Centroid suspension simulation test platform with three degree of freedom

Abstract

The invention relates to a centroid suspension simulation test platform with three degrees of freedom. A suspension chamber system is a hollow cylindrical chamber body; a suspension point is arranged in the central inner part of the chamber body; a spacing ring is arranged right above the suspension point; screws are installed in the axial direction, the radial direction and the normal direction around the suspension point; an adjustable balancing weight is installed on each screw; tested equipment is installed at the back part of the chamber body; a guiding head or other tested equipment is installed at the head of the chamber body; a fixed balancing weight is installed on the outer wall of the chamber body; a centroid suspension system comprises a rigid rod and a three-direction bearing; the upper end of the rigid rod is fixed on a roof beam of a laboratory; the lower end of the rigid rod is fixedly connected with the three-direction bearing; the rigid rod passes through the spacing ring of the suspension chamber system; the lower end of the three-direction bearing is fixedly connected with the suspension point in the central part of the suspension chamber system; a cold spray system comprises a nozzle assembly, a hard air pipe and two pressure-accumulating air cylinders; the two pressure-accumulating air cylinders are installed at the outer two sides of the suspension chamber system; the cold air nozzle assembly is installed at the tail outside the suspension chamber system; and the pressure-accumulating air cylinders and the air path interface of the nozzle assembly are connected by the hard air pipe.

Description

technical field [0001] The invention belongs to a test platform for small space vehicles and can be directly applied to the full physical simulation test of the control systems of various small space vehicles. Background technique [0002] In the full physical simulation test of the control system of various space vehicles, in order to verify the algorithm design of attitude control, guidance and navigation, the test equipment of the control system is usually placed on some test platform, and the movement of the test platform can be controlled. Create a kinematics and dynamics simulation of the spacecraft's on-orbit state. Traditional implementations of testbeds are: [0003] Single-axis and three-axis air-bearing turntables: In order to simulate the mechanical environment where the space vehicle suffers a small disturbance moment in outer space, the air-bearing turntable supported by spherical air-bearing bearings is usually used as the aircraft kinematics and dynamics sim...

AI Technical Summary

Problems solved by technology

[0003] Single-axis and three-axis air-bearing turntables: In order to simulate the mechanical environment in which the space vehicle suffers a small disturbance moment in outer space, the air-bearing turntable supported by spherical air-bearing bearings is usually used as the aircraft kinematics and dynamics simulation test platform; but the air-bearing The mass of the spacecraft simulated by the floating turntable is at least 100kg, and the moment of inertia is at least 10kg·m 2 The above are not suitable for full physical simulation tests of small space vehicles such as kinetic energy interceptors

[0004] Three-axis servo turntable: Although this equipment is indispensable among many simulation test equipment, it can only simulate the kinematics of the space vehicle, not the dynamics simulation

That is to say, when the three-axis servo turntable is used for the simulation test, the nozzle on the spacecraft is only a link connected in series in the entire simulation test system, and the attitude change caused by its thrust acting on the aircraft is applied to the three-axis system through the simulation program. It is implemented on the axis servo turntable instead of directly acting on the aircraft, which may lead to deviations in attitude control design

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