Combined autonomous navigation method of mars exploration approach section

Abstract

The invention provides a combined autonomous navigation method of a mars exploration approach section. The combined autonomous navigation method comprises the following steps: the step 1 of using a spacecraft-mounted sun sensor to measure the viewing direction of the sun and using a spacecraft-mounted solar-spectrum velocity-measurement navigation sensor to measure the relative movement velocity of a mars explorer to the sun; the step 2 of using a wireless responder to obtain distance and relative velocity information with a mars surrounding device; the step 3 of establishing an orbital dynamics equation and establishing a navigation system model under a J2000.0 heliocentric ecliptic inertial coordinate system and using a corresponding navigation filtering algorithm to obtain autonomous navigation position and velocity information. The combined autonomous navigation method disclosed by the invention avoids depending on ground wireless information, can achieve autonomous navigation of a spacecraft in a flying process by only needing optical information from the sun and the wireless information from the mars surrounding device, can establish a system equation of an autonomous navigation system of the explorer, utilizes different navigation filter algorithms to achieve real-time estimation of navigation information of the explorer and is simple, easy, practical and free of time delay.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to a combined autonomous navigation method for Mars exploration approach segments. Background technique [0002] The Mars approach stage usually refers to the time when the probe enters the Mars influence sphere to the completion of Mars braking and capture. It is one of the most critical stages in the entire Mars exploration mission process. At this stage, the space environment where the probe is located is complex, the flight speed is fast, the control requirements are high, and the opportunity is unique. When the navigation accuracy of the brake capture segment does not meet the index requirements, it will affect the subsequent exploration tasks in the stages of orbiting and landing, and even lead to consequences such as leaping or hitting Mars, resulting in mission failure. Therefore, high-precision autonomous navigation in the approaching segment of Mars is very important. [0003] C...

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