CN101811572A

CN101811572A - Coaxial-inversion birotor eight-rotary wing aircraft

Info

Publication number: CN101811572A
Application number: CN 201010152265
Authority: CN
Inventors: 白越; 孙强; 续志军; 李也凡; 高庆嘉; 王凯
Original assignee: Changchun Institute of Optics Fine Mechanics and Physics of CAS
Current assignee: Changchun Institute of Optics Fine Mechanics and Physics of CAS
Priority date: 2010-04-22
Filing date: 2010-04-22
Publication date: 2010-08-25

Abstract

The invention provides a coaxial-inversion birotor eight-rotary wing aircraft, relating to the technical field of unmanned aircrafts and comprising an engine body (1), four supporting arms (2), four birotors (3), undercarriages (4) and an electric control system (5), wherein the four supporting arms (2) are connected to the periphery of the engine body (1), the geometrical center lines of the four supporting arms (2) are on the same plane, and the included angle of the geometrical center lines of the adjacent two supporting arms (2) is 90 degrees; the four birotors (3) are respectively arranged on the ends of the four supporting arms (2); the undercarriages (4) are symmetrically connected to the engine body (1); and the electric control system (5) is arranged in the engine body (1), controls and is connected with the four birotors (3). The aircraft has high lift force/weight ratio and loading capacity.

Description

Coaxial-inversion birotor eight-rotary wing aircraft

Technical field

The invention belongs to the unmanned vehicle technical field, relate to a kind of coaxial-inversion birotor multi-rotor aerocraft of new structure.

Background technology

Current most of aircraft all is a fixed-wing formula aircraft, and this aircraft can't be finished vertical and landing takeoff, needs special-purpose runway or feedway, and its maneuvering performance is limited.Lifting vehicle has the vertical and landing takeoff function, can also aloft hover, and has demand widely in fields such as military surveillance, anti-terrorism, public security, fire-fighting, forest inspection, nuclear leakage detection and the disaster relief.Particularly the microminiature rotor craft has very wide application prospect aspect dual-use, is included as Field Operational scouting and supervision under the complex-terrain situation are provided; Communication repeating; Detect nuclear pollution or carry out detection under the particular surroundings; Scout the interior of building situation; Supervision, monitoring, hostile takedown and anti-terrorism etc.Aspect civilian, the microminiature rotor craft can be used for searching for disaster survivor, noxious gas or chemical pollution, the supervisory assessment of building, oil and various application occasions such as power pipeline inspection and civil aviation shooting.Current lifting vehicle mainly contains single rotor (main rotor+tail-rotor) helicopter, the two outstanding wing (contrarotation) helicopter and three kinds of versions of four rotor crafts, such as four rotor crafts of the MH-16 helicopter of U.S. McDonnell-Douglas Corporation, Muscovite card-29 helicopter, German Microdrone company etc.The lift and the weight ratio of above-mentioned rotor craft are lower, and load capacity is very poor when being designed to micro air vehicle, have greatly restricted its application in every field.

Summary of the invention

The objective of the invention is existingly have vertical takeoff and landing and the lift force of the aircraft of the function of hovering is low and problem such as miniaturization load capacity deficiency, propose a kind of coaxial-inversion birotor eight-rotary wing aircraft with high load capacity for solving.

To achieve these goals, technical scheme of the present invention is as follows:

Coaxial-inversion birotor eight-rotary wing aircraft, comprise body, four hold-down arms, four birotors, alighting gear and electric-control systems, four hold-down arms are connected the periphery of body, the geometric center lines of four hold-down arms at grade, the geometric center lines angle of two adjacent hold-down arms is 90 °; Four birotors are separately positioned on the end of four hold-down arms, and alighting gear is connected on the body, and electric-control system is arranged in the body, control and connect four birotors.

Above-mentioned birotor is motor or the oily mechanism one-tenth that is connected rotor by two rotors with direct drive, each two-spool two gyroplane rotate speed is identical and hand of rotation is opposite, each one of two-spool two rotor is that one on positive oar is anti-oar, the lift direction that each two-spool two rotors rotation produces all makes progress, and motor or oily facility have two independent output shafts to connect each two-spool two rotor respectively.

Each birotor has been eliminated the loss in efficiency of driving system by motor or oily machine direct drive, has improved the lift force of energy utilization efficiency and aircraft.Each two-spool two gyroplane rotate speed is identical and hand of rotation is opposite, and the torque magnitude that body is produced equates but direction is opposite, therefore to body with torsional moment be zero, guaranteed the body attitude stabilization.Reduce the rotating speed of two rotors of a birotor simultaneously, aircraft is pointed to the direction flight of rotor along connecting this two-spool hold-down arm geometric center lines by body, reduce any two-spool rotating speed, fly before aircraft is finished, inverted flight, a left side flies and the right side flies.When reducing the rotating speed of adjacent two two-spool two rotors separately simultaneously, aircraft can fly to any direction along plane, hold-down arm geometric center lines place.Four birotors are installed in the end of four hold-down arms and the two ends that each two-spool two rotor is connected motor, the space availability ratio and the capacity usage ratio of aircraft have been improved, therefore aircraft of the present invention has high lift force and load capacity, has broad application prospects on dual-use.

Description of drawings

Fig. 1 is the structural representation of coaxial-inversion birotor eight-rotary wing aircraft of the present invention;

Fig. 2 is a dual-rotor structure scheme drawing of the present invention.

Among the figure, 1, body, 2, hold-down arm, 3, birotor, 4, alighting gear, 5, electric-control system, 301, first rotor, 302, second rotor, 303, driver train.

The specific embodiment

Below in conjunction with the drawings and specific embodiments the present invention is described in further detail.

As shown in Figure 1, coaxial-inversion birotor eight-rotary wing aircraft of the present invention, comprise: body 1, four hold-down arms 2 on being connected around the body 1, be separately positioned on four birotors 3 on each hold-down arm 2 end, be connected the alighting gear 4 on the body 1 and be arranged on the electric-control system 5 of each rotor of control linkage in the body 1, the geometric center lines of described four hold-down arms 2 at grade, the geometric center lines angle of two hold-down arms 2 that each is adjacent is 90 °.Described alighting gear 4 symmetries are connected on the body 1, and for aircraft provides support, rotor does not collide ground when protection aircraft takeoff and landing.

As shown in Figure 2, above-mentioned birotor 3 is to be made of first rotor 301, second rotor 302 are connected first rotor 301, second rotor 302 with direct drive driver train 303, driver train 303 is motor or oily machine, first rotor 301 and 302 1 of second rotors are that one on positive oar is anti-oar, and first rotor 301 and second rotor 302 are connected on two output shafts of driver train 303.

As depicted in figs. 1 and 2, the geometric center lines place plane parallel of the plane of rotation of first rotor 301 of each birotor 3 and second rotor 302 and four hold-down arms 2.

Claims

1. coaxial-inversion birotor eight-rotary wing aircraft, it is characterized in that, this aircraft comprises body (1), four hold-down arms (2), four birotors (3), alighting gear (4) and electric-control system (5), four hold-down arms (2) are connected the periphery of body (1), the geometric center lines of four hold-down arms (2) at grade, the geometric center lines angle of adjacent two hold-down arms (2) be 90 the degree; Four birotors (3) are separately positioned on the end of four hold-down arms (2), and alighting gear (4) symmetry is connected on the body (1), and electric-control system (5) is arranged in the body (1), control and connect four birotors (3).

2. coaxial-inversion birotor eight-rotary wing aircraft as claimed in claim 1, it is characterized in that, described birotor (3) is made up of first rotor (301), second rotor (302) and driver train (303), the rotating speed of first rotor (301) and second rotor (302) is identical and hand of rotation is opposite, driver train (303) is provided with two independent output shafts, connects first rotor (301) and second rotor (302) respectively.

3. coaxial-inversion birotor eight-rotary wing aircraft as claimed in claim 2 is characterized in that, described driver train (303) is motor or oily machine.

4. coaxial-inversion birotor eight-rotary wing aircraft as claimed in claim 1 or 2 is characterized in that, the plane of rotation of described first rotor (301) and second rotor (302) and the geometric center lines place plane parallel of described four hold-down arms (2).