Parachute pneumatic parameter multifunctional measuring system

Abstract

The invention discloses a parachute pneumatic parameter multifunctional measuring system. The system comprises a control module, a measuring module, a data processing module and an output module, wherein the control module can control the wind hole testing condition setting and the connecting condition setting of a parachute system and a balance system, the measuring module can measure the loads on front and rear balances connected with the parachute under the wind hole testing conditions of the parachute system controlled by the settings and given flow incoming conditions, the data processingmodule performs numerical value simulation under the same flow incoming condition with the wind hole testing to obtain the loads borne by the parachute, so that a wind hole testing correcting coefficient is calculated, and the parachute pneumatic parameter is determined, and the output module is used for outputting the measured loads on the front and rear balances of the parachute, the wind holetesting correcting coefficient and the parachute pneumatic parameter. The system has the advantages that the effectiveness of a wind hole testing result can be rapidly judged, and a basis is providedfor correctly evaluating the stability and resistance performance of the parachute through simulation correction on numerical values.

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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