Hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and flight control method thereof

A vertical take-off and landing, hybrid power technology, applied in the aviation field, can solve the problems of high empty weight ratio, power surplus, and short battery life of the tail-sitting UAV, and achieve the weight reduction of the power system and the fuel consumption rate. Low, the effect of improving the load capacity

Active Publication Date: 2017-08-25
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the tilting power UAV, since a set of power system is used to provide vertical take-off and landing lift and horizontal flight pulling force respectively, the power required for vertical take-off and landing is usually the largest, while the power required for fixed-wing cruise flight is the largest. Smaller, so the power and weight of its power plant a

Method used

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  • Hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and flight control method thereof
  • Hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and flight control method thereof
  • Hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and flight control method thereof

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Embodiment approach 1

[0025] This embodiment is a hybrid power tail-sitting vertical take-off and landing long-endurance UAV with a design take-off weight of 30kg. This embodiment includes a fuselage 1, a main drive motor 3 installed on the head of the fuselage, and a The main tension propeller 2 folded towards the rear of the fuselage, the large aspect ratio wing 4 is installed in the middle of the fuselage, and the outer aileron 5 and the inner flaperon 6 are arranged on it. The piston engine 10 and the ducted propeller system 9 driven by it are installed at the rear of the fuselage, the horizontal tail 7 and the vertical tail 8 are installed on the duct, and the elevator 11 and the rudder 12 are respectively installed on it, and a part of the deflection rudder surface is in the duct. Inboard propeller slipstream coverage area.

[0026] Fuselage 1 contains the main drive motor battery, fuel oil tank, mission load and necessary flight instruments and equipment, etc., and is designed in a cylindric...

Embodiment approach 2

[0030] This embodiment is a hybrid power tail-sitting vertical take-off and landing long-endurance UAV with a design take-off weight of 30kg. This embodiment includes a fuselage 1 and two main drives mounted on the wings. Motor 3 and main tension propeller 2, large aspect ratio wing 4 are installed in the middle of the fuselage, and outer aileron 5 and inner flaperon 6 are arranged on it. The piston engine 10 and the ducted propeller system 9 driven by it are installed at the rear of the fuselage, the horizontal tail 7 and the vertical tail 8 are installed on the duct, and the elevator 11 and the rudder 12 are respectively installed on it, and a part of the deflection rudder surface is in the duct. Inboard propeller slipstream coverage area.

[0031] The present embodiment fuselage, wing, empennage, piston engine and ducted propeller system are the same as embodiment one, the difference is that there are two main drive motors and they are installed on the wing. The diameter o...

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Abstract

The invention provides a hybrid power tail sitting type vertical takeoff and landing long-endurance unmanned aerial vehicle and a flight control method thereof. The unmanned aerial vehicle comprises a fuselage, wings, a main driving motor, propellers, a piston power ducted propeller and tail wings mounted on a duct. According to the invention, two sets of power systems, namely a motor and a piston engine, are adopted; in a vertical takeoff and landing stage which is short in time and requires large power, the motor serves as driving power, the advantage of high power-weight ratio of the motor can be fully exerted, and thus the weight of the power systems is reduced; in a cruising flight stage, the tail piston engine and the ducted propeller system driven by the tail piston engine drive the unmanned aerial vehicle to fly forward, and the piston power and the ducted propeller system can be selected and designed according to the optimal cruising state without considering the vertical takeoff and landing state, so that the fuel consumption rate of the cruising state can be effectively reduced; in combination with high-aspect-ratio wings, long-time flight of the unmanned aerial vehicle can be ensured; and meanwhile, because the weight of the power systems is reduced, the empty weight ratio of the unmanned aerial vehicle can be reduced, and the loading capacity of the unmanned aerial vehicle can be effectively improved.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a hybrid tail-sitting vertical take-off and landing long-endurance unmanned aerial vehicle and a flight control method thereof. Background technique [0002] Based on the development situation at home and abroad, there are many forms of vertical take-off and landing fixed-wing UAVs, one of which is the tilting power type, which uses the thrust and pull generated by the power to support the weight of the aircraft during vertical take-off and landing. The power tilt is used as the driving force for forward flight, and the power is generally a rotor, a propeller or a ducted fan. These can be subdivided into three categories: one is to install the power on the fuselage or wing, and simply tilt the power, such as the American unmanned tilt-rotor UAV "Hawkeye", the Israeli Aircraft Industry Company's "Hawkeye" Panther" tilting propeller UAV, etc.; one type is to install the power on...

Claims

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Application Information

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IPC IPC(8): B64C29/00B64C29/02
CPCB64C29/0025B64C29/02B64U50/11B64U10/25B64U30/20B64U50/19B64U50/14B64U50/13
Inventor 邓阳平田力高正红
Owner NORTHWESTERN POLYTECHNICAL UNIV
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