CN109747831A - A kind of tail portion slip rope formula space base unmanned plane emitter and launching technique - Google Patents
A kind of tail portion slip rope formula space base unmanned plane emitter and launching technique Download PDFInfo
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- CN109747831A CN109747831A CN201811618851.7A CN201811618851A CN109747831A CN 109747831 A CN109747831 A CN 109747831A CN 201811618851 A CN201811618851 A CN 201811618851A CN 109747831 A CN109747831 A CN 109747831A
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- slip rope
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Abstract
The invention discloses a kind of tail portion slip rope formula space base unmanned plane emitter and launching techniques, including winch, slip rope, positioning pulley, attitude-control device, extractor parachute, winch is arranged in machine tool fuselage interior, positioning pulley is arranged at machine tool fuselage rear door edge, slip rope one end is fixed on winch, the other end is connect after positioning pulley with extractor parachute, slip rope is divided into sliding area and abscission zone, the boundary of sliding area and abscission zone is to be detached from mouth, attitude-control device is arranged on abscission zone, it is adjacent with mouth is detached from, the present invention can realize multiple UAVs successively sequential transmission by a set of equipment, and unmanned plane can directly slip over turbulent region, carry out the steady air current area of safety, launching success rate and efficiency are higher, and it can realize batch sequential transmission.
Description
Technical field
The present invention relates to aircraft space base lift-off technology fields more particularly to a kind of tail portion slip rope formula space base unmanned plane to emit
Device and launching technique.
Background technique
With the eruptive growth of unmanned air vehicle technique, unmanned plane is gradually used widely in many military, civilian fields.It is special
Not in military domain, " unmanned plane cluster tactics " have obtained the great attention of countries in the world.But due to medium and small unmanned plane
Universal weight is small, and speed is low, and combat radius is limited, causes it that cannot execute long-range operation task, can not efficiently play bee colony
The advantage of operation limits the application range of medium and small unmanned plane.For this purpose, there has been proposed " mother and sons' machine " schemes, i.e., by navigating
Unmanned handset is transported mission area by journey, the biggish machine tool of load-carrying, by air-launched technology, realize the big quantity of unmanned plane,
Rapid fire not only can greatly increase the cruising radius of handset, and can get rid of the limitation of ground airport, increase
The flexibility of handset application.The core of " mother and sons' machine " scheme is exactly the transmitting of unmanned plane space base and recovery technology, and wherein unmanned plane is empty
The quick high-volume lift-off technology of base is exactly one of difficult point.
Existing unmanned plane space base launching technique and device such as patent CN204507271U, CN207417155U and
CN205998129U etc., use is gravity putting mode mostly, passes through turbulent region to unmanned plane and does not protect, transmitting peace
Full property is lower, is easy to cause unmanned plane stall, and launch inefficient.The method being mentioned herein is guaranteeing unmanned plane emission effciency
While, emission security design is increased, and smaller to the limitation of the body configuration of unmanned plane, the scope of application is wider.
Summary of the invention
The purpose of the present invention:
The purpose of the present invention: propose a kind of tail portion slip rope formula space base unmanned plane emitter and launching technique, it can be achieved that nothing
The man-machine accurate rapid fire of space base, improves emission security, expands the scope of application of unmanned plane.Technical solution of the present invention:
A kind of tail portion slip rope formula space base unmanned plane emitter, including winch, slip rope, positioning pulley, attitude-control device,
Extractor parachute, in machine tool fuselage interior, the positioning pulley is arranged in machine tool fuselage rear door edge, institute for the winch setting
The slip rope one end stated is fixed on winch, and the other end is connect after positioning pulley with extractor parachute, and the slip rope is divided into sliding
The boundary of area and abscission zone, sliding area and abscission zone is to be detached from mouth, and the attitude-control device is arranged on abscission zone, and de-
It is adjacent from mouth.
The attitude-control device includes balance fuselage, two elevator shafts, both direction rudder shaft, two liftings
Rudder, both direction rudder, one end of two elevator shafts are fixedly connected with balance fuselage, the other end respectively with it is corresponding
Rudder shaft is fixedly connected, and two elevators are connected with corresponding elevator shaft respectively by bearing, is arranged symmetrically in flat
Weigh fuselage two sides, and can around elevator shaft up and down deflect, the both direction rudder by bearing respectively with corresponding direction
The connection of rudder shaft, is arranged in elevator both ends, and can be around rudder shaft deflection.
The attitude-control device further includes three steering engines, flight control system, Position and attitude sensors, the flight control system and
Position and attitude sensor is arranged with balancing machine, and any of three steering engines are mounted on balancing machine, and rocker arm passes through connecting rod
It is fixedly connected respectively with two elevators, other two steering engine is separately mounted to the outer end of two elevator shafts, and the two
The rocker arm of steering engine is fixedly connected with both direction rudder respectively by connecting rod.
The sliding area of the slip rope is T shape section, and abscission zone is circular section.
Power supply line is embedded with inside the slip rope, power supply line can be by three rudders on machine on power supply attitude-control device
Machine, flight control system and Position and attitude sensor.
The slip rope is fabricated from a flexible material.
A kind of tail portion slip rope formula space base unmanned plane emitter, launching technique the following steps are included:
Step 1: extraction parachute is launched from machine tool fuselage rear door, under the action of extraction parachute, attitude-control device and cunning
Rope is skidded off out of machine tool fuselage compartment；
Step 2: after the abscission zone of slip rope enters steady air current area, Position and attitude sensor is started to work, and obtains posture control
The roll angle of device processed, yaw angle, pitch angle information, and flight control system is passed it to, flight control system gives three steering engines
Instruction is issued, three steering engines respectively drive two elevators and both direction rudder kick, enter attitude-control device stable flat
Fly state, meanwhile, under the influence of the pose of attitude-control device, it is detached from the unmanned plane transmitting that mouth near zone slip rope keeps specified
Angle；
Step 3: in the buckle that the installation of unmanned plane ventral matches with slip rope, unmanned plane being placed on slip rope by buckle
Sliding area；
Step 4: push unmanned plane to skid off along slip rope from machine tool fuselage rear door, under air-flow and inertia force effect, nobody
Machine passes through air turbulence area along slip rope, reaches the stable abscission zone of air-flow from sliding area；
Step 5: unmanned plane is detached from slip rope under the action of air-flow and inertia force, with the specified angle of departure, completes unmanned plane
Transmitting；
Step 6: after unmanned plane single rack time enters slip rope, the Launch Operation of next sortie can be directly carried out, without waiting for upper
The completion of one sortie Launch Operation, can significantly improve emission effciency.
Beneficial effects of the present invention:
It proposes a kind of tail portion slip rope formula space base unmanned plane emitter and launching technique, has the advantage that
(1) multiple UAVs successively sequential transmission can be realized by a set of equipment, and unmanned plane can directly slip over turbulent flow
Area carries out safe steady air current area, and launching success rate and efficiency are higher, and can realize batch sequential transmission；
(2) angle of departure of unmanned plane is controllable, and the emission security of unmanned plane can be effectively ensured；
(3) slip rope is made of flexible material, it is possible to reduce impact of the turbulent flow to unmanned plane；
(4) slip rope abscission zone is located at the steady layer of air-flow, and machine tool is smaller to the aerodynamic interference of unmanned plane, improves emission process
The safety of middle unmanned plane and machine tool；
(5) emission process is controlled without dedicated unit, need to only controls the horizontal angle for being detached from mouth, sent out convenient for unmanned plane batch
It penetrates；
(6) there is no particular/special requirement to unmanned plane housing construction, emitter is applied widely.
Detailed description of the invention
Fig. 1 is the device of the invention structural schematic diagram；
Fig. 2 is the sliding area sectional view of slip rope；
Fig. 3 is the abscission zone sectional view of slip rope；
Fig. 4 is attitude-control device structural schematic diagram；
The sliding area of buckle and slip rope on Fig. 5 unmanned plane cooperates schematic diagram；
The abscission zone of buckle and slip rope on Fig. 6 unmanned plane cooperates schematic diagram；
It is identified in figure: 1, winch, 2, positioning pulley, 3, slip rope, 4, attitude-control device, 5, extractor parachute, 4-1 elevator,
4-2 rudder, 4-3 balance fuselage, 4-4 elevator shaft, 4-5 rudder shaft.
Specific embodiment
It is further introduced with reference to the accompanying drawing back to invention, a kind of tail portion slip rope formula space base unmanned plane emitter,
Including winch 1, slip rope 3, positioning pulley 2, attitude-control device 4, extractor parachute 5, the winch 1 is arranged in machine tool fuselage
Portion, the positioning pulley 3 are arranged at machine tool fuselage rear door edge, and described 3 one end of slip rope is fixed on winch 1, another
End is connect after positioning pulley 2 with extractor parachute 5, and the slip rope 3 divides for sliding area and abscission zone, sliding area and abscission zone
Boundary is to be detached from mouth, and the attitude-control device 4 is arranged on abscission zone, adjacent with mouth is detached from.
The attitude-control device includes balance fuselage 4-3, two elevator shaft 4-4, both direction rudder shaft 4-
5, two elevator 4-1, both direction rudder 4-2, two elevator shaft 4-4 one end and balance fuselage 4-3 fix
Connection, the other end is fixedly connected with corresponding rudder shaft 4-5 respectively, two elevator 4-1 by bearing respectively with it is corresponding
The 4-4 connection of elevator shaft, be arranged symmetrically in the balance two sides fuselage 4-3, and can be deflected around elevator shaft 4-4 or more, institute
The both direction rudder 4-2 stated, respectively with corresponding rudder shaft 4-5 connection, is arranged in elevator 4-1 two by bearing
End, and can be around rudder shaft 4-5 deflection.
The attitude-control device 4 further includes three steering engines, flight control system, Position and attitude sensors, the flight control system
With Position and attitude sensor setting on balance fuselage 4-3, any of three steering engines are mounted on balance fuselage 4-3, rocker arm
It is fixedly connected respectively with two elevator 4-1 by connecting rod, other two steering engine is separately mounted to two elevator shaft 4-4's
Outer end, and the rocker arm of the two steering engines is fixedly connected with both direction rudder 4-2 respectively by connecting rod.
The sliding area of the slip rope 3 is T shape section, and abscission zone is circular section, is embedded with power supply line inside slip rope 3, can incite somebody to action
Three steering engines, flight control system and Position and attitude sensor on machine tool on power supply attitude-control device 4.
The slip rope 3 is fabricated from a flexible material.
A kind of tail portion slip rope formula space base unmanned plane emitter, launching technique the following steps are included:
Step 1: extraction parachute 5 is launched from machine tool fuselage rear door, under the action of extraction parachute 5, attitude-control device 4 and
Slip rope 3 is skidded off out of machine tool fuselage compartment；
Step 2: after the abscission zone of slip rope 3 enters steady air current area, Position and attitude sensor is started to work, and obtains posture control
The roll angle of device 4 processed, yaw angle, pitch angle information, and flight control system is passed it to, flight control system gives three steering engines
Instruction is issued, three steering engines respectively drive two elevator 4-1 and both direction rudder 4-2 deflection, enter attitude-control device 4
Stablize flat winged state, meanwhile, under the influence of the pose of attitude-control device 4, the slip rope 3 of disengaging mouth near zone keeps specified
The unmanned plane angle of departure, the angle of departure of the unmanned plane is close to 0 degree；
Step 3: in the buckle that the installation of unmanned plane ventral matches with slip rope 3, unmanned plane being placed in slip rope 3 by buckle
On sliding area；
Step 4: push unmanned plane to skid off along slip rope from machine tool fuselage rear door, under air-flow and inertia force effect, nobody
Machine passes through air turbulence area along slip rope 3, reaches the stable abscission zone of air-flow from sliding area；
Step 5: unmanned plane is detached from slip rope under the action of air-flow and inertia force, with the specified angle of departure, completes unmanned plane
Transmitting；
Step 6: after unmanned plane single rack time enters slip rope, the Launch Operation of next sortie can be directly carried out, without waiting for upper
The completion of one sortie Launch Operation, can significantly improve emission effciency.
Claims (7)
1. a kind of tail portion slip rope formula space base unmanned plane emitter, it is characterised in that: slided including winch (1), slip rope (3), positioning
(2), attitude-control device (4), extractor parachute (5) are taken turns, in machine tool fuselage interior, the positioning is sliding for the winch (1) setting
It takes turns (2) to be arranged at machine tool fuselage rear door edge, the slip rope (3) one end is fixed on winch (1), and the other end is by positioning
Pulley (2) is connect with extractor parachute (5) afterwards, and the slip rope (3) is divided into sliding area and abscission zone, the boundary of sliding area and abscission zone
To be detached from mouth, the attitude-control device (4) is arranged on abscission zone, adjacent with mouth is detached from.
2. a kind of tail portion slip rope formula space base unmanned plane emitter according to claim 1, it is characterised in that: the appearance
State control device (4) rises including balance fuselage (4-3), two elevator shafts (4-4), both direction rudder shaft (4-5), two
Drop rudder (4-1), both direction rudder (4-2), one end of two elevator shafts (4-4) respectively with balance fuselage (4-3)
Be fixedly connected, the other end is fixedly connected with corresponding rudder shaft (4-5) respectively, two elevators (4-1) respectively with it is corresponding
Elevator shaft (4-4) connection, be arranged symmetrically in balance the two sides fuselage (4-3), and can around elevator shaft (4-4) up and down partially
Turn, the both direction rudder (4-2) is connected with corresponding rudder shaft (4-5) respectively, is arranged in elevator (4-1)
Both ends, and can be around rudder shaft (4-5) deflection.
3. a kind of tail portion slip rope formula space base unmanned plane emitter according to claim 1, it is characterised in that: the appearance
State control device (4) further includes three steering engines, flight control system, Position and attitude sensors, and the flight control system and Position and attitude sensor are set
It sets in balance fuselage (4-1), any of three steering engines are mounted in balance fuselage (4-1), and rocker arm passes through connecting rod point
It not being fixedly connected with two elevators (4-1), other two steering engine is separately mounted to the outer end of two elevator shafts (4-4),
And the rocker arm of the two steering engines is fixedly connected with both direction rudder (4-2) respectively by connecting rod.
4. a kind of tail portion slip rope formula space base unmanned plane emitter according to claim 1, it is characterised in that: the slip rope
(3) sliding area is T shape section, and abscission zone is circular section.
5. a kind of tail portion slip rope formula space base unmanned plane emitter according to claim 1, it is characterised in that: the cunning
Power supply line is embedded with inside rope (3), power supply line can be by three steering engines on machine tool on power supply attitude-control device (4), winged control
System and Position and attitude sensor.
6. a kind of tail portion slip rope formula space base unmanned plane emitter according to claim 1, it is characterised in that: the cunning
Rope (3) is fabricated from a flexible material.
7. a kind of tail portion slip rope formula space base unmanned plane emitter, it is characterised in that: launching technique the following steps are included:
Step 1: extraction parachute (5) is launched from machine tool fuselage rear door, under the action of extraction parachute (5), attitude-control device (4)
And slip rope (3) is skidded off out of machine tool fuselage compartment；
Step 2: after the abscission zone of slip rope (3) enters steady air current area, Position and attitude sensor is started to work, and obtains gesture stability
The roll angle of device (4), yaw angle, pitch angle information, and flight control system is passed it to, flight control system gives three steering engines
Instruction is issued, three steering engines respectively drive two elevators (4-1) and both direction rudder (4-2) deflection, make attitude-control device
(4) enter and stablize flat winged state, meanwhile, under the influence of the pose of attitude-control device (4), it is detached from the slip rope of mouth near zone
(3) the specified unmanned plane angle of departure is kept；
Step 3: in the buckle that the installation of unmanned plane ventral matches with slip rope (3), unmanned plane being placed in slip rope (3) by buckle
On sliding area；
Step 4: push unmanned plane to skid off along slip rope (3) from machine tool fuselage rear door, under air-flow and inertia force effect, unmanned plane
Air turbulence area is passed through along slip rope (3), reaches the stable abscission zone of air-flow from sliding area；
Step 5: unmanned plane is detached from slip rope under the action of air-flow and inertia force, with the specified angle of departure, completes unmanned plane transmitting；
Step 6: after unmanned plane single rack time enters slip rope, the Launch Operation of next sortie can be directly carried out, without waiting for a upper frame
The completion of secondary Launch Operation can significantly improve emission effciency.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811618851.7A CN109747831B (en) | 2018-12-27 | 2018-12-27 | Tail sliding cable type air-based unmanned aerial vehicle launching device and launching method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811618851.7A CN109747831B (en) | 2018-12-27 | 2018-12-27 | Tail sliding cable type air-based unmanned aerial vehicle launching device and launching method |
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| Publication Number | Publication Date |
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| CN109747831A true CN109747831A (en) | 2019-05-14 |
| CN109747831B CN109747831B (en) | 2022-04-19 |
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| CN201811618851.7A Active CN109747831B (en) | 2018-12-27 | 2018-12-27 | Tail sliding cable type air-based unmanned aerial vehicle launching device and launching method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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| CN109747831B (en) | 2022-04-19 |
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