Real-time calculation method for climbing performance data of transportation aircraft

A transport aircraft, real-time computing technology, applied in computing, electrical digital data processing, computer-aided design, etc., to reduce the number of iterations, ensure fluency, improve convergence speed and computing efficiency

Pending Publication Date: 2022-05-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Application Information

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Problems solved by technology

[0004] The purpose of this application is to provide a real-time calculation method for the climb performance data of transport aircraft, to solve or alleviate at least one of the problems in the background technology

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  • Real-time calculation method for climbing performance data of transportation aircraft
  • Real-time calculation method for climbing performance data of transportation aircraft
  • Real-time calculation method for climbing performance data of transportation aircraft

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Embodiment Construction

[0086] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0087] In order to solve the above-mentioned problems, the application proposes a real-time calculation method for the climb performance data of a transport aircraft. The method includes the original data input for calculation—the processing method of the aerodynamic characteristic data and the dynamic characteristic data. The basic climb performance parameters: climb The real-time calculation model and computer implementation method of rate, rapid ascent speed and ceiling.

[0088] In the ground task planning system, realize the rapid ascent speed, maximum climb rate, and cruise ceiling (maximum climb rate 1.5m / s) of a certain transport aircraft at various altitudes under the conditions of flight weight m (g...

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Abstract

The invention provides a transportation aircraft climbing performance data real-time calculation method, which comprises the following steps: acquiring input data including aircraft basic layout parameters, aircraft longitudinal aerodynamic characteristic data and engine power data; determining a climbing speed range and corresponding aerodynamic characteristic data of the transportation aircraft according to the input data, fitting aircraft longitudinal aerodynamic characteristic data required by climbing performance into a linear function or polynomial form, fitting engine power data into a polynomial form, and forming a fairing curve; and carrying out approximation on the lift curve model and the climbing rate model of the airplane in the climbing state, and calculating to obtain the climbing rate, the fast lifting speed, the corresponding climbing rate and the corresponding lift limit. According to the method, the relevant parameters of the climbing performance can be calculated in real time, a climbing performance database with huge data does not need to be established, the workload of aircraft designers is relieved, and the working efficiency is improved.

Description

technical field [0001] The application belongs to the technical field of aircraft performance design, and in particular relates to a method for real-time calculation of climb performance data of transport aircraft. Background technique [0002] In the flight management system, it is necessary to display the climb performance data of the aircraft in the current configuration, temperature and weight state in real time, such as fast ascent speed, steep ascent speed, ceiling, etc. Climb time, distance, and fuel consumption are estimated based on the climb rate, and the climb performance of the aircraft also needs to be predicted in the aircraft mission planning system. At present, in these airborne or ground support systems, the prediction of climb performance data is to pre-calculate the climb performance data under various conditions based on the overall parameters, aerodynamic characteristics, and dynamic characteristic data of the aircraft, and establish that the aircraft is...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F119/08G06F119/14
CPCG06F30/15G06F2119/14G06F2119/08
Inventor 商立英张超明亚丽谭蓉蓉任江涛赵科社
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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