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Aerodynamic parameter measurement method for aircraft

A technology of aerodynamic parameters and measurement methods, which is applied in the direction of measuring devices, aerodynamic tests, and machine/structural component testing, can solve problems such as failure of measurement schemes, and achieve the effect of improving reliability

Inactive Publication Date: 2018-01-16
BEIJING SPACE TECH RES & TEST CENT
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Problems solved by technology

In the conventional scheme, due to the lack of redundant configuration, when a hardware or algorithm fails, the entire measurement scheme will fail

Method used

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  • Aerodynamic parameter measurement method for aircraft

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Embodiment Construction

[0018] Specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0019] figure 1 It is a schematic diagram of the measurement method of aerodynamic parameters. Such as figure 1 Shown, aircraft aerodynamic parameter measurement method of the present invention, comprises the steps:

[0020] Step 1: Calculate the airflow angle, that is, obtain the data of the aircraft's angle of attack and sideslip angle.

[0021] The airflow angle calculation can be obtained through the embedded air data sensing system or the ballistic reconstruction method, and the two methods are mutually backup.

[0022] Method 1: Obtain the airflow angle through an embedded air data sensing system (FADS). A certain pressure measuring hole is arranged on the aircraft body, and a pressure sensor is used to measure the atmospheric pressure transmitted by the pressure measuring hole. The atmospheric pressure measured by the pressure senso...

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Abstract

The invention provides an aerodynamic parameter measurement method for an aircraft, which is used for measuring key data in three aspects of an airflow angle, dynamic pressure and an aerodynamic force. The method comprises the following steps: the airflow angle is calculated, the airflow angle is acquired through an embedded atmospheric data sensing system or a trajectory reconstruction mode, andthe above two modes are in mutual backup; the dynamic pressure is calculated, data are outputted according to pressure sensors configured by the embedded atmospheric data sensing system on the aircraft, the dynamic pressure is calculated and input is provided for calculating an aerodynamic coefficient; and the aerodynamic coefficient is calculated, the output is measured by using accelerometers, the aerodynamic force, that is, the lift force and the drag force, is calculated, and in combination of the dynamic pressure data, an aerodynamic calculation formula is used to directly determine the lift force coefficient and the drag force coefficient of the aircraft. The embedded atmospheric data sensing system is equipped with two sets of pressure sensors and multiple sets of accelerometers andgyroscopes. A hardware redundancy design and an algorithm redundancy design are adopted, and the aerodynamic parameter measurement reliability is improved.

Description

technical field [0001] The invention relates to the design technology of an aircraft aerodynamic parameter measurement system, in particular to an aircraft aerodynamic parameter measurement method, and belongs to the technical field of aircraft aerodynamic measurement. Background technique [0002] The aerodynamic parameters of the aircraft mainly include the key data of three aspects: airflow angle, dynamic pressure and aerodynamic force. Aerospace vehicles such as fighter jets, spacecraft return capsules, etc. all need to measure aerodynamic parameters. The measurement accuracy of aerodynamic parameters seriously affects the performance of aircraft guidance and control. It can be seen that the design of aerodynamic parameter measurement method is an important part of aircraft design. [0003] The current conventional measurement methods need to further strengthen the redundant configuration of hardware and algorithms, which makes the conventional methods have higher requ...

Claims

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Application Information

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IPC IPC(8): G01M9/06
Inventor 侯砚泽左光杨雷郭斌石泳黄震杨庆吴文瑞陈冲刘岩田政方杰
Owner BEIJING SPACE TECH RES & TEST CENT
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