CN112693620A - Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle - Google Patents
Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle Download PDFInfo
- Publication number
- CN112693620A CN112693620A CN202110158434.4A CN202110158434A CN112693620A CN 112693620 A CN112693620 A CN 112693620A CN 202110158434 A CN202110158434 A CN 202110158434A CN 112693620 A CN112693620 A CN 112693620A
- Authority
- CN
- China
- Prior art keywords
- catapult
- unmanned aerial
- aerial vehicle
- wing unmanned
- flapping wing
- 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
- 230000008719 thickening Effects 0.000 claims description 16
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 description 16
- 230000008569 process Effects 0.000 description 12
- 238000005381 potential energy Methods 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses an catapult-assisted take-off device of a flapping wing unmanned aerial vehicle, wherein the lower end of the flapping wing unmanned aerial vehicle is provided with an catapult hook, the catapult hook defines a first through groove which is communicated in the left-right direction, and the catapult-assisted take-off device of the flapping wing unmanned aerial vehicle comprises a slide rail, a slide block, a spring and a cylinder; the sliding rail extends in the front-rear direction, and is provided with an initial position and a final position, and the final position is provided with a stop block; the sliding block can be arranged on the sliding rail along the sliding rail in a sliding way; the spring is arranged between the stop block and the sliding block, one end of the spring is connected with the stop block, and the other end of the spring is connected with the sliding block; the cylinder extends along left right direction, and the both ends of cylinder are fixed with the upper end of slider, and the capital between the both ends of cylinder is in unsettled state for the slider, and the capital is used for passing first logical groove to install flapping wing unmanned aerial vehicle on flapping wing unmanned aerial vehicle catapult-assisted take-off. The invention can effectively improve the takeoff speed and the flight stability of the flapping wing unmanned aerial vehicle, and has the advantages of large ejection power, high safety, simple structure and convenient disassembly.
Description
Technical Field
The invention relates to the technical field of flapping wing aircrafts, in particular to an catapult-assisted take-off device of a flapping wing unmanned aerial vehicle.
Background
The take-off mode of a flapping wing unmanned aerial vehicle is generally manual throwing take-off, and the specific process of manual throwing take-off is as follows: firstly, holding the flapping wing unmanned aerial vehicle in the hand of an operator to start flapping; then, pushing an accelerator to enable the flapping wing unmanned aerial vehicle to reach a certain flapping wing frequency; and finally, when the flapping wing unmanned aerial vehicle meets the takeoff flapping wing frequency, an operator manually throws the flapping wing unmanned aerial vehicle out horizontally to the right front side, and after the operator takes off the hand, the flapping wing unmanned aerial vehicle has a certain initial speed to finish the takeoff process.
However, the hand throwing and throwing take-off process has the following disadvantages: firstly, the speed of hand throwing, throwing and taking off is low: due to the fact that the force of people is limited, the take-off speed of the flapping wing unmanned aerial vehicle is limited due to manual throwing, the take-off process is dangerous, and when the take-off speed is insufficient, the flapping wing unmanned aerial vehicle cannot take off; second, artifical manual throwing flapping wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle take off the angle unstability, take off the hand in the twinkling of an eye to flapping wing unmanned aerial vehicle control than more difficult, because the angle of taking off is not good easily, lead to flapping wing unmanned aerial vehicle to take off the failure, fall to ground.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention aims to provide an ejection take-off device of the flapping wing unmanned aerial vehicle, which can effectively improve the take-off speed and flight stability of the flapping wing unmanned aerial vehicle, and has the advantages of large ejection power, high safety, simple structure and convenience in disassembly.
According to the catapult-assisted take-off device of the flapping wing unmanned aerial vehicle, the lower end of the flapping wing unmanned aerial vehicle is provided with the catapult hook, the catapult hook defines the first through groove which is communicated in the left-right direction, the front end of the first through groove is closed, the rear end of the first through groove is open, and the catapult-assisted take-off device of the flapping wing unmanned aerial vehicle comprises:
the sliding rail extends in the front-rear direction, and is provided with an initial position and a final position for catapult takeoff, and the final position is provided with a stop block;
the sliding block can be arranged on the sliding rail in a sliding mode along the sliding rail;
the spring is arranged between the stop block and the sliding block, one end of the spring is connected with the stop block, and the other end of the spring is connected with the sliding block;
the cylinder, the cylinder extends along left and right directions, the both ends of cylinder with the upper end of slider is fixed, the column section between the both ends of cylinder for the slider is in unsettled state, between the both ends of cylinder the column section is used for passing first logical groove, in order to with flapping wing unmanned aerial vehicle installs on the flapping wing unmanned aerial vehicle catapult-assisted take-off device.
The catapult-assisted take-off device of the flapping wing unmanned aerial vehicle provided by the embodiment of the invention has the working process that: an operator manually slides the sliding block to the initial position on the sliding rail along the sliding rail, the sliding block is fixedly locked at the initial position, then the catapult hook of the flapping wing unmanned aerial vehicle is hung on the cylinder, the cylinder section between the two ends of the cylinder passes through the first through groove, so that the flapping wing unmanned aerial vehicle is installed on the catapult take-off device of the flapping wing unmanned aerial vehicle, and at the moment, the spring is stretched and deformed to generate elastic potential energy; when triggering flapping wing unmanned aerial vehicle catapult-assisted take-off operation, under the pulling force effect of spring, the slider can be followed the slide rail by the initial position and slided to the terminal position with higher speed, therefore, flapping wing unmanned aerial vehicle's ejection hook produces inseparable cooperation with the column section of cylinder, thereby flapping wing unmanned aerial vehicle can be accelerated motion forward under the drive of slider, when the slider reachs the terminal position, it blocks the slider and continues to slide forward to block the piece, but flapping wing unmanned aerial vehicle still keeps high-speed motion, because the velocity of motion of ejection hook is greater than the velocity of motion of cylinder, the column section of cylinder can break away from in following first spout, flapping wing unmanned aerial vehicle's ejection hook breaks away from and continues the forward motion with flapping wing unmanned aerial vehicle catapult-assisted take-off device.
According to the catapult-assisted take-off device for the flapping wing unmanned aerial vehicle, the spring is arranged between the blocking block and the sliding block, the elastic potential of the spring is used as the power for catapult-assisted take-off of the flapping wing unmanned aerial vehicle, the catapult-assisted power is large, the device is suitable for catapult-assisted take-off of various flapping wing unmanned aerial vehicles, the initial take-off speed is high, and the operation safety is improved; in the catapult-assisted take-off process of the flapping wing unmanned aerial vehicle, the flapping wing unmanned aerial vehicle moves along the direction of the slide rail, so that the stable posture and stable flight direction of the flapping wing unmanned aerial vehicle in the catapult-assisted take-off process are ensured. In conclusion, the catapult-assisted take-off device of the flapping wing unmanned aerial vehicle can effectively improve the take-off speed and flight stability of the flapping wing unmanned aerial vehicle, and has the advantages of large catapult power, high safety, simple structure and convenience in disassembly.
According to one embodiment of the invention, the device further comprises a bolt; the sliding block is provided with a bolt through hole, the sliding rail is provided with a clamping groove at the starting position, and when the sliding block is at the starting position, the bolt can be inserted into the bolt through hole and the clamping groove in a pulling mode so as to lock the sliding block on the sliding rail.
According to a further embodiment of the present invention, the locking groove is located on the bottom wall of the sliding groove, and when the sliding block is located at the initial position, the through hole of the plug pin is opposite to the locking groove.
According to one embodiment of the invention, the sliding block comprises a sliding block body and a support, the support comprises a left support and a right support, the left support and the right support are oppositely arranged at intervals in the left-right direction, and the left support and the right support are both fixed with the upper end of the sliding block body; the left end of the column body is fixed with the left support, and the right end of the column body is fixed with the right support.
According to a further embodiment of the invention, the ejection hook comprises a front ejection hook and a rear ejection hook, the post comprises a front post and a rear post, the post section of the front post and the post section of the rear post are adapted to pass in the first through slot of the front ejection hook and the first through slot of the rear ejection hook, respectively.
According to a still further embodiment of the present invention, the first through groove is linear in the front-rear direction; the front column bodies are arranged in a plurality of order at intervals in the front-rear direction.
According to one embodiment of the invention, the ejection hook thickening piece is used for limiting a second through groove which penetrates in the left-right direction, the front end of the second through groove is closed, and the rear end of the second through groove is opened; the ejection hook thickening piece is fixed with the ejection hook, the second through groove is aligned with the first through groove in the left-right direction, and the column section of the column body is used for penetrating through the first through groove and the second through groove.
According to a further embodiment of the invention, the ejection hook thickening is distributed on both left and right sides of the ejection hook.
According to some embodiments of the invention, the sliding rail further comprises a front supporting rod, and the upper end of the front supporting rod is fixed with the front end of the sliding rail so as to support the front end of the sliding rail, so that the front end of the sliding rail is higher than the rear end of the sliding rail.
According to some embodiments of the invention, the sliding rail defines a sliding groove extending in the front-rear direction, the sliding groove is a dovetail groove or a T-shaped groove, and the lower end of the cross section of the sliding block is dovetail-shaped or T-shaped, so that the sliding block is matched with the sliding groove in a fitting manner.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic structural diagram of an catapult takeoff device of a flapping wing unmanned aerial vehicle in an embodiment of the invention.
Fig. 2 is an exploded view of an catapult takeoff device of a flapping wing unmanned aerial vehicle in an embodiment of the invention.
Fig. 3 is a schematic structural view of an assembly part of the flapping wing unmanned aerial vehicle catapult-assisted take-off device and the flapping wing unmanned aerial vehicle according to the embodiment of the invention.
Fig. 4 is an exploded view of an assembly part of the flapping wing unmanned aerial vehicle catapult take-off device and the flapping wing unmanned aerial vehicle according to the embodiment of the invention.
Fig. 5 is a schematic partial structural view of a slide rail of the catapult take-off device of the flapping wing unmanned aerial vehicle in the embodiment of the invention.
Fig. 6 is a schematic structural diagram of a slider body of the catapult take-off device of the flapping wing unmanned aerial vehicle in the embodiment of the invention.
Fig. 7 is a schematic structural diagram of a bolt of the catapult take-off device of the flapping wing unmanned aerial vehicle in the embodiment of the invention.
Reference numerals:
catapult-assisted take-off device 1000 for flapping wing unmanned aerial vehicle
Slider 2 slider body 21 latch through hole 211 support 22 left support 221 right support 222
Stop block 5
Bolt 6
Second through groove 71 of ejection hook thickening piece 7
Supporting front bar 8
First through groove 913 of front ejection hook 911 and rear ejection hook 912 of flapping wing unmanned aerial vehicle 9 ejection hook 91
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
An catapult-assisted take-off 1000 for an ornithopter according to an embodiment of the invention is described below with reference to fig. 1 to 7.
As shown in fig. 1 to 7, according to the catapult-assisted take-off device 1000 for the flapping wing unmanned aerial vehicle according to the embodiment of the invention, the lower end of the flapping wing unmanned aerial vehicle 9 is provided with the catapult hook 91, the catapult hook 91 defines a first through groove 913 which is through in the left-right direction, the front end of the first through groove 913 is closed, the rear end of the first through groove 913 is open, and the catapult-assisted take-off device 1000 for the flapping wing unmanned aerial vehicle comprises a slide rail 1, a slide block 2, a spring; the slide rail 1 extends in the front-rear direction, the slide rail 1 is provided with an ejection takeoff starting position 11 and an ejection takeoff ending position 12, and the ejection takeoff starting position 12 is provided with a stop block 5; the slide block 2 can be arranged on the slide rail 1 along the slide rail 1 in a sliding way; the spring 3 is arranged between the stop block 5 and the sliding block 2, one end of the spring 3 is connected with the stop block 5, and the other end of the spring 3 is connected with the sliding block 2; cylinder 4 extends along left right direction, and the both ends of cylinder 4 are fixed with the upper end of slider 2, and the capital between the both ends of cylinder 4 is in unsettled state for slider 2, and the capital between the both ends of cylinder 4 is used for passing first logical groove 913 to install flapping wing unmanned aerial vehicle 9 on flapping wing unmanned aerial vehicle catapult-assisted take-off 1000.
Specifically, the slide rail 1 can extend in the front-back direction with a high front and a low back, the slide rail 1 is provided with an initial position 11 and a final position 12 for catapult takeoff, and the final position 12 is provided with a stop block 5; the slide block 2 is slidably disposed on the slide rail 1 along the slide rail 1. It can be understood that by arranging the slide rail 1, when the flapping wing unmanned aerial vehicle 9 takes off in an ejection manner, the slide block 2 slides from the initial position 11 to the final position 12 along the slide rail 1, the flapping wing unmanned aerial vehicle 9 always moves along the slide rail 1, the attitude is stable, the flight direction is stable, and the safety of the flapping wing unmanned aerial vehicle 9 in the ejection manner is improved; the sliding rail 1 is arranged in the front-back direction in a high-back-low manner, so that the flapping wing unmanned aerial vehicle 9 has an initial elevation angle when being separated from the flapping wing unmanned aerial vehicle catapult take-off device 1000, and the take-off lift force of the flapping wing unmanned aerial vehicle 9 is ensured; by providing the stop 5 at the end position 12, the slide 2 is prevented from continuing to slide forward after reaching the end position 12, and the slide 2 is stopped.
The spring 3 is arranged between the stop block 5 and the sliding block 2, one end of the spring 3 is connected with the stop block 5, and the other end of the spring 3 is connected with the sliding block 2. It can be understood that when the spring 3 is in tensile deformation, the spring 3 can generate elastic potential energy which is used as power for catapult takeoff of the flapping wing unmanned aerial vehicle 9, the elastic potential energy of the spring 3 is large, the catapult weight range is large, and therefore the elastic potential energy generated by the spring 3 can be used as power for catapult takeoff of various flapping wing unmanned aerial vehicles 9.
Cylinder 4 extends along left right direction, and the both ends of cylinder 4 are fixed with the upper end of slider 2, and the capital between the both ends of cylinder 4 is in unsettled state for slider 2, and the capital between the both ends of cylinder 4 is used for passing first logical groove 913 to install flapping wing unmanned aerial vehicle 9 on flapping wing unmanned aerial vehicle catapult-assisted take-off 1000. It will be appreciated that, by passing the column section between the ends of the column 4 through the first through slots 913, the flapping wing unmanned aerial vehicle 9 can be conveniently hung on the cylinder 4, the two ends of the cylinder 4 are fixed with the upper end of the sliding block 2, so that the flapping wing unmanned aerial vehicle 9 can move along with the sliding block 2, in the catapult takeoff process of the flapping wing unmanned aerial vehicle 9, when the column 4 moves forwards, the column section passes through the first through groove 913 and abuts against the front end of the first through groove 913 so as to drive the flapping wing unmanned aerial vehicle 9 to move forwards, when the slide block 2 reaches the end position 12, the blocking block 5 blocks the slide block 2 from continuing to slide forwards, but the flapping wing unmanned aerial vehicle 9 still keeps moving at high speed, because the moving speed of the ejection hook 91 is greater than that of the cylinder 4, the cylinder section of the cylinder 4 can be separated from the rear end of the first sliding groove 14, and the ejection hook 91 of the flapping wing unmanned aerial vehicle 9 is separated from the cylinder 4 and continues to move forwards, so that the ejection takeoff of the flapping wing unmanned aerial vehicle 9 is completed.
The catapult-assisted take-off device 1000 for the flapping wing unmanned aerial vehicle according to the embodiment of the invention has the working process that: an operator manually slides the sliding block 2 to the initial position 11 on the sliding rail 1 along the sliding rail 1, the sliding block 2 is fixedly locked at the initial position 11, then the ejection hook 91 of the flapping wing unmanned aerial vehicle 9 is hung on the column body 4, the column section between the two ends of the column body 4 passes through the first through groove 913, so that the flapping wing unmanned aerial vehicle 9 is installed on the ejection take-off device 1000 of the flapping wing unmanned aerial vehicle, and at the moment, the spring 3 is stretched and deformed to generate elastic potential energy; when triggering flapping wing unmanned aerial vehicle 9 and launching the operation, under the pulling force effect of spring 3, slider 2 can be by initial position 11 along slide rail 1 to the accelerated sliding of final position 12, therefore, flapping wing unmanned aerial vehicle 9's ejection hook 91 produces inseparable cooperation with the column segment of cylinder 4, thereby flapping wing unmanned aerial vehicle 9 can forward accelerated motion under the drive of slider 2, when slider 2 reachs final position 12, block piece 5 and block slider 2 and continue to slide forward, but flapping wing unmanned aerial vehicle 9 still keeps high-speed motion, because the velocity of motion of ejection hook 91 is greater than the velocity of motion of cylinder 4, the column segment of cylinder 4 can break away from in first spout 14, the ejection hook 91 of flapping wing unmanned aerial vehicle 9 breaks away from and continues forward motion with flapping wing unmanned aerial vehicle launching device 1000, thereby take off and accomplish flapping wing unmanned aerial vehicle 9.
According to the catapult-assisted take-off device 1000 for the flapping wing unmanned aerial vehicle, the spring 3 is arranged between the blocking block 5 and the sliding block 2, the elastic potential of the spring 3 is used as the power for catapult-assisted take-off of the flapping wing unmanned aerial vehicle 9, the catapult-assisted power is high, the device is suitable for catapult-assisted take-off of various flapping wing unmanned aerial vehicles 9, the initial take-off speed is high, and the operation safety is improved; in the catapult-assisted take-off process of the flapping wing unmanned aerial vehicle 9, the flapping wing unmanned aerial vehicle 9 moves along the direction of the slide rail 1, so that the stable posture and stable flight direction of the flapping wing unmanned aerial vehicle 9 in the catapult-assisted take-off process are ensured. In summary, the catapult-assisted take-off device 1000 for the flapping wing unmanned aerial vehicle has the advantages of large catapult power, high safety, capability of effectively improving the take-off speed and flight stability of the flapping wing unmanned aerial vehicle 9, simple structure and convenience in disassembly.
As shown in fig. 2 and 7, according to an embodiment of the present invention, further includes a latch 6; the slide block 2 is provided with a bolt through hole 211, the slide rail 1 is provided with a clamping groove 13 at the starting position 11, and when the slide block 2 is at the starting position 11, the bolt 6 can be inserted into the bolt through hole 211 and the clamping groove 13 in a pulling way so as to lock the slide block 2 on the slide rail 1. It can be understood that, through the manual slider 2 that draws to initial position 11 of operating personnel, when the bolt is perforated 211 and draw-in groove 13 and aligns, insert bolt 6 in the bolt is perforated 211 and draw-in groove 13 to conveniently fix slider 2 at initial position 11, later install flapping wing unmanned aerial vehicle 9 on flapping wing unmanned aerial vehicle catapult-assisted take-off 1000, through extracting bolt 6, can trigger flapping wing unmanned aerial vehicle 9 and catapult and take off, simple structure is reasonable, convenient operation.
As shown in fig. 5, according to a further embodiment of the present invention, the locking slot 13 is located on the bottom wall of the sliding slot 14, and when the sliding block 2 is at the starting position 11, the pin through hole 211 is opposite to the locking slot 13, so that the pin 6 can be easily inserted into the pin through hole 211 and the locking slot 13 to fix the sliding block 2 at the starting position 11 of the sliding rail 1.
As shown in fig. 2 to 4, according to one embodiment of the present invention, the slider 2 includes a slider body 21 and a holder 22, the holder 22 includes a left holder 221 and a right holder 222, the left holder 221 and the right holder 222 are oppositely disposed at a spacing in the left-right direction, and both the left holder 221 and the right holder 222 are fixed to the upper end of the slider body 21; the left end of the column 4 is fixed to the left support 221, and the right end of the column 4 is fixed to the right support 222. It can be understood that, because the slider body 21 is high, through setting up left support 221 and right support 222, the cylinder 4 passes left support 221, first logical groove 913 and right support 222 in proper order, can install slider 2 and flapping wing unmanned aerial vehicle 9 steadily.
As shown in fig. 3 and 4, according to a further embodiment of the present invention, the ejection hook 91 comprises a front ejection hook 911 and a rear ejection hook 912, the column 4 comprises a front column 41 and a rear column 42, and a column section of the front column 41 and a column section of the rear column 42 are adapted to pass through the first through slot 913 of the front ejection hook 911 and the first through slot 913 of the rear ejection hook 912, respectively. Specifically, set up preceding ejection hook 911 and back ejection hook 912 at flapping wing unmanned aerial vehicle 9's lower extreme interval, the first logical groove 913 of preceding ejection hook 911 is passed to the column section between the both ends of preceding cylinder 41, the left end and the left support 221 of preceding cylinder 41 are fixed, the right-hand member and the right support 222 of preceding cylinder 41 are fixed, the first logical groove 913 of back ejection hook 912 is passed to the column section between the both ends of back cylinder 42, the left end 913 of back cylinder 42 is fixed with left support 221, the right-hand member and the right support 222 of back cylinder 42 are fixed, can install flapping wing unmanned aerial vehicle 9 on flapping wing unmanned aerial vehicle catapult-off device 1000 more steadily through preceding ejection hook 911 and back ejection hook 912.
As shown in fig. 4, according to still further embodiment of the present invention, the first through groove 913 is linear in the front-rear direction; the front cylinder 41 is plural, and the plural front cylinders 41 are arranged at intervals in the front-rear direction in series. It can be understood that the first through groove 913 of the front ejection hook 911 and the first through groove 913 of the rear ejection hook 912 are linear in the front-rear direction, so that when the flapping wing unmanned aerial vehicle 9 is ejected and takes off, the column section of the front column 41 can smoothly slide out of the first through groove 913 of the front ejection hook 911, the column section of the rear column 42 can smoothly slide out of the first through groove 913 of the rear ejection hook 912, and the attitude of the flapping wing unmanned aerial vehicle 9 is kept stable in the ejection process; the front column 41 has a plurality ofly, preferably, the front column 41 has two, back cylinder 42 has one, pass the first logical groove 913 of preceding ejection hook 911 through the column section between the both ends with two front column 41, the left end and the left support 221 of two front column 41 are fixed, the right-hand member and the right support 222 of two front column 41 are fixed, the column section between the both ends of back cylinder 42 passes the first logical groove 913 of back ejection hook 912, in order to install flapping wing unmanned aerial vehicle 9 on flapping wing unmanned aerial vehicle ejection take-off device 1000, the cooperation is stable, guarantee that flapping wing unmanned aerial vehicle 9 gesture is stable not rocked.
As shown in fig. 3 and 4, according to an embodiment of the present invention, the ejection hook thickening member 7 is further included, the ejection hook thickening member 7 defines a second through groove 71 penetrating in the left-right direction, a front end of the second through groove 71 is closed, and a rear end of the second through groove 71 is open; the ejection hook thickening member 7 is fixed to the ejection hook 91, the second through-groove 71 is aligned with the first through-groove 913 in the left-right direction, and the column section of the column 4 is adapted to pass through the first through-groove 913 and the second through-groove 71. It can be understood that, the flapping wing unmanned aerial vehicle 9 is installed on the catapult-assisted take-off device 1000 of the flapping wing unmanned aerial vehicle through the front cylinder 41 and the rear cylinder 42, because the front catapult hook 911 and the rear catapult hook 912 of the flapping wing unmanned aerial vehicle 9 are thinner, the flapping wing unmanned aerial vehicle 9 can generate larger shaking, by fixing the catapult hook thickening piece 7 on the side surfaces of the front catapult hook 911 and the rear catapult hook 912, for example, corresponding screw holes can be arranged on the catapult hook thickening piece 7, the front catapult hook 911 and the rear catapult hook 912, by passing through the screw holes on the catapult hook thickening piece 7, the front catapult hook 911 and the rear catapult hook 912 through bolts, the catapult hook thickening piece 7 can be conveniently fixed on the side surfaces of the front catapult hook 911 and the rear catapult hook 912, the second through groove 71 is aligned with the first through groove 913 in the left-right direction, the column section of the front cylinder 41 passes through the first through groove 913 of the front catapult hook 911 and the second through groove 71 of the second 71, can effectively increase the column section of cylinder 4 and flapping wing unmanned aerial vehicle 9's cooperation area, guarantee that flapping wing unmanned aerial vehicle 9 is in the gesture stability of launching the in-process.
According to a further embodiment of the invention, the ejection hook thickening 7 is distributed on both the left and right sides of the ejection hook 91. It can be understood that, through setting up ejection hook thickening piece 7 respectively at the left surface and the right flank of ejecting hook 91, the column segment of cylinder 4 is the same with flapping wing unmanned aerial vehicle 9 in the cooperation area of the left and right sides, can guarantee that flapping wing unmanned aerial vehicle 9 is stable at the gesture of ejecting the in-process, and is rational in infrastructure.
As shown in fig. 1 and 2, according to some embodiments of the present invention, a front support rod 8 is further included, and an upper end of the front support rod 8 is fixed to the front end of the slide rail 1 to support the front end of the slide rail 1, so that the front end of the slide rail 1 is higher than the rear end of the slide rail 1. It can be understood that, by arranging the supporting front rod 8, the front end of the slide rail 1 is higher than the rear end of the slide rail 1, so that the flapping wing unmanned aerial vehicle 9 has an initial elevation angle when separating from the catapult takeoff device 1000 of the flapping wing unmanned aerial vehicle, thereby ensuring the takeoff lift force of the flapping wing unmanned aerial vehicle 9, and preferably, the angle of the initial elevation angle is 10-20 °.
According to some embodiments of the present invention, the sliding rail 1 defines a sliding groove 14 extending in a front-rear direction, the sliding groove 14 is a dovetail groove or a T-shaped groove, and the lower end of the cross section of the sliding block 2 is dovetail-shaped or T-shaped, so that the sliding block 2 is fittingly matched with the sliding groove 14. It can be understood that, through set up spout 14 on slide rail 1, like this, at flapping wing unmanned aerial vehicle 9 launch the in-process, slider 2 slides along spout 14, and flapping wing unmanned aerial vehicle 9 launches along the direction of spout 14, guarantees the stability of the gesture stability and the flight direction of flapping wing unmanned aerial vehicle 9 launch the in-process, and the security is high.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. The utility model provides a flapping wing unmanned aerial vehicle catapult-assisted take-off device, its characterized in that, flapping wing unmanned aerial vehicle's lower extreme is equipped with the ejection hook, the ejection hook is injectd the first logical groove that link up in the left and right sides direction, the front end of first logical groove is sealed just the rear end of first logical groove is opened, flapping wing unmanned aerial vehicle catapult-assisted take-off device includes:
the sliding rail extends in the front-rear direction, and is provided with an initial position and a final position for catapult takeoff, and the final position is provided with a stop block;
the sliding block can be arranged on the sliding rail in a sliding mode along the sliding rail;
the spring is arranged between the stop block and the sliding block, one end of the spring is connected with the stop block, and the other end of the spring is connected with the sliding block;
the cylinder, the cylinder extends along left and right directions, the both ends of cylinder with the upper end of slider is fixed, the column section between the both ends of cylinder for the slider is in unsettled state, between the both ends of cylinder the column section is used for passing first logical groove, in order to with flapping wing unmanned aerial vehicle installs on the flapping wing unmanned aerial vehicle catapult-assisted take-off device.
2. The catapult-assisted take-off device for ornithopters as claimed in claim 1, further comprising a latch; the sliding block is provided with a bolt through hole, the sliding rail is provided with a clamping groove at the starting position, and when the sliding block is at the starting position, the bolt can be inserted into the bolt through hole and the clamping groove in a pulling mode so as to lock the sliding block on the sliding rail.
3. The catapult-assisted take-off device for ornithopters as claimed in claim 2, wherein said slot is located in a bottom wall of said chute, and said latch hole is aligned with said slot when said slider is in said home position.
4. The catapult-assisted take-off device of the ornithopter as claimed in claim 1, wherein the slider comprises a slider body and a support, the support comprises a left support and a right support, the left support and the right support are oppositely arranged in the left-right direction at intervals, and the left support and the right support are both fixed with the upper end of the slider body; the left end of the column body is fixed with the left support, and the right end of the column body is fixed with the right support.
5. The catapult-assisted take-off device for ornithopters as claimed in claim 4, wherein said catapult hook comprises a front catapult hook and a rear catapult hook, and said post comprises a front post and a rear post, said post segment of said front post and said post segment of said rear post being adapted to pass through said first through slot of said front catapult hook and said first through slot of said rear catapult hook, respectively.
6. The catapult-assisted take-off device for ornithopters as claimed in claim 5, wherein the first through slot is linear in the front-to-rear direction; the front column bodies are arranged in a plurality of order at intervals in the front-rear direction.
7. The catapult-assisted take-off device for the ornithopter as claimed in claim 1, further comprising a catapult hook thickening member defining a second through slot extending in the left-right direction, wherein the front end of the second through slot is closed and the rear end of the second through slot is open; the ejection hook thickening piece is fixed with the ejection hook, the second through groove is aligned with the first through groove in the left-right direction, and the column section of the column body is used for penetrating through the first through groove and the second through groove.
8. The catapult-assisted take-off device for ornithopters as claimed in claim 7, wherein said catapult hook thickening members are distributed on both left and right sides of said catapult hook.
9. The catapult-assisted take-off device for the ornithopter-based aircraft as claimed in any one of claims 1 to 8, further comprising a support front rod, wherein the upper end of the support front rod is fixed to the front end of the slide rail to support the front end of the slide rail so that the front end of the slide rail is higher than the rear end of the slide rail.
10. The catapult-assisted take-off device for the ornithopter-assisted unmanned aerial vehicle as claimed in any one of claims 1 to 8, wherein a sliding groove extending in the front-rear direction is defined on the sliding rail, the sliding groove is a dovetail groove or a T-shaped groove, and the lower end of the cross section of the sliding block is dovetail-shaped or T-shaped, so that the sliding block is matched with the sliding groove in a matching manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110158434.4A CN112693620A (en) | 2021-02-04 | 2021-02-04 | Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110158434.4A CN112693620A (en) | 2021-02-04 | 2021-02-04 | Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112693620A true CN112693620A (en) | 2021-04-23 |
Family
ID=75516571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110158434.4A Pending CN112693620A (en) | 2021-02-04 | 2021-02-04 | Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112693620A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115489749B (en) * | 2022-11-16 | 2023-03-24 | 成都航空职业技术学院 | Fixed wing unmanned aerial vehicle launches take-off and land integrated system |
-
2021
- 2021-02-04 CN CN202110158434.4A patent/CN112693620A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115489749B (en) * | 2022-11-16 | 2023-03-24 | 成都航空职业技术学院 | Fixed wing unmanned aerial vehicle launches take-off and land integrated system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108408076B (en) | Boost rocket fixing and guiding separating mechanism for unmanned aerial vehicle | |
| CN104401493A (en) | Cabin type guide rope locked aircraft carrier for releasing and recycling airborne aircraft | |
| CN201907656U (en) | Zero length launching device for pilotless planes | |
| CN209834038U (en) | Unmanned aerial vehicle launches automatic release mechanism | |
| CN112693620A (en) | Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle | |
| CN110395402B (en) | Low-disturbance unmanned aerial vehicle ejection frame separating mechanism and separating method | |
| CN109353537A (en) | Mechanism is let in a kind of locking of unmanned aerial vehicle ejecting fly away | |
| CN215514189U (en) | Catapult-assisted take-off device for flapping-wing unmanned aerial vehicle | |
| CN203623978U (en) | Unmanned aerial vehicle catapulting frame | |
| CN211810243U (en) | Air-drop unmanned aerial vehicle | |
| US4917526A (en) | Clevis assembly for hanging airborne stores | |
| DE102016014309A1 (en) | Throw-catch device for unmanned fixed-wing aircraft | |
| CN210707854U (en) | Novel wing connection structure | |
| US3006576A (en) | Airplane having two separable flyable sections | |
| WO2001085541A1 (en) | Aircraft and propulsion system for an aircraft, and operating method | |
| CN107444660B (en) | Opening mechanism and opening method for drag parachute cabin door of airplane | |
| CN205837216U (en) | A kind of light-duty stealthy electromagnetism unlocks drag parachute housing structure | |
| CN114013629B (en) | Passive wing extending structure | |
| CN109972945A (en) | A kind of anti-left-hand thread unmanned plane umbrella hatchcover unlocking mechanism of avoiding improper opening | |
| CN104354862A (en) | Flying aircraft carrier for air recovery of guide rope locking airborne equipment | |
| DE102005034975A1 (en) | Drive for e.g. power glider, has carrier, where jet engine is extended and retracted over carrier by single hand movement, carrier is arranged over central point and hand lever is supported on base plate | |
| US20220250733A1 (en) | Systems and methods for indicating release of a canopy an aircraft | |
| CN211766366U (en) | A launch release for unmanned aerial vehicle launches | |
| CN116588371B (en) | Patrol aircraft separation guiding device and patrol aircraft assembly | |
| CN110758748B (en) | Helicopter and ejection escape buffering device |
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 |