Aircraft attitude control method and system under high-altitude condition based on numerical simulation

A numerical simulation and attitude control technology, applied in the field of aircraft control, can solve the problem of high calculation cost, achieve the effect of reducing the number of iteration steps, efficient control, and saving calculation time

Active Publication Date: 2022-05-06
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, to obtain a high-precision aerodynamic force/moment curve that varies with the angle of attack/sideslip angle, several o

Method used

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  • Aircraft attitude control method and system under high-altitude condition based on numerical simulation
  • Aircraft attitude control method and system under high-altitude condition based on numerical simulation
  • Aircraft attitude control method and system under high-altitude condition based on numerical simulation

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Embodiment 1

[0039] Please refer to figure 1 , figure 1 It is a schematic flow chart of an aircraft attitude control method based on numerical simulation under high-altitude conditions. Embodiment 1 of the present invention provides a numerical simulation-based aircraft attitude control method under high-altitude conditions. The method includes:

[0040] Step 1: Obtain aircraft shape information and N calculation states related to the aircraft. The N calculation states are respectively calculation state 1 to calculation state N. Each calculation state includes the following parameters: aircraft altitude, flight Mach number, aircraft Angle of attack and sideslip angle of the aircraft, where, when the angle of attack of the aircraft is a variable, the angles of attack corresponding to the N calculation states are: , , ,…and , the angle of attack interval is ; When the sideslip angle of the aircraft is a variable, the sideslip angles corresponding to the N calculation states are: ...

Embodiment 2

[0072] Embodiment 2 of the present invention provides a numerical simulation-based aircraft attitude control system under high-altitude conditions, the system comprising:

[0073] The calculation state obtaining unit is used to obtain the shape information of the aircraft and N calculation states related to the aircraft. The N calculation states are respectively calculation state 1 to calculation state N. Each calculation state includes the following parameters: aircraft height, flight Mach number, aircraft angle of attack, and aircraft sideslip angle, where, when the aircraft angle of attack is a variable, the angles of attack corresponding to the N calculation states are: , , ,…and , the angle of attack interval is ; When the sideslip angle of the aircraft is a variable, the sideslip angles corresponding to the N calculation states are: , , ,…and , and the sideslip angle interval is ;

[0074] The physical space grid acquisition unit is used to construct t...

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Abstract

The invention discloses an aircraft attitude control method and system under a high-altitude condition based on numerical simulation, and relates to the field of aircraft control, and the method comprises the steps: obtaining the shape information of an aircraft and N calculation states related to the aircraft, and obtaining a physical space grid of the aircraft; constructing a first flow field based on the incoming flow condition, and calculating the calculation state 1 based on the first flow field and the physical space grid to obtain a corresponding aerodynamic coefficient or aerodynamic torque coefficient; according to the sequence of the calculation states, calculating the calculation state 2 to the calculation state N in sequence to obtain corresponding aerodynamic coefficients or aerodynamic moment coefficients, and based on the aerodynamic coefficients or aerodynamic moment coefficients corresponding to all the calculation states, obtaining aircraft aerodynamic or aerodynamic moment static derivatives under corresponding aircraft heights and flight Mach numbers; the aircraft control system performs real-time control on the aircraft attitude based on the aircraft aerodynamic force or aerodynamic moment static derivative. According to the method, the calculation cost of numerical simulation in aircraft attitude control is reduced.

Description

technical field [0001] The invention relates to the field of aircraft control, in particular to a numerical simulation-based aircraft attitude control method and system under high-altitude conditions. Background technique [0002] In the construction of aircraft installed aerodynamic database and many engineering applications, it is necessary to obtain the expression of aerodynamic force / moment through modeling, and it is very important to give the correct static derivative of force / torque in this process. Taking the static derivative of the pitching moment as an example, the static derivative is usually defined as the rate of change of the pitching moment with the angle of attack. The static derivative of the pitching moment at the aircraft's equilibrium position is negative, indicating that the aircraft has longitudinal static stability, which means that when the aircraft deviates from the equilibrium position by a small angle, the effect of the pitching moment is toward t...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/23G06F113/08G06F119/14
CPCG06F30/15G06F30/23G06F2119/14G06F2113/08Y02T90/00
Inventor 江定武李锦王沛万钊郭勇颜毛枚良黎昊旻
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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