Six-freedom parallel control self-correction return apparatus for space vector force loading

Abstract

The invention discloses a six-freedom parallel control self-correction return apparatus for space vector force loading. The apparatus comprises a loading point 32, a loading part 33, a moving platform 1, a fixed platform 4 and six self-correction return parts, wherein the moving platform 1 and the fixed platform 4 are connected through the six self-correction return parts, and connection relations are arranged according to six-freedom parallel Stewart platform structure. Each self-correction return part comprises a first ball hinge 41, a universal flexible element 42, a force transducer 43, a telescoping rod 44, a driving mechanism 45 and a second ball hinge 46, wherein the universal flexible element 42 is an elastic element only transmitting axial forces and is connected with the moving platform 1 through the first ball hinge 41, the other end of the universal flexible element 42 is connected with a telescoping rod driving mechanism through the force transducer 43, the telescoping rod driving mechanism comprises the telescoping rod 44 and the driving mechanism 45, and the other end of the driving mechanism 45 is connected with the fixed platform 4 through the second ball hinge 46.

Description

Technical field: [0001] The invention belongs to the field of space vector force testing, in particular to a six-degree-of-freedom parallel control self-calibration return device for space vector force loading. Background technique: [0002] In the field of aero-engine, rocket engine and aerodynamic testing, the measurement of space vector force (that is, three-directional force and three-directional torque) is a very important test content, which greatly affects the performance of the test piece. There are a lot of test equipment for space vector force measurement, such as wind tunnel balances of various forms, aero-engine vector thrust test benches, and rocket engine vector thrust test benches. [0003] In order to accurately obtain the aerodynamic vector force on the test piece, it is necessary to use a calibration device to calibrate the force measuring system before the test. The performance of the calibration device directly affects the calibration accuracy of the for...

AI Technical Summary

Problems solved by technology

[0004] At present, there are many wind tunnel balance loading devices, most of which can simulate the real force of the aircraft. They are mainly divided into two types: the ground axis system and the body axis system. The calibration methods include the unit calibration method and the multi-element calibration method, but the calibration time is long and the structure is complicated. and other shortcomings, and the applied space vector force cannot be guaranteed to be at the calibration origin

For the loading of the vector force measurement system of aero-engine and rocket engine, an approximate method is adopted, that is, the force and moment are respectively applied on the axis of the load cell, and the calibration is not performed at the position where the space vector force is generated, so its force measurement The system accuracy is not high

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