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Launching system of unmanned aerial vehicle

A technology of unmanned aerial vehicle and nose, applied in the field of unmanned aerial vehicles, can solve problems such as difficulty in adjusting the attitude of unmanned aerial vehicles, and achieve the effects of easy engineering application, high safety and reliability, and reducing the number of times of attitude adjustment.

Active Publication Date: 2018-05-18
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] At present, the suspension mode of the UAV is generally a four-point suspension method, that is to say, the two double tail struts on both sides of the wing each have a suspension point, and the tail has two suspension points. Difficulty adjusting posture

Method used

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  • Launching system of unmanned aerial vehicle
  • Launching system of unmanned aerial vehicle

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Embodiment Construction

[0055] Compared with the four-point connection between the unmanned aerial vehicle and the fixed component in the prior art, there is a defect that it is difficult to adjust the launching posture of the unmanned aerial vehicle. The present invention provides a delivery system for the unmanned aerial vehicle. The UAV is a three-point connection, and the body is in a predetermined launch posture. When it is fixed, the UAV is in the predetermined launch posture. It is easier to keep the UAV in this posture when launching, reducing the number of times to adjust the posture. The speed gained after the release of the aircraft helps the aircraft attitude to level off quickly, reducing the transition process and ensuring the safety of the aircraft.

[0056] In order to make the purpose, technical solutions and advantages of the present disclosure clearer, the present disclosure will be further described in detail below in conjunction with specific embodiments and with reference to the ...

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Abstract

The invention provides a launching system of an unmanned aerial vehicle. The launching system comprises a fixing assembly used for hanging fixing of a to-be-launched unmanned aerial vehicle. The unmanned aerial vehicle comprises a nose and two wings. Hanging fixing is conducted in the mode that the fixing assembly is connected with the nose and the two wings so as to form three-point type connection, the nose faces the ground, and a vehicle body is in a predetermined launching posture. The fixing assembly of the launching system and the to-be-launched unmanned aerial vehicle are in three-pointtype connection, and the unmanned aerial vehicle is in the predetermined launching posture when fixed so that the unmanned aerial vehicle can be in the predetermined launching posture more easily when launched, and the number of posture adjusting times is decreased; meanwhile, through the posture, the speed can be further obtained advantageously after the aerial vehicle is released, rapid flareout of the posture of the aerial vehicle is facilitated, the transition process is reduced, and the safety of the aerial vehicle is ensured; and in addition, the launching system is simple in structure,high in safety and reliability, and convenient to apply in engineering.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a delivery system for unmanned aerial vehicles. Background technique [0002] Near-space UAVs have the characteristics of fast flight speed, wide coverage, long cruising time, and reusability, and have been widely demanded by the military in recent years. At present, there are two main ways for UAVs to enter the adjacent space: autonomous climbing and ball-borne take-off. The first method is that the UAV climbs to a predetermined cruising height by its own power plant. This method has relatively high requirements on the motor performance of the UAV, and in the case of a certain total energy, excessive energy consumption during the climb It will inevitably affect the subsequent cruising time; in addition, excessive energy demand also means that a more powerful power plant needs to be equipped, which will also increase the structural weight of the UAV itself and r...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64B1/00B64D5/00
CPCB64B1/00B64D5/00B64U70/20
Inventor 闫晓鹏户艳鹏周礼洋陈万里李珂曾冠南刘冠宇王翔宇
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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