A multifunctional measurement system for parachute aerodynamic parameters

Abstract

A multifunctional measurement system for aerodynamic parameters of a parachute, comprising: a control module, a measurement module, a data processing module, and an output module; the control module can control the setting of the wind tunnel test conditions of the parachute system and the setting of the connection conditions of the parachute system and the balance system The measurement module can measure the load of the parachute on the front and rear balances connected to it under the given flow conditions under the wind tunnel test conditions of the control parachute system; the data processing module can be used in the same flow as the wind tunnel test Under certain conditions, numerical simulation is carried out to obtain the load on the parachute, so as to calculate the correction coefficient of the wind tunnel test, and then determine the aerodynamic parameters of the parachute; the output module outputs the load of the measured parachute to the front and rear balances connected to it, the correction coefficient of the wind tunnel test, and the aerodynamic parameters of the parachute. parameter. The invention can quickly judge the validity of the wind tunnel test results, and through numerical simulation correction, it provides a basis for accurately evaluating the stability and resistance performance of the parachute.

Description

technical field [0001] The invention relates to a multifunctional measuring system for parachute aerodynamic parameters, which belongs to the field of aviation aerodynamic deceleration. Background technique [0002] In the aerospace field, the parachute is an important aerodynamic deceleration device. The parachute is made of soft and breathable special spinning material. The shape of the canopy will be significantly deformed under the action of the air flow. The air flow flows through the parachute, and its flow field is very complicated. The aerodynamic parameters of the general parachute include test methods and theoretical calculations. [0003] The current commonly used wind tunnel test method generally only installs the load measuring device at the point where the concentrated force of the parachute acts, so it can only obtain the drag coefficient of the parachute, but cannot obtain the axial force coefficient and normal force coefficient of the parachute. The aerodyn...

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Problems solved by technology

[0003] The current commonly used wind tunnel test method generally only installs the load measuring device at the point where the concentrated force of the parachute acts, so it can only obtain the drag coefficient of the parachute, but cannot obtain the axial force coefficient and normal force coefficient of the parachute. aerodynamic moment coefficients are not available to determine performance data for parachute stability

[0004] In theoretical calculations, the parachute is often assumed to be a rigid body, and the axial force coefficient, normal force coefficient, and aerodynamic moment coefficient of the parachute cannot be accurately obtained.

When considering the coupling between the parachute and the fluid, the amount of calculation is relatively large, and the aerodynamic parameters of the parachute cannot be quickly obtained

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