Vertical-takeoff auxiliary system for fixed-wing aircraft

Abstract

The invention provides a vertical-takeoff auxiliary system for a fixed-wing aircraft. The vertical-takeoff auxiliary system comprises a multi-shaft rotor-wing aircraft and a fixed-wing aircraft. A plurality of throwing devices are installed in the middle of the fuselage bottom of the multi-shaft rotor-wing aircraft, and a plurality of hanging parts are installed in the fuselage middle of the fixed-wing aircraft; the hanging parts are connected with the throwing devices in a hung mode, and the fixed-wing aircraft is hung below the multi-shaft rotor-wing aircraft accordingly; the multi-shaft rotor-wing aircraft carries the fixed-wing aircraft to vertically take off to the preset height and the preset speed, then the throwing devices release the hanging parts, and the fixed-wing aircraft is separated from the multi-shaft rotor-wing aircraft to autonomously fly. By means of the vertical-takeoff auxiliary system in the mode, vertical takeoff of the fixed-wing aircraft can be achieved under the condition that an existing fixed-wing aircraft does not need to be greatly modified.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off auxiliary system for a fixed-wing aircraft. Background technique [0002] The fixed-wing aircraft utilizes the pressure difference generated on the upper and lower surfaces of the wings to obtain lift when it flies fast, and takes off against gravity. Therefore, it must reach the take-off speed before it takes off. Fixed-wing aircraft have long range, fast speed, and low fuel consumption. Once they lose power, they still have a chance to reduce the speed of descent by gliding to reduce crash losses. However, the disadvantage of fixed-wing aircraft is that it needs a very long runway to take off. [0003] Thus, people began to study the take-off assist device of fixed-wing aircraft. For example, the fixed-wing aircraft is launched in the air by the helicopter carrier, but the disadvantages of this method are mainly: 1) the pylons of the helic...

AI Technical Summary

Problems solved by technology

However, the disadvantage of fixed-wing aircraft is that it needs a long runway to take off

Disadvantages of this method: 1) When taking off vertically, the wing remains horizontal, and a part of the area of ​​the paddle disc overlaps with the wing, so that the lift force of the paddle disc is partially offset, which reduces the efficiency of the paddle and increases power consumption; 2) The engine and power system are installed on the tip of the wing, forming a cantilever beam structure with a large tip load and weight, which makes the structure very prone to vibration. To reduce vibration, the structure must be strengthened, which will greatly increase the weight of the structure. At the same time Limit the aspect ratio of the main wing; 3) The aerodynamic efficiency of the main wing, that is, the lift-to-drag ratio is low

Due to the limitation of the layout, the aspect ratio of the main wings of this scheme is relatively small, which makes the lift and drag of the whole aircraft relatively small, which will increase fuel consumption and reduce the range. Therefore, although the range of this type of aircraft is greater than that of helicopters, it is still Much smaller than the conventional layout aircraft of the same level; 4) When this type of aircraft adopts taxiing take-off mode, the propeller cannot be completely placed in the horizontal position because the blades are too long, which will limit the maximum take-off weight in the taxiing mode; 5) When the aircraft takes off with a short-distance roll, if the take-off speed is too low, it may not be able to take off due to the insufficient rudder effect provided by the tail, which restricts its minimum take-off distance and ground speed in the short-distance take-off mode

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