Conventional layout aircraft flight path stability determination method and device

A technology of flight trajectory and determination method, which is applied in the field of aircraft, and can solve the problems of unstable flight trajectory and increased flight control burden, etc.

Active Publication Date: 2019-12-20
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
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  • Application Information

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Problems solved by technology

When an aircraft lands at a low altitude (arriving into a ship) or in a special low-altitude working environment, the flight tra...

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  • Conventional layout aircraft flight path stability determination method and device
  • Conventional layout aircraft flight path stability determination method and device
  • Conventional layout aircraft flight path stability determination method and device

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[0044] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the related application, not to limit the application. In addition, it should be noted that, for ease of description, only parts relevant to the present application are shown in the drawings.

[0045] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0046] figure 1 It is a schematic flowchart of a method for determining flight trajectory stability of a conventional layout aircraft provided in an embodiment of the present application.

[0047] Such as figure 1 As shown, the method includes the following steps:

[0048] Ste...

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Abstract

The invention provides a conventional layout aircraft flight path stability determination method and device, and the method comprises the steps: determining a steady-state attack angle of an aircraftunder the conditions of a given flight height and a given flight airspeed according to a condition that the direction sum external force in an airflow shafting is zero; substituting the steady-state attack angle into the pitching moment equation, and determining the steady-state elevator skewness of the aircraft based on the condition that the pitching moment is equal to zero; substituting the steady-state attack angle and the steady-state elevator skewness into a resistance balance equation, and determining a steady-state track inclination angle of the aircraft; determining different steady-state track inclination angles according to different flight airspeeds, and drawing a track inclination angle and airspeed curve; solving the derivative of the track inclination angle to the airspeed at different flight airspeeds on the track inclination angle and airspeed curve; and determining the flight path stability characteristics of the aircraft at different flight airspeeds according to thederivative of the flight path inclination angle to the airspeed at different flight airspeeds.

Description

technical field [0001] The present application relates to the field of aircraft technology, and specifically provides a method and device for determining flight trajectory stability of an aircraft with a conventional layout. Background technique [0002] The rationality of aircraft flight trajectory stability design directly affects the flight safety and flight control characteristics of the aircraft, especially when the aircraft lands at low altitude (arrives into the ship) or flies in a special low-altitude working environment. When an aircraft lands at a low altitude (arriving into a ship) or in a special low-altitude working environment, the flight trajectory of the aircraft is unstable, and the pilot controls the aircraft blindly, which greatly increases the burden of flight control. Contents of the invention [0003] In order to solve at least one of the above technical problems, the present application provides a method and device for determining flight trajectory s...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 武虎子姚海林刘岳锋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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