machine body, 52, a tail wing, 53, a support plate, 54, a roller, 55, a flying wing, 56, a second gear, 57, a first telescopic rod, 58, a second telescopic rod, 59, a spring, 6, a shielding mechanism, 61, a guide rail, 62, a first sliding block, 63, a connecting rod, 64, a third rotating shaft, 65, a lead screw, 66, a second sliding block, 67, a fixed frame, a high-speed motor, a high, Driving motor 68, support bar 69, folding skin.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1 to 9, the unmanned aerial vehicle and the ejector thereof according to the present invention include a flying mechanism 5, the flying mechanism 5 includes a body 51, a support plate 53 is disposed on the body 51, a plurality of rollers 54 are mounted on the support plate 53, three tail fins 52 are mounted on the body 51, two flying wings 55 are rotatably mounted on the body 51, a second gear 56 is disposed on the flying wings 55, the two second gears 56 are rotatably connected in the body 51 and are engaged with each other, a first telescopic rod 57 and a second telescopic rod 58 are rotatably disposed between the two second gears 56, the first telescopic rod 57 and the second telescopic rod 58 are slidably engaged, a spring 59 is abutted between the second telescopic rod 58 and the first telescopic rod 57, and the spring 59 drives the first telescopic rod 57 and the second telescopic rod 58; through flight mechanism 5 set up and then be convenient for fold the wing of accomodating unmanned aerial vehicle, it is convenient settle mechanism 1 transports it, reduces unmanned aerial vehicle occupation space, promptly: when the body 51 needs to be ejected for flight, the vehicle body 11 needs to be started first, the body 51 is transferred to an open area through the vehicle body 11 to fly, the driving motor 67 is started to drive the plurality of support rods 68 to be stored and folded to expose the body 11, the flying wings 55 are operated to enable the two second gears 56 to rotate in an engaged manner, the two second gears 56 are arranged to enable the two flying wings 55 to synchronously deflect to the outer side of the body 51, the foldable flying wings 55 are arranged to reduce the occupied space of the unmanned aerial vehicle, so that the transfer of the body 11 is facilitated, the second gears 56 during deflection drive the two first telescopic rods 57 and the second telescopic rods 58 to be in sliding fit, and when the flying wings 55 rotate to a flying position, the spring 59 pushes against the first telescopic rods 57 and the second telescopic rods 58, the two second gears 56 are kept at the deflection positions, and since the spring 59 is in a compressed state at first, when the first telescopic rod 57 and the second telescopic rod 58 rotate along with the second gears 56, and when the first telescopic rod 57 and the second telescopic rod 58 rotate to be connected with the axis of the second gears 56, the spring 59 is changed to be in a stretched state from the compressed state, and at this time, the rotation angle of the second gears 56 is 90 degrees, namely the rotation angle of the flying wing 55. Then the first telescopic rod 57 and the second telescopic rod 58 rotate by a small angle with the second gear 56, the spring 59 in the stretching state has inward contracting tension, the two ends of the spring 59 can pull the first telescopic rod 57 and the second telescopic rod 58, and at this time, the first telescopic rod 57 and the second telescopic rod 58 are influenced by the tension of the spring 59, so that the flying wing 55 is fixed after rotating to the flying position; the two flying wings 55 are driven to the deployed position so as to obtain the lift force required for flying by using the flying wings 55, and the body 51 is placed on the movable base 44 by a plurality of rollers 54 so as to be quickly separated from the movable base 44 for flying when ejected.
Specifically, the ejection mechanism 4 is arranged on the machine body 51, the folding mechanism 2 is arranged on the ejection mechanism 4, the power mechanism 3 is arranged between the folding mechanism 2 and the ejection mechanism 4, the power mechanism 3 drives the ejection mechanism 4, the arrangement mechanism 1 is rotated on the folding mechanism 2, and the shielding mechanism 6 is arranged on the arrangement mechanism 1.
Specifically, the placing mechanism 1 comprises a vehicle body 11, the vehicle body 51 is provided with the vehicle body 11, the vehicle body 11 is provided with a bracket 14, the vehicle body 11 is provided with a placing plate 12, the placing plate 12 rotates on the vehicle body 11, and the placing plate 12 is fixed with a fixing frame 13.
Specifically, the folding mechanism 2 includes a first rail 21, the first rail 21 is rotatably disposed on the fixed frame 13, a second rail 22 is disposed on the first rail 21, a first rotating shaft 23 is rotatably disposed between the second rail 22 and the first rail 21, a hydraulic telescopic rod 24 is rotatably disposed between the first rail 21 and the second rail 22, and the hydraulic telescopic rod 24 drives the first rail 21 and the second rail 22; folding mechanism 2 is last to rotate and to have mounting mechanism 1, mounting mechanism 1 is last to settle and to have and to shelter from mechanism 6, through mounting mechanism 1 set up and conveniently carry folding mechanism 6 with flight mechanism 5 removes, and is convenient for hold in the palm the expansion folding mechanism 6, through folding mechanism 6 set up and then be convenient for prolong the flight track, make flight mechanism 5 obtains sufficient acceleration, has guaranteed the effect of launching, promptly: when the unmanned aerial vehicle and the auxiliary equipment thereof need to be carried and moved, the unmanned aerial vehicle and the auxiliary equipment thereof can be transferred by driving the vehicle body 11, the placing plate 12 is rotatably connected with the vehicle body 11, so that the first rail 21 and the second rail 22 can be deflected to adjust the ejection angle, the first rail 21 and the second rail 22 are rotatably connected through the first rotating shaft 23, the first rail 21 and the second rail 22 are folded through the hydraulic telescopic rod 58, the ejection rail is prolonged, the retraction and the collection are convenient, the space utilization rate of auxiliary flight components is further improved, the second rail 22 can be supported on the bracket 14 on the vehicle body 11 after being unfolded, the load of the second rail 22 after being unfolded can be reduced, and the use effect of the first rail 21 and the second rail 22 is ensured.
Specifically, the power mechanism 3 includes a reciprocating wheel 31, the reciprocating wheels 31 are respectively rotated between the first rail 21 and the second rail 22, a connecting band 36 is wound between the two reciprocating wheels 31, a guard ring 37 is installed on the reciprocating wheel 31, and the connecting band 36 assembles the two reciprocating wheels 31 together.
Specifically, a high-speed motor 33 is mounted on the first rail 21, first gears 34 are respectively fixed on the high-speed motor 33 and the reciprocating wheel 31, a chain 35 is engaged between the two first gears 34, and the high-speed motor 33 drives the reciprocating wheel 31 through the chain 35.
Specifically, the ejection mechanism 4 includes a fixed block 41, a plurality of fixed blocks 41 are mounted on the connecting belt 36, an arcuate frame 42 is connected between the plurality of fixed blocks 41, a moving seat 44 is disposed on the arcuate frame 42, a protrusion 43 is disposed between the moving seat 44 and the arcuate frame 42, the protrusion 43 is clamped on the moving seat 44, the protrusion 43 assembles the moving seat 44 and the arcuate frame 42 together, the roller 54 contacts the moving seat 44, and a plurality of balls 45 roll between the moving seat 44 and the first rail 21; be equipped with ejection mechanism 4 on the organism 51, be provided with on the ejection mechanism 4 folding mechanism 2, install between folding mechanism 2 and the ejection mechanism 4 power unit 3, through power unit 3 conveniently makes ejection mechanism 4 obtains the fast moving speed, promptly: when the unmanned aerial vehicle is fast carried by the moving seat 44 and is moved in need of driving, firstly, the moving seat 44 is arranged on two convex blocks 43, so that the convex blocks 43 can carry the moving seat 44 to move fast, a plurality of balls 45 are connected between the moving seat 44 and the first track 21 and the second track 22 in a rolling manner, so that the friction force between the moving seat 44 and the first track 21 and the second track 22 is reduced, the power loss in moving is reduced, the high-speed motor 33 is started, the high-speed motor 33 drives the reciprocating wheel 31 to rotate through the chain 35, the connecting belt 36 is wound between the two reciprocating wheels 31, the connecting belt 36 drives the convex blocks 43 to move through the fixed block 41 and the arched frame 42, the convex blocks 43 can be detachably connected with the moving seat 44, so that the moving seat 44 can be fast slid in a clamping manner, after moving to the end of the second rail 22, the projection 43 is disengaged from the moving seat 44, and is then carried by the connecting band 36 to the inside of the first rail 21, so as to be ready for the next engagement of the moving seat 44.
Specifically, the shielding mechanism 6 includes a guide rail 61, the vehicle body 11 is provided with the guide rail 61, a plurality of first sliders 62 and second sliders 66 are slidably fitted in the guide rail 61, a connecting rod 63 is rotatably arranged between the first sliders 62 and the second sliders 66, and the connecting rod 63 fits the first sliders 62 and the second sliders 66 together.
Specifically, be equipped with third pivot 64 and lead screw 65 on the guide rail 61, third pivot 64 and lead screw 65 fixed connection, lead screw 65 threaded connection is in second slider 66, install driving motor 67 on the guide rail 61, driving motor 67 is fixed in lead screw 65, driving motor 67 passes through lead screw 65 drive second slider 66.
Specifically, a support rod 68 is arranged between the first slide block 62 and the second slide block 66, and a folding leather 69 is arranged between the support rods 68; settling mechanism 1 is last to settle and to shelter from mechanism 6, through shelter from mechanism 6 set up and then be convenient for right 5 machine auxiliary components of flight mechanism shelter from the protection, avoid the wind to blow the sun, promptly: when the unmanned aerial vehicle and the ejection component need to be protected, the driving motors 67 in the two guide rails 61 are started firstly, the driving motor 67 drives the screw rod 65 to rotate, the screw rod 65 is in threaded connection with the second sliding block 66, the screw 65 drives the second slide block 66 to move along the guide rail 61, the first slide block 62 and the second slide block 66 are linked through the connecting rod 63, thereby conveniently driving a plurality of first sliding blocks 62 to synchronously and uniformly move onto the guide rail 61, realizing the pitch-changing function, the first slider 62 and the second slider 66 drive the U-shaped support bar 68 to move, the support bar 68 supports the folding skin 69, thereby can shelter from unmanned aerial vehicle and ejection part, avoid idle unmanned aerial vehicle wind-blown to drench, improve the maintenance effect of spare part.
When the unmanned aerial vehicle is used, when the aircraft body 51 needs to be ejected to fly, firstly, the vehicle body 11 needs to be started, the aircraft body 51 is transferred to an open area through the vehicle body 11 to fly, the driving motor 67 is started, the supporting rods 68 are driven to be stored and folded to expose the aircraft body 11, the flying wings 55 are operated to enable the two second gears 56 to be meshed and rotated with each other, the two second gears 56 are arranged to enable the two flying wings 55 to be synchronously deflected to the outer side of the aircraft body 51, the foldable flying wings 55 are arranged to reduce the occupied space of the unmanned aerial vehicle and facilitate the transfer of the aircraft body 11, the second gears 56 during deflection drive the two first telescopic rods 57 and the second telescopic rods 58 to be in sliding fit, when the flying wings 55 rotate to the flying position, the springs 59 pull the first telescopic rods 57 and the first telescopic rods 58 to enable the two second gears 56 to keep the deflection position, so that the two flying wings 55 are driven to the unfolded position, and further facilitate the flying wings 55 to obtain the lifting force required by flying wings, the body 51 is arranged on the movable seat 44 through a plurality of rollers 54, so as to be conveniently separated from the movable seat 44 for flying when being ejected; when the unmanned aerial vehicle and the accessory equipment thereof need to be carried and moved, the unmanned aerial vehicle and the accessory equipment thereof can be transferred by driving the vehicle body 11, the placing plate 12 is rotatably connected with the vehicle body 11, so that the first rail 21 and the second rail 22 can be deflected to adjust the ejection angle, the first rail 21 and the second rail 22 are rotatably connected through the first rotating shaft 23, the first rail 21 and the second rail 22 are folded through the hydraulic telescopic rod 58, the ejection rails can be conveniently extended and retracted, the space utilization rate of the auxiliary flight part is further improved, the second rail 22 can be supported on the bracket 14 on the vehicle body 11 after being unfolded, the load of the second rail 22 after being unfolded can be reduced, and the use effect of the first rail 21 and the second rail 22 is ensured; when the movable base 44 needs to be driven to rapidly carry the unmanned aerial vehicle to move, the movable base 44 is firstly arranged on the two convex blocks 43, so that the convex blocks 43 can carry the movable base 44 to rapidly move, a plurality of balls 45 are connected between the movable base 44 and the first rail 21 and the second rail 22 in a rolling manner, so that the friction force between the movable base 44 and the first rail 21 and the second rail 22 is reduced, the power loss during moving is reduced, the high-speed motor 33 is started, the high-speed motor 33 drives the reciprocating wheels 31 to rotate through the chains 35, the connecting belt 36 is wound between the two reciprocating wheels 31, the connecting belt 36 drives the convex blocks 43 to move through the fixed blocks 41 and the arched frames 42, the convex blocks 43 can be detachably connected with the movable base 44, so that the movable base 44 can be clamped to rapidly slide, the convex blocks 43 are separated from the movable base 44 after moving to the end part of the second rail 22, and are driven to the inside of the first rail 21 by the connecting belt 36, ready for the next engagement of the mobile seat 44; when need play the guard action to unmanned aerial vehicle and ejection part, at first start the inside driving motor 67 of two guide rails 61, driving motor 67 drive lead screw 65 rotates, lead screw 65 and the threaded connection of second slider 66, then lead screw 65 drive second slider 66 moves along guide rail 61, link through connecting rod 63 between first slider 62 and the second slider 66, thereby conveniently drive the synchronous even removal of a plurality of first sliders 62 to guide rail 61 on, realize the displacement effect, first slider 62 and second slider 66 drive are the bracing piece 68 removal of U style of calligraphy, bracing piece 68 supports folding skin 69, thereby can shelter from unmanned aerial vehicle and ejection part.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and the embodiments and descriptions given above are only illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. An unmanned aerial vehicle, includes flight mechanism (5), its characterized in that: the flying mechanism (5) comprises a body (51), a support plate (53) is arranged on the body (51), a plurality of rollers (54) are arranged on the supporting plate (53), three empennages (52) are arranged on the machine body (51), two flying wings (55) are rotatably arranged on the machine body (51), second gears (56) are arranged on the flying wings (55), the two second gears (56) are rotatably connected in the machine body (51) and are mutually meshed, a first telescopic rod (57) and a second telescopic rod (58) are rotatably arranged between the two second gears (56), the first telescopic rod (57) is in sliding fit with the second telescopic rod (58), a spring (59) is propped between the second telescopic rod (58) and the first telescopic rod (57), the spring (59) drives the first telescopic rod (57) and the second telescopic rod (58).
2. The catapult for unmanned aerial vehicles of claim 1, wherein: the ejection mechanism (4) is arranged on the machine body (51), the folding mechanism (2) is arranged on the ejection mechanism (4), the power mechanism (3) is installed between the folding mechanism (2) and the ejection mechanism (4), the ejection mechanism (4) is driven by the power mechanism (3), the arrangement mechanism (1) is rotated on the folding mechanism (2), and the shielding mechanism (6) is arranged on the arrangement mechanism (1).
3. The catapult for unmanned aerial vehicles of claim 2, wherein: the arrangement mechanism (1) comprises a vehicle body (11), the vehicle body (11) is arranged on the machine body (51), a bracket (14) is arranged on the vehicle body (11), an arrangement plate (12) is installed on the vehicle body (11), the arrangement plate (12) rotates on the vehicle body (11), and a fixing frame (13) is fixed on the arrangement plate (12).
4. The catapult for unmanned aerial vehicles of claim 3, wherein: folding mechanism (2) include first track (21), it has first track (21) to rotate on mount (13), be equipped with second track (22) on first track (21), it has first pivot (23) to rotate between second track (22) and first track (21), it has hydraulic telescoping rod (24) to rotate between first track (21) and second track (22), hydraulic telescoping rod (24) drive first track (21) and second track (22).
5. The catapult for unmanned aerial vehicles of claim 4, wherein: the power mechanism (3) comprises reciprocating wheels (31), the reciprocating wheels (31) are respectively rotated between the first rail (21) and the second rail (22), a connecting belt (36) is wound between the reciprocating wheels (31), a protective ring (37) is installed on each reciprocating wheel (31), and the two reciprocating wheels (31) are assembled together through the connecting belt (36).
6. The catapult for unmanned aerial vehicles of claim 5, wherein: install high-speed motor (33) on first track (21), be fixed with first gear (34) respectively on high-speed motor (33) and reciprocating wheel (31), two meshing has chain (35) between first gear (34), high-speed motor (33) pass through chain (35) drive reciprocating wheel (31).
7. The catapult for drones, according to claim 6, characterized in that: the ejection mechanism (4) comprises fixing blocks (41), a plurality of fixing blocks (41) are installed on the connecting belt (36), an arched frame (42) is connected between the fixing blocks (41), a moving seat (44) is arranged on the arched frame (42), a convex block (43) is arranged between the moving seat (44) and the arched frame (42), the convex block (43) is clamped on the moving seat (44), the moving seat (44) and the arched frame (42) are assembled together through the convex block (43), the roller (54) contacts the moving seat (44), and a plurality of balls (45) roll between the moving seat (44) and the first rail (21).
8. The catapult for unmanned aerial vehicles of claim 7, wherein: the shielding mechanism (6) comprises a guide rail (61), the guide rail (61) is arranged on the vehicle body (11), a plurality of first sliding blocks (62) and second sliding blocks (66) are arranged in the guide rail (61) in a sliding fit mode, a connecting rod (63) is arranged between the first sliding blocks (62) and the second sliding blocks (66) in a rotating mode, and the first sliding blocks (62) and the second sliding blocks (66) are matched together through the connecting rod (63).
9. The catapult for unmanned aerial vehicles of claim 8, wherein: be equipped with third pivot (64) and lead screw (65) on guide rail (61), third pivot (64) and lead screw (65) fixed connection, lead screw (65) threaded connection is in second slider (66), install driving motor (67) on guide rail (61), driving motor (67) are fixed in lead screw (65), driving motor (67) are through lead screw (65) drive second slider (66).
10. The catapult for unmanned aerial vehicles of claim 9, wherein: a supporting rod (68) is arranged between the first sliding block (62) and the second sliding block (66), and a folding leather (69) is arranged between the supporting rods (68).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210377139.2A CN114701642A (en) | 2022-04-11 | 2022-04-11 | Unmanned aerial vehicle and catapult thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210377139.2A CN114701642A (en) | 2022-04-11 | 2022-04-11 | Unmanned aerial vehicle and catapult thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114701642A true CN114701642A (en) | 2022-07-05 |
Family
ID=82173627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210377139.2A Pending CN114701642A (en) | 2022-04-11 | 2022-04-11 | Unmanned aerial vehicle and catapult thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114701642A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115285370A (en) * | 2022-08-06 | 2022-11-04 | 中国人民解放军69246部队 | Wheeled armored vehicle-mounted unmanned aerial vehicle system and linkage control method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030089820A1 (en) * | 2000-10-12 | 2003-05-15 | Martorana Richard T. | Flyer assembly |
| CN103587686A (en) * | 2013-12-02 | 2014-02-19 | 哈尔滨工业大学 | Catapulted folding wing flying robot |
| CN107685848A (en) * | 2017-08-15 | 2018-02-13 | 浙江大学 | A kind of unmanned plane wing-folding device |
| CN207417115U (en) * | 2017-11-17 | 2018-05-29 | 西安云骋电子科技有限公司 | A kind of wheeled unmanned plane wing electric foldable unfolding mechanism of bidentate |
| CN110316398A (en) * | 2019-08-02 | 2019-10-11 | 西安探索鹰航空科技有限公司 | A kind of unmanned plane takes off and recycles institutional operation vehicle |
| CN113998137A (en) * | 2021-11-09 | 2022-02-01 | 任黎黎 | Cadastral survey unmanned aerial vehicle |
-
2022
- 2022-04-11 CN CN202210377139.2A patent/CN114701642A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030089820A1 (en) * | 2000-10-12 | 2003-05-15 | Martorana Richard T. | Flyer assembly |
| CN103587686A (en) * | 2013-12-02 | 2014-02-19 | 哈尔滨工业大学 | Catapulted folding wing flying robot |
| CN107685848A (en) * | 2017-08-15 | 2018-02-13 | 浙江大学 | A kind of unmanned plane wing-folding device |
| CN207417115U (en) * | 2017-11-17 | 2018-05-29 | 西安云骋电子科技有限公司 | A kind of wheeled unmanned plane wing electric foldable unfolding mechanism of bidentate |
| CN110316398A (en) * | 2019-08-02 | 2019-10-11 | 西安探索鹰航空科技有限公司 | A kind of unmanned plane takes off and recycles institutional operation vehicle |
| CN113998137A (en) * | 2021-11-09 | 2022-02-01 | 任黎黎 | Cadastral survey unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115285370A (en) * | 2022-08-06 | 2022-11-04 | 中国人民解放军69246部队 | Wheeled armored vehicle-mounted unmanned aerial vehicle system and linkage control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108557106B (en) | Unmanned aerial vehicle cluster transmission recovery unit with store and supply function | |
| US3520502A (en) | Cargo launching and recovery apparatus for aircraft | |
| CN109018349B (en) | Multi-rotor unmanned aerial vehicle system suitable for stable throwing under high-speed flight condition | |
| CN105292446B (en) | A kind of damping undercarriage of four-axle aircraft | |
| US7900866B2 (en) | System and methods for airborne launch and recovery of aircraft | |
| CN107117325B (en) | Unmanned aerial vehicle ground emission and recovery dolly | |
| CN109204860B (en) | Carrier-borne unmanned aerial vehicle launches/retrieves integrated device | |
| US20220041280A1 (en) | Amphibious Aerial Vehicle | |
| CN105667789A (en) | Universal type elastic potential energy mechanical catapult for single tandem wing unmanned aerial vehicle with rear propeller | |
| US11745868B2 (en) | Amphibious aerial vehicle | |
| CN108408076B (en) | Boost rocket fixing and guiding separating mechanism for unmanned aerial vehicle | |
| US20210362866A1 (en) | Unmanned Aerial Vehicle Power System for Minimizing Propulsion Failure | |
| US3003717A (en) | Flying landing platform | |
| US11572164B2 (en) | Method of flight control in a fixed-wing drone | |
| CN115837995B (en) | Unmanned aerial vehicle with telescopic wings | |
| CN112498727A (en) | Unmanned aerial vehicle boosting launcher | |
| CN114701642A (en) | Unmanned aerial vehicle and catapult thereof | |
| CN114684383A (en) | Bullet hanging vehicle and bullet transporting and hanging integrated bullet hanging equipment | |
| CN207670685U (en) | A kind of boarding bridge joint anticollision mechanism and the connecting bridge comprising the mechanism | |
| CN103963989B (en) | Portable folding type electromagnetic launch technology of unmanned aerial vehicle device | |
| CN116039991A (en) | Vehicle-mounted ejection unmanned aerial vehicle capable of accommodating straight barrel and transmitting | |
| CN113002757B (en) | Collapsible rotor unmanned aerial vehicle's independently expandes device | |
| CN110803292A (en) | Steel cable retaining mechanism | |
| CN115123467A (en) | Unmanned boat-mounted stable platform for taking off and landing of unmanned aerial vehicle | |
| CN113879519A (en) | Survey unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |