CN102556336A

CN102556336A - Wing fast unfolding device for folding-wing unmanned plane

Info

Publication number: CN102556336A
Application number: CN201110456520XA
Authority: CN
Inventors: 何光林; 贺伟; 蒋铁英; 高丽军; 张忠伟; 刘学庆; 田鹤飞; 纪秀玲
Original assignee: Beijing Institute of Technology BIT
Current assignee: Beijing Institute of Technology BIT
Priority date: 2011-12-30
Filing date: 2011-12-30
Publication date: 2012-07-11

Abstract

The invention discloses a device for quickly deploying the wings of a folding-wing unmanned aerial vehicle, which belongs to the technical field of folding-wing unmanned aircraft structures. Cover, rocker arm, connecting rod and actuator; the two wing shafts are respectively vertically fixed below the horizontal fixing plate inside the fuselage through bearing seats, bearings and bearing covers, and the two wing shafts are respectively located in the center of the fuselage On the left and right sides of the axis, the left wing and the right wing are fixed above the fixed plate through the upper ends of the two wing shafts, and the lower ends of the wing shafts are respectively fixedly connected to one end of the rocker arm arranged horizontally, and the other end of the rocker arm is connected to the connecting rod. The two connecting ends of the rod are hinged, and the other end of the connecting rod is hinged with the actuator arranged along the axis of the fuselage. The invention effectively completes the fast unfolding of the folded wing, has simple device structure, is convenient to realize, has fast unfolding time and good synchronization.

Description

A kind of folding wings unmanned plane wing rapid deployment device

Technical field

The present invention relates to a kind of wing expanding unit, be specifically related to a kind of folding wings unmanned plane wing rapid deployment device, belong to folding wings unmanned vehicle technical field of structures.

Background technology

Unmanned vehicle is the not manned craft of controlling through radio robot or airborne computer stored program controlled.Unmanned vehicle is simple in structure, use cost is low, not only can accomplish the task that manned aircraft is carried out, and more is applicable to the task that people's aircraft should not be carried out, like scouting, air rescue commander and the remote sensing monitoring of hazardous location.

Mainly on the market now use following three kinds: fixedly aerofoil profile unmanned plane, pilotless helicopter and driverless operation dirigible; Compare with these ripe unmanned planes, the largest benefit of folding wings unmanned vehicle is saved the space exactly, and is easy to carry and transport; Improved the convenience of unmanned vehicle greatly; But because evening is wanted in its research starting, and technology is comparatively complicated, hereat in use present commercial market, also is in space state basically.

Summary of the invention

In view of this, the invention provides a kind of folding wings unmanned plane wing rapid deployment device, can make wing realize quick, synchronous expansion.

A kind of folding wings unmanned plane wing rapid deployment device comprises adapter plate, port wing, starboard wing, wing rotating shaft, bearing, bearing seat, bearing cap shim, rocking arm, connecting rod and actuator; Its annexation is following: two wing rotating shafts vertically are fixed on the below of the horizontal fixed plate of fuselage interior respectively through bearing seat, bearing and bearing cap shim; Two wing rotating shafts lay respectively at the left and right sides of fuselage central axis; Port wing and starboard wing are fixed on the top of adapter plate through the upper end of two wing rotating shafts; The lower end of wing rotating shaft is an end of the horizontally disposed rocking arm of captive joint separately; a coupling end of the rocking arm other end and connecting rod is hinged, and another coupling end and the rod assembly on the actuator of connecting rod are hinged, and actuator is fixedly connected on the below of adapter plate along the fuselage axis.

Working process: before the unmanned plane emission, port wing and starboard wing are close to the upper surface of adapter plate and are fixed and spacing by actuator and connecting rod and rocking arm; The height that flies to and set after the unmanned plane emission; Actuator starts and the pulling connecting rod moves along fuselage axis alignment tail direction fast; Connecting rod pulling rocking arm; the rotating shaft of rocking arm pulling wing is rotated back rapid deployment thereby drive port wing with starboard wing around its rotational is automatically locked after the actuator work completion after port wing and starboard wing horizontally rotate an angle of 90 degrees; The span of wing rotating shaft rotating band motivation is opened required power and is provided by actuator and control.

Beneficial effect: wing expanding unit of the present invention is simple in structure, realization is convenient, reliable effect; The power that launches is provided by the priming system actuator, has therefore overcome the limited deficiency of operational forces of torsion spring; And the ability rapid deployment, synchronism is good; And then make the range of use of unmanned plane more extensive.

Description of drawings

Fig. 1 is an integral structure scheme drawing of the present invention;

Fig. 2 is a longitudinal profile structural representation of the present invention;

Fig. 3 is the A-A view of Fig. 2.

Wherein, 1-adapter plate, 2-port wing, 3-starboard wing, the rotating shaft of 4-wing, 5-rocking arm, 6-bearing cap shim, 7-bearing, 8-bearing seat, 9-connecting rod, 10-actuator.

The specific embodiment

Describe the present invention below in conjunction with accompanying drawing.

Shown in accompanying drawing 1,2 and 3, the invention provides a kind of folding wings unmanned plane wing rapid deployment device, comprise adapter plate 1, port wing 2, starboard wing 3, wing rotating shaft 4, bearing 7, bearing seat 8, bearing cap shim 6, Rocker arm 5, connecting rod 9 and actuator 10; Its annexation is following: two wing rotating shafts 4 vertically are fixed on the below of the horizontal fixed plate of fuselage interior respectively through bearing seat 8, bearing 7 and bearing cap shim 6; Two wing rotating shafts 4 lay respectively at the left and right sides of fuselage central axis; Port wing 2 and starboard wing 3 are fixed on the top of adapter plate 1 through the upper end of two wing rotating shafts 4; The lower end of wing rotating shaft 4 is an end of the horizontally disposed Rocker arm 5 of captive joint separately; a coupling end of the Rocker arm 5 other end and connecting rod 9 is hinged, and another coupling end and the rod assembly on the actuator 10 of connecting rod 9 are hinged, and actuator 10 is fixedly connected on the below of adapter plate 1 along the fuselage axis.

Wherein, rod assembly is made up of the pull bar of pipe link and actuator 10, and pipe link is connected with the mutual vertical fixing of the pull bar of actuator 10.

Working process: before the unmanned plane emission, port wing 2 is close to the upper surface of adapter plate with starboard wing 3 and is fixed with spacing by actuator 10 and connecting rod 9 and Rocker arm 5; The height that flies to and set after the unmanned plane emission; Actuator 10 starts and pulling connecting rod 9 moves along fuselage axis alignment tail direction fast; Connecting rod 9 pulling Rocker arm 5s; the rotating shaft 4 of Rocker arm 5 pulling wing is rotated back rapid deployment thereby drive port wing 2 with starboard wing 3 around its rotational, automatically locks after actuator 10 work are accomplished after port wing 2 and starboard wing 3 horizontally rotate an angle of 90 degrees; The wing rotating shaft 4 rotating band motivation spanes are opened required power and are provided by actuator 10 and control, and actuator can adopt priming system actuator, motor-driven cylinder, hydraulic actuator.

In sum, more than being merely preferred embodiment of the present invention, is not to be used to limit protection scope of the present invention.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.

Claims

1. a folding wings unmanned plane wing rapid deployment device is characterized in that comprising adapter plate (1), port wing (2), starboard wing (3), wing rotating shaft (4), bearing (7), bearing seat (8), bearing cap shim (6), rocking arm (5), connecting rod (9) and actuator (10);

Its annexation is following: two wing rotating shafts (4) vertically are fixed on the below of the horizontal fixed plate (1) of fuselage interior respectively through bearing seat (8), bearing (7) and bearing cap shim (6); Two wing rotating shafts (4) lay respectively at the left and right sides of fuselage central axis; Port wing (2) and starboard wing (3) are fixed on the top of adapter plate (1) through the upper end of two wing rotating shafts (4); The lower end of wing rotating shaft (4) is an end of the horizontally disposed rocking arm of captive joint (5) separately; a coupling end of rocking arm (5) other end and connecting rod (9) is hinged; the rod assembly on another coupling end of connecting rod (9) and the actuator (10) is hinged, and actuator (10) is fixedly connected on the below of adapter plate (1) along the fuselage axis.

2. unmanned plane wing rapid deployment device as claimed in claim 1 is characterized in that said rod assembly is made up of the pull bar of pipe link and actuator (10), and pipe link is connected with the mutual vertical fixing of pull bar of actuator (10).

3. unmanned plane wing rapid deployment device as claimed in claim 1, it is characterized in that the emission of cartridge type emission unmanned plane before, port wing (2) and starboard wing (3) are close to the upper surface of adapter plate 1 and are fixed and spacing by actuator (10) and connecting rod (9) and rocking arm (5); Actuator (10) automatically locked after port wing (2) and starboard wing (3) horizontally rotated an angle of 90 degrees.

4. unmanned plane wing rapid deployment device as claimed in claim 1 is characterized in that the span of wing rotating shaft (4) rotating band motivation opens required power and provided by actuator (10) and control.

5. like claim 1,2,3 or 4 described unmanned plane wing rapid deployment devices, it is characterized in that said actuator (10) adopts priming system actuator, motor-driven cylinder or hydraulic actuator.