CN109229410A - A kind of rotary unmanned plane air-launching method and device - Google Patents
A kind of rotary unmanned plane air-launching method and device Download PDFInfo
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- CN109229410A CN109229410A CN201811234584.3A CN201811234584A CN109229410A CN 109229410 A CN109229410 A CN 109229410A CN 201811234584 A CN201811234584 A CN 201811234584A CN 109229410 A CN109229410 A CN 109229410A
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- unmanned plane
- launcher
- launching tube
- locking mechanism
- ejector
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000010304 firing Methods 0.000 claims abstract description 4
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 12
- 238000005183 dynamical system Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 claims description 3
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 108091092878 Microsatellite Proteins 0.000 description 9
- 238000010586 diagram Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000007599 discharging Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000012954 risk control Methods 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 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
-
- 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
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of rotary unmanned plane aerial-launcher, which includes rotation launcher, launching tube, limit locking mechanism and ejector；Multiple launching tubes can be set on every launcher, a frame unmanned plane can be placed in each launching tube, before transmitting, first unmanned plane is loaded into launching tube.When being connected to firing order, limit locking mechanism is opened, unmanned aerial vehicle ejecting is gone out launching tube and completes transmitting by the elastic force generated by ejector.Compared with existing launching technique, the present invention can be in the requirement of very short time completion transmitting multiple UAVs, high degree of automation, emission effciency height.
Description
Technical field
The present invention relates to air vehicle technique fields, and in particular to a kind of rotary unmanned plane air-launching method and device.
Background technique
Since the 1930s, people begin to the air-launched for thirsting for realizing aircraft, the original of this radiation pattern
Reason is mainly carried unmanned plane to aerial by carrier aircraft, is launched unmanned plane by corresponding emitter.Aerial hair
It penetrates mode unmanned plane is transported by mission area by carrier aircraft and emit again, increase the cruising radius of unmanned plane, get rid of
The limitation on ground airport increases the flexibility of unmanned plane landing.But it is limited by the limit of technical conditions, risk control and cost
System, unmanned plane air-launched technology do not obtain big development.
In recent years, with the fast development of unmanned air vehicle technique and the proposition and upsurge of unmanned plane bee colony tactics, specially
It is given more sustained attention for the air-launched technology of Small and micro-satellite by more and more aviation people and aviation big country.Microminiature without
It is man-machine to have had been demonstrated that its value for being present in each battlefield, either conventional operation, also or special force of various countries carry out it is special
When kind is fought, Small and micro-satellite all is being applied, coordinate points, battle route are provided, the investigation of prewar environment, locking is carried out and tracks
Target, the assessment of war damage and various other innovative applications.The appearance and extensive use of Small and micro-satellite are to air fighting
Strength is enhanced and has been reinterpreted by changing " battlefield game rule ", current various types of Small and micro-satellite operations
Method emerges one after another, and unmanned plane bee colony tactics are exactly one of them.But inherent defect present in current Small and micro-satellite
Still the practical application to unmanned plane bee colony tactics in battlefield plays vital restrictive function.Small and micro-satellite is generally more
Small for weight, speed is low, and endurance and voyage are much more much smaller than large-scale unmanned plane, so that itself cruising radius also greatly reduces,
It not can be carried out long-range operation, this play the advantage of Small and micro-satellite bee colony tactics cannot to the greatest extent, above
These key factors for just becoming limitation Small and micro-satellite bee colony tactics innovation and application and actually fighting.Solve microminiature without
The method of itself man-machine inherent defect is exactly to select air-launched mode, using large-scale unmanned plane as empty day aircraft carrier.Utilize large size
Small and micro-satellite is carried to mission area as aerial carrier aircraft, carries out rapid fire later, utilize unmanned plane bee by unmanned plane
Group's operational superiority, carries out scouting strike to target area, carrier aircraft can be according to the actual situation to bee colony unmanned plane after task
It is recycled.
The existing aerial rapid fire device of unmanned plane, such as patent CN108100287A, it is right near carrier aircraft hatch door to need
Carrier aircraft is open, and to release emitter apparatus, can destroy the integrality of carrier aircraft in this way, reduce the structural strength of carrier aircraft
And transmitter is smaller, primary transmitting unmanned plane sortie is less, emission effciency is low.For another example patent CN107792371A passes through carrier aircraft
The aviation trailing cable for releasing a root long 900-1200m is provided with unmanned plane emitter on towing cable to carry out unmanned plane transmitting.
It is 2-5mm that this device, which needs to release diameter in the sky, and the aviation trailing cable of long 1200m, towing cable is after discharging, by air
Power and carrier aircraft tail flow field influence, and towing cable extremely unstable can do in the sky irregular disturbance, it is difficult to guarantee that unmanned plane is sent out
The completion penetrated, while setting emitter sortie is limited on towing cable, emission effciency is lower.
Summary of the invention
To solve the above problems, the present invention provides a kind of rotary unmanned plane air-launching method and device, operation letter
Single, space efficiency is high, and emission effciency is high.
To achieve the above object, the technical scheme adopted by the invention is as follows:
A kind of rotary unmanned plane aerial-launcher, the emitter are locked including rotation launcher, launching tube, limit
Mechanism and ejector；The rotation launcher is made of pedestal, bracket, axis, bearing, connecting rod；Pedestal upper end passes through bracket water
Safety is equipped with an axis, and configuration is there are four bearing on the axis, and both ends are respectively arranged one, centre setting two；
The launching tube be by connecting rod and centre two bearings it is affixed, can be revolved with the rotation of axis and bearing
Turn, hollow out and be designed to two-part among launching tube barrel and launching tube, in this way can to greatest extent it is upper reduce weight from
And have the function that reduce oil consumption；
At limit locking mechanism setting launching tube leading edge, limitation unmanned plane during transportation in launching tube before
After move；
The ejector is arranged at launching tube back edge, and hair limit locking mechanism is by compressing unmanned plane to ejector
One pressure, after opening limit locking mechanism, ejector goes out unmanned aerial vehicle ejecting, completes transmitting.
Further, the pedestal is rectangle, and base bottom, which is provided with sliding rail, can be stuck in tank top, pass through driving
Device drives it mobile in cargo compartment.
Further, bracket one end is connected with pedestal, and the other end is connected with the bearing at both ends.
Further, the axis is hollow, can reduce entire mechanism weight to greatest extent in this way.
Further, the launching tube is designed to the size to match with unmanned plane full-size, and cross section is circle, can be with
Guarantee unmanned plane not double swerve in transit, plays the role of limit.
The present invention also provides a kind of above-mentioned launching techniques of rotary unmanned plane aerial-launcher, including walk as follows
It is rapid:
Emitter described in carrier aircraft carried and transported multi rack reaches air-drop region, when being connected to firing order, staff behaviour
Making launcher control system drives the emitter to be moved to carrier aircraft hatch door；
Successively carrier aircraft hatch door, limit locking mechanism, limit locking mechanism is applied by compressing unmanned plane before ejector release
The pressure added, unmanned aerial vehicle ejecting is gone out, and unmanned plane is moved forward by the effect of self gravity and inertia, arrives safety zone
Wing tail and dynamical system are opened behind domain, completes unmanned plane transmitting, and unmanned plane voluntarily works execution task later.
The invention has the following advantages:
1. transmitting multi rack time unmanned plane may be implemented in emitter of the invention, emission effciency is greatly improved；
2. unmanned plane may be implemented successively to emit, safety is good, and accuracy is high；
3. easy to operate, operator participates in less；
4. multiple UAVs can be configured in frame rotation launcher, space utilization rate is improved；
5. different unmanned plane sizes can be directed to, various sizes of launching tube is set, flexibility ratio is high.
Detailed description of the invention
Fig. 1 is unmanned plane Launch System of the present invention composition figure.
Fig. 2 is that unmanned plane air-launched of the present invention rotates launcher perspective view.
Fig. 3 is that unmanned plane aerial-launcher of the present invention rotates launcher loading schematic diagram.
Fig. 4 is that unmanned plane aerial-launcher of the present invention rotates shooting sequence and direction of rotation schematic diagram.
Fig. 5 is that unmanned plane aerial-launcher of the present invention discharges schematic diagram after unmanned plane when executing launch mission.
Fig. 6 is drone status 1 after present invention transmitting unmanned plane.
Fig. 7 is drone status 2 after present invention transmitting unmanned plane.
Fig. 8 is drone status 3 after present invention transmitting unmanned plane.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
With reference to Fig. 1, a kind of rotary aerial-launcher that the present invention is implemented, including rotation launcher, launching tube 3, limit
Position locking mechanism 5 and ejector 2；The rotation launcher is made of pedestal 10, bracket 9, axis 8, bearing 7, connecting rod 6；It is described
Pedestal 10 is rectangle, and base bottom, which is provided with sliding rail, can be stuck in tank top, drive it in cargo hold by driving device
Portion is mobile, and pedestal upper end is horizontally installed with an axis 8 by bracket 9, the axis 8 be it is hollow, can reduce to greatest extent so whole
A mechanism weight, configuration is there are four bearing 7 on the axis 8, and both ends are respectively arranged one, and centre setting two can be according to specific
Unmanned plane size flexible arrangement, strong operability；
The launching tube be by connecting rod and centre two bearings it is affixed, can be revolved with the rotation of axis and bearing
Turn, hollow out and be designed to two-part among launching tube barrel and launching tube, in this way can to greatest extent it is upper reduce weight from
And have the function that reduce oil consumption；
The limit locking mechanism 5 is arranged at 3 leading edge of launching tube, limits unmanned plane during transportation in launching tube 3
Middle back-and-forth motion；
The ejector is arranged at 3 back edge of launching tube, and hair limit locking mechanism is by compressing unmanned plane to ejection
One pressure of device, after opening limit locking mechanism, ejector goes out unmanned aerial vehicle ejecting, completes transmitting.
Referring to Fig. 2, launcher is chosen to install for the present invention and loads unmanned plane perspective view.
With reference to Fig. 3-Fig. 4, launcher shooting sequence number is rotated for present invention rotation launcher left view and the present invention
Figure and direction of rotation schematic diagram, shooting sequence from 1. -10. successively emit in this order, in this way can be to avoid between two frame unmanned planes
It damages.
It is state diagram after air-launched of the present invention with reference to Fig. 5.
It is three position drone status figures after air-launched unmanned plane of the present invention, state shown in Fig. 6 with reference to Fig. 6-Fig. 8
Drone status when for a position shown in Fig. 5, drone status figure when state shown in Fig. 7 is the position b shown in Fig. 5, Fig. 8 institute
Show drone status figure when state is the position c shown in Fig. 5.In this specific implementation, multiple transmittings can be set on every launcher
Cylinder, can place a frame unmanned plane in each launching tube, when transmitting, include the following steps:
Emitter described in carrier aircraft carried and transported multi rack reaches air-drop region, when being connected to firing order, staff behaviour
Making launcher control system drives the emitter to be moved to carrier aircraft hatch door；
Successively carrier aircraft hatch door, limit locking mechanism 5, limit locking mechanism is applied by compressing unmanned plane before ejector release
The pressure added launches away unmanned plane 4, and unmanned plane 4 is moved forward by the effect of self gravity and inertia, to safety
Wing tail and dynamical system are opened behind region, completes unmanned plane transmitting, and unmanned plane voluntarily works execution task later.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (6)
1. a kind of rotary unmanned plane aerial-launcher, which is characterized in that the emitter includes rotation launcher, launching tube
(3), locking mechanism (5) and ejector (2) are limited；The rotation launcher is by pedestal (10), bracket (9), axis (8), bearing
(7), connecting rod (6) forms；Pedestal upper end is horizontally installed with an axis (8) by bracket (9), on the axis (8) there are four configurations
Bearing (7), both ends are respectively arranged one, centre setting two；
The launching tube be by connecting rod and centre two bearings it is affixed, can be rotated with the rotation of axis and bearing, send out
Hollow out and two-part is designed among shooting cylinder barrel and launching tube；
At described limit locking mechanism (5) setting launching tube (3) leading edge, unmanned plane is limited during transportation in launching tube
(3) it is moved forward and backward in；
The ejector is arranged at launching tube (3) back edge, and hair limit locking mechanism is by compressing unmanned plane to ejector
One pressure, after opening limit locking mechanism, ejector goes out unmanned aerial vehicle ejecting, completes transmitting.
2. a kind of rotary unmanned plane aerial-launcher as described in claim 1, which is characterized in that the pedestal (10) is
Rectangle, base bottom, which is provided with sliding rail, can be stuck in tank top, drive it mobile in cargo compartment by driving device.
3. a kind of rotary unmanned plane aerial-launcher as described in claim 1, which is characterized in that bracket (9) one end with
Pedestal is connected, and the other end is connected with the bearing at both ends.
4. a kind of rotary unmanned plane aerial-launcher as described in claim 1, which is characterized in that during the axis (8) is
It is empty.
5. a kind of rotary unmanned plane aerial-launcher as described in claim 1, which is characterized in that the launching tube design
At the size to match with unmanned plane full-size, cross section is circle, it is ensured that unmanned plane not double swerve in transit,
Play the role of limit.
6. a kind of launching technique of rotary unmanned plane aerial-launcher as described in any one in claim 1-5, feature
It is, includes the following steps:
Emitter described in carrier aircraft carried and transported multi rack reaches air-drop region, and when being connected to firing order, staff operates hair
Injection device control system drives the emitter to be moved to carrier aircraft hatch door；
Successively carrier aircraft hatch door, limit locking mechanism (5), limit locking mechanism is applied by compressing unmanned plane before ejector release
Pressure, unmanned plane (4) is launched away, unmanned plane (4) is moved forward by the effect of self gravity and inertia, to peace
Wing tail and dynamical system are opened behind entire area, completes unmanned plane transmitting, and unmanned plane voluntarily works execution task later.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811234584.3A CN109229410A (en) | 2018-10-23 | 2018-10-23 | A kind of rotary unmanned plane air-launching method and device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811234584.3A CN109229410A (en) | 2018-10-23 | 2018-10-23 | A kind of rotary unmanned plane air-launching method and device |
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| CN109229410A true CN109229410A (en) | 2019-01-18 |
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| CN201811234584.3A Pending CN109229410A (en) | 2018-10-23 | 2018-10-23 | A kind of rotary unmanned plane air-launching method and device |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260718A (en) * | 2019-06-26 | 2019-09-20 | 刘峰 | Anti- unmanned plane Small Universal launching tower |
| CN112173153A (en) * | 2020-09-18 | 2021-01-05 | 中国人民解放军国防科技大学 | Continuous-transmission unmanned aerial vehicle electromagnetic ejection system and unmanned aerial vehicle hangar |
| CN112224432A (en) * | 2020-09-22 | 2021-01-15 | 南京航空航天大学 | Interference bomb suitable for mixed marshalling aircraft is empty base transmission in batches |
| CN112298595A (en) * | 2020-11-20 | 2021-02-02 | 江西洪都航空工业股份有限公司 | Unmanned aerial vehicle rotary launching device and launching method |
| CN112407314A (en) * | 2020-11-19 | 2021-02-26 | 西安爱生无人机技术有限公司 | Land-based movable swarm unmanned aerial vehicle transmitting device |
| CN112607031A (en) * | 2020-12-22 | 2021-04-06 | 西安羚控电子科技有限公司 | Modular unmanned aerial vehicle cluster aerial rapid delivery system |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
| CN113200146A (en) * | 2021-05-18 | 2021-08-03 | 重庆交通大学 | Missile type folding cluster unmanned aerial vehicle control method, system, medium and unmanned aerial vehicle |
| CN113788130A (en) * | 2021-08-17 | 2021-12-14 | 河北汉光重工有限责任公司 | Underwater vehicle launching device of imitation revolver |
| CN114229027A (en) * | 2021-11-03 | 2022-03-25 | 沈阳天晴航空航天科技有限公司 | Quick aerial correlation launching box device |
| CN117465671A (en) * | 2023-12-27 | 2024-01-30 | 四川省天域航通科技有限公司 | Cargo conveying system for air-drop and air-delivery unmanned aerial vehicle and control method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU59521U1 (en) * | 2006-08-08 | 2006-12-27 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | AVIATION COMPLEX |
| CN105173083A (en) * | 2015-07-31 | 2015-12-23 | 北京邮电大学 | Dropping device for rotor craft |
| CN205615724U (en) * | 2016-05-12 | 2016-10-05 | 三翼航空科技南通有限公司 | Rocket launcher fire extinguishing bomb emitter |
| CN206031787U (en) * | 2016-08-30 | 2017-03-22 | 北方天途航空技术发展（北京）有限公司 | A kicker for unmanned aerial vehicle |
| CN108100287A (en) * | 2017-11-23 | 2018-06-01 | 北京航空航天大学 | A kind of unmanned plane space base emitter |
| CN207575598U (en) * | 2017-08-09 | 2018-07-06 | 江苏溧航航空科技有限公司 | A kind of vertical delivery device of UAV system fire extinguisher bomb |
-
2018
- 2018-10-23 CN CN201811234584.3A patent/CN109229410A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU59521U1 (en) * | 2006-08-08 | 2006-12-27 | Открытое Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | AVIATION COMPLEX |
| CN105173083A (en) * | 2015-07-31 | 2015-12-23 | 北京邮电大学 | Dropping device for rotor craft |
| CN205615724U (en) * | 2016-05-12 | 2016-10-05 | 三翼航空科技南通有限公司 | Rocket launcher fire extinguishing bomb emitter |
| CN206031787U (en) * | 2016-08-30 | 2017-03-22 | 北方天途航空技术发展（北京）有限公司 | A kicker for unmanned aerial vehicle |
| CN207575598U (en) * | 2017-08-09 | 2018-07-06 | 江苏溧航航空科技有限公司 | A kind of vertical delivery device of UAV system fire extinguisher bomb |
| CN108100287A (en) * | 2017-11-23 | 2018-06-01 | 北京航空航天大学 | A kind of unmanned plane space base emitter |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260718B (en) * | 2019-06-26 | 2024-02-27 | 刘峰 | Anti-unmanned aerial vehicle is with small-size general vertical emission device |
| CN110260718A (en) * | 2019-06-26 | 2019-09-20 | 刘峰 | Anti- unmanned plane Small Universal launching tower |
| CN112173153A (en) * | 2020-09-18 | 2021-01-05 | 中国人民解放军国防科技大学 | Continuous-transmission unmanned aerial vehicle electromagnetic ejection system and unmanned aerial vehicle hangar |
| CN112224432A (en) * | 2020-09-22 | 2021-01-15 | 南京航空航天大学 | Interference bomb suitable for mixed marshalling aircraft is empty base transmission in batches |
| CN112407314B (en) * | 2020-11-19 | 2022-08-09 | 西安爱生无人机技术有限公司 | Land-based movable swarm unmanned aerial vehicle transmitting device |
| CN112407314A (en) * | 2020-11-19 | 2021-02-26 | 西安爱生无人机技术有限公司 | Land-based movable swarm unmanned aerial vehicle transmitting device |
| CN112298595A (en) * | 2020-11-20 | 2021-02-02 | 江西洪都航空工业股份有限公司 | Unmanned aerial vehicle rotary launching device and launching method |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
| CN112607031B (en) * | 2020-12-22 | 2022-02-22 | 西安羚控电子科技有限公司 | Modular unmanned aerial vehicle cluster aerial rapid delivery system |
| CN112607031A (en) * | 2020-12-22 | 2021-04-06 | 西安羚控电子科技有限公司 | Modular unmanned aerial vehicle cluster aerial rapid delivery system |
| CN113200146A (en) * | 2021-05-18 | 2021-08-03 | 重庆交通大学 | Missile type folding cluster unmanned aerial vehicle control method, system, medium and unmanned aerial vehicle |
| CN113788130A (en) * | 2021-08-17 | 2021-12-14 | 河北汉光重工有限责任公司 | Underwater vehicle launching device of imitation revolver |
| CN114229027A (en) * | 2021-11-03 | 2022-03-25 | 沈阳天晴航空航天科技有限公司 | Quick aerial correlation launching box device |
| CN117465671A (en) * | 2023-12-27 | 2024-01-30 | 四川省天域航通科技有限公司 | Cargo conveying system for air-drop and air-delivery unmanned aerial vehicle and control method |
| CN117465671B (en) * | 2023-12-27 | 2024-04-02 | 四川省天域航通科技有限公司 | Cargo conveying system for air-drop and air-delivery unmanned aerial vehicle and control method |
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