Hypersonic wind tunnel parallel type separation model relative position continuous adjustment device

Abstract

The invention discloses a hypersonic wind tunnel parallel type separation model relative position continuous adjustment device. A model X direction relative position adjustment device of the adjustment device is horizontally placed, the front end of the model X direction relative position adjustment device is fixedly connected with the tail end of a secondary test model, and the rear end is fixedly connected with a tail supporting mechanism of a hypersonic wind tunnel; a model Y direction relative position adjustment device is vertically placed, the upper end of the model Y direction relativeposition adjustment device is fixedly connected with an abdominal supporting connector below a primary test model, and the lower end is fixedly connected with an abdominal supporting mechanism of thehypersonic wind tunnel; and a Y direction locking and auxiliary adjustment device is vertically placed, fixed on a leeward surface of the model Y direction relative position adjustment device and in charge of Y direction locking and auxiliary adjustment. The adjustement device disclosed by the invention is simple in structure, processing cost is low, test model state can be easily changed, labor intensity of field staff is reduced, test efficiency is improved, an error caused by processing and installing errors is avoided, reliability precision is improved, and a test state can be temporarilyadded in an adjustable range.

Description

technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a device for continuously adjusting relative positions of parallel separation models in a hypersonic wind tunnel. Background technique [0002] At present, the state of the hypersonic wind tunnel model is complex, and the attitude of the model changes frequently. For the parallel two-stage separation test, there may be a large number of relative X and relative Y position adjustment states in any combination of the first-level test model and the second-level test model. However, conventional support mechanisms in hypersonic wind tunnels can only change the attitudes of the first-level test model and the second-level test model at the same time, but cannot change the attitudes of the first-level test model and the second-level test model separately, and cannot adjust the first-level test model and the second-level test model. The relative position b...

AI Technical Summary

Problems solved by technology

[0002] At present, the state of the hypersonic wind tunnel model is complex, and the attitude of the model changes frequently. For the parallel two-stage separation test, there may be a large number of relative X and relative Y position adjustment states in any combination of the first-level test model and the second-level test model.

However, conventional support mechanisms in hypersonic wind tunnels can only change the attitudes of the first-level test model and the second-level test model at the same time, but cannot change the attitudes of the first-level test model and the second-level test model separately, and cannot adjust the first-level test model and the second-level test model. The relative position between the level test models

[0003] At present, the relative position adjustment of the first-level test model and the second-level test model is usually achieved by processing pin holes at different positions on the web support plate of the first-level test model and the tail support rod of the second-level test model, but continuous adjustment cannot be achieved.

This method has the following disadvantages: First, due to the large number of processed pin holes, while the internal space of the web support plate or tail support rod is limited, too many pin holes may cause weakening of the support strength, local stress concentration, and bring safety hazards

Secondly, once the position of the pin hole is processed, it cannot be adjusted again, resulting in a limited number of relative positions of the first-level test model and the second-level test model that can be adjusted, and it is at a loss when the relative position of the test needs to be temporarily increased.

Finally, the web support plate of the first-level test model and the tail support rod of the second-level test model are generally located in different positions of the conventional support mechanism of the hypersonic wind tunnel, and the distance between the two positions is relatively long. Due to the cumulative processing error, the relative X and the relative Y coordinates cannot be given according to the original picture. In some cases, the original picture cannot be obtained, and the exact relative position cannot be obtained by actual measurement. Since the exact position of the reference cannot be found, the position of the positioning pin hole cannot be determined. Cannot meet the requirements of the two-level preset relative position, resulting in low relative position accuracy of the first-level test model and the second-level test model

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