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Aircraft with anti-crash function after aerodynamic configuration damage

An aerodynamic shape, aircraft technology, applied in the field of aircraft, can solve problems such as scrapping, aircraft falling, the remote controller cannot control the aircraft, etc., and achieve the effect of avoiding damage

Active Publication Date: 2021-03-26
成都飞航智云科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention provides an aircraft with a crash prevention function after the aerodynamic shape is damaged to solve the problem that at present, when the aerodynamic shape of the aircraft is damaged, the aircraft will lose control, the remote control can no longer control the aircraft, and the aircraft will often fall and cause damage , even scrapping the problem

Method used

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  • Aircraft with anti-crash function after aerodynamic configuration damage
  • Aircraft with anti-crash function after aerodynamic configuration damage
  • Aircraft with anti-crash function after aerodynamic configuration damage

Examples

Experimental program
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Effect test

Embodiment 1

[0033] Such as figure 1 , figure 2 , image 3 and Figure 4 As shown, a kind of aircraft with anti-crash function after the aerodynamic appearance is damaged, comprises: the aircraft includes remote controller 4, fuselage 6 and wing 7, and the surface of fuselage 6 and wing 7 are all provided with pressure sensor, fuselage The control center system 1, the power control system 2 and the auxiliary control system 3 are installed in the 6, the control center system 1 is wirelessly connected with the remote controller 4, and the control center system 1 is respectively connected with the pressure sensor, the power control system 2 and the auxiliary control system 3;

[0034] The power control system 2 includes a ducted propeller 8 and a driving motor used in conjunction with the ducted propeller 8, one end of the wing 7 is connected to the fuselage 6, and the other end is connected to the ducted propeller 8; the auxiliary control system 3 includes a side hatch 9 and The auxiliar...

Embodiment 2

[0049] Embodiment 2 is a further optimization of Embodiment 1.

[0050] Such as figure 2 As shown, a storage battery 5 is also installed in the fuselage 6, and the storage battery 5 is respectively connected with the control center system 1, the power control system 2 and the auxiliary control system 3. The accumulator 5 provides power for the aircraft.

[0051] Such as Figure 5 As shown, the side hatch 9 includes an upper fixed hatch 18, an upper action hatch 19, a lower fixed hatch 20, a lower action hatch 21 and a limiting device 22, and one end of the upper fixed hatch 18 is fixedly connected with the fuselage 6, The other end is movably connected with the upper action hatch 19, and one end of the lower fixed hatch 20 is fixedly connected with the end of the fuselage 6 away from the upper fixed hatch 18, and the other end is movably connected with the lower action hatch 21, and the upper action hatch 19 is away from the upper end. One end of the fixed hatch 18 matches...

Embodiment 3

[0056] Embodiment three is a further optimization of embodiment two.

[0057] Drive motor is connected with ducted propeller 8.

[0058] The control center system 1 is connected with the remote controller 4 through wireless data transmission, and receives the control signal sent by the remote control terminal. The control center system 1 is connected with the power control system 2 through the data line, and sends flight instructions to the drive motor, and then controls the ducted propeller. 8 rotation directions and rotation speeds to achieve different specified flight attitudes.

[0059] The control center system 1 is connected to the auxiliary control system 3 through a data line, and calculates the surface airflow data detected by the pressure sensor as a closed-loop feedback signal and the control signal sent by the remote controller 4, and sends the calculation result to the auxiliary control system 3, Thereby the auxiliary control system 3 controls the paraglider 16 t...

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Abstract

The invention provides an aircraft with an anti-crash function after aerodynamic configuration damage. The aircraft comprises a remote controller, an aircraft body and wings, pressure sensors are arranged on the surface of the aircraft body and the surfaces of the wings, a control center system, a power control system and an auxiliary control system are installed in the aircraft body, and the control center system is in wireless connection with the remote controller. The control center system is connected with the pressure sensor, the power control system and the auxiliary control system. Theauxiliary control system comprises a side cabin door and an auxiliary flight device arranged behind the side cabin door, and the auxiliary flight device is a paraglider; the auxiliary control system is used for receiving working signals to control the side cabin door to be opened and the paraglider to extend out, and the paraglider, the fuselage and the wings form a gliding structure. The problemsthat at present, after the aerodynamic configuration of an aircraft is damaged, the aircraft loses control, a remote controller cannot control the aircraft any more, and the aircraft often falls downto be damaged and even scrapped are solved.

Description

technical field [0001] The invention relates to the technical field of aircraft, and more particularly relates to an aircraft with a crash prevention function after the aerodynamic shape is damaged. Background technique [0002] With the development trend of integration and miniaturization of unmanned aerial vehicles, micro air vehicles have gradually highlighted their performance advantages and become an important tool for many applications such as long-range cruise, intelligence acquisition, high-altitude aerial photography, monitoring and search and rescue. Research on micro air vehicles mainly includes structural design, aerodynamic performance, autonomous control, intelligent navigation, advanced materials, etc. Among them, the unique structural design and autonomous flight control strategy have become an important method and effective means to improve the flight stability of the aircraft. [0003] At present, when the aerodynamic shape of the aircraft is damaged, the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D17/80B64D17/54B64D45/00B64C39/02
CPCB64D17/80B64D17/54B64D45/00B64C39/024B64U2201/20
Inventor 薛令德
Owner 成都飞航智云科技有限公司
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