Flapping aircraft autonomous takeoff control system and method

The technology of a flapping-wing aircraft and control method, which is applied in the field of flapping-wing aircraft, can solve problems such as involuntary take-off, and achieve the effects of reducing power, compact structure, and improving efficiency

Active Publication Date: 2018-08-03
UNIV OF SCI & TECH BEIJING
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the embodiment of the present invention is to solve the problem in the prior art that the flapping-wing aircraft must rely on hand-holding to launch and give initial speed, and proposes an autonomous take-off auxiliary system and autonomous take-off control method of the flapping-wing aircraft, which can get rid of the traditional flapping-wing aircraft take-off Involuntary predicament, use th

Method used

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  • Flapping aircraft autonomous takeoff control system and method
  • Flapping aircraft autonomous takeoff control system and method
  • Flapping aircraft autonomous takeoff control system and method

Examples

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no. 1 example

[0064] This embodiment provides an autonomous take-off assisting system for a flapping-wing aircraft, figure 1 It is a structural schematic diagram of the autonomous take-off auxiliary system of the flapping-wing aircraft in this embodiment. like figure 1 As shown, the autonomous take-off auxiliary system of the flapping wing aircraft described in this embodiment includes: remote control car 1, support 2, strain measuring device 3, vehicle speed measuring device 4, vehicle-mounted control board 5, airborne control board 6 ( figure 1 not shown in); among them,

[0065] The remote control car 1 is used to carry a support 2 , a strain measuring device 3 , a vehicle speed measuring device 4 , and a vehicle control panel 5 . figure 2 Shown is a schematic structural diagram of the remote control car described in this embodiment. like figure 2 As shown, the remote control car 1 has four installation holes a, b, c, d. In the actual preparation process, the remote control car is...

no. 2 example

[0083] This embodiment provides a control system for autonomous take-off of a flapping-wing aircraft, Figure 7 Shown is a schematic structural diagram of the autonomous take-off control system of the flapping-wing aircraft in this embodiment. like Figure 7 As shown, the autonomous take-off control system of the flapping-wing aircraft in this embodiment includes the autonomous take-off assisting system of the flapping-wing aircraft in the first embodiment, and also includes: a remote controller, a wireless receiver, the flapping-wing aircraft, and an attitude sensor. The wireless receiver here can be mounted on the remote control car for wireless communication with the remote control. The airborne control board is installed on the flapping-wing aircraft; the attitude sensor is installed on the flapping-wing aircraft.

[0084] Figure 8 Shown is a schematic diagram of the working principle of the autonomous take-off control system of the flapping-wing aircraft in this embod...

no. 3 example

[0086] This embodiment provides a control method for autonomous take-off of a flapping-wing aircraft, said method is realized based on the control system for autonomous take-off of the flapping-wing aircraft described in the second embodiment, Figure 9 It is a schematic flow chart of the autonomous take-off control method of the flapping-wing aircraft in this embodiment. Such as Figure 9 As shown, the autonomous take-off control method of the flapping wing aircraft of the present embodiment comprises the following steps:

[0087] Step S1, fix the flapping-wing aircraft on the remote control car, and preset the vehicle speed threshold for autonomous take-off and start of the flapping-wing aircraft.

[0088] Preferably, in this step, fixing the flapping-wing aircraft on the remote control car is further as follows:

[0089] The flapping wing aircraft is fixed on the beam of the remote control car through the magnetism generated by electrifying the electromagnet, and the comm...

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PUM

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Abstract

The invention provides a flapping aircraft autonomous takeoff control system and method. The system comprises a remote control trolley, a bracket, a strain measuring device, a vehicle speed measuringdevice, a vehicle control panel and an airborne control panel. According to the invention, the vehicle speed measuring device is used to precisely control the speed of the remote control trolley; thestrain measuring device is used to measure the stress state; the data are used to accurately acquire the state information before the takeoff of a flapping aircraft; the flapping aircraft gets rid ofthe dilemma of hand-held and involuntary takeoff of a traditional flapping aircraft, and realizes autonomous takeoff; a better initial flight state of the flapping aircraft is acquired; at a suitableflapping frequency, the combination of the trolley system and the aircraft system can reduce power and improve efficiency; and the auxiliary system provided by the invention has the advantages of compact structure, light weight, easy carrying and convenient installation, and is suitable for application in autonomous takeoff control of the flapping aircraft.

Description

technical field [0001] The invention belongs to the technical field of flapping-wing aircraft, and in particular relates to an autonomous take-off control system and method of the flapping-wing aircraft. Background technique [0002] In recent years, Flapping-wing aerial vehicles (Flapping-wing aerial vehicles), as a new type of bionic aircraft, are bionic robots manufactured by imitating the flight methods of insects and birds. It has low and significant advantages, and has broad application prospects in national defense, military and civilian fields. However, because the flapping wing aircraft cannot flap its wings and take off in situ like the birds in reality. Through the force analysis of the flapping-wing aircraft, the weight of the aircraft is 10mN greater than the maximum lift it can provide under static conditions, which means that it is difficult for the fuselage to take off directly from a static state on the ground to generate enough lift to achieve flight. Th...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/101
Inventor 贺威康业猛冯富森穆新星田淑芬李鸿一孙长银
Owner UNIV OF SCI & TECH BEIJING
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