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Fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof

A technology of unmanned aerial vehicles and fixed wings, which is applied in the field of unmanned aerial vehicles, can solve problems such as limiting the performance of unmanned aerial vehicles, and achieve the effects of low requirements for take-off and landing environments, simplified systems, and simple systems

Pending Publication Date: 2018-08-14
成鑫
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Stall landing is suitable for drones with a small weight. Generally, the take-off weight does not exceed 5kg. For drones that use parachuting, there is no strict requirement on the weight, but the parachute is a useless mass during flight, which limits the performance of the drone.

Method used

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  • Fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof
  • Fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof
  • Fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof

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Embodiment Construction

[0051] The present invention will be described in further detail and completely below in conjunction with the embodiments and accompanying drawings.

[0052] Basic knowledge introduction:

[0053] Thrust-to-weight ratio: Thrust-to-weight ratio is an important technical performance index of aircraft and aeroengines. It is the ratio of aircraft engine thrust to engine gravity or aircraft gravity, which indicates the thrust generated by aircraft engine or aircraft unit gravity. The ratio of the thrust produced by an aircraft engine at its maximum state (the afterburner engine is in the full afterburner state) to the weight of the engine structure under static conditions at sea level is called the thrust-to-weight ratio of the aircraft engine.

[0054] Stall Landing: A stall is a condition in which an aircraft or wing operates at an angle of attack greater than the maximum lift angle of attack, and is characterized by separation of the airflow, making it impossible to maintain fli...

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Abstract

The invention provides a fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof. A multi-engine combined power form is adopted. The takeoff method of the unmanned aerial vehicle comprises the steps before takeoff, in a takeoff process, in a level flight process and the like. The landing method of the unmanned aerial vehicle comprises the steps of gliding and landing, stalling and descending, touching the ground and landing and the like. The fixed-wing unmanned aerial vehicle provided by the invention has the advantages that hand throwing takeoff of the unmanned aerial vehicle with relatively great takeoff weight can be realized, and auxiliary power in the takeoff process can be used for assisting the takeoff and also can be used for assisting landing; the system is simple; the performance of the unmanned aerial vehicle is improved; a takeoff and landing manner has strong adaptability; the scheme has relatively low requirements on a takeoff and landing environment and almost can realize takeoff and landing on any field.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and relates to a fixed-wing unmanned aerial vehicle and a take-off and landing method thereof. Background technique [0002] With the rapid development of multi-rotor UAVs and the continuous expansion of the scope of application, the potential of multi-rotor UAVs has been continuously explored, from civilian fields such as inspections, surveys, and logistics to military fields such as battlefield reconnaissance. For fixed-wing unmanned aerial vehicles, its take-off and landing methods have certain restrictions on its application. For example, aircraft that need to taxi to take off have higher requirements on the venue. The emergence of multi-rotor UAVs provides a UAV solution without a runway, but its application is limited due to its endurance and flight speed. [0003] The traditional fixed-wing aircraft has the advantages of high flight efficiency, fast speed, long distance, ...

Claims

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Application Information

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IPC IPC(8): B64C39/02B64D27/02
CPCB64C39/02B64D27/023B64U70/00B64U10/25
Inventor 成鑫
Owner 成鑫
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