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An aircraft gravity envelope calculation method

A calculation method and aircraft technology, applied in calculation, special data processing applications, instruments, etc., to achieve the effect of simple process, convenient calculation and accurate calculation

Pending Publication Date: 2019-05-03
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, the existing research on the envelope of the center of gravity of the aircraft lacks a more accurate calculation method for the envelope of the center of gravity of the aircraft

Method used

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  • An aircraft gravity envelope calculation method
  • An aircraft gravity envelope calculation method
  • An aircraft gravity envelope calculation method

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Embodiment Construction

[0020] The present invention will be further described below in conjunction with the accompanying drawings.

[0021] Such as figure 1 Shown is a method for calculating the envelope of the center of gravity of an aircraft, including the following steps:

[0022] Step 1: Input the original parameters of the aircraft and the limit of the control range, given the loading situation and the initial center of gravity position;

[0023] Step 2: Calculate the aerodynamic force and aerodynamic moment of the aircraft according to the aircraft aerodynamic model, landing gear model, engine model, and overall flight mechanics model, and complete the trimming;

[0024] Step 3: Constraint 1: According to the trim results, judge whether the control amount obtained by trimming exceeds the limit of the aircraft control range; Constraint 2: Simulate the takeoff process of the aircraft under the load condition, and judge whether the landing gear is damaged; Constraint 3: Determine whether Static...

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Abstract

The invention discloses an airplane gravity center envelope calculation method. The method comprises the steps that original parameters of an airplane are input, and the loading condition and the initial gravity center position are given; according to the aircraft aerodynamic model, the undercarriage model, the engine model and the full-aircraft flight mechanical model, calculating full-aircraft aerodynamic force and aerodynamic moment of the aircraft, and finishing trimming; the load weight and the gravity center position are dispersed; judging whether the aircraft can normally cruise and flyand normally take off and land or not; and then introducing static stability margin constraint and wing and horizontal tail limit load constraint under the condition of large aircraft load under thecondition of minimum horizontal flight speed to obtain a relation graph of front and rear gravity center limits and aircraft flight weight. According to the method, discretization processing is carried out on the load gravity center coordinate point, the flight process and the take-off and landing process of the aircraft are simulated, the gravity center of the aircraft is accurately calculated, the process is simple, and calculation is convenient.

Description

technical field [0001] The invention relates to a calculation method for an aircraft center of gravity envelope, which belongs to the technical field of aviation envelope calculation. Background technique [0002] Since the Wright Brothers successfully piloted the "Aviator" 1 in 1903 to realize the human flying dream, the aircraft has developed rapidly. The aircraft center of gravity envelope refers to the allowable variation range of the center of gravity of a civil aircraft in all flight processes. The positional relationship between the center of gravity and the focal point has an important impact on the overall safety, flight quality, performance and geometric parameters. In terms of safety, the center of gravity point within the envelope of the center of gravity should allow the aircraft to achieve maneuverable and safe flight; in terms of flight quality, a reasonable center of gravity can improve the maneuverability of civil aircraft, thereby improving the overall mot...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 王坤朱清华陈建炜申遂愿朱振华招启军
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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