Small asymmetrical reentry body aerodynamic force measuring device supported by air bearing

Abstract

The invention provides a small asymmetrical reentry body aerodynamic force measuring device supported by an air bearing.The device achieves measuring through an inner and outer balance nest combination measuring method, a center ventilation rod type six-component balance assembly is selected in an inner balance, and a hollow spoke type structure is adopted in an outer balance, and the inner balance and the outer balance are connected through the air bearing with tiny rolling frictional damping.The small asymmetrical reentry body aerodynamic force measuring device comprises a tail fulcrum bar, an air bearing supporting device, a model back section and a model front section.The tail fulcrum bar is fixedly connected with the air bearing supporting device and a model mechanism.The air bearing supporting device is connected with the model back section, and the model back section and the model front section are connected through threads.The aerodynamic force measuring device is simple in structure, small in size and high in integral rigidity.Different measurement components are distributed on the inner balance and the outer balance according to measurement load characters and balance structure constraint conditions, the aerodynamic force measuring device is suitable for hypersonic speed wind tunnel tests of small asymmetrical reentry body aerodynamic force measuring and especially can control measurement interference of other large load components on small rolling moment, and the measuring precision is improved.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to an aerodynamic measuring device for a small asymmetric reentry body supported by an air bearing. Background technique [0002] Traditional axisymmetric hypersonic re-entry bodies (such as intercontinental missile warheads, returnable satellites, etc., hereinafter referred to as re-entry bodies) generally adopt a zero-angle-of-attack inertial re-entry method, and the ablation shape of the end of the re-entry body is generally axisymmetric Low degree of asymmetry in distribution and shape. In particular, the mass, inertia and size of the large-scale re-entry body are relatively large, so the impact of the above-mentioned shape changes on the aerodynamic performance of the re-entry body is relatively small. At present, some hypersonic reentry bodies adopt a small inclination angle reentry method, and small asymmetric ablation phenomena will inevitab...

AI Technical Summary

Problems solved by technology

At present, some hypersonic reentry bodies adopt a small inclination angle reentry method, and small asymmetric ablation phenomena will inevitably occur during the reentry process, which will affect the aerodynamic characteristics of the reentry body (including lift-drag characteristics, moment characteristics, etc.) ) and static and dynamic stability; and at the same time, due to the needs of the control system, the system puts forward higher requirements for the prediction accuracy of the aerodynamic characteristics of the reentry body with a small inclination angle, and the prediction accuracy of the roll aerodynamic moment coefficient error constant value item requires reach 10 -5 order of magnitude (rolling moment measurement accuracy needs to reach 10 -2 Nm level, that is, the rolling damping moment of the reentry body model support device itself must be less than 10 -4 Nm level)

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