CN111216916A - Unmanned aerial vehicle launching cradle - Google Patents
Unmanned aerial vehicle launching cradle Download PDFInfo
- Publication number
- CN111216916A CN111216916A CN201911229095.3A CN201911229095A CN111216916A CN 111216916 A CN111216916 A CN 111216916A CN 201911229095 A CN201911229095 A CN 201911229095A CN 111216916 A CN111216916 A CN 111216916A
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- pulley
- locking
- track
- 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
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—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The invention provides an unmanned aerial vehicle ejection rack, which comprises a track, a pulley and an elastic piece, wherein the track is arranged on the track; the pulley is arranged on the track; one end of the elastic part is connected with the track, and the other end of the elastic part is connected with the pulley; wherein the rail is provided with a locking member for locking the trolley. Compared with the prior art, the invention omits a speed reducer in front of the movement of the pulley, thereby simplifying the overall structure of the unmanned aerial vehicle ejection rack, simplifying the production process of the unmanned aerial vehicle ejection rack, simplifying the use method of the unmanned aerial vehicle ejection rack, greatly reducing the generation and maintenance cost, greatly reducing the selling price of the unmanned aerial vehicle ejection rack, and simplifying the overall structure of the unmanned aerial vehicle ejection rack and the use method of the unmanned aerial vehicle to ensure that consumers can carry and use more conveniently.
Description
Technical Field
The invention relates to the field of ejection devices, in particular to an unmanned aerial vehicle ejection rack.
Background
A transmitting system for unmanned aerial vehicle takes off generally is provided with slider, and slider drives the unmanned aerial vehicle motion through high-speed motion, and after slider drove the motion of unmanned aerial vehicle and produces great kinetic energy, slider need slow down to make unmanned aerial vehicle break away from slider and take off. In the prior art, a speed reducing device such as a spring is generally arranged in front of a sliding device moving at a high speed, the sliding device is decelerated by striking the speed reducing device, but the sliding device has high noise when striking the speed reducing device and is easy to damage.
Disclosure of Invention
Based on the problems of the prior art, the invention provides an unmanned aerial vehicle ejection rack.
The invention provides an unmanned aerial vehicle ejection rack, which comprises a track, a pulley and an elastic piece, wherein the track is arranged on the pulley; the pulley is arranged on the track; one end of the elastic part is connected with the track, and the other end of the elastic part is connected with the pulley; wherein the content of the first and second substances,
the track is provided with a locking piece for locking the pulley;
when the unmanned aerial vehicle is ejected, the pulley is locked through the locking piece, so that the elastic piece is in a stretched energy storage state under the pulling of the pulley;
after the unmanned aerial vehicle is positioned on the pulley, the locking piece releases the pulley, so that the elastic piece contracts to release energy to pull the pulley, and the pulley moves on the track;
when the tackle moves to a preset position, the elastic piece is stretched again to decelerate the tackle, so that the unmanned aerial vehicle continuously moves forwards under the action of inertia to separate from the tackle to finish ejection.
Further, the tackle comprises a sliding plate, a bracket and a locking lock; the sliding plate is arranged on the track in a sliding manner; the bracket is fixedly arranged on the sliding plate and used for supporting the unmanned aerial vehicle; the locking lock is rotatably arranged on the sliding plate and used for supporting the unmanned aerial vehicle; wherein the content of the first and second substances,
one end of the elastic piece is connected with the track, and the other end of the elastic piece is connected with a stop lock of the pulley;
when the pulley moves to a preset position and the elastic piece is stretched again, the elastic piece pulls the locking lock, so that the locking lock pushes the unmanned aerial vehicle in the direction of the unmanned aerial vehicle movement through rotation.
Further, the locking lock comprises a support section and a connecting section; the supporting section is connected with the connecting section in a bending mode, so that a bending part is formed at the connecting position of the supporting section and the connecting section; the locking lock is rotatably arranged on the sliding plate through the bending part; wherein the content of the first and second substances,
the support section is used for supporting unmanned aerial vehicle, the linkage segment is used for connecting the elastic component.
Further, the support is arranged on the front side of the sliding plate and used for supporting the head of the unmanned aerial vehicle; the locking lock is arranged on the rear side of the sliding plate and used for supporting the tail of the unmanned aerial vehicle.
Furthermore, the connecting section is provided with a U-shaped notch; a connecting rod is arranged in the notch; the elastic piece is connected to the connecting rod.
Further, the pulley also comprises a rotating shaft; the sliding plate is provided with a first abdicating hole and a mounting block; the mounting block is arranged around the first abdicating hole; the bending part is rotatably arranged on the mounting block through the rotating shaft; wherein the content of the first and second substances,
when the locking lock rotates, the connecting section of the locking lock can move in the first yielding hole, and the connecting section can abut against the hole wall of the first yielding hole or the mounting block.
Further, the pulley still includes a plurality of wheels, a plurality of wheels set up on the slide, and the slide passes through the wheel slip sets up on the track.
Further, the tackle is provided with a locking plate, the locking plate is provided with a locking hole, and the locking piece is matched with the locking hole to lock the tackle.
Further, the elastic part is an elastic rope.
Further, the pulley is provided with a pulley, one end of the elastic part is connected with the track, and the other end of the elastic part bypasses the pulley to be connected with the pulley.
The invention has the beneficial effects that: after the pulley of unmanned aerial vehicle ejection rack moved preset position, the elastic component was stretched again, and at this moment, the kinetic energy of pulley is absorbed by the elastic component and makes speed descend to the stop condition. Compared with the prior art, the invention omits a speed reducer in front of the movement of the pulley, thereby simplifying the overall structure of the unmanned aerial vehicle ejection rack, simplifying the production process of the unmanned aerial vehicle ejection rack, simplifying the use method of the unmanned aerial vehicle ejection rack, avoiding the condition that the pulley impacts the speed reducer to generate noise or damage, and greatly reducing the generation and maintenance cost; due to the fact that the generation cost and the maintenance cost are greatly reduced, the selling price of the unmanned aerial vehicle ejection rack can be greatly reduced, in addition, the overall structure of the unmanned aerial vehicle ejection rack and the using method of the unmanned aerial vehicle are simplified, and the unmanned aerial vehicle ejection rack is more convenient to carry and use for consumers. In conclusion, the unmanned aerial vehicle ejector rack has great commercial advantages.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle ejector rack provided by an embodiment of the invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
fig. 3 is a diagram of an operating state of an unmanned aerial vehicle ejector rack provided by an embodiment of the present invention, where the carrier is in a locked state, and the unmanned aerial vehicle engaged with the carrier is also shown in the diagram;
fig. 4 is another diagram of an operating state of an unmanned aerial vehicle ejection rack provided by an embodiment of the invention, where the operating state is a state where the trolley ejects an unmanned aerial vehicle, and the unmanned aerial vehicle engaged with the trolley is also shown in the diagram;
fig. 5 is a diagram of another working state of the unmanned aerial vehicle ejector rack provided by an embodiment of the invention, wherein the working state is a state when the trolley is locked, and the unmanned aerial vehicle matched with the trolley is further shown in the diagram.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all directional indicators (such as up, down, left, right, front, back, horizontal, vertical, etc.) in the embodiments of the present invention are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly, the "connection" may be a direct connection or an indirect connection, and the setting, and the disposing may be a direct setting or an indirect setting.
Moreover, the descriptions relating to the first, second, etc. in the present invention are for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit ly indicating the number of technical features indicated. Thus, the first and second features defined may explicitly or implicitly include at least one of the features. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle ejector provided in an embodiment of the present invention, where the unmanned aerial vehicle ejector includes a rail 20, a pulley 30, and an elastic member 40; the trolley 30 is arranged on the track 20; one end of the elastic element 40 is connected with the track 20, and the other end is connected with the pulley 30; wherein the rail 20 is provided with a locking member 21 for locking the trolley 30; when the unmanned aerial vehicle 10 is ejected, the pulley 30 is locked through the locking piece 21, so that the elastic piece 40 is in a stretched energy storage state under the pulling of the pulley 30; after the unmanned aerial vehicle 10 is positioned on the pulley 30, the locking piece 21 releases the pulley 30, so that the elastic piece 40 is contracted to release energy to pull the pulley 30, and further the pulley 30 moves on the track 20; when the tackle 30 moves to the preset position, the elastic member 40 is stretched again to decelerate the tackle 30, so that the unmanned aerial vehicle 10 continues to move forward under the inertia effect to separate from the tackle 30 and finish ejection.
In this embodiment, after the pulley 30 of the unmanned aerial vehicle ejection rack moves to the preset position, the elastic member 40 is stretched again, and at this time, the kinetic energy of the pulley 30 is absorbed by the elastic member 40, so that the speed is reduced to the stop state. Compared with the prior art, the invention omits a speed reducer before the pulley 30 moves, thereby simplifying the overall structure of the unmanned aerial vehicle ejection rack, simplifying the production process of the unmanned aerial vehicle ejection rack, simplifying the use method of the unmanned aerial vehicle ejection rack, avoiding the condition that the pulley 30 impacts the speed reducer to generate noise or damage, and greatly reducing the generation and maintenance cost; because greatly reduced generation and cost of maintenance for the selling price of unmanned aerial vehicle ejector rack can reduce by a wide margin, in addition, has simplified the overall structure of unmanned aerial vehicle ejector rack and unmanned aerial vehicle 10's application method, makes the consumer carry and use more convenient. In conclusion, the unmanned aerial vehicle ejector rack has great commercial advantages.
In an alternative embodiment, such as the present embodiment, shown in FIG. 1, the sled 30 includes a sled 31, a carriage 32, and a stop lock 33; the sliding plate 31 is arranged on the track 20 in a sliding manner; the bracket 32 is fixedly arranged on the sliding plate 31 and used for supporting the unmanned aerial vehicle 10; the locking lock 33 is rotatably arranged on the sliding plate 31 and used for supporting the unmanned aerial vehicle 10; wherein, one end of the elastic element 40 is connected with the track 20, and the other end is connected with the stop lock 33 of the pulley 30; when the coaster 30 moves to the preset position, when the elastic component 40 is stretched again, the elastic component 40 pulls the locking lock 33, makes the locking lock 33 push the unmanned aerial vehicle 10 through the direction of turning to the unmanned aerial vehicle 10 motion, makes the kinetic energy of unmanned aerial vehicle 10 bigger, takes off more easily.
In an alternative embodiment, such as the present embodiment, shown in FIG. 2, the detent lock 33 includes a support section 332 and a connecting section 331; the supporting section 332 bends the connecting section 331, so that a bent part is formed at the joint of the supporting section 332 and the connecting section 331; the stop lock 33 is rotatably arranged on the sliding plate 31 through a bending part; wherein, support section 332 is used for supporting unmanned aerial vehicle 10, and connection section 331 is used for connecting elastic component 40.
In an alternative embodiment, such as that shown in fig. 3 or 4, a bracket 32 is provided on the front side of the sled 31 to support the head of the drone 10, and a stop lock 33 is provided on the rear side of the sled 31 to support the tail of the drone 10. Preferably, the height of the bracket 32 is higher than that of the latch 33.
In an alternative embodiment, such as the present embodiment, the connecting section 331 is provided with a "U" shaped notch 334; a connecting rod 333 is arranged in the notch 334; the elastic member 40 is connected to the link 333.
Further, the pulley 30 further includes a rotating shaft 336; the sliding plate 31 is provided with a first abdicating hole 311 and a mounting block 335; the mounting block 335 is disposed around the first yielding hole 311; the bending part is rotatably arranged on the mounting block 335 through a rotating shaft 336; when the locking lock 33 rotates, the connecting section 331 of the locking lock 33 can move in the first yielding hole 311, and the connecting section 331 can abut against the hole wall of the first yielding hole 311 or abut against the mounting block 335.
In this embodiment, the connecting rod 333 is connected to the elastic member 40, so as to facilitate installation of the elastic member 40 and prevent the connecting section 331 from affecting the expansion and contraction of the elastic member 40 when rotating. The installation of the locking lock 33 by the installation block 335 and the first relief hole 311 can make the installation of the locking lock 33 more convenient and the rotation of the locking lock 33 more flexible. When the locking lock 33 rotates to a certain position and pushes out the unmanned aerial vehicle 10, the locking lock 33 can abut against the hole wall of the first yielding hole 311 or the mounting block 335, so that the locking lock 33 is prevented from rotating too much to affect the extension of the elastic part 40, and the support section 332 is prevented from impacting the track 20.
In an alternative embodiment, such as the present embodiment, as shown in fig. 3 or fig. 4, the trolley 30 further includes a plurality of wheels 35, the plurality of wheels 35 are disposed on the sliding plate 31, and the sliding plate 31 is slidably disposed on the rail 20 via the wheels 35. Further, as shown in fig. 5, the trolley 30 further includes a limiting plate 301, and the limiting plate 301 is disposed on the rail 20 and is used for cooperating with the rail 20 and the wheel 35 to limit the movement of the trolley 30 on the rail 20.
In an alternative embodiment, such as that shown in fig. 1, the carriage 30 is provided with a locking plate 34, the locking plate 34 is provided with a locking hole, and the locking member 21 is engaged with the locking hole to lock the carriage 30. Further, the locking member 21 is a locking hook, a root portion of which is rotatably provided on the rail 20, and a hook portion for hooking a locking hole to lock the tackle 30.
In an alternative embodiment, such as the present embodiment, the elastic member 40 is a rubber string, which will be more elastic. In other embodiments, the elastic member 40 may be other elastic rope, which can generate enough kinetic energy for the pulley 30 to take off.
In an alternative embodiment, for example, as shown in fig. 3 or fig. 4, the pulley 30 is provided with the pulley 22, one end of the elastic member 40 is connected to the rail 20, and the other end of the elastic member 40 passes around the pulley 22 to be connected to the pulley 30, so that friction on the elastic member 40 is reduced through the pulley 22, the service life of the elastic member 40 is prolonged, resistance of the pulley 30 during movement is smaller and more flexible, and the experience effect of a consumer is greatly increased.
In an alternative embodiment, such as the present embodiment, as shown in fig. 1 to 4, the locking member 21 is provided on the rear side of the rail 20; the pulley 22 is disposed within the rail 20 near the front side of the rail 20; a second abdicating hole 23 is arranged at the upper side of the track 20; the trolley 30 is arranged on the upper side of the track 20 through wheels 35; one end of the elastic member 40 is connected to the rail 20, and the end of the elastic member 40 is located behind and below the pulley 22; the other end of the elastic member 40 passes through the second yielding hole 23, the space between the sliding plate 31 and the rail 20, and the first yielding hole 311 after passing around the groove of the pulley 22, and then is connected with the connecting section 331 of the locking latch 33. When the unmanned aerial vehicle 10 is ejected, the pulley 30 is pulled to move the pulley 30 to the rear side of the track 20 against the elastic force of the elastic member 40 and to be matched with the locking member 21, at this time, the pulley 22 supports the elastic member 40 to enable the elastic member 40 to be in an energy storage state, the supporting section 332 of the retaining lock 33 is pulled to be in a vertical state, and the notch 334 of the retaining lock 33 faces to the front side of the track 20; supporting and positioning the drone 10 on the cradle 32 and the support section 332 of the stop lock 33; poking the locking piece 21 and letting the locking piece 21 release the pulley 30, the pulley 30 moves at a high speed under the pulling of the elastic piece 40, drive the unmanned aerial vehicle 10 to also move at a high speed, the elastic piece 40 is stretched again after the pulley 30 moves to the preset position and pulls the linkage segment 331 of the stop lock 33, make the pulley 30 start decelerating, and the speed drops to zero at a high speed, wherein, when the elastic piece 40 pulls the linkage segment 331 of the stop lock 33, the linkage segment 331 rotates to a certain position around the bend and then abuts against the mounting block 335 or the hole wall of the first abdicating hole 311, the support segment 332 also rotates synchronously along with the linkage segment 331 and pushes the unmanned aerial vehicle 10. In the present embodiment, the preset position is determined according to the length of the elastic member 40.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle ejection rack is characterized by comprising a rail, a pulley and an elastic piece; the pulley is arranged on the track; one end of the elastic part is connected with the track, and the other end of the elastic part is connected with the pulley; wherein the content of the first and second substances,
the track is provided with a locking piece for locking the pulley;
when the unmanned aerial vehicle is ejected, the pulley is locked through the locking piece, so that the elastic piece is in a stretched energy storage state under the pulling of the pulley;
after the unmanned aerial vehicle is positioned on the pulley, the locking piece releases the pulley, so that the elastic piece contracts to release energy to pull the pulley, and the pulley moves on the track;
when the tackle moves to a preset position, the elastic piece is stretched again to decelerate the tackle, so that the unmanned aerial vehicle continuously moves forwards under the action of inertia to separate from the tackle to finish ejection.
2. The unmanned aerial vehicle ejector rack of claim 1, wherein the sled comprises a sled, a cradle, and a latch; the sliding plate is arranged on the track in a sliding manner; the bracket is fixedly arranged on the sliding plate and used for supporting the unmanned aerial vehicle; the locking lock is rotatably arranged on the sliding plate and used for supporting the unmanned aerial vehicle; wherein the content of the first and second substances,
one end of the elastic piece is connected with the track, and the other end of the elastic piece is connected with a stop lock of the pulley;
when the pulley moves to a preset position and the elastic piece is stretched again, the elastic piece pulls the locking lock, so that the locking lock pushes the unmanned aerial vehicle in the direction of the unmanned aerial vehicle movement through rotation.
3. The unmanned aerial vehicle ejector cartridge of claim 2, wherein said latch lock includes a support section and a connecting section; the supporting section is connected with the connecting section in a bending mode, so that a bending part is formed at the connecting position of the supporting section and the connecting section; the locking lock is rotatably arranged on the sliding plate through the bending part; wherein the content of the first and second substances,
the support section is used for supporting unmanned aerial vehicle, the linkage segment is used for connecting the elastic component.
4. The unmanned aerial vehicle ejector rack of claim 2, wherein said carriage is disposed on a front side of said sled for supporting a head of said unmanned aerial vehicle; the locking lock is arranged on the rear side of the sliding plate and used for supporting the tail of the unmanned aerial vehicle.
5. The unmanned aerial vehicle ejector rack of claim 3, wherein said connecting section is provided with a "U" shaped notch; a connecting rod is arranged in the notch; the elastic piece is connected to the connecting rod.
6. The unmanned aerial vehicle ejector rack of claim 3, wherein the sled further comprises a shaft; the sliding plate is provided with a first abdicating hole and a mounting block; the mounting block is arranged around the first abdicating hole; the bending part is rotatably arranged on the mounting block through the rotating shaft; wherein the content of the first and second substances,
when the locking lock rotates, the connecting section of the locking lock can move in the first yielding hole, and the connecting section can abut against the hole wall of the first yielding hole or the mounting block.
7. The unmanned aerial vehicle ejector cartridge of claim 6, wherein the sled further comprises a plurality of wheels, the plurality of wheels being disposed on the sled, and the sled being slidably disposed on the track via the wheels.
8. The unmanned aerial vehicle ejector cartridge of claim 1, wherein said carriage is provided with a locking plate, said locking plate being provided with an aperture, said locking member engaging said aperture to lock said carriage.
9. The unmanned aerial vehicle ejector cartridge of claim 1, wherein the resilient member is a rubber cord.
10. The unmanned aerial vehicle ejector cartridge of claim 1, wherein the carriage is provided with a pulley, and the elastic member is connected to the rail at one end and connected to the carriage at the other end by passing around the pulley.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911229095.3A CN111216916A (en) | 2019-12-04 | 2019-12-04 | Unmanned aerial vehicle launching cradle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911229095.3A CN111216916A (en) | 2019-12-04 | 2019-12-04 | Unmanned aerial vehicle launching cradle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111216916A true CN111216916A (en) | 2020-06-02 |
Family
ID=70830724
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911229095.3A Pending CN111216916A (en) | 2019-12-04 | 2019-12-04 | Unmanned aerial vehicle launching cradle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111216916A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4238093A (en) * | 1978-12-21 | 1980-12-09 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft launcher |
| US4411248A (en) * | 1981-11-27 | 1983-10-25 | Gilbert Kivenson | Catapult construction |
| FR2869017A1 (en) * | 2004-04-19 | 2005-10-21 | Jean Marc Mouligne | Catapult for ejecting parachutist, has double pulley block that supports counterweight, where parachutist is catapulted in air, when catapult is released and counterweight is dropped |
| CN101096224A (en) * | 2006-06-29 | 2008-01-02 | 珠海星宇模型实业有限公司 | Locking mechanism applied for unmanned aerial vehicle ejecting system and unmanned aerial vehicle locking method |
| US20100096496A1 (en) * | 2008-10-20 | 2010-04-22 | Aai Corporation | Sliding frame aircraft launcher and related method |
| CN203064205U (en) * | 2013-02-28 | 2013-07-17 | 杜普利 | Unmanned aerial vehicle ejector |
| CN104554814A (en) * | 2014-12-24 | 2015-04-29 | 南京航空航天大学 | Quickly and integrally folding type rubber band ejector |
| CN105460230A (en) * | 2015-12-11 | 2016-04-06 | 陕西飞机工业（集团）有限公司 | Pneumatic catapult-assisted take-off device and method used for unmanned plane |
| CN105711851A (en) * | 2016-01-25 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Electric and light-weight catapult with multiple strands of rubber strings for small unmanned aerial vehicle |
| CN108313324A (en) * | 2017-12-22 | 2018-07-24 | 成都才智圣有科技有限责任公司 | A kind of small drone take-off launch frame |
-
2019
- 2019-12-04 CN CN201911229095.3A patent/CN111216916A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4238093A (en) * | 1978-12-21 | 1980-12-09 | The United States Of America As Represented By The Secretary Of The Navy | Aircraft launcher |
| US4411248A (en) * | 1981-11-27 | 1983-10-25 | Gilbert Kivenson | Catapult construction |
| FR2869017A1 (en) * | 2004-04-19 | 2005-10-21 | Jean Marc Mouligne | Catapult for ejecting parachutist, has double pulley block that supports counterweight, where parachutist is catapulted in air, when catapult is released and counterweight is dropped |
| CN101096224A (en) * | 2006-06-29 | 2008-01-02 | 珠海星宇模型实业有限公司 | Locking mechanism applied for unmanned aerial vehicle ejecting system and unmanned aerial vehicle locking method |
| US20100096496A1 (en) * | 2008-10-20 | 2010-04-22 | Aai Corporation | Sliding frame aircraft launcher and related method |
| CN203064205U (en) * | 2013-02-28 | 2013-07-17 | 杜普利 | Unmanned aerial vehicle ejector |
| CN104554814A (en) * | 2014-12-24 | 2015-04-29 | 南京航空航天大学 | Quickly and integrally folding type rubber band ejector |
| CN105460230A (en) * | 2015-12-11 | 2016-04-06 | 陕西飞机工业（集团）有限公司 | Pneumatic catapult-assisted take-off device and method used for unmanned plane |
| CN105711851A (en) * | 2016-01-25 | 2016-06-29 | 中国人民解放军国防科学技术大学 | Electric and light-weight catapult with multiple strands of rubber strings for small unmanned aerial vehicle |
| CN108313324A (en) * | 2017-12-22 | 2018-07-24 | 成都才智圣有科技有限责任公司 | A kind of small drone take-off launch frame |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108557106B (en) | Unmanned aerial vehicle cluster transmission recovery unit with store and supply function | |
| CN101367438B (en) | Takeoff ejecting system of self-service flying platform | |
| CN106114890B (en) | A kind of small drone catapult-launching gear and unmanned plane takeoff method | |
| CN108082522B (en) | Unmanned aerial vehicle launching device and method | |
| CN101081639A (en) | Ejecting system applied for unmanned aerial plane launching system | |
| CN107503301A (en) | A kind of road cone of automatic moving | |
| CN111216916A (en) | Unmanned aerial vehicle launching cradle | |
| CN106586761B (en) | Based on hydromechanical braking control system | |
| CN115535510A (en) | Logistics storage conveyer | |
| CN201317464Y (en) | Unmanned flying platform takeoff ramping device | |
| CN114629071B (en) | Cable conveying rack convenient to install and capable of achieving cable shaking buffering effect and used for electric pole | |
| CN109649672B (en) | Fixed wing unmanned aerial vehicle equipment of taking off | |
| JPH09133604A (en) | Traction dolly for collision test of vehicle | |
| CN207259990U (en) | A kind of road cone of automatic moving | |
| CN114934701A (en) | Device for taking and placing vehicle carrying plate | |
| CN210364436U (en) | Drop-out restraining device for launch vehicle filling connector | |
| CN213801642U (en) | Rack-rail type cable dragging device | |
| CN114132533B (en) | Connector forced disengaging mechanism and method with inconsistent disengaging and unwinding directions | |
| CN210698752U (en) | Triggering type anti-falling device | |
| CN211122590U (en) | Pipeline detection device | |
| CN216424776U (en) | Launcher for unmanned aerial vehicle detection | |
| CN108891394B (en) | Brake pedal connecting pin disengaging mechanism, brake pedal device and vehicle | |
| CN210822814U (en) | Unmanned aerial vehicle platform launching ejection system | |
| CN218493259U (en) | Stop mechanism for longitudinally moving vehicle carrying plate from front to back | |
| CN211003271U (en) | Instrument panel holding tool conveying system |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20200602 |
|
| WD01 | Invention patent application deemed withdrawn after publication |