Semi-physical simulation testing system and method for deep space autonomous navigation star sensor

Abstract

The invention provides a semi-physical simulation testing system for a deep space autonomous navigation star sensor and a method thereof. A star sensor simulator is placed on a similar support frame, and an autonomous navigation star sensor is fixed on a three-axis rate rotating table; the center of an entrance pupil of the autonomous navigation star sensor is arranged on a horizontal rotation central axis of the three-axis rate rotating table; an emergent pupil of the star sensor simulator is in butt joint with the entrance pupil of the autonomous navigation star sensor, and an optical axis of the star sensor simulator is superposed with the optical axis of the autonomous navigation star sensor; and the autonomous navigation star sensor, the three-axis rate rotating table and the star sensor simulator are all connected with a control and information processing computer. By adopting the system and the method, star simulation for the very high-precision star sensor for autonomous navigation of a minor planet can be solved, and the measurement precision of the star sensor and the autonomous navigation positioning precision are verified, thereby having broad application prospects for developing the deep space autonomous navigation sensors.

Description

technical field [0001] The invention relates to a semi-physical simulation test system and method of a deep-space autonomous navigation star sensor, which can be applied to a semi-physical simulation experiment of a deep-space autonomous navigation optical sensor. Background technique [0002] In the field of aerospace technology, the star sensor for deep space exploration optical navigation is a very high-precision star sensor, such as: its accuracy requires 0.5″, which is quite different from traditional star sensors, such as the entrance pupil diameter is about 150mm, The focal length is about 1000m, and the field of view is 1°~2°. Such a type of sensor mainly identifies the asteroids around the orbit of the cruise section of the deep space probe, and determines its angular position relative to the inertial space. The ephemeris data is used to calculate the position and velocity of the deep space probe relative to the earth-centered inertial coordinate system. [0003] A...

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Problems solved by technology

All current liquid crystal light valve star simulators are limited by the accuracy of the star simulati

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