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Aircraft system based on missile power propulsion

An aircraft system and power system technology, applied in aircraft parts, aircraft power units, military equipment configuration, etc., to achieve the effects of small impact, increased power reserve and redundancy, and shortened take-off and landing distance

Pending Publication Date: 2021-02-12
西安忠林世纪电子科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The technology of using the power on the missile to boost the flight of the aircraft has not yet been applied

Method used

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  • Aircraft system based on missile power propulsion
  • Aircraft system based on missile power propulsion
  • Aircraft system based on missile power propulsion

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Embodiment Construction

[0019] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0020] refer to figure 1 , figure 2 , image 3 and Figure 4 , a kind of aircraft system based on missile power propulsion that the present invention proposes, and described missile power propulsion aircraft is comprised of fuselage 100, wing 101 and aircraft flight control system 110 inside fuselage 100, missile power system 120, missile flight control system 130 and a switcher 140; the wings 101 are arranged on both sides of the fuselage 100, and the missile 102 is installed on the wing 101 or the fuselage 100; the missile 102 is fixed on the wing 101 and the multi-rotor by mounting 101-1 on.

[0021] refe...

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PUM

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Abstract

The invention discloses an aircraft system based on missile power propulsion. A missile power propulsion aircraft is composed of an aircraft body, wings, an aircraft flight control system, a missile power system, a missile flight control system and a switcher, wherein the aircraft flight control system, the missile power system, the missile flight control system and the switcher are arranged in the aircraft body. When an aircraft flight power control network of the aircraft flight control system is connected with the missile power system, and when the aircraft flight power control network of the aircraft flight control system is connected to the missile power system, the whole system works in a missile power propulsion state; the aircraft flight control system controls the power of the missile, the power of the missile is used for helping the aircraft to take off quickly, and when the power of the aircraft breaks down, the power of the missile can help the aircraft to keep the flight height emergently. Through reuse of the thrust of the missile, the aircraft is helped to achieve power backup, and when the main engine of the aircraft breaks down, the aircraft is helped to break awayfrom a dangerous stall state, and the thought of reuse of missile power is achieved.

Description

technical field [0001] The invention relates to the technical field of missile propulsion, in particular to an aircraft system based on missile power propulsion. Background technique [0002] Aircraft with strike capability have missiles hung on the wings or belly, and the missiles are generally powered. But at present, the power of the missile is generally only activated when the missile is launched, which does not help the take-off and flight of the aircraft. For aircraft, missiles affect aerodynamic resistance, which has a negative impact on aircraft endurance and speed improvement. In addition, there are aircraft that use rocket-assisted technology to take off. A rocket engine is attached to the fuselage of the aircraft. When the aircraft takes off, the rocket engine is started at the same time. Accelerate, thereby shortening the takeoff roll distance. But these booster rockets are dedicated rockets that will be jettisoned after takeoff. The technology of using the p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/02B64D31/00B64D7/00
CPCB64D7/00B64D27/02B64D31/00
Inventor 李长琦
Owner 西安忠林世纪电子科技有限公司
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