CN207292471U - A kind of unmanned plane launcher - Google Patents
A kind of unmanned plane launcher Download PDFInfo
- Publication number
- CN207292471U CN207292471U CN201720767186.2U CN201720767186U CN207292471U CN 207292471 U CN207292471 U CN 207292471U CN 201720767186 U CN201720767186 U CN 201720767186U CN 207292471 U CN207292471 U CN 207292471U
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- unmanned plane
- chassis
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Abstract
A kind of unmanned plane launcher, it is characterised in that：Including chassis, front support component, rear support component, front support component is arranged on the front end of chassis, support the front portion of unmanned plane, rear support component is arranged on the rear end of chassis, the afterbody of sustainable unmanned plane, rear support component includes rear support strut, U-shaped supports, self-locking spring, rear support strut is fixed on chassis, U-shaped support both ends are hinged with rear support strut, self-locking spring connects chassis and U-shaped support, U-shaped supports the elastic force by self-locking spring to act on, the rack supporting with unmanned drive end unit crossbeam is additionally provided with U-shaped support, the top of rack is equipped with U-lag, unmanned drive end unit crossbeam can be placed in U-lag.The launcher of the utility model is pure mechanic structure, it is not necessary to control circuit, it is simple in structure, and it is light-weight, it is convenient for carrying, use scope is wide, can meet the needs of launching unmanned plane under different mal-conditions, and mission controller is not required.
Description
Technical field
It the utility model is related to unmanned plane emitter design field, and in particular to a kind of unmanned plane launcher.
Background technology
The radiation pattern of unmanned plane can be divided at present：Takeoff, catapult-assisted take-off, rocket assist transmitting, hand throw transmitting, sky
It is middle to launch and take off vertically.
Takeoff refers to that unmanned plane runs device equipped with sliding, and after unmanned plane is started, unmanned plane is existed by the sliding device that runs
Take off on runway the process of lift-off.Takeoff has the advantage that to be set for the advantage of lower cost of this mode, required guarantee
Standby fewer, the overload in accelerator is smaller；Its shortcomings that is high to the requirement of runway ground environment, and undercarriage is airborne
On.At present, mainly there are U.S. predator, Australian Jin Diweike unmanned planes etc. using the unmanned plane of takeoff.
After catapult-assisted take-off refers to that unmanned plane is installed on slide, give acceleration by outside energy, then go up to the air
Process.Catapult-assisted take-off it the advantages of be that concealment is relatively good, it the shortcomings that the slide that takes off for unmanned plane can not be too long, and
Quality when unmanned plane is launched cannot be too big.The difference of possessed power source can divide when catapult-assisted take-off is launched according to unmanned plane
For following several ways：Hydraulic catapult, Pneumatic ejection, electromagnetic launch, elastic force ejection and combustion gas ejection etc..
In rocket assist emission process, the kinetic energy that unmanned plane takes off comes from rocket booster produced by the burning of fuel
Energy.Rocket assist radiation pattern have the advantage that for whole emitter take it is local smaller, cost is relatively low, is subject to
External influence is smaller, can be disposed with faster speed etc.；Its shortcomings that is priming system used and dangerous, is launched
Cheng Zhonghui generations sound, light, cigarette, are so easy for the place of exposure transmitting.
Hand throws transmitting and refers to strength of the unmanned plane by means of operator's hand, and unmanned plane is thrown aerial completion emission process.
The unmanned plane that radiation pattern is thrown using hand is generally small-sized and miniature drone.
Wherein rocket assist lift-off technology own seriation, and cost is low at present, thrust is big, is widely used.Unmanned plane is adopted
With during rocket assist launch without airfield runway, and maneuverability, therefore be used widely.Present rocket assist
The launcher that lift-off technology uses generally employs the electrical control gears such as various kinds of sensors, this greatly reduces rocket assist hair
Technology use scope under extreme conditions is penetrated, such as all may shadow in the situation without electricity, cold area, rainwater weather etc.
Ring the stability of unmanned plane transmitting.Igniting is first stage for taking off to launcher is departed from from unmanned plane launcher, studies this
Research of the radiation pattern and emission parameter in a stage to whole unmanned plane emission process has great significance.
Utility model content
The purpose of the utility model is to overcome the shortcomings that the prior art, there is provided control circuit, structure letter is not required in one kind
List, disclosure satisfy that situation of the extreme condition such as without electricity, cold area, the mission need of rainwater weather, easy to operate, Neng Gou
The unmanned plane launcher of unmanned plane transmitting is carried out on uneven terrain.
In order to solve the above-mentioned technical problem the technical solution of the utility model is as follows：A kind of unmanned plane launcher, its feature
It is：Including chassis, front support component, rear support component, front support component is arranged on the front end of chassis, before supporting unmanned plane
Portion, rear support component are arranged on the rear end of chassis, support the afterbody of unmanned plane, and rear support component includes rear support strut, U-shaped branch
Support, self-locking spring, rear support strut is fixed on chassis, and U-shaped support both ends are hinged with rear support strut, self-locking spring connect chassis with
U shapes support, and U-shaped supports the elastic force by self-locking spring to act on, and are additionally provided with U-shaped support and unmanned drive end unit crossbeam is supporting puts
Frame is put, the top of rack is equipped with U-lag, and unmanned drive end unit crossbeam is placed in U-lag.
Optional embodiment, the front support component includes forward support post and dove-tail form slide, forward support post are fixed
On chassis, dove-tail form slide is installed on the top of forward support post, and dove-tail form slide matches with the dovetail groove of unmanned plane.
Preferably, the forward support post quantity is 2, and 2 forward support posts are fixedly mounted on chassis side by side, described
Dove-tail form slide is 2.
Optional embodiment, the front support component include forward support post, dove-tail form slide, jack, described thousand
Jin top bottom is fixed on chassis, and top is fixedly connected with forward support post bottom, and the dove-tail form slide is installed on forward support post
Top, dove-tail form slide matches with the dovetail groove of unmanned plane.
Further, the jack is rhombic lifting jack.
Optional embodiment, a kind of unmanned plane launcher further include angular adjustment frame, the angular adjustment
Frame is formed by being fixedly connected in the vertical pole of conplane two with cross bar, and one end of angular adjustment frame and the tail end of chassis are cut with scissors
Connect, the front support component includes forward support post, dove-tail form slide, jack, and described jack one end is hinged with chassis, separately
One end and the cross bar of angular adjustment frame are hinged, and the forward support post is fixedly mounted on angular adjustment frame, and the dove-tail form is slided
Rail is installed on the top of forward support post, and dove-tail form slide matches with the dovetail groove of unmanned plane.
Further, the forward support post is vertical with adjusting bracket is fixedly mounted.
Further, the jack is rhombic lifting jack.
Further, the chassis is equipped with support leg, and the end of support leg is equipped with dismountable disk support feet.
Further, is additionally provided with gag lever post in U-shaped support, gag lever post one end is fixed in U-shaped support, one end chassis or
Angular adjustment frame is fixed.
The beneficial effects of the utility model are：
1. unmanned plane is placed in the U-lag of U-shaped support, U-shape support is connected by self-locking spring with chassis, when nobody
Machine take off igniting when, unmanned plane, which obtains a forward thrust, the trend of forward slip, but because has the work of self-locking spring
With U shapes support meeting remains stationary, U-shaped support is in self-locking state, and unmanned drive end unit crossbeam is placed in U-lag and will not skid off
Go.Then the passage of time at any time, the increasing just slowly forward slip of thrust that unmanned plane is subject to, unmanned plane forward slip band
Dynamic U shapes support turns forward, and self-locking spring is elongated, and U-shaped supports received spring force increasing, prevents unmanned plane straight
Connect depart from U-shaped support, unmanned plane obtain thrust continue to increase, thrust after unmanned plane is lighted a fire hit pay dirk take off it is critical
During thrust, the elastic force of self-locking spring is pulled to maximum, and the notch of the U-lag of U-shaped support departs from towards the front of aircraft, unmanned plane
The U-lag of U shapes support, unmanned plane successful launch.
2. launcher described in the utility model is pure mechanic structure, it is not necessary to control circuit.Because there is self-locking spring company
Connect chassis and self-locking device that U-shaped support is formed, pushed away when the thrust that unmanned plane is fired a rocket is not reaching to successfully take off critical
During power, the direction that flies out when the U-lag opening direction of the rack on launcher is launched with unmanned plane is vertical or reverse, Neng Gouqi
To self-locking；When the thrust that unmanned plane is fired a rocket hits pay dirk the critical thrust to take off, the thrust of rocket overcomes self-locking
The elastic force of spring, the direction that flies out when making the U-lag opening direction of rack launch with unmanned plane is identical, the horizontal stroke of unmanned drive end unit
Beam departs from U-lag, unmanned plane successful launch.Whether the unmanned plane launcher control unmanned plane of the utility model departs from launcher only
A self-locking device is employed, it is simple in structure, it is light-weight, it is convenient for carrying, use scope is wide, can meet that different mal-conditions issue
Penetrate the demand of unmanned plane, it is not necessary to which mission controller, improves the reliability of launcher.
3. front support component sets dove-tail form slide, matched with the dovetail groove of unmanned plane body, allow unmanned drive end unit to depart from U
It after new support, smoothly can forward launch along dove-tail form slide, improve the reliability of unmanned plane transmitting.
4. jack is connected with forward support post, the height of forward support post is adjusted, and then adjust bowing for unmanned plane transmitting
Elevation angle degree.Meet different terrain, the requirement launched under different scenes.
5. adjusting the function of unmanned plane take-off angle when rhombic lifting jack can not only meet to use, while storing and transporting
When defeated, rhombic lifting jack can be accepted completely, reduce being taken up space for unmanned plane launcher, convenient storage and transport.
6. setting angular adjustment frame, front support component is installed on angular adjustment frame, jack connection chassis and angle tune
Save frame so that angle adjusting mechanism is more reliable and more stable, and front support component is installed on angular adjustment frame, when adjusting nobody
During machine launch angle, the angle of front support component and angular adjustment frame does not have to change, and front support component can use fixed peace
The mode of dress is fixed, and makes launcher is overall more to stablize.
7. setting support feet and support leg, can meet the needs of when different scenes use.When in smooth bottom-emissive
During unmanned plane, using support feet, launcher is avoided specifically to be recessed so that launch angle deviates；When launching unmanned plane on inclined-plane,
Such as hillside transmitting, support feet is removed, support leg is fallen on the ground, avoids launcher from being slided with inclined-plane.
8. setting gag lever post, elastic stage can be in so that self-locking spring can be set under readiness, it is default for U-shaped support
A part of elastic force, when unmanned plane is launched, after reaching larger thrust, just beginning stress turns forward for U-shaped support, can suitably drop
The performance requirement of low spring, improves the reliability of launcher.
Brief description of the drawings
It is required in being described below to embodiment in order to illustrate more clearly of the technical scheme in the embodiment of the utility model
Attached drawing to be used is briefly described, it should be apparent that, drawings in the following description are only some realities of the utility model
Example is applied, for those of ordinary skill in the art, without creative efforts, can also be according to these attached drawings
Obtain other attached drawings.
Fig. 1 is a kind of front view of the structure diagram of the unmanned plane launcher with adjusting bracket of the utility model.
Fig. 2 is a kind of left view of the structure diagram of the unmanned plane launcher with adjusting bracket of the utility model.
Fig. 3 is the structure diagram of the U-shaped support in a kind of unmanned plane launcher of the utility model.
In figure, chassis 1, front support component 2, rear support component 3, adjusting bracket 4, forward support post 201, dove-tail form slide 202,
Jack 203, rear support strut 301, U-shaped support 302, self-locking spring 303, rack 3021, angle limit bar 3022.
Embodiment
The following is a combination of the drawings in the embodiments of the present utility model, the technical solution in embodiment is carried out clear, complete
Ground describes.Obviously, described embodiment is only the part of the embodiment of the utility model, instead of all the embodiments.
Embodiment based on the utility model, the institute that those of ordinary skill in the art are obtained without creative efforts
There is other embodiment, shall fall within the protection scope of the present invention.
As shown in Figs. 1-3, a kind of unmanned plane launcher, it is characterised in that：Including chassis 1, front support component 2, rear support
Component 3, front support component 2 are arranged on the front end of chassis 1, support the front portion of unmanned plane, and rear support component 3 is arranged on chassis 1
Rear end, supports the afterbody of unmanned plane, and rear support component 3 includes rear support strut 301, U-shaped support 302, self-locking spring 303, rear branch
Dagger 301 is fixed on chassis 1, and U-shaped supports 302 both ends hinged with rear support strut 301, and self-locking spring 303 connects chassis 1 and U
Shape support 302, U-shaped support 302 are acted on by the elastic force of self-locking spring 303, are additionally provided with U-shaped support 302 horizontal with unmanned drive end unit
The supporting rack 3021 of beam, the top of rack 3021 are equipped with U-lag, and unmanned drive end unit crossbeam is placed in U-lag.Fig. 1
It is the specific embodiment that has adjusting bracket and jack with Fig. 2, adjusting bracket can also be not required in the technical solution of the utility model
And jack, front support component is directly fixed to the front end of chassis, but can so reduce adjusting unmanned plane transmitting and face upward
Angle function.
Unmanned plane is placed in the U-lag of U-shaped support 302, and U-shape support is connected by self-locking spring 303 with chassis 1,
When unmanned plane takes off igniting, unmanned plane, which obtains a forward thrust, the trend of forward slip, but because has self-locking bullet
The effect of spring 303,302 meeting remains stationary of U-shaped support, U-shaped support 302 are in self-locking state, and unmanned drive end unit crossbeam is placed on
It will not be skidded off in U-lag.Then the passage of time at any time, the increasing just slowly forward slip of thrust that unmanned plane is subject to,
Unmanned plane forward slip drives U-shaped support 302 to turn forward, and self-locking spring 303 is elongated, and U-shaped supports 302 received spring bullets
Power is increasing, prevents unmanned plane from directly departing from U-shaped support 302, and the thrust that unmanned plane obtains continues to increase, when unmanned plane is lighted a fire
Thrust afterwards hit pay dirk the critical thrust to take off when, the elastic force of self-locking spring 303 is pulled to maximum, the U-shaped of U-shaped support 302
For the notch of groove towards the front of aircraft, unmanned plane departs from the U-lag of U-shaped support 302, unmanned plane successful launch.
Launcher described in the utility model is pure mechanic structure, it is not necessary to control circuit.Because there is self-locking spring connection
Chassis 1 and U-shaped support 302 form self-locking devices, when the thrust that unmanned plane is fired a rocket be not reaching to successfully take off it is critical
During thrust, the direction that flies out when the U-lag opening direction of the rack 3021 on launcher is launched with unmanned plane is vertical or reverse,
Self-locking can be played；When the thrust that unmanned plane is fired a rocket hits pay dirk the critical thrust to take off, the thrust gram of rocket
The elastic force of self-locking spring is taken, the direction that flies out when making the U-lag opening direction of rack 3021 launch with unmanned plane is identical, nobody
The crossbeam of drive end unit departs from U-lag, unmanned plane successful launch.Whether the unmanned plane launcher control unmanned plane of the utility model takes off
It is simple in structure from launcher only with a self-locking device, it is light-weight, it is convenient for carrying, use scope is wide, can meet different evils
Launch the demand of unmanned plane under the conditions of bad, it is not necessary to which mission controller, improves the reliability of launcher.
Further optional embodiment, the front support component 2 include forward support post 201 and dove-tail form slide
202, forward support post 201 is fixedly mounted on chassis 1, and dove-tail form slide 202 is installed on the top of forward support post 201, dove-tail form
Slide 202 matches with the dovetail groove of unmanned plane.
Embodiment still more preferably, 201 quantity of forward support post are 2, and 2 forward support posts 201 are simultaneously
Row is fixedly mounted on chassis 1, and the dove-tail form slide 202 is 2.
Front support component 2 sets dove-tail form slide 202, is matched with the dovetail groove of unmanned plane body, allows unmanned drive end unit to take off
It after newly being supported from U, smoothly can forward launch along dove-tail form slide 202, prevent unmanned plane under rocket assist effect directly
Launcher is upwardly separated from, further improves the reliability of unmanned plane transmitting.
A kind of optional embodiment, the front support component 2 include forward support post 201, dove-tail form slide 202, thousand
Jin top 203,203 bottom of jack is fixed on chassis 1, and top is fixedly connected with 201 bottom of forward support post, the swallow
Tail type slide 202 is installed on the top of forward support post 201, and dove-tail form slide 202 matches with the dovetail groove of unmanned plane.The implementation
Example eliminates adjusting bracket this technical characteristic compared to Fig. 1 Fig. 2.
Jack 203 is connected with forward support post 201, adjusts the height of forward support post 201, and then adjusts unmanned plane transmitting
Pitch angle.Meet different terrain, the requirement launched under different scenes.
Further, the jack 203 is rhombic lifting jack.
The function of unmanned plane take-off angle is adjusted when rhombic lifting jack can not only meet to use, while is storing and is transporting
When, rhombic lifting jack can be accepted completely, reduce being taken up space for unmanned plane launcher, convenient storage and transport.
Further alternative embodiment, a kind of unmanned plane launcher further include angular adjustment frame 4, the angle
Degree adjusting bracket 4 is formed by being fixedly connected in the vertical pole of conplane two with cross bar, one end of angular adjustment frame 4 and chassis
1 tail end is hinged, and the front support component 2 includes forward support post 201, dove-tail form slide 202, jack 203, described very heavy
It is hinged with chassis 1 to push up 203 one end, the cross bar of the other end and angular adjustment frame 4 is hinged, and the forward support post 201 is fixedly mounted
On angular adjustment frame 4, the dove-tail form slide 202 be installed on forward support post 201 top, dove-tail form slide 202 and nobody
The dovetail groove of machine matches.
Angular adjustment frame 4 is set, and front support component 2 is installed on angular adjustment frame 4, and jack 203 connects chassis 1 and angle
Spend adjusting bracket 4 so that angle adjusting mechanism is more reliable and more stable, and front support component 2 is installed on angular adjustment frame 4, when
When adjusting unmanned plane launch angle, the angle of front support component 2 and angular adjustment frame 4 does not have to change, and front support component 2 can
Fixed by the way of fixed installation, make launcher is overall more to stablize.
Further, the forward support post 201 is vertical with adjusting bracket 4 is fixedly mounted.It is convenient to process and fix.
Further, the jack 203 is rhombic lifting jack.
The function of unmanned plane take-off angle is adjusted when rhombic lifting jack can not only meet to use, while is storing and is transporting
When, rhombic lifting jack can be accepted completely, reduce being taken up space for unmanned plane launcher, convenient storage and transport.
Further, the chassis 1 is equipped with support leg, and the end of support leg is equipped with dismountable disk support feet.
Support feet and support leg are set, can meet the needs of when different scenes use.When smooth bottom-emissive without
When man-machine, using support feet, launcher is avoided specifically to be recessed so that launch angle deviates；When launching unmanned plane on inclined-plane, such as
Hillside is launched, and removes support feet, and support leg is fallen on the ground, avoids launcher from being slided with inclined-plane.
Further, gag lever post 3022 is additionally provided with U-shaped support 302,3022 one end of gag lever post is fixed on U-shaped support
On 302, one end chassis 1 or angular adjustment frame 4 are fixed.
Gag lever post 3022 is set, elastic stage can be in so that self-locking spring can be set under readiness, it is pre- for U-shaped support
If a part of elastic force, when unmanned plane is launched, after reaching larger thrust, just beginning stress turns forward for U-shaped support, can be appropriate
The performance requirement of spring is reduced, improves the reliability of launcher.
Claims (10)
- A kind of 1. unmanned plane launcher, it is characterised in that：It is preceding including chassis (1), front support component (2), rear support component (3) Support component (2) is arranged on the front end of chassis (1), supports the front portion of unmanned plane, and rear support component (3) is arranged on chassis (1) Rear end, supports the afterbody of unmanned plane, and rear support component (3) includes rear support strut (301), U-shaped support (302), self-locking spring (303), rear support strut (301) is fixed on chassis (1), and U-shaped support (302) both ends and rear support strut (301) are hinged, self-locking bullet Spring (303) connection chassis (1) and U-shaped support (302), U-shaped supports to be additionally provided with and unmanned drive end unit crossbeam is supporting puts on (302) Frame (3021) is put, the top of rack (3021) is equipped with U-lag, and unmanned drive end unit crossbeam is placed in U-lag.
- A kind of 2. unmanned plane launcher according to claim 1, it is characterised in that：The front support component (2) includes Forward support post (201) and dove-tail form slide (202), forward support post (201) are fixedly mounted on chassis (1), dove-tail form slide (202) top of forward support post (201) is installed on, dove-tail form slide (202) matches with the dovetail groove of unmanned plane.
- A kind of 3. unmanned plane launcher according to claim 2, it is characterised in that：Forward support post (201) quantity is 2 Root, 2 forward support posts (201) are fixedly mounted on chassis (1) side by side, and the dove-tail form slide (202) is 2.
- A kind of 4. unmanned plane launcher according to claim 1, it is characterised in that：The front support component (2) includes Forward support post (201), dove-tail form slide (202), jack (203), jack (203) bottom are fixed on chassis (1), Top is fixedly connected with forward support post (201) bottom, and the dove-tail form slide (202) is installed on the top of forward support post (201), Dove-tail form slide (202) matches with the dovetail groove of unmanned plane.
- A kind of 5. unmanned plane launcher according to claim 4, it is characterised in that：The jack (203) is diamond shape Jack.
- A kind of 6. unmanned plane launcher according to claim 1, it is characterised in that：Angular adjustment frame (4) is further included, it is described Angular adjustment frame (4) formed by being fixedly connected in the vertical pole of conplane two with cross bar, the one of angular adjustment frame (4) The tail end with chassis (1) is held to be hinged, the front support component (2) includes forward support post (201), dove-tail form slide (202), thousand Jin top (203), described jack (203) one end is hinged with chassis (1), and the other end and the cross bar of angular adjustment frame (4) are hinged, institute The forward support post (201) stated is fixedly mounted on angular adjustment frame (4), and the dove-tail form slide (202) is installed on forward support post (201) top, dove-tail form slide (202) match with the dovetail groove of unmanned plane.
- A kind of 7. unmanned plane launcher according to claim 6, it is characterised in that：The forward support post (201) is with adjusting Frame (4) is saved vertically to be fixedly mounted.
- A kind of 8. unmanned plane launcher according to claim 6, it is characterised in that：The jack (203) is diamond shape Jack.
- A kind of 9. unmanned plane launcher according to any one in claim 1-8, it is characterised in that：The chassis (1) support leg is equipped with, the end of support leg is equipped with dismountable disk support feet.
- A kind of 10. unmanned plane launcher according to any one in claim 6-8, it is characterised in that：U-shaped supports (302) be additionally provided with gag lever post (3022) on, gag lever post (3022) one end is fixed in U-shaped support (302), one end chassis (1) or Angular adjustment frame (4) is fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720767186.2U CN207292471U (en) | 2017-06-27 | 2017-06-27 | A kind of unmanned plane launcher |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720767186.2U CN207292471U (en) | 2017-06-27 | 2017-06-27 | A kind of unmanned plane launcher |
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| Publication Number | Publication Date |
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| CN207292471U true CN207292471U (en) | 2018-05-01 |
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ID=62450541
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720767186.2U Withdrawn - After Issue CN207292471U (en) | 2017-06-27 | 2017-06-27 | A kind of unmanned plane launcher |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107176310A (en) * | 2017-06-27 | 2017-09-19 | 武汉华伍航空科技有限公司 | A kind of unmanned plane launcher |
| CN108639371A (en) * | 2018-07-09 | 2018-10-12 | 中国科学院长春光学精密机械与物理研究所 | Ejection link for launching takeoff unmanned plane |
| CN113277106A (en) * | 2021-07-05 | 2021-08-20 | 航天神舟飞行器有限公司 | Unmanned aerial vehicle zero-length launcher |
-
2017
- 2017-06-27 CN CN201720767186.2U patent/CN207292471U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107176310A (en) * | 2017-06-27 | 2017-09-19 | 武汉华伍航空科技有限公司 | A kind of unmanned plane launcher |
| CN107176310B (en) * | 2017-06-27 | 2023-09-15 | 安徽国援智能科技有限公司 | Unmanned aerial vehicle launching cradle |
| CN108639371A (en) * | 2018-07-09 | 2018-10-12 | 中国科学院长春光学精密机械与物理研究所 | Ejection link for launching takeoff unmanned plane |
| CN108639371B (en) * | 2018-07-09 | 2020-05-19 | 中国科学院长春光学精密机械与物理研究所 | A launch link for launching jogging take-off unmanned aerial vehicle |
| CN113277106A (en) * | 2021-07-05 | 2021-08-20 | 航天神舟飞行器有限公司 | Unmanned aerial vehicle zero-length launcher |
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