CN102963525A

CN102963525A - Unmanned aerial vehicle

Info

Publication number: CN102963525A
Application number: CN2012103202326A
Authority: CN
Inventors: 张明明; 吕敬; 张志成; 李龙; 张永威
Original assignee: Individual
Current assignee: Individual
Priority date: 2012-09-03
Filing date: 2012-09-03
Publication date: 2013-03-13

Abstract

The invention relates to a novel unmanned aerial vehicle, especially a cycloidal propeller aerial vehicle. The aerial vehicle includes a fuselage, a power unit, an energy system, a control system, and bracket systems. The aerial vehicle is mainly characterized in that: the power unit is composed of a cycloidal propeller structure and a propeller structure, and the two structures interact to generate maximum power. The fuselage consists of a large elliptical frame and a small elliptical frame. The large elliptical frame can make 360-degree free rotation around the small elliptical frame under the action of rotation shafts. The energy system is made up of hydrogen fuel cells. The bracket systems include light metal rods, bracket retraction and release devices, as well as elastic rubber balls. The elastic rubber balls play a shock attenuation role during aerial vehicle landing. After the aerial vehicle takes off, under the action of the control system, the four bracket systems are retracted into the small elliptical frame. The novel aerial vehicle provided in the invention has the advantages of small size, low noise, weak radar visible signal, and high flexibility, etc., thus having very broad application prospects.

Description

A kind of unmanned vehicle

Technical field

The present invention relates to a kind of course of new aircraft, especially the unmanned vehicle of cycloid propeller and screw propeller collaborative work.

Background technology

Unmanned machine is a kind of take radio telecommand or by the unmanned aircraft of self programming control as leading.The new page of " the untouchable war " of taking as the leading factor with remote attack smart weapon, intelligence weapon has been opened in succeeding in developing with the battlefield utilization of it.Compare with manned craft, it has, and volume is little, cost is low, easy to use, low to the operational environment requirement, the advantage such as battlefield survival is stronger, and therefore, each main military country of the world is all at the research-and-development activity that steps up to carry out unmanned vehicle.Meanwhile, body micro-miniaturisation, comprehensive integration and stealthyization of body will be the important development directions of unmanned vehicle.The microminiature unmanned vehicle has the conventional advantage that unmanned vehicle did not have: target is little, and noise is low, and a little less than the radar optical signal, high degree of flexibility can be investigated dead angle that satellite and scout can not survey etc.Domestic achievement in research to the microminiature unmanned vehicle mainly is divided three classes: rotor type, fixedly aerofoil profile, flapping wing type.

Different from the microminiature unmanned vehicle of routine, the present invention adopts on existing Research foundation that the Reasonable of cycloid propeller and screw propeller is incompatible to be controlled aircraft.Before 100 years, just the someone has proposed the concept of cycloid propeller aircraft, and so-called cycloidal propeller refers to the edge of several blades installations at the cylindrical frame of a rotation when each blade moves, will be produced lift and thrust aloft.Cycloid propeller has following advantage: 1, can produce on demand the full vectored thrust of 360 degree, and also instantaneous variable; 2, cycloid propeller has higher thrust level than conventional screw propeller and turbine engine; 3, thrust is perpendicular to propeller axis of rotation, and cycloid propeller aircraft physical location can not change when changing the direction of thrust vectoring; 4, thrust increases along with the increase of forward flight speed, reaches maximum when speed is 111.12km/h, and consumption of fuel is little under cruising speed, will strengthen voyage like this; 5, cycloid propeller is no matter rotate with much power, and noise is all very low; 6, cycloid propeller has a variety of installation methods, and it can substitute the effect of conventional airplane horizontal tail, yaw rudder and elevating rudder; 7, owing to the appearance of cycloid propeller, the manoevreability of overall aircraft will improve greatly, a kind of new attitude maneuver field may occur, and it can be used as the attitude controller of aircraft.Consider the complexity of cycloidal oar blade motion, still do not have in the world ripe analysis theories at present, research still is in the exploratory stage.The cycloid propeller technology has been carried out the research of over half a century abroad, but during owing to the cycloidal oar blade motion, have strong the interference between blade, the flow field is very complicated, add the reasons such as control mechanism and flight stability, never have in the world the record about the controllable flight of this type of aircraft.Until the large undergraduate of western worker develops " Hot Wheels " and rolls and just indicate that this type of aircraft realizes remote control distributor first after the wing machine on the international unmanned vehicle creative contest of China first university student in 2011.

Summary of the invention

The purpose of the present invention's design is to provide a kind of simple in structure, and reliability is high, the course of new aircraft that realizability and practicality are high.

Technical scheme of the present invention is: this aircraft comprises fuselage, engine installation, energy source device, control system, mounting system.Described fuselage is comprised of a large ellipse frame and a little ellipse frame, and large ellipse frame can rotate freely around little ellipse frame 360 degree by the turning cylinder between two ellipse frames.Described engine installation is comprised of cycloid propeller structure and propeller arrangement.Described cycloid propeller structure is positioned at the inside of little ellipse frame, and two cycloid propeller is coaxial and hand of rotation is opposite.It is outside that described two propeller arrangements are positioned at large ellipse frame, and symmetrical.Described energy source device is positioned at the inside of little ellipse frame, and is symmetrical.Described control system is by two sub-composition of the control systems, and sub-control system is positioned at the inside of little ellipse frame, is symmetrically distributed.Described mounting system can be carried out the folding and unfolding campaign, and when this aircraft was positioned at ground, the support that is comprised of light-weight metal bar and elastic caoutchouc ball put down the effect of playing the support fuselage, when this aircraft movements, and the inside of support income ellipse frame.

Described cycloid propeller structure comprises control stalk, eccentric wheel, blade, axle drive shaft, vane drive bar (such as Fig. 2).

Described propeller arrangement comprises three leaf oar and put-puts.

Described energy source device is hydrogen cell.

Described mounting system is comprised of light-weight metal bar, support draw off gear, elastic caoutchouc ball.

The course of new aircraft of this invention has following advantage: 1, this unmanned vehicle adopts cycloid propeller and screw propeller array configuration, and noise is little, larger lift and thrust can be provided; 2, simple in structure, volume is little, quality is light; 3, manoevreability is good, reliability is high, the cruise time is long

Description of drawings

Be described in further detail below in conjunction with the course of new aircraft of accompanying drawing to this invention;

Fig. 1 is the overall structure scheme drawing of the course of new aircraft of this invention;

Fig. 2 is the cycloid propeller structural representation of the course of new aircraft of this invention;

Fig. 3 is the design sketch that cruises of the course of new aircraft of this invention;

Fig. 4 is the design sketch that climbs of the course of new aircraft of this invention;

Among Fig. 1-2,1, the support draw off gear; 2, elastic caoutchouc ball; 3, large ellipse frame; 4, axle drive shaft; 5, little ellipse frame; 6, sub-control system; 7, turning cylinder; 8, put-put; 9, three leaf oars; 10, hydrogen cell; 11, light-weight metal bar; 12, blade; 13, fixed support; 14, control stalk; 15, eccentric wheel; 16, vane drive bar.

The specific embodiment

Shown in Fig. 1-2, the present invention includes fuselage, engine installation, energy source device, control system, mounting system.Described fuselage is comprised of large ellipse frame 3 and little ellipse frame 5, and large ellipse frame 3 can carry out 360 degree around little ellipse frame 5 by turning cylinder 7 and rotates freely.Described engine installation is comprised of two cycloid propeller structures and two propeller arrangements.Described propeller arrangement is made of three leaf oars 9 and put-put 8, and two screw propellers are fixedly mounted on great circle framework 3 both sides by fixed support 13.Described cycloid propeller structure is made of blade 12, eccentric wheel 15, control stalk 14, vane drive bar 16, axle drive shaft 4 as shown in Figure 2.Described control system is comprised of two sub-control systems 6, described each sub-control system 6 is controlled the rotating speed of screw propellers and a cycloid propeller and is turned to, also control simultaneously the folding and unfolding campaign of two adjacent mounting systems, each sub-control system 6 is also controlled adjacent S. A. 7 in addition, and described large ellipse frame 3 can be rotated freely around little ellipse frame 5 under described S. A. 7 effects.The axle drive shaft 4 coaxial and direction of rotation of described each cycloid propeller structure, and then prevent that two cycloid propeller structures from causing the upset of aircraft because of the different moments of torsion that produce of hand of rotation.Described energy source device is comprised of two hydrogen cells 10, and they are power resources of whole aircraft.

Described mounting system comprises support draw off gear 1, light-weight metal bar 11 and elastic caoutchouc ball 2, and when aircraft landed, the elastic caoutchouc ball played certain buffer action, thereby reduces to clash into the impact on internal unit.

Described two cycloid propeller structures at first drive vane drive bar 16 by axle drive shaft 4, last blade drive spindle 16 band moving blades 12 rotatablely move accordingly, simultaneously axle drive shaft 4 band movable eccentric wheels 15 motions, eccentric wheel 15 drives control stalk 14 motions, control stalk 14 band moving blades 12, and then change the angle of attack value of blade 12, so described cycloid propeller changes rotatablely moving of the angle of attack constantly, to reach the purpose of larger lift.

Principle of work and process: give an example one: when aircraft takes off vertically, sub-control system 6 control turning cylinders 7, large ellipse frame 3 is in the same level face with little ellipse frame 5 under the effect of turning cylinder 7, under the effect of sub-control system 6, each axle drive shaft 4 drives corresponding cycloid propeller structure and carries out the synchronized rotation of different directions, because rotating speed is identical, so two cycloid propeller structures are rotated the moment of torsion that produces and are cancelled out each other, thereby so that aircraft takes off vertically, after liftoff, under the effect of two sub-control systems 6, mounting system takes in the little ellipse frame 5 support that is made of light-weight metal bar 11 and elastic caoutchouc ball 2 by 1 effect of support draw off gear.During the aircraft landing, under the effect of two sub-control systems 6, mounting system puts down the support that is made of light-weight metal bar 11 and elastic caoutchouc ball 2 by support draw off gear 1, the cycloid propeller rotating speed reduces simultaneously, aircraft slowly descends slowly and lightly, elastic caoutchouc ball 2 has certain buffer action during landing, thereby has increased the reliability of this course of new aircraft.Give an example two: when aircraft carries out deflection, two sub-control systems 6 are controlled respectively two axle drive shafts 4, each axle drive shaft 4 drives the differential rotation that corresponding cycloid propeller structure is carried out different directions, because two cycloid propeller structures can't be offset because of the moment of torsion that rotation produces, so fuselage will be subject to the effect of a moment of torsion, this moment of torsion overturns aircraft, aircraft arrives after the predetermined direction, sub-control system 6 will be controlled two cycloid propeller structures and do synchronized rotation, the moment of torsion of generation is cancelled out each other, aircraft is flown by predetermined direction.Give an example three: when aircraft is in cruising condition (as shown in Figure 3), sub-control system 6 control S. A.s 7, S. A. 7 drives large ellipse frame 3 rotations, makes its plane, place and plane, little ellipse frame 5 place be 90 degree and distributes, and this moment, aircraft can have maximum thrust; For example four: when the climbing and dive of aircraft (as shown in Figure 4), sub-control system 6 control S. A.s 7, S. A. 7 drives large ellipse frame 3 rotations, make its plane, place and little ellipse frame 5 plane included angles between 0 degree is spent to 90, propeller arrangement will provide the thrust of horizontal direction and the part lift of vertical direction to reach the flight attitude requirement.

Claims

1. a kind of unmanned vehicle of this invention comprises fuselage, engine installation, energy resource system, control system, mounting system.Described fuselage is comprised of a large ellipse frame and a little ellipse frame, and wherein large ellipse frame can rotate freely around little ellipse frame 360 degree by turning cylinder under the S. A. effect between two ellipse frames.Described engine installation is comprised of cycloid propeller structure and propeller arrangement, and described cycloid propeller structure is positioned at the inside of little ellipse frame, and it is outside that described propeller arrangement is installed in large ellipse frame symmetrically by fixed support.Described energy resource system is symmetrically distributed in the inside of little ellipse frame.Described control system is comprised of two sub-control setups, and described sub-control system is symmetrically distributed in the inside of little ellipse frame.Described mounting system is connected on the little ellipse frame by the support distributor.

2. a kind of unmanned vehicle according to claim 1, it is characterized in that: adopt the Novel power system cycloid propeller, axle drive shaft drives driving arm and eccentric wheel, driving arm band moving blade is rotated motion, eccentric wheel drives control stalk, control stalk band moving blade changes the size of the angle of attack, and then changes the size of power.

3. a kind of unmanned vehicle according to claim 1 and 2, it is characterized in that: described two cycloid propellers are coaxial, and the driving direction of drive spindle is opposite.

4. a kind of unmanned vehicle according to claim 1, it is characterized in that: large ellipse frame can rotate freely around little ellipse frame 360 degree under the S. A. effect between two ellipse frames, and then the direction vector of change screw propeller application force makes this aircraft reach required athletic posture.

5. a kind of unmanned vehicle according to claim 1, it is characterized in that: described mounting system is comprised of support draw off gear, light-weight metal bar and elastic caoutchouc ball, makes aircraft have certain buffer action, has increased the reliability of aircraft.