Calculation method, device and medium of maneuvering window of relative navigation tributary satellite
A technology of relative navigation and calculation method, which is applied in the field of satellite control, can solve the problems such as the orbital maneuver window and the overall distribution analysis of orbit change speed that cannot be accompanied by missions, and achieve the effect of clear overall distribution and strong reference value
Active Publication Date: 2019-05-07
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
The traditional method is mainly based on the calculation of ignition elements, and calculates the ignition direction for a given ignition time and speed increment, so as to realize the rendezvous with the companion star, but it is unable to analyze the overall distribution of the orbital maneuver window and orbital velocity of the accompanying mission.
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[0049] A method for calculating the maneuvering window of the relative navigation satellite accompanying the aircraft. First, according to the position and velocity parameters of the primary star and the secondary star, the orbit change velocity increment and the relative velocity when rendezvous with the secondary star are calculated under the given primary star ignition time and orbit transfer time; Secondly, given the ignition time range and orbit transfer time range of the primary star, take the ignition time as the abscissa and the orbit transfer time as the ordinate to obtain the acceleration velocity increment of the primary star and the velocity contour map relative to the companion star during rendezvous; finally, according to From the velocity contour map, the ignition moment and orbit transfer time satisfying the constraint of the primary star's orbit change velocity increment are obtained. In addition, according to the velocity contour map, the maneuver window with ...
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The invention discloses a calculation method of a maneuvering window of a relative navigation tributary satellite. The method comprises the following steps: calculating an orbital transition speed increment and a relative speed when interacting with a companion star of a main star at a specified ignition timing and an orbital transition time according to the position and the velocity parameters ofthe main star and the companion star; setting the ignition timing range and the orbital transition time range of the main star, taking the ignition timing as the abscissa and the orbital transition time as the ordinate, so as to obtain a velocity increment when the main star accelerates and a velocity contour map relative to the companion star when interacting with the companion star; and obtaining the ignition timing and the orbital transition time satisfying a main star orbital velocity increment constraint according to the velocity contour map. In addition, according to the velocity contour map, the maneuvering window with the optimal incremental speed and the optimal orbit transition time of the main star can be obtained. The invention can also obtain the direction and speed incrementrequirements of the main star ignition and the speed and direction of the relative companion when interacting with the companion star according to the specified ignition timing and the orbit transition time.
Description
technical field [0001] The invention relates to a method, a device and a medium for calculating a maneuvering window accompanying a navigation satellite, and belongs to the technical field of satellite control. Background technique [0002] Space has become a crucial strategic commanding height for safeguarding national security and interests, and carrying out research on space relative navigation tasks is an important step towards intelligence and autonomy in my country's space technology. The relative navigation mission orbital maneuver involves the mutual movement of the main star and the companion star. The main star chooses the opportunity to ignite the orbital maneuver, and realizes the companion flight mission with the companion star within the specified time. [0003] Since the relative navigation mission binary stars are orbiting the earth in space, the window that satisfies the orbit transfer conditions (constraints such as orbit change speed increment, ignition di...
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Inventor 田百义黄美丽王大轶张相宇赵峭冯昊刘德成周静张磊邹元杰
Owner BEIJING INST OF SPACECRAFT SYST ENG