CN109229409A - A kind of aerial rapid fire system of cluster type small drone - Google Patents
A kind of aerial rapid fire system of cluster type small drone Download PDFInfo
- Publication number
- CN109229409A CN109229409A CN201811234528.XA CN201811234528A CN109229409A CN 109229409 A CN109229409 A CN 109229409A CN 201811234528 A CN201811234528 A CN 201811234528A CN 109229409 A CN109229409 A CN 109229409A
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- cartridge type
- unmanned plane
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- type loader
- spring
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- 230000007246 mechanism Effects 0.000 claims abstract description 50
- 238000000034 method Methods 0.000 claims abstract description 18
- 230000008569 process Effects 0.000 claims abstract description 15
- 238000000926 separation method Methods 0.000 claims abstract description 12
- 230000001133 acceleration Effects 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 238000011105 stabilization Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 230000002452 interceptive effect 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
- 238000004904 shortening Methods 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses a kind of aerial rapid fire system of cluster type small drone, which includes cartridge type loader and the ejection mechanism being integrated in cartridge type loader and drag parachute relieving mechanism；Cartridge type loader is made of streamlined loader shell, unmanned machine support；Ejection mechanism is installed in unmanned machine support, is made of spring piston system and locking mechanism.When unmanned plane emits, cartridge type loader is cast by carrier aircraft, after leaving carrier aircraft safe distance, the separation of cartridge type loader shell, cartridge type loader release drag parachute slows down, after speed is reduced to safe speed, unmanned plane is successively launched along cartridge type loader radial direction to aerial, emission process completion by preset program by cartridge type loader tail portion to head.Unmanned plane emission process is far from carrier aircraft and smaller with respect to ground speed in the present invention, improves air-launched success rate while improving the safety of carrier aircraft.
Description
Technical field
The present invention relates to air vehicle technique fields, and in particular to a kind of aerial rapid fire system of cluster type small drone
System.
Background technique
Mini-Unmanned Aerial Vehicles are proved its value afield, and conventional operation and SOF all use small-sized
UAV system carries out offer point, route and environment scouting, target acquistion, war damage assessment etc. innovation and application.In recent years, bee
Group's unmanned plane tactics are completely new as one kind, overturn attention of the ideal combat mode of formula by various countries.It is with Intelligent cluster technology
For core, the fight capability of single machine weakness is linked to each other by the contract network of unmanned plane, being configured to one kind has
Low cost, anti-strike capability is strong, the diversified novel combat system-of-systems of combat mode.
The Core Superiority of unmanned plane bee colony is: single machine is at low cost, number of groups is big, swarm intelligence degree is high, though however
Right bee colony unmanned plane has the advantages that above, they still include some fatal disadvantages, such as voyage is low that combat radius is caused to have
Limit, flying speed is low easily intercepted, and the low single machine fight capability of maximum take-off weight is limited etc., this, which becomes to restrict, uses small-sized nothing
The obstacle of people's implementation machine bee colony tactics.Traditional small drone is typically employed in the mode that broad place is voluntarily taken off and puts into work
War, or it is mounted in single rack Mobile launch on continental rise platform.That there are mobility is low for these radiation patterns, is easy intercepted destroy etc.
Disadvantage.Most effective solution is using air-launched mode.Small drone is carried close to mission area using carrier aircraft
Transmitting, can effectively increase the mobility flexibility of transmitting, increase the combat radius of small drone, someone can also be effectively ensured and drive
Sail the safety of flat pad.
Due to limiting factors such as platform movement and weight, the unmanned plane of continental rise, sea base merely cannot be emitted dress by we
It sets and is directly transported to the aerial transmitting for carrying out unmanned plane, they are unable to reach the requirement of disposable transmitting multi rack bee colony unmanned plane.
Existing aerial-launcher such as patent CN 107792371A and CN 108100287A etc. is carried out using devices such as launching tubes
Ejection launch.Although these modes can accomplish air-launched and multi rack transmitting, there are significant drawbacks.Such as patent CN
Mode described in 108100287A, since carrier aircraft speed is fast, unmanned plane is directly launched out of carrier aircraft, it is difficult to guarantee that unmanned plane emits
Not out of control afterwards and carrier aircraft safety.And although mode described in patent CN 107792371A enables unmanned plane emitter far from load
Machine, but too long towing cable system will increase the stability of carrier aircraft flight resistance reduction carrier aircraft, improve the risk of carrier aircraft flight；Together
When be difficult to adapt to weather conditions, can not accomplish round-the-clock deployment transmitting；The weight cost as caused by streamer length can not also neglect
Depending on.
Summary of the invention
To solve the above problems, being used the present invention provides a kind of aerial rapid fire system of cluster type small drone
The large size carrier aircraft such as transporter carries out the quick air-launched, it can be achieved that small drone, and trigger mechanism simple structure is suitable for more
Kind platform carry or loading, low in cost, maintenance is simple.
To achieve the above object, the technical scheme adopted by the invention is as follows:
A kind of aerial rapid fire system of cluster type small drone, which includes cartridge type loader and integration
In ejection mechanism and drag parachute relieving mechanism in cartridge type loader；The cartridge type loader is by streamlined loader shell, nothing
Man-machine bracket is constituted；The ejection mechanism is installed in unmanned machine support, is made of spring piston system and locking mechanism；It is described
Drag parachute relieving mechanism is made of brake chute stowage and drag parachute ejection mechanism；
When executing air-launched task, the streamlined cartridge type loader shell is used using two spring arrangements end to end
The separation of two valve flat push type separation methods is abandoned；The spring piston system and locking mechanism are in unmanned plane and the unmanned machine support
It is common before separation that unmanned plane and the unmanned machine support is kept to be connected；After separation starts, the spring piston system opens lock
Crash structure simultaneously starts compressed spring, completes unmanned aerial vehicle ejecting mask work；The drag parachute relieving mechanism is in the streamline
Type tube formula loader shell is abandoned and starting when far from the drag parachute relieving mechanism, pops up and slows down through drag parachute ejection mechanism
Umbrella, this mode, which can prevent from interfering with each other between streamlined cartridge type loader shell and drag parachute, causes failure.
Further, in ejection process, unmanned plane is close to spring piston system described in bullet, the locked machine on the outside of unmanned plane
Structure is associated with the spring piston system, and when receiving instruction, the spring piston system is activated, living in the spring
After spring in plug system is released, spring pushes piston to generate thrust to unmanned plane；Under the control of pre-set programs, unmanned plane
The locking mechanism in outside is opened, and unmanned plane is discharged；Under the thrust of the spring piston system, unmanned plane is along the cartridge type
Loader radial direction is launched to aerial, the ejection of one group of unmanned plane of completion bracket axial direction same position.
Further, the streamlined loader shell is using two spring mechanism realities for being arranged in loader both ends end to end
The existing two valves flat push type separation.
Further, carrier aircraft arrives at preplanned mission place, detects that the cartridge type loader is reaching in range sensor
With carrier aircraft have sufficiently apart from when, the cartridge type loader is abandoned the streamlined cartridge type using two valve flat push type separation methods and is loaded
Device shell；Range sensor measurement reaches drag parachute and streamlined loader shell will not interfere apart from when, starting
The drag parachute ejection mechanism, drag parachute are dished out and are unfolded；Velocity-stabilization, posture and velocity pick-up are detected to acceleration transducer
Device detects that loader is vertical posture, and when speed is lower, the ejection mechanism in the unmanned machine support is started to work, institute
It states spring piston system to open the locking mechanism 7 and start compressed spring, unmanned plane is loaded by preset program by cartridge type
It successively launches along cartridge type loader radial direction to aerial, the ejection process of one group of unmanned plane of completion on device tail portion to head；Then
Under pre-set programs control, behind separated in time interval, next group of unmanned plane starts to launch；It is all left to unmanned plane described
After unmanned machine support, ejection process is completed；Unmanned plane voluntarily formation execution task, abandons the cartridge type loader.
The invention has the following advantages:
1, unmanned plane emission process is far from carrier aircraft and smaller with respect to ground speed, mentions while improving the safety of carrier aircraft
High air-launched success rate；
2, there is the risk that launch time is poor, and unmanned plane mutually collides in reduction emission process between unmanned plane to be launched；
3, emit a large amount of unmanned planes simultaneously using cartridge type loader, space utilization rate is high, emission rate and high-efficient, shortening
Launch time；
4, cartridge type loader outer dimension existing hanger can be used to adapt to different carrier aircraft platforms similar to aerial bomb, general
Property is strong；
5, trigger mechanism simple structure, low in cost, operation, maintenance are simple.
Detailed description of the invention
Fig. 1 is cluster type small drone air-launched process schematic
Fig. 2 is the structural schematic diagram of cartridge type loader.
Fig. 3 is the scheme of installation of ejection mechanism and unmanned machine support.
Fig. 4 is the top view of Fig. 3.
Fig. 5 is unmanned aerial vehicle ejecting process schematic.
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.
As shown in figs 2-4, the embodiment of the invention provides a kind of aerial rapid fire system of cluster type small drone,
The emission system includes cartridge type loader 1 and the ejection mechanism being integrated in cartridge type loader 12 and drag parachute relieving mechanism 3；
The cartridge type loader 1 can be applicable to various skies according to air-drop weapon standard and unmanned plane size, shipped quantity design size
Middle platform is emitted, and constitutes 5 by streamlined loader shell 4, unmanned machine support；The ejection mechanism 2 is installed on unmanned plane
In bracket 5, it is made of spring piston system 6 and locking mechanism 7；The drag parachute relieving mechanism 3 is by brake chute stowage and drag parachute
Ejection mechanism composition；.
As shown in Figure 1 and Figure 5, when executing air-launched task, carrier aircraft arrives at preplanned mission place, in range sensor
Detect the cartridge type loader 1 reach with carrier aircraft have sufficiently apart from when, the cartridge type loader 1 is using two valve flat push types point
The streamlined cartridge type loader shell 4 is abandoned from method；Reach drag parachute and streamlined loader in range sensor measurement
Shell 4 will not interfere apart from when, start the drag parachute ejection mechanism, drag parachute is dished out and is unfolded；It is passed to acceleration
Sensor detects velocity-stabilization, and posture and velocity sensor detect that loader is vertical posture, when speed is lower, the unmanned plane
The ejection mechanism 2 in bracket is started to work, and the spring piston system 6, which is opened the locking mechanism 7 and started, to be compressed
Spring, unmanned plane successively launches along cartridge type loader radial direction to sky by preset program by cartridge type loader tail portion to head
In, complete the ejection process of one group of unmanned plane；Then pre-set programs control under, behind separated in time interval, next group without
It is man-machine to start to launch；After unmanned plane all leaves the unmanned machine support 5, ejection process is completed；Unmanned plane is voluntarily formed into columns and is held
Row task abandons the cartridge type loader 1.
Further, in ejection process, unmanned plane is close to spring piston system 6 described in bullet, described locked on the outside of unmanned plane
Mechanism 7 is associated with the spring piston system 6, and when receiving instruction, the spring piston system 6 is activated, described
After spring in spring piston system 6 is released, spring pushes piston to generate thrust to unmanned plane；In the control of pre-set programs
Under, the locking mechanism 7 on the outside of unmanned plane is opened, and unmanned plane is discharged；Under the thrust of the spring piston system 6, nobody
Machine is launched along 1 radial direction of cartridge type loader to aerial, the ejection of one group of unmanned plane of completion bracket axial direction same position.
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 (4)
1. a kind of aerial rapid fire system of cluster type small drone, which is characterized in that the emission system includes that cartridge type loads
Device (1) and the ejection mechanism (2) and drag parachute relieving mechanism (3) being integrated in cartridge type loader (1)；The cartridge type loader
(1) (5) are constituted by streamlined loader shell (4), unmanned machine support；The ejection mechanism (2) is installed on unmanned machine support (5)
It is interior, it is made of spring piston system (6) and locking mechanism (7)；The drag parachute relieving mechanism (3) is by brake chute stowage and drag parachute
Ejection mechanism composition；
When executing air-launched task, the streamlined cartridge type loader shell (4) is used using two spring arrangements end to end
The separation of two valve flat push type separation methods is abandoned；The spring piston system (6) and locking mechanism (7) unmanned plane and it is described nobody
It is common before machine support (5) separation that unmanned plane and the unmanned machine support (5) is kept to be connected；After separation starts, the spring is living
Plug system (6) opens locking mechanism (7) and starts compressed spring, completes unmanned aerial vehicle ejecting mask work；The drag parachute
Relieving mechanism (3) is abandoned in the streamlined cartridge type loader shell (4) and far from drag parachute relieving mechanism (3) when opens
It is dynamic, drag parachute is popped up through drag parachute ejection mechanism.
2. the aerial rapid fire system of a kind of cluster type small drone according to claim 1, which is characterized in that ejection
In the process, unmanned plane is close to spring piston system (6) described in bullet, and the locking mechanism (7) and the spring on the outside of unmanned plane are living
Plug system (6) is associated, and when receiving instruction, the spring piston system (6) is activated, in the spring piston system
(6) after the spring in is released, spring pushes piston to generate thrust to unmanned plane；Under the control of pre-set programs, outside unmanned plane
The locking mechanism (7) of side is opened, and unmanned plane is discharged；Under the thrust of the spring piston system (6), unmanned plane is described in
Cartridge type loader (1) radial direction is launched to aerial, the ejection of one group of unmanned plane of completion bracket axial direction same position.
3. the aerial rapid fire system of a kind of cluster type small drone according to claim 1, which is characterized in that described
Streamlined loader shell (4) realizes the two valves flat push type point using two spring mechanisms for being arranged in loader both ends end to end
From.
4. the aerial rapid fire system of a kind of cluster type small drone according to claim 1, which is characterized in that carrier aircraft
Arrive at preplanned mission place, range sensor detect the cartridge type loader (1) reach with carrier aircraft have sufficiently apart from when,
The cartridge type loader (1) abandons the streamlined cartridge type loader shell (4) using two valve flat push type separation methods；In distance
Sensor measurement reach drag parachute and streamlined loader shell (4) will not interfere apart from when, start the drag parachute
Ejection mechanism, drag parachute are dished out and are unfolded；Velocity-stabilization is detected to acceleration transducer, posture and velocity sensor detect dress
Load device is vertical posture, and when speed is lower, the ejection mechanism (2) in the unmanned machine support is started to work, the spring
Piston system (6) opens the locking mechanism (7) and starts compressed spring, and unmanned plane is by preset program by cartridge type loader
It successively launches along cartridge type loader radial direction to aerial, the ejection process of one group of unmanned plane of completion on tail portion to head；Then exist
Under pre-set programs control, behind separated in time interval, next group of unmanned plane starts to launch；The nothing is all left to unmanned plane
After man-machine bracket (5), ejection process is completed；Unmanned plane voluntarily formation execution task, abandons the cartridge type loader (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811234528.XA CN109229409B (en) | 2018-10-23 | 2018-10-23 | Cluster type unmanned aerial vehicle aerial rapid transmitting system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811234528.XA CN109229409B (en) | 2018-10-23 | 2018-10-23 | Cluster type unmanned aerial vehicle aerial rapid transmitting system |
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| Publication Number | Publication Date |
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| CN109229409A true CN109229409A (en) | 2019-01-18 |
| CN109229409B CN109229409B (en) | 2022-04-05 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109941422A (en) * | 2019-03-22 | 2019-06-28 | 北京理工大学 | A kind of the aerodynamic configuration structure and control method of folding wings missile-borne unmanned plane |
| CN110920892A (en) * | 2019-11-29 | 2020-03-27 | 西北工业大学 | Device is scattered to whole small-size cluster unmanned aerial vehicle of puting in |
| 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 |
| CN112254589A (en) * | 2020-09-23 | 2021-01-22 | 北京特种机械研究所 | Range-extending distribution method and system for unmanned aerial vehicle |
| CN112937832A (en) * | 2021-03-18 | 2021-06-11 | 艾肯拓(常熟)科技有限公司 | Air-drop type unmanned aerial vehicle and throwing method thereof |
| CN113492992A (en) * | 2021-07-21 | 2021-10-12 | 中国电子科技集团公司电子科学研究院 | Throwing device and throwing method of folding wing unmanned aerial vehicle |
| CN113859569A (en) * | 2021-10-25 | 2021-12-31 | 成都飞机工业（集团）有限责任公司 | Portable swarm unmanned aerial vehicle system and use method thereof |
| 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 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109941422A (en) * | 2019-03-22 | 2019-06-28 | 北京理工大学 | A kind of the aerodynamic configuration structure and control method of folding wings missile-borne unmanned plane |
| CN110920892A (en) * | 2019-11-29 | 2020-03-27 | 西北工业大学 | Device is scattered to whole small-size cluster unmanned aerial vehicle of puting in |
| 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 |
| CN112254589A (en) * | 2020-09-23 | 2021-01-22 | 北京特种机械研究所 | Range-extending distribution method and system for unmanned aerial vehicle |
| CN112937832A (en) * | 2021-03-18 | 2021-06-11 | 艾肯拓(常熟)科技有限公司 | Air-drop type unmanned aerial vehicle and throwing method thereof |
| CN113492992A (en) * | 2021-07-21 | 2021-10-12 | 中国电子科技集团公司电子科学研究院 | Throwing device and throwing method of folding wing unmanned aerial vehicle |
| CN113859569A (en) * | 2021-10-25 | 2021-12-31 | 成都飞机工业（集团）有限责任公司 | Portable swarm unmanned aerial vehicle system and use method thereof |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN109229409B (en) | 2022-04-05 |
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