Mechanical-bearing supported small asymmetrical reentry body aerodynamic force measuring apparatus

Abstract

The invention provides a mechanical-bearing supported small asymmetrical reentry body aerodynamic force measuring apparatus. The measuring apparatus is implemented through a measuring method using nested combination of inner and outer balances, wherein the inner balance selects a normal rod type 6-component balance structure; the outer balance selects a hollow radial structure; and the inner and outer balances are connected through a mechanical bearing with smaller rolling frictional damping. The measuring apparatus includes a tail support rod, a mechanical-bearing support device, a back segment of a model, and a front segment of a model, wherein the tail support rod is fixedly connected with the mechanical-bearing support device and a model mechanism; the mechanical-bearing support device is connected with the back segment of a model; and the back segment of a model is in threaded connection with the front segment of a model. The aerodynamic force measuring apparatus has the advantages of being simple in structure, being small in volume and being high in rigidity, can distribute different measuring components on the inner and outer balances according to the coupling feature of the measuring load and the balance structure constrained condition, is suitable for a hypersonic wind tunnel test for small asymmetrical reentry body aerodynamic force measurement, and is especially able to control the measuring interference of other large load components on a small roller torque to improve the measuring accuracy.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a small asymmetric reentry body aerodynamic measurement device supported by mechanical bearings. 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 re-entry body model support device itself needs to reach 10 -2 Nm level)

Images