CN106043731B - Derivative aircraft launcher - Google Patents
Derivative aircraft launcher Download PDFInfo
- Publication number
- CN106043731B CN106043731B CN201610471296.4A CN201610471296A CN106043731B CN 106043731 B CN106043731 B CN 106043731B CN 201610471296 A CN201610471296 A CN 201610471296A CN 106043731 B CN106043731 B CN 106043731B
- Authority
- CN
- China
- Prior art keywords
- sliding panel
- supporting beam
- main shaft
- launcher
- sliding
- 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.)
- Expired - Fee Related
Links
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
-
- 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
Abstract
The invention discloses a kind of derivative aircraft launcher.By adjusting the movable part of front support arm upper end, the distance between two front support arms is adjusted, to be adapted to aircraft support width, adjusts the front and back position of rear support seat, to be adapted to the rear support point position of vehicle launch.The height of rear support seat is adjusted, with the angle of departure required when being adapted to vehicle launch, the position of adjusting rocket baffle, to require booster rocket when being adapted to vehicle launch.The use scope for using identical emission principle, the aircraft of different model, expanding launcher can be launched using follow-on launcher.
Description
Technical background
The present invention relates to vehicle launch equipment, and in particular to a kind of derivative aircraft launcher.
Background technology
Aircraft is widely used in society now, 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 extremely wide.At present, it is numerous
Small aircraft, particularly unmanned plane, all employ and are launched on launcher with the mode of rocket assist.Aircraft is in boosting fire
Launcher is flown away under the effect of arrow motor power, after taking off, throws away booster rocket, flight is completed by the sustainer on machine and is appointed
Business.Launcher is the platform of vehicle launch, and in general, the launcher used of different aircraft is different.Launcher will
Developed according to the characteristics of aircraft.The component that common vehicle launch frame is connected with aircraft mainly has front support arm, rear branch
Support seat and rocket baffle.But the cost for thereby resulting in launcher is higher, cost requirement can not be adapted to.
The content of the invention
It is an object of the invention to solve vehicle launch frame in the prior art not adapting to different vehicle launch needs
The problem of, and a kind of derivative aircraft launcher is provided.Concrete technical scheme of the present invention is as follows：
Derivative aircraft launcher, has a base, and pan frontward end is fixed two front support arms, propped up before every side by side
The supporting point for setting up aircraft is equipped with the top of brace；The middle of the base both sides offer bar shape trench hole respectively, for fixing
Boost motor stent；The boost motor stent includes curved baffle, connecting rod, rod set, casing and main shaft, the main shaft both ends
It is respectively clamped into the bar shape trench hole, and only there is the free sliding degree along bar shape trench hole direction；The casing is coaxially embedding
Outside set and main shaft, and with using free sliding degree of the main shaft as the rotary freedom in axle center and along main shaft extending direction；It is described
Rod set be fixed on casing, and the connecting rod that internal installation can stretch along rod set direction, the curved baffle are fixed on company
At the top of extension bar；Base rear end fixes two rear support arms side by side, and the rear support arm top sets up supporting beam, and supporting beam two
End is respectively provided with the free sliding degree along rear support arm direction；It is fixed with fixed plate in the supporting beam, layer successively in fixed plate
The first sliding panel, the second sliding panel, the 3rd sliding panel and support base are laminated with, first sliding panel has along fixed plate plane
And have perpendicular to the free sliding degree in supporting beam direction, second sliding panel along the first sliding panel plane and parallel to branch
The free sliding degree in beam direction is supportted, the 3rd sliding panel has along the second sliding panel plane and perpendicular to supporting beam direction
Free sliding degree, the support base have along the 3rd sliding panel plane and parallel to the free sliding degree in supporting beam direction.This
In invention, free sliding degree refers to the straight-line displacement for allowing between two components to have respective direction.Rotary freedom refers to two portions
Allow to rotate in a circumferential direction between part, main shaft is motionless, and casing is rotated, so as to adjust the angle of connecting rod.In the present invention
Refer to along A planes and along the free sliding degree in B directions：Object can be slided in A planes along B directions.
The present invention provides a kind of follow-on vehicle launch frame, can launch use using follow-on launcher
Identical emission principle, the aircraft of different model, expands the use scope of launcher.By the activity for adjusting front support arm upper end
Component, adjusts the distance between two front support arms, to be adapted to aircraft support width, the front and back position of rear support seat is adjusted, with suitable
Close the rear support point position of vehicle launch.The height of rear support seat is adjusted, with the transmitting required when being adapted to vehicle launch
Angle, adjusts the position of rocket baffle, to require booster rocket when being adapted to vehicle launch.This addresses the problem different model flight
The transmitting problem of device.
Based on such scheme, can also be improved as follows.
Preferably, the supporting point described in two may be contained within regulating device, and two supporting points are adjusted by screw rod
The distance between.
Preferably, offering several slots in the rod set, location hole is offered in the connecting rod, is positioned
Positioned between hole and slot by latch, length in rod set is stretched into for adjusting connecting rod.
Preferably, the rear support arm top, which is equipped with, is provided with the connecting plates of several slots, in the supporting beam
Location hole is offered, is positioned by latch between the location hole and slot at supporting beam both ends, is propped up for adjusting after supporting beam is located at
Height in brace.
Preferably, the positioning of a diameter of d of some row's vertical support beam direction arrangements is offered in the fixed plate
Hole, offers the bar shape trench hole that several width are d on first sliding panel, the bar shaped on location hole and the first sliding panel
Positioned between slot by latch, for position of the first sliding panel of coarse adjustment in fixed plate plane on supporting beam direction
Put.
Further, offered on second sliding panel several width be d bar shape trench hole, the first sliding panel and
Positioned by latch between bar shape trench hole on second sliding panel, put down for the second sliding panel of coarse adjustment in the first sliding panel plane
Row is in the position on supporting beam direction.
Preferably, being provided through the screw rod of the 3rd sliding panel on second sliding panel, slided for finely tuning the 3rd
Position of the movable plate in the second sliding panel plane on supporting beam direction.
Preferably, the screw rod of support base is provided through on the 3rd sliding panel, for finely tuning support base
Parallel to the position on supporting beam direction in three sliding panel planes.
Preferably, gap is left between the casing and base side wall, for casing transverse shifting；Casing and main shaft
On be equipped with several location holes, the rotation angle for adjusting sleeve pipe；The main shaft both ends are respectively and fixedly provided with hex nut simultaneously
It is caught in the bar shape trench hole, main shaft is not rotated in a circumferential direction.
Preferably, the different frees degree selects one or more as needed.
Compared with existing launcher, the invention has the advantages that：
Distance between front support arm of the present invention, rear support seat are put, and the angle of departure can be adjusted, and are changed traditionally launcher and are flown
The problem of difficult is adjusted after row device restocking, simultaneously because it is adjustable, the aircraft with regard to that can launch different model, solves different shaped
The problem of number aircraft is with same launcher.
Brief description of the drawings
Fig. 1 is the overall structure diagram of derivative aircraft launcher；
Fig. 2 is the supporting point partial schematic diagram of derivative aircraft launcher；
Fig. 3 is the boost motor stent 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, boost motor stent 6, branch
Support point 101, regulating device 102, the first screw rod 103, side arm 301, bar shape trench hole 302, fixed plate 501, the first sliding panel 502,
Second sliding panel 503, the 3rd sliding panel 504, support base 505, the second screw rod 506, the 3rd screw rod 507, curved baffle 601, company
Extension bar 602, rod set 603, casing 604 and main shaft 605.
Embodiment
The present invention is further elaborated and illustrated with reference to the accompanying drawings and detailed description.Each implementation in the present invention
The technical characteristic of mode can carry out respective combination on the premise of not colliding with each other.
As shown in Figure 1, a kind of derivative aircraft launcher, its bottom sets and is used to support fixed base 3.Base 3
Two front support arms 2 are fixed in front end side by side, and every top of front support arm 2 is equipped with the front supporting device 1 for setting up aircraft.
The front bottom end of aircraft is set up on this two front supporting devices 1.3 on both sides of the middle of base has two side arms 301, side arm 301
It is upper to offer bar shape trench hole 302 respectively, for fixing boost motor stent 6.And as shown in figure 3, boost motor stent 6 is kept off including arc
Plate 601, connecting rod 602, rod set 603, casing 604 and main shaft 605,605 both ends of main shaft are respectively clamped into bar shape trench hole 302, and
Only there is the free sliding degree along 302 direction of bar shape trench hole；Outside the coaxial nested and main shaft 605 of casing 604, and with main shaft
605 rotary freedoms for axle center and the free sliding degree along 605 extending direction of main shaft.Rod set 603 is fixed on casing 604,
And the connecting rod 602 that internal installation can stretch along 603 direction of rod set.Curved baffle 601 is fixed on the top of connecting rod 602, it is in
Semicircle, the weight of boost motor (such as rocket) can be supported by baffle.Two rear support arms 4 are fixed in 3 rear end of base side by side, after
4 top of support arm sets up supporting beam, and supporting beam both ends are respectively provided with the free sliding degree along 4 direction of rear support arm.In supporting beam
Rear support device 5 is set, for being supported to the rear end of aircraft.5 concrete structure of rear support device is：It is fixed in supporting beam
There is fixed plate 501, the first sliding panel 502, the second sliding panel 503,504 and of the 3rd sliding panel are sequentially laminated with fixed plate 501
Support base 505, the first sliding panel 502 have along 501 plane of fixed plate and perpendicular to the free sliding degree in supporting beam direction, and second
Sliding panel 503 has along 502 plane of the first sliding panel and parallel to the free sliding degree in supporting beam direction, the 3rd sliding panel 504
With along 503 plane of the second sliding panel and perpendicular to the free sliding degree in supporting beam direction, support base 505, which has along the 3rd, to be slided
504 plane of plate and parallel to the free sliding degree in supporting beam direction.
Rotation and free sliding degree between above-mentioned difference component can be realized by different structures, provide it separately below
A kind of middle implementation.During actual realization, it can be adjusted as needed.
As shown in Fig. 2, being respectively equipped with supporting point 101 in front supporting device 1, two supporting points 101 may be contained within adjusting dress
In putting 102, and the distance between two supporting points 101 are adjusted by the first screw rod 103.For 6 part of boost motor stent, rod set
Several slots are offered on 603, location hole is offered in connecting rod 602, adjustment connecting rod 602 is inserted into the position in rod set 603
Put, then make to match between corresponding location hole and slot in the position annex fine setting, positioned by latch, thus adjust connection
Bar 602 stretches into the length in rod set 603.4 top of rear support arm is equipped with connecting plate, several grooves are from top to bottom provided with connecting plate
Hole, offers location hole in supporting beam, and supporting beam is adjusted to relevant position, the location hole and slot at fine setting supporting beam both ends,
It is positioned after coincideing by latch, thus adjust the height that supporting beam is located on rear support arm 4.
As shown in figure 4, the location hole of a diameter of d of some row's vertical support beam direction arrangements is offered in fixed plate 501,
The bar shape trench hole 302 that several width are d, the bar shaped on location hole and the first sliding panel 502 are offered on first sliding panel 502
Positioned between slot 302 by latch, for the first sliding panel of coarse adjustment 502 in 501 plane of fixed plate perpendicular to supporting beam side
Upward position.The bar shape trench hole 302 that several width are d, the first sliding panel 502 and the are offered on second sliding panel 503
Positioned between bar shape trench hole 302 on two sliding panels 503 by latch, for the second sliding panel of coarse adjustment 503 in the first sliding panel
Parallel to the position on supporting beam direction in 502 planes.The of the 3rd sliding panel 504 is provided through on second sliding panel 503
Two screw rods 506, set the screw hole to match on the 3rd sliding panel 504, can be micro- by rotating the second screw rod 506 during use
Adjust position of the 3rd sliding panel 504 in 503 plane of the second sliding panel on supporting beam direction.On 3rd sliding panel 504
The 3rd screw rod 507 of support base 505 is provided through, the screw hole to match is set on support base 505, for finely tuning support base
505 in 504 plane of the 3rd sliding panel parallel to the position on supporting beam direction.Between being left between 3 side wall of casing 604 and base
Gap, for 604 transverse shifting of casing；Casing 604 on main shaft 605 with being equipped with several location holes, for adjusting sleeve pipe 604
Rotation angle；605 both ends of main shaft are respectively and fixedly provided with hex nut and are caught in bar shape trench hole 302, main shaft 605 is not revolved circumferentially
Turn.Method of adjustment between above-mentioned slot and location hole is that fine setting makes after two components substantially first are moved to relevant position
Two holes coincide, then are fixed with latch.Latch includes the various parts such as pin, screw.
In addition, the free degree between different components foregoing in the present invention, it is not necessary to be provided simultaneously with it is adjustable from
By spending, one or more can be selected as needed, not as restriction.
The method of adjustment of above-mentioned launcher is：
The regulating device 102 of derivative aircraft launcher front support arm 2 is adjusted first, and left and right support is adjusted by screw rod
101) point, makes two front support non-colinear positions of its spacing and aircraft.Secondly the position of rear support device 5 is adjusted, makes flight
Device reaches the suitable angle of departure.Rear support device 5 can first pass through up and down adjustment support depth of beam, then coarse adjustment all around the
The position of one sliding panel 502, then the second sliding panel 503 and the 3rd sliding panel 504 are finely tuned by screw rod respectively, finally make support base
505 are located at suitable position, ensure the angle of departure of aircraft, and can be reliably connected with aircraft.Finally, curved baffle 601 is adjusted
Position；Curved baffle has all around adjustable space up and down；Curved baffle position is adjusted, meets booster rocket
Installation requirement.Curved baffle can pass through bar shape trench hole 302, connecting rod 602 and the rotation of the flexible of rod set 603, axle sleeve structure
The comprehensive adjusting of baffle is realized with axial movement.Follow-on vehicle launch frame transmitting different model thus can be used
Aircraft.
Embodiment described above is a kind of preferable scheme of the present invention, and so it is not intended to limiting the invention.Have
The those of ordinary skill of technical field is closed, without departing from the spirit and scope of the present invention, various changes can also be made
Change and modification.Therefore the technical solution that all modes for taking equivalent substitution or equivalent transformation are obtained, all falls within the guarantor of the present invention
In the range of shield.
Claims (9)
1. a kind of derivative aircraft launcher, it is characterised in that pan frontward end fixes two front support arms side by side, is propped up before every
The supporting point for setting up aircraft is equipped with the top of brace；The middle of the base both sides offer bar shape trench hole respectively, for fixing
Boost motor stent；The boost motor stent includes curved baffle, connecting rod, rod set, casing and main shaft, the main shaft both ends
It is respectively clamped into the bar shape trench hole, and only there is the free sliding degree along bar shape trench hole direction；The casing is coaxially embedding
It is placed on outside main shaft, and with using free sliding degree of the main shaft as the rotary freedom in axle center and along main shaft extending direction；It is described
Rod set be fixed on casing, and the connecting rod that internal installation can stretch along rod set direction, the curved baffle are fixed on company
At the top of extension bar；Base rear end fixes two rear support arms side by side, and the rear support arm top sets up supporting beam, and supporting beam two
End is respectively provided with the free sliding degree along rear support arm direction；It is fixed with fixed plate in the supporting beam, layer successively in fixed plate
The first sliding panel, the second sliding panel, the 3rd sliding panel and support base are laminated with, first sliding panel has along fixed plate plane
And have perpendicular to the free sliding degree in supporting beam direction, second sliding panel along the first sliding panel plane and parallel to branch
The free sliding degree in beam direction is supportted, the 3rd sliding panel has along the second sliding panel plane and perpendicular to supporting beam direction
Free sliding degree, the support base have along the 3rd sliding panel plane and parallel to the free sliding degree in supporting beam direction.
2. derivative aircraft launcher as claimed in claim 1, it is characterised in that the supporting point described in two may be contained within
In regulating device, and the distance between two supporting points are adjusted by screw rod.
3. derivative aircraft launcher as claimed in claim 1, it is characterised in that offer several in the rod set
Slot, offers location hole in the connecting rod, is positioned by latch between location hole and slot, stretched for adjusting connecting rod
Enter the length in rod set.
4. derivative aircraft launcher as claimed in claim 1, it is characterised in that the rear support arm top is equipped with and opens
There is the connecting plate of several slots, location hole is offered in the supporting beam, between the location hole and slot at supporting beam both ends
Positioned by latch, the height being located at for adjusting supporting beam on rear support arm.
5. derivative aircraft launcher as claimed in claim 1, it is characterised in that offered in the fixed plate some
The location hole of a diameter of d of vertical support beam direction arrangement is arranged, it is d's that several width are offered on first sliding panel
Bar shape trench hole, is positioned between the bar shape trench hole on location hole and the first sliding panel by latch, existed for the first sliding panel of coarse adjustment
Position in fixed plate plane on supporting beam direction.
6. derivative aircraft launcher as claimed in claim 5, it is characterised in that offered on second sliding panel
Several width are the bar shape trench hole of d, are positioned between the bar shape trench hole on the first sliding panel and the second sliding panel by latch, are used
In the second sliding panel of coarse adjustment in the first sliding panel plane parallel to the position on supporting beam direction.
7. derivative aircraft launcher as claimed in claim 1, it is characterised in that be provided with second sliding panel
Through the screw rod of the 3rd sliding panel, for finely tuning the 3rd sliding panel in the second sliding panel plane on supporting beam direction
Position.
8. derivative aircraft launcher as claimed in claim 1, it is characterised in that be provided with the 3rd sliding panel
Through the screw rod of support base, for finely tuning support base in the 3rd sliding panel plane parallel to the position on supporting beam direction.
9. derivative aircraft launcher as claimed in claim 1, it is characterised in that between the casing and base side wall
Gap is left, for casing transverse shifting；Casing on main shaft with being equipped with several location holes, the anglec of rotation for adjusting sleeve pipe
Degree；The main shaft both ends are respectively and fixedly provided with hex nut and are caught in the bar shape trench hole, main shaft is not rotated in a circumferential direction.
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 CN106043731A (en) | 2016-10-26 |
| CN106043731B true 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) |
Families Citing this family (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 |
| 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 |
| TWI688519B (en) * | 2018-01-08 | 2020-03-21 | 經緯航太科技股份有限公司 | Fixed-wing aeroplane take-off system and method thereof |
| 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 |
| 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 |
| CN115503976B (en) * | 2022-11-15 | 2023-05-02 | 杭州牧星科技有限公司 | Rocket mounting device |
Family Cites Families (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 |
| CN205837229U (en) * | 2016-06-22 | 2016-12-28 | 浙江大学 | A kind of derivative aircraft launcher |
-
2016
- 2016-06-22 CN CN201610471296.4A patent/CN106043731B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN106043731A (en) | 2016-10-26 |
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Inventor after: Liu Fuping Inventor after: Tao Weiming Inventor after: Han Bo Inventor after: Jiang Han Inventor after: Jian Yongqing Inventor after: Zheng Yao Inventor before: Liu Fuping Inventor before: Tao Weiming Inventor before: Han Bo Inventor before: Jiang Han Inventor before: Jian Yongqing |
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