CN108545180A - Gu it is a kind of it is more-- from rotor combined type unmanned vehicle - Google Patents

Abstract

The present invention relates to vehicle technology fields, specially a kind of how solid from rotor combined type unmanned vehicle, including fuselage：The fuselage upper end is provided with one group from rotor, the fuselage both sides are respectively arranged with one group of fixed-wing, two groups of propellers are respectively arranged on fixed-wing described in every group, the back body is provided with engine, the engine is connect with one group of thrust machine paddle, and the back body is also fixedly connected with one group of balance empennage；The fuselage lower end is additionally provided with one group of landing dress；The present invention is integrated by fixed-wing, more rotors, from rotor, is had the advantages that fixed-wing, more rotors, from three kinds of aircrafts of rotor, can be translated with positive and negative winged, hovering, left and right, scan-type flight.

Description

A multi-solid-rotor compound unmanned aerial vehicle

technical field

The invention relates to the technical field of aircraft, in particular to a multi-solid-rotor composite unmanned aerial vehicle.

Background technique

The autogyro is known as the "safest" small aircraft. Its flight principle is similar to that of a fixed-wing aircraft (high-speed propulsion makes it rely on the top autorotator to generate lift). It has the characteristics of large load capacity and fast flight speed, and its uses are becoming more and more It is of great significance to further improve its application range and reduce its use cost to make it "unmanned". However, since the flight principle of autogyro aircraft is similar to that of "fixed-wing" aircraft, it must have a certain taxiing runway (generally about 80 meters) for takeoff, and it cannot be lifted quickly when encountering obstacles such as trees and utility poles during low-altitude operations. , which limits its scope of application, and also makes it difficult to give full play to its advantages such as "large load and high speed" in the field of ultra-low altitude. The meaning of the purpose of the present invention is to reduce the sliding distance even close to zero, and when it encounters an obstacle and needs to climb up urgently, it can be pulled up rapidly, thereby making it suitable for ultra-low-altitude operations. At the same time, it has the characteristics of multi-rotor, that is, it can "translate" left and right, and by installing a clutch on the thrust paddle shaft, the thrust paddle can be reversed, so that the aircraft can realize "reverse scanning" flight.

Contents of the invention

The present invention overcomes the deficiencies of the above-mentioned prior art, and provides a multi-solid-rotor composite unmanned aerial vehicle. By integrating the fixed wing, the multi-rotor and the auto-rotor, the present invention has the advantages of the fixed-wing, multi-rotor and auto-rotor aircrafts, and can fly forward and backward, hover, move left and right, and fly in scanning mode.

Technical scheme of the present invention:

A multi-solid-rotary-wing composite unmanned aerial vehicle, including a fuselage: a group of self-rotating wings is arranged on the upper end of the fuselage, and a group of fixed wings are respectively arranged on both sides of the fuselage, and each group of fixed wings is respectively There are two sets of propellers, the rear end of the fuselage is provided with an engine, the engine is connected with a set of thrust propellers, and the rear end of the fuselage is also fixedly connected with a set of balance empennages; the lower end of the fuselage is also provided with a Group landing gear.

Further, the two sets of propellers are arranged symmetrically.

Further, the blades of the rotator are forward and reverse propellers or adjustable forward and reverse propellers.

Further, the blades of the thruster propellers are forward and reverse propellers or adjustable forward and reverse propellers.

Compared with the prior art, the present invention has the following beneficial effects:

The invention is an aircraft combined with fixed wing, multi-rotor and auto-rotor, which has the advantages of fixed-wing, multi-rotor and auto-rotor aircraft, and can fly forward and backward, hover, move left and right, and fly in scanning mode;

The propeller blades of the spin wing of the present invention are positive and negative paddles or adjustable positive and negative paddles, both of which generate lift;

Description of drawings

Fig. 1 is a structural representation of the present invention;

Fig. 2 is the front view of the present invention;

Figure 3 is a side view of the present invention.

In the figure 1-body; 2-rotor; 3-fixed wing; 4-propeller; 5-engine; 6-thrust propeller; 7-balanced tail; 8-take-off and landing gear.

Detailed ways

The present invention will be described in detail below in conjunction with the accompanying drawings.

Shown in conjunction with Fig. 1-Fig. 3, a kind of multi-solid-spin-rotor compound unmanned aerial vehicle disclosed in this embodiment comprises a fuselage 1: a group of spin-wings 2 are arranged on the upper end of the fuselage 1, and the two sides of the fuselage A group of fixed wings 3 are respectively arranged on each side, and two groups of propellers 4 are respectively arranged on each group of the fixed wings 3, and an engine 5 is arranged at the rear end of the fuselage 1, and the engine 5 is connected with a group of thrust propellers 6, The rear end of the fuselage 1 is also fixedly connected with a set of stabilizer fins 7 ; the lower end of the fuselage 1 is also provided with a set of take-off and landing devices 8 .

Specifically, two sets of propellers 4 are arranged symmetrically.

Specifically, the blades of the spinner 2 are forward and reverse propellers or adjustable forward and reverse propellers.

Specifically, the blades of the thrust paddle 6 are positive and negative paddles or adjustable positive and negative paddles

Working process of the present invention:

When the plane takes off, start the motor to drive the four propellers to rotate at high speed to provide enough lift for the plane to make the plane take off vertically. The rotor blades and fixed wings generate lift. As the forward flight speed of the aircraft further increases, the thrust increases rapidly. The multi-rotor propellers reduce the speed in time, and the lift provided gradually decreases. When flying forward, the rotor blades and fixed wings When the generated lift is sufficient to support the aircraft to fly horizontally, the multi-rotor propellers are completely stopped, and the aircraft relies entirely on the lift generated by the rotor blades and fixed wings to maintain a stable altitude flight. When the aircraft needs to hover, reduce the speed of the engine and cut off the power of the thrust propellers to open the speed brakes on the fixed wings, and at the same time start the motor at the right time to drive the multi-rotor propeller blades to rotate and gradually generate lift until the aircraft hovers stably at a certain height ; At this time, the aircraft can translate left and right under the action of the multi-rotor propeller blades. When the aircraft needs to fly backwards, the thrust paddles are reversed to generate pulling force through the "clutch" installed on the thrust paddle shaft to make the aircraft "fly backwards", and the flight process is the same as the forward flight. When the aircraft lands, the process is similar to hovering. At this time, the rotation speed of the multi-rotor propeller blades is gradually reduced to make the aircraft land smoothly, or it can taxi and land on the runway like an autogyro.

The above embodiments are only exemplary illustrations of this patent, and do not limit its protection scope. Those skilled in the art can also make partial changes to it, as long as they do not exceed the spirit and essence of this patent, they are all within the protection scope of this patent.

Claims (4)

1. A kind of multi-solid-spin-rotor composite unmanned aerial vehicle, comprises fuselage (1): it is characterized in that: described fuselage (1) upper end is provided with a group of spin-wings (2), described fuselage both sides A group of fixed wings (3) are respectively arranged, and two groups of propellers (4) are respectively arranged on the fixed wings (3) of each group, and an engine (5) is arranged at the rear end of the fuselage (1), and the engine ( 5) It is connected with a set of thrust propellers (6), and the rear end of the fuselage (1) is also fixedly connected with a set of balance empennages (7); the lower end of the fuselage (1) is also provided with a set of take-off and landing gear ( 8). 2. A kind of many-solid-spin-rotor composite unmanned aerial vehicle according to claim 1, is characterized in that, two groups of described propellers (4) are arranged symmetrically. 3. A kind of many-solid-spin-rotor composite unmanned aerial vehicle according to claim 1, is characterized in that, the blade of described spin-wing (2) is positive and negative paddle or adjustable positive and negative paddle. 4. A kind of multi-solid-rotor compound unmanned aerial vehicle according to claim 1, is characterized in that, the blade of described thrust propeller (6) is positive and negative paddle or adjustable positive and negative paddle.