Aircraft with horizontal take-off and landing and vertical take-off and landing functions

Abstract

The invention discloses an aircraft which comprises an aircraft body, wings, an empennage, a main propeller, an oil-drive piston engine, secondary propellers, driving components and servo mechanisms, wherein an undercarriage is arranged on the aircraft body; the wings are arranged on the left side and the right side of the aircraft body; the empennage is arranged at the tail part of the aircraft body; the main propeller is arranged on the aircraft body or the wings; four secondary propellers are divided into two groups; each group comprises two secondary propellers; the first group of the secondary propellers are arranged on the wing on the left side of the aircraft body; the two secondary propellers of the first group of the secondary propellers are connected through a first connecting rod; the second group of the secondary propellers are positioned on the wing on the right side of the aircraft body; the two secondary propellers of the second group of the secondary propellers are connected through a second connecting rod; the servo mechanisms are arranged on the wings to drive the first connecting rod and the second connecting rod to rotate. By adopting the aircraft disclosed by the embodiment of the invention, the problems that a conventional aircraft is large in difficulty in the vertical take-off and landing and level flight process, hard in power system matching and large in coupling control difficulty can be solved.

Description

Technical field [0001] The present invention relates to the field of aviation technology, in particular to an aircraft with horizontal take-off and landing and vertical take-off and landing functions. Background technique [0002] Vertical take-off and landing aircraft generally refer to a type of aircraft that can take off and land vertically like a helicopter, has the ability to hover, and can fly as a fixed-wing aircraft. Compared with traditional helicopters, it has a higher flight speed and longer range, and has low dependence on take-off and landing sites compared with traditional fixed-wing aircraft. The above-mentioned advantages make the vertical take-off and landing aircraft have important application value in military and civilian use. [0003] Vertical take-off and landing UAVs face many difficulties, mainly in the following aspects: [0004] 1. The process of vertical to horizontal flight is difficult [0005] The conversion process from vertical take-off and landing to...

AI Technical Summary

Problems solved by technology

[0008] 2. It is difficult to match the power system

[0009] The vertical take-off and landing aircraft requires the engine to have sufficient thrust-to-weight ratio in the vertical take-off and landing stage, while the wings provide the main lift in the horizontal flight stage, and the lift-drag ratio is relatively high. The thrust required by the engine is much smaller than that in the vertical take-off and landing stage. It has good work efficiency under all kinds of working conditions, which restricts the actual application

[0010] When the propeller works at high speed in the vertical take-off and landing stage, and the vertical ascent speed is not high, the small-pitch propeller has higher efficiency, but it works at low speed in the level flight stage, and it is often necessary to increase the propeller when flying forward at high speed. It is difficult for ordinary fixed-pitch propellers to adapt to the difference between the two states. To take into account the two flight states, special design of the propeller is required.

[0011] In order to achieve high power output of the power system in a short period of time during vertical take-off and landing, a motor with a high power-to-weight ratio is often the first choice, but the energy density of the battery limits the battery life of the electric aircraft. The fuel engine can guarantee the battery life, but when flying horizontally The required power is small, causing the engine and its auxiliary equipment to die heavily, and there are also disadvantages of poor reliability. The slow response speed of the oil-operated piston engine makes it difficult to adapt to the precise control during vertical take-off and landing and hovering

[0012] The above problems lead to the difficulty in matching the power system of vertical take-off and landing aircraft. It is necessary to comprehensively consider various factors, establish an optimization model, and find a suitable power configuration or power combination for a specific aircraft.

[0013] 3. Coupling control is difficult

Due to the aerodynamic interference between the propeller and the fuselage, wings and other components, this interference has different effects on flight control in different flight states, and the design of the control system becomes complicated

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