CN106043731A - Improved aircraft launching cradle - Google Patents
Improved aircraft launching cradle Download PDFInfo
- Publication number
- CN106043731A CN106043731A CN201610471296.4A CN201610471296A CN106043731A CN 106043731 A CN106043731 A CN 106043731A CN 201610471296 A CN201610471296 A CN 201610471296A CN 106043731 A CN106043731 A CN 106043731A
- Authority
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- China
- Prior art keywords
- sliding panel
- support beam
- hole
- support
- main shaft
- 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.)
- Granted
Links
- 230000001105 regulatory effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 4
- 238000007689 inspection Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/70—Launching or landing using catapults, tracks or rails
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses an improved aircraft launching cradle. Movable components at the upper ends of front supporting arms are adjusted, and the distance between the two front supporting arms is adjusted, so that the improved aircraft launching cradle adapts to the supporting width of an aircraft; and the front and back position of a rear supporting seat is adjusted, so that the improved aircraft launching cradle adapts to the position of a rear supporting point used for launching the aircraft. The height of the rear supporting seat is adjusted, so that the improved aircraft launching cradle adapts to the launching angle required in the launching process of the aircraft. The position of a rocket baffle is adjusted, so that the improved aircraft launching cradle adapts to a booster rocket required in the launching process of the aircraft. By the utilization of the improved aircraft launching cradle, different models of aircrafts adopting the same launching principle can be launched, and the use range of the launching cradle is expanded.
Description
Technical background
The present invention relates to vehicle launch equipment, be specifically related to a kind of derivative aircraft launcher.
Background technology
Aircraft is widely used in present society, take pictures in aviation, forest fire protection inspection, geological survey, high voltage power transmission
Line inspection, oil filed pipeline inspection, freeway management, emergency management and rescue and rescue application prospect are the most wide.At present, numerous
Small aircraft, particularly unmanned plane, all have employed and launch by the mode of rocket assist on launcher.Aircraft is at boosting fire
Fly away from launcher under arrow motor power effect, after taking off, throw away booster rocket, the sustainer on machine complete flight and appoint
Business.Launcher is the platform of vehicle launch, and in general, the launcher of the use of different aircraft is different.Launcher is wanted
Feature development according to aircraft.The parts that conventional vehicle launch frame is connected with aircraft mainly have front support arm, prop up afterwards
Support seat and rocket baffle plate.But thereby result in the relatively costly of launcher, it is impossible to adapt to cost requirement.
Summary of the invention
It is an object of the invention to solve vehicle launch frame in prior art and cannot adapt to different vehicle launch needs
Problem, and provide a kind of a kind of derivative aircraft launcher.Concrete technical scheme of the present invention is as follows:
Derivative aircraft launcher, has a base, and pan frontward end fixes two front support arms side by side, props up before every
Brace top is equipped with the strong point for setting up aircraft；In the middle part of base, both sides offer bar shape trench hole respectively, are used for fixing
Booster support；Described booster support includes curved baffle, connecting rod, bar set, sleeve pipe and main shaft, described main shaft two ends
It is respectively clamped in described bar shape trench hole, and only there is the free sliding degree along bar shape trench hole direction；Described sleeve pipe is the most embedding
Outside set and main shaft, and there is the rotary freedom with main shaft as axle center and the free sliding degree along main shaft bearing of trend；Described
Bar set be fixed on sleeve pipe, and the internally installed connecting rod can stretched along sleeve pipe direction, described curved baffle is fixed on even
Extension bar top；Base rear end fixes two rear support arm side by side, and described rear support arm top sets up support beam, and support beam two
End is respectively provided with the free sliding degree along rear support arm direction；Fixed plate it is fixed with, layer successively in fixed plate in described support beam
Being laminated with the first sliding panel, the second sliding panel, the 3rd sliding panel and support seat, the first described sliding panel has along fixed plate plane
And it being perpendicular to the free sliding degree in support beam direction, the second described sliding panel has along the first sliding panel plane and is parallel to
The free sliding degree in support beam direction, the 3rd described sliding panel has along the second sliding panel plane and is perpendicular to support beam direction
Free sliding degree, the described seat that supports has along the 3rd sliding panel plane and the free sliding degree that is parallel to support beam direction.This
In invention, free sliding degree refers to the straight-line displacement allowing have respective direction between two parts.Rotary freedom refers to two portions
Allowing between part to rotate in a circumferential direction, main shaft is motionless, and sleeve pipe rotates, thus adjusts the angle of connecting rod.In the present invention
Free sliding degree along A plane and along B direction refers to: object can slide along B direction in A plane.
The invention provides a kind of follow-on vehicle launch frame, utilize this follow-on launcher can launch employing
Identical emission principle, the aircraft of different model, expand the range of launcher.By regulating the activity of front support arm upper end
Parts, regulate the distance between two front support arms, and with applicable aircraft support width, position before and after regulation rear support seat, with suitable
Close the rear support point position of vehicle launch.The height of regulation rear support seat, with the transmitting required during applicable vehicle launch
Angle, the position of regulation rocket baffle plate, to require booster rocket during applicable vehicle launch.This addresses the problem different model flight
The transmitting problem of device.
Based on such scheme, it is also possible to improve as follows.
As preferably, two described strong points may be contained within adjusting means, and regulates two strong points by screw rod
Between distance.
As preferably, described bar puts and offers several slotted eyes, and described connecting rod offers hole, location, location
Positioned by latch between hole and slotted eye, stretch into the length in bar set for regulating connecting rod.
As preferably, described rear support arm top is provided with the connecting plate having several slotted eyes, in described support beam
Offer hole, location, positioned by latch between hole, location and the slotted eye at support beam two ends, be used for regulating after support beam is positioned at and propping up
Height in brace.
As preferably, described fixed plate offers the location of a diameter of d of some row's vertical support beam directions arrangement
Hole, the first described sliding panel offers the bar shape trench hole that several width are d, hole, location and the bar shaped on the first sliding panel
Positioned by latch between slotted eye, the position being perpendicular in fixed plate plane on support beam direction for coarse adjustment the first sliding panel
Put.
Further, the second described sliding panel offers the bar shape trench hole that several width are d, the first sliding panel and
Positioned by latch between bar shape trench hole on second sliding panel, put down in the first sliding panel plane for coarse adjustment the second sliding panel
Row position on support beam direction.
As preferably, the second described sliding panel is provided through the screw rod of the 3rd sliding panel, sliding for fine setting the 3rd
Dynamic plate is perpendicular to the position on support beam direction in the second sliding panel plane.
As preferably, the 3rd described sliding panel is provided through support the screw rod of seat, is used for finely tuning support seat the
It is parallel to the position on support beam direction in three sliding panel planes.
As preferably, between described sleeve pipe and base side wall, leave gap, for sleeve pipe transverse shifting；Sleeve pipe and main shaft
On be equipped with several location hole, for the anglec of rotation of adjusting sleeve pipe；Described main shaft two ends are respectively and fixedly provided with hex nut also
Snap in described bar shape trench hole, make main shaft to rotate in a circumferential direction.
As preferably, different degree of freedom selects one or more as required.
Compared with existing launcher, present invention have the advantage that
Front support spacing arm of the present invention from, rear support seat is put, and the angle of departure all can be adjusted, and changes launcher traditionally and flies
The problem that after row device is added, regulation is difficult, simultaneously because its scalable, just can launch the aircraft of different model, solve different shaped
Number aircraft problem of same launcher.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of derivative aircraft launcher；
Fig. 2 is the strong point partial schematic diagram of derivative aircraft launcher；
Fig. 3 is the booster support partial schematic diagram of derivative aircraft launcher；
Fig. 4 is the rear support device partial schematic diagram of derivative aircraft launcher；
In figure: front supporting device 1, front support arm 2, base 3, rear support arm 4, rear support device 5, booster support 6,
Support point 101, adjusting means the 102, first screw rod 103, side arm 301, bar shape trench hole 302, fixed plate the 501, first sliding panel 502,
Second sliding panel the 503, the 3rd sliding panel 504, support seat the 505, second screw rod the 506, the 3rd screw rod 507, curved baffle 601, company
Extension bar 602, bar set 603, sleeve pipe 604 and main shaft 605.
Detailed description of the invention
With detailed description of the invention the present invention it is further elaborated below in conjunction with the accompanying drawings and illustrates.In the present invention, each is implemented
The technical characteristic of mode, on the premise of not colliding with each other, all can carry out respective combination.
As it is shown in figure 1, a kind of derivative aircraft launcher, it is provided for bottom it supporting fixing base 3.Base 3
Front end fixes two front support arms 2 side by side, and every front support arm 2 top is equipped with the front supporting device 1 for setting up aircraft.
The front bottom end of aircraft is set up on these two front supporting devices 1.In the middle part of base 3, there are two side arms 301, side arm 301 in both sides
Upper offer bar shape trench hole 302 respectively, be used for fixing booster support 6.And as it is shown on figure 3, booster support 6 includes that arc keeps off
Plate 601, connecting rod 602, bar set 603, sleeve pipe 604 and main shaft 605, main shaft 605 two ends are respectively clamped in bar shape trench hole 302, and
Only there is the free sliding degree along bar shape trench hole 302 direction；Sleeve pipe 604 is coaxial nested outside with main shaft 605, and has with main shaft
605 is the rotary freedom in axle center and along the free sliding degree of main shaft 605 bearing of trend.Bar set 603 is fixed on sleeve pipe 604,
And the internally installed connecting rod 602 can stretched along sleeve pipe 604 direction.Curved baffle 601 is fixed on connecting rod 602 top, its in
Semicircle, the weight of booster (such as rocket) can be supported by baffle plate.Base 3 rear end fixes two rear support arm 4 side by side, after
Support arm 4 top sets up support beam, and support beam two ends are respectively provided with the free sliding degree along rear support arm 4 direction.In support beam
Rear support device 5 is set, for being supported the rear end of aircraft.Rear support device 5 concrete structure is: fixing in support beam
There is fixed plate 501, fixed plate 501 is sequentially laminated with first sliding panel the 502, second sliding panel the 503, the 3rd sliding panel 504 and
Supporting seat 505, the first sliding panel 502 has along fixed plate 501 plane and the free sliding degree that is perpendicular to support beam direction, and second
Sliding panel 503 has along the first sliding panel 502 plane and the free sliding degree that is parallel to support beam direction, the 3rd sliding panel 504
Have along the second sliding panel 503 plane and the free sliding degree that is perpendicular to support beam direction, support seat 505 and have along the 3rd slip
Plate 504 plane and be parallel to the free sliding degree in support beam direction.
Rotation and free sliding degree between above-mentioned different parts can be realized by different structures, provide it separately below
Middle a kind of implementation.During actual realization, can be adjusted as required.
As in figure 2 it is shown, be respectively equipped with the strong point 101 in front supporting device 1, two strong points 101 may be contained within regulation dress
Put in 102, and regulate the distance between two strong points 101 by the first screw rod 103.For booster support 6 part, bar set
Offer several slotted eyes on 603, connecting rod 602 offers hole, location, adjust the position in connecting rod 602 insertion rod set 603
Put, then make to position accordingly in the fine setting of this position adnexa and match between hole with slotted eye, positioned by latch, thus regulate connection
Bar 602 stretches into the length in bar set 603.Rear support arm 4 top is provided with connecting plate, and connecting plate from top to bottom has several grooves
Hole, support beam offers hole, location, and support beam adjusts to relevant position, the hole, location at fine setting support beam two ends and slotted eye,
Making it be positioned by latch after coincideing, thus regulation support beam is positioned at the height on rear support arm 4.
As shown in Figure 4, fixed plate 501 offers the hole, location of a diameter of d of some row's vertical support beam directions arrangement,
The bar shape trench hole 302 that several width are d, hole, location and the bar shaped on the first sliding panel 502 is offered on first sliding panel 502
Positioned by latch between slotted eye 302, in fixed plate 501 plane, be perpendicular to support beam side for coarse adjustment the first sliding panel 502
Position upwards.The bar shape trench hole 302 that several width are d, the first sliding panel 502 and is offered on second sliding panel 503
Positioned by latch between bar shape trench hole 302 on two sliding panels 503, for coarse adjustment the second sliding panel 503 at the first sliding panel
The position on support beam direction it is parallel in 502 planes.The of the 3rd sliding panel 504 it is provided through on second sliding panel 503
Two screw rods 506, the 3rd sliding panel 504 arranges the screw matched, can be micro-by rotating the second screw rod 506 during use
The 3rd sliding panel 504 is adjusted to be perpendicular to the position on support beam direction in the second sliding panel 503 plane.On 3rd sliding panel 504
It is provided through supporting the 3rd screw rod 507 of seat 505, supports and on seat 505, the screw matched is set, be used for finely tuning support seat
505 are parallel to the position on support beam direction in the 3rd sliding panel 504 plane.Between leaving between sleeve pipe 604 and base 3 sidewall
Gap, for sleeve pipe 604 transverse shifting；It is equipped with several holes, location, for adjusting sleeve pipe 604 on sleeve pipe 604 and main shaft 605
The anglec of rotation；Main shaft 605 two ends are respectively and fixedly provided with hex nut and snap in bar shape trench hole 302, make main shaft 605 circumference to revolve
Turn.Method of adjustment between above-mentioned slotted eye and hole, location is and is first substantially moved to relevant position by two parts, and fine setting makes
Two holes coincide, then are fixed with latch.Latch includes the various parts such as pin, screw.
It addition, degree of freedom between aforesaid different parts in the present invention, it is not necessary to be provided simultaneously with adjustable from
By spending, can select one or more, not as restriction as required.
The method of adjustment of above-mentioned launcher is:
First regulate derivative aircraft launcher front support arm 2 adjusting means 102, by screw rod regulate about support
Point 101) so that it is spacing matches with two front support positions of aircraft.Secondly regulate the position of rear support device 5, make flight
Device reaches the suitable angle of departure.Rear support device 5 can first pass through up-down adjustment and support depth of beam, then coarse adjustment all around the
The position of one sliding panel 502, then finely tune the second sliding panel 503 and the 3rd sliding panel 504 by screw rod respectively, finally make support seat
505 are positioned at correct position, it is ensured that the angle of departure of aircraft, and can be reliably connected with aircraft.Finally, regulation curved baffle 601
Position；Curved baffle has the most adjustable space；Regulation curved baffle position, meets booster rocket
Installation requirement.Curved baffle can pass through bar shape trench hole 302, connecting rod 602 and flexible, the rotation of axle sleeve structure of bar set 603
With move axially the comprehensive regulation realizing baffle plate.. follow-on vehicle launch frame thus can be used to launch different model
Aircraft.
Embodiment described above is the one preferably scheme of the present invention, and so it is not intended to limiting the invention.Have
Close the those of ordinary skill of technical field, without departing from the spirit and scope of the present invention, it is also possible to make various change
Change and modification.The technical scheme that the most all modes taking equivalent or equivalent transformation are obtained, all falls within the guarantor of the present invention
In the range of protecting.
Claims (10)
1. a derivative aircraft launcher, it is characterised in that pan frontward end fixes two front support arms side by side, props up before every
Brace top is equipped with the strong point for setting up aircraft；In the middle part of base, both sides offer bar shape trench hole respectively, are used for fixing
Booster support；Described booster support includes curved baffle, connecting rod, bar set, sleeve pipe and main shaft, described main shaft two ends
It is respectively clamped in described bar shape trench hole, and only there is the free sliding degree along bar shape trench hole direction；Described sleeve pipe is the most embedding
Outside set and main shaft, and there is the rotary freedom with main shaft as axle center and the free sliding degree along main shaft bearing of trend；Described
Bar set be fixed on sleeve pipe, and the internally installed connecting rod can stretched along sleeve pipe direction, described curved baffle is fixed on even
Extension bar top；Base rear end fixes two rear support arm side by side, and described rear support arm top sets up support beam, and support beam two
End is respectively provided with the free sliding degree along rear support arm direction；Fixed plate it is fixed with, layer successively in fixed plate in described support beam
Being laminated with the first sliding panel, the second sliding panel, the 3rd sliding panel and support seat, the first described sliding panel has along fixed plate plane
And it being perpendicular to the free sliding degree in support beam direction, the second described sliding panel has along the first sliding panel plane and is parallel to
The free sliding degree in support beam direction, the 3rd described sliding panel has along the second sliding panel plane and is perpendicular to support beam direction
Free sliding degree, the described seat that supports has along the 3rd sliding panel plane and the free sliding degree that is parallel to support beam direction.
2. derivative aircraft launcher as claimed in claim 1, it is characterised in that two described strong points may be contained within
In adjusting means, and by the distance between screw rod two strong points of regulation.
3. derivative aircraft launcher as claimed in claim 1, it is characterised in that described bar puts and offers several
Slotted eye, described connecting rod is offered hole, location, is positioned by latch, be used for regulating connecting rod and stretch between hole, location and slotted eye
Enter the length in bar set.
4. derivative aircraft launcher as claimed in claim 1, it is characterised in that described rear support arm top is provided with out
There is the connecting plate of several slotted eyes, described support beam offers hole, location, between hole, location and the slotted eye at support beam two ends
Positioned by latch, for regulating the height that support beam is positioned on rear support arm.
5. derivative aircraft launcher as claimed in claim 1, it is characterised in that offer some in described fixed plate
The hole, location of a diameter of d of row vertical support beam direction arrangement, it is d's that the first described sliding panel offers several width
Bar shape trench hole, is positioned by latch between the bar shape trench hole on hole, location and the first sliding panel, exists for coarse adjustment the first sliding panel
The position on support beam direction it is perpendicular in fixed plate plane.
6. derivative aircraft launcher as claimed in claim 5, it is characterised in that offer on the second described sliding panel
Several width are the bar shape trench hole of d, are positioned by latch between the bar shape trench hole on the first sliding panel and the second sliding panel, use
In the first sliding panel plane, it is parallel to the position on support beam direction in coarse adjustment the second sliding panel.
7. derivative aircraft launcher as claimed in claim 1, it is characterised in that be provided with on the second described sliding panel
Run through the screw rod of the 3rd sliding panel, be perpendicular on support beam direction in the second sliding panel plane for fine setting the 3rd sliding panel
Position.
8. derivative aircraft launcher as claimed in claim 1, it is characterised in that be provided with on the 3rd described sliding panel
Run through the screw rod supporting seat, in the 3rd sliding panel plane, be parallel to the position on support beam direction for finely tuning support seat.
9. derivative aircraft launcher as claimed in claim 1, it is characterised in that between described sleeve pipe and base side wall
Leave gap, for sleeve pipe transverse shifting；It is equipped with several holes, location, for the anglec of rotation of adjusting sleeve pipe on sleeve pipe and main shaft
Degree；Described main shaft two ends are respectively and fixedly provided with hex nut and snap in described bar shape trench hole, make main shaft to rotate in a circumferential direction.
10. derivative aircraft launcher as claimed in claim 1, it is characterised in that different degree of freedom selects as required
Select one or more.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610471296.4A CN106043731B (en) | 2016-06-22 | 2016-06-22 | Derivative aircraft launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610471296.4A CN106043731B (en) | 2016-06-22 | 2016-06-22 | Derivative aircraft launcher |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106043731A true CN106043731A (en) | 2016-10-26 |
| CN106043731B CN106043731B (en) | 2018-04-27 |
Family
ID=57167183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610471296.4A Expired - Fee Related CN106043731B (en) | 2016-06-22 | 2016-06-22 | Derivative aircraft launcher |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106043731B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828962A (en) * | 2016-12-27 | 2017-06-13 | 航天神舟飞行器有限公司 | Rocket assist formula high-speed unmanned aerial vehicle trigger mechanism |
| CN108128477A (en) * | 2017-12-22 | 2018-06-08 | 航天神舟飞行器有限公司 | A kind of adjustable rocket bracket of rato formula unmanned plane launcher |
| CN108513569A (en) * | 2017-12-30 | 2018-09-07 | 深圳市富斯科技有限公司 | Vehicle launch frame |
| CN109573086A (en) * | 2018-12-05 | 2019-04-05 | 中国人民解放军总参谋部第六十研究所 | The thrust line vision-control method and regulating device of unmanned plane booster rocket |
| CN110015421A (en) * | 2018-01-08 | 2019-07-16 | 经纬航太科技股份有限公司 | Fixed wing machine take-off system and its method |
| CN110631419A (en) * | 2019-08-22 | 2019-12-31 | 中国人民解放军国防科技大学 | Portable detachable folding missile-rocket launching device |
| CN115503976A (en) * | 2022-11-15 | 2022-12-23 | 杭州牧星科技有限公司 | Rocket mounting device |
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| GB577353A (en) * | 1942-09-09 | 1946-05-15 | Reginald Alfred Charles Brie | Landing and launching means for aircraft |
| US2729406A (en) * | 1952-02-01 | 1956-01-03 | Glenn L Martin Co | Zero-length launcher for aircraft |
| US2843020A (en) * | 1953-06-22 | 1958-07-15 | Northrop Aircraft Inc | Zero-length launcher |
| CN201907656U (en) * | 2010-12-28 | 2011-07-27 | 江西洪都航空工业集团有限责任公司 | Zero length launching device for pilotless planes |
| CN204489204U (en) * | 2015-01-21 | 2015-07-22 | 北京国遥星图航空科技有限公司 | Unmanned aerial vehicle ejecting frame |
| CN205837229U (en) * | 2016-06-22 | 2016-12-28 | 浙江大学 | A kind of derivative aircraft launcher |
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2016
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB577353A (en) * | 1942-09-09 | 1946-05-15 | Reginald Alfred Charles Brie | Landing and launching means for aircraft |
| US2729406A (en) * | 1952-02-01 | 1956-01-03 | Glenn L Martin Co | Zero-length launcher for aircraft |
| US2843020A (en) * | 1953-06-22 | 1958-07-15 | Northrop Aircraft Inc | Zero-length launcher |
| CN201907656U (en) * | 2010-12-28 | 2011-07-27 | 江西洪都航空工业集团有限责任公司 | Zero length launching device for pilotless planes |
| CN204489204U (en) * | 2015-01-21 | 2015-07-22 | 北京国遥星图航空科技有限公司 | Unmanned aerial vehicle ejecting frame |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828962A (en) * | 2016-12-27 | 2017-06-13 | 航天神舟飞行器有限公司 | Rocket assist formula high-speed unmanned aerial vehicle trigger mechanism |
| CN108128477A (en) * | 2017-12-22 | 2018-06-08 | 航天神舟飞行器有限公司 | A kind of adjustable rocket bracket of rato formula unmanned plane launcher |
| CN108513569A (en) * | 2017-12-30 | 2018-09-07 | 深圳市富斯科技有限公司 | Vehicle launch frame |
| WO2019127565A1 (en) * | 2017-12-30 | 2019-07-04 | 深圳市富斯科技有限公司 | Aircraft launcher |
| CN108513569B (en) * | 2017-12-30 | 2021-06-18 | 东莞市富斯遥控模型技术有限公司 | Aircraft launcher |
| CN110015421A (en) * | 2018-01-08 | 2019-07-16 | 经纬航太科技股份有限公司 | Fixed wing machine take-off system and its method |
| CN109573086A (en) * | 2018-12-05 | 2019-04-05 | 中国人民解放军总参谋部第六十研究所 | The thrust line vision-control method and regulating device of unmanned plane booster rocket |
| CN109573086B (en) * | 2018-12-05 | 2022-02-18 | 中国人民解放军总参谋部第六十研究所 | Thrust line display adjusting method and device for unmanned aerial vehicle booster rocket |
| CN110631419A (en) * | 2019-08-22 | 2019-12-31 | 中国人民解放军国防科技大学 | Portable detachable folding missile-rocket launching device |
| CN110631419B (en) * | 2019-08-22 | 2022-04-08 | 中国人民解放军国防科技大学 | Portable detachable folding missile-rocket launching device |
| CN115503976A (en) * | 2022-11-15 | 2022-12-23 | 杭州牧星科技有限公司 | Rocket mounting device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043731B (en) | 2018-04-27 |
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