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Aircraft flight performance algorithm based on linearized incremental equation

An incremental equation and flight performance technology, applied in the field of aviation flight, can solve problems such as poor solution stability, achieve the effect of improving algorithm stability, efficient and stable calculation, and avoiding divergence problems

Active Publication Date: 2020-10-13
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0022] This patent document discloses a fast frequency-domain identification method for flight experiment data suitable for fly-by-wire helicopters. According to the characteristics of different convergence speeds of each parameter to be identified, an accelerated optimization algorithm is designed to improve the calculation efficiency, but the solution stability is poor. Applicable to application scenarios that require high stability and timeliness

Method used

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  • Aircraft flight performance algorithm based on linearized incremental equation
  • Aircraft flight performance algorithm based on linearized incremental equation
  • Aircraft flight performance algorithm based on linearized incremental equation

Examples

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Effect test

Embodiment 1

[0079] see Figure 1-Figure 5 , an aircraft flight performance algorithm based on a linearized incremental equation, comprising the following steps:

[0080] a. Linearization of nonlinear dynamic equations

[0081] Linearize the nonlinear dynamic equation to obtain a linear incremental equation. For the equation described in the analytical form, Taylor series expansion is performed at the reference state point, and the first-order reciprocal is retained; for the kinetic equation described in the form of discrete data, the numerical value is used. The algorithm is linearized; the dynamic characteristics are described through the linearized incremental equation;

[0082] b. Determine calculation conditions and output;

[0083] Determine the known conditions and unknown quantities according to the solved flight performance parameters, and process the known quantities into incremental forms as the input of the equation;

[0084] c. Use the linearized incremental equation to sol...

Embodiment 2

[0090] see Figure 1-Figure 5 , an aircraft flight performance algorithm based on a linearized incremental equation, comprising the following steps:

[0091] a. Linearization of nonlinear dynamic equations

[0092] Linearize the nonlinear dynamic equation to obtain a linear incremental equation. For the equation described in the analytical form, Taylor series expansion is performed at the reference state point, and the first-order reciprocal is retained; for the kinetic equation described in the form of discrete data, the numerical value is used. The algorithm is linearized; the dynamic characteristics are described through the linearized incremental equation;

[0093] b. Determine calculation conditions and output;

[0094] Determine the known conditions and unknown quantities according to the solved flight performance parameters, and process the known quantities into incremental forms as the input of the equation;

[0095] c. Use the linearized incremental equation to sol...

Embodiment 3

[0105] see Figure 1-Figure 5 , an aircraft flight performance algorithm based on a linearized incremental equation, comprising the following steps:

[0106] a. Linearization of nonlinear dynamic equations

[0107] Linearize the nonlinear dynamic equation to obtain a linear incremental equation. For the equation described in the analytical form, Taylor series expansion is performed at the reference state point, and the first-order reciprocal is retained; for the kinetic equation described in the form of discrete data, the numerical value is used. The algorithm is linearized; the dynamic characteristics are described through the linearized incremental equation;

[0108] b. Determine calculation conditions and output;

[0109] Determine the known conditions and unknown quantities according to the solved flight performance parameters, and process the known quantities into incremental forms as the input of the equation;

[0110] c. Use the linearized incremental equation to sol...

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Abstract

The invention discloses an aircraft flight performance algorithm based on a linearized incremental equation. The invention belongs to the technical field of aviation flight. The method comprises the following steps: a, performing linearization of a nonlinear kinetic equation: performing linearization processing on the nonlinear kinetic equation to obtain a linear increment equation, performing Taylor series expansion on an equation described in an analysis form at a reference state point, and reserving a first-order reciprocal; linearizing a kinetic equation described in a discrete data form by adopting a numerical algorithm; carrying out dynamic characteristic description through a linearized incremental equation; b, determining calculation conditions and output; c, solving an unknown quantity by utilizing a linearized increment equation; and d, solving performance characteristic parameters. According to the method, efficient and stable calculation of the performance data can be realized, and the method can be applied to various application scenes with relatively high requirements on timeliness and stability.

Description

technical field [0001] The invention relates to the technical field of aviation flight, in particular to an aircraft flight performance algorithm based on a linearized incremental equation. Background technique [0002] The prior art solves the aircraft flight performance based on nonlinear, full-scale aircraft particle dynamics and kinematic equations. such as formula Among them: α is the angle of attack; V is the flight speed; T is the thrust, which is generally a function of engine speed, altitude, and flight Mach number, that is, T=T f (n, h, M), n is the engine speed, h is the flight altitude, M is the flight Mach number; D is the resistance; L is the lift; is the angle between the thrust action line and the reference line of the aircraft angle of attack; θ is the inclination angle of the flight path; m=G / g——mass, kg; G is gravity, N; g is the acceleration due to gravity, m / s 2 ; h is the altitude; L is the range, the horizontal distance; q h is the hourly fue...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F111/10G06F119/14
CPCG06F30/15G06F2111/10G06F2119/14
Inventor 李锐黄楚云韩锐闫林明夏斌冯宇鹏李阳李涛陈斌
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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