Method for improving orbit-transferring safety of inclined orbit satellite

An inclined orbit and safety technology, applied in the field of improving the safety of inclined orbit satellite orbit change, can solve the problems affecting the safety of satellite power supply, affecting the completion of satellite launch tasks, increasing the cost of satellite development, etc., so as to reduce the development cost and launch time Flexibility, less restrictive effects

Active Publication Date: 2013-01-16
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

According to calculations, in the case of high sun angles, if the common flight program design method for medium and high orbit satellites is adopted, the discharge depth of the battery will exceed the design value, which will affect the safety of satellite power supply.
If the design of the satellite is changed, such as increasing the

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  • Method for improving orbit-transferring safety of inclined orbit satellite
  • Method for improving orbit-transferring safety of inclined orbit satellite

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Embodiment Construction

[0024] Specific embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0025] The safety of energy and thermal control is the basis for the implementation of satellite orbit change maneuvers. However, for satellites in inclined orbits launched in some seasons (the common inclination angle is 55°), the solar altitude angle will be very large (if the inclination angle is 55°, the maximum solar altitude angle is 55° (inclination angle) + 23.5° (ecliptic and equatorial) ) = 78.5°), so that during the period from the establishment of the ignition attitude of the satellite to the restoration of the earth pointing attitude after the ignition, the sun illumination angle (the angle between the normal of the sail and the sunlight) is relatively large, and the solar wing The output power cannot meet the demand for satellite power supply, and battery power is required. However, the capacity of the battery is limited...

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Abstract

The invention relates to a method for improving the orbit-transferring safety of an inclined orbit satellite, wherein the problem of energy-source shortage of the inclined orbit satellite in the period of orbit-transferring motorization under the condition of high solar angles is solved through the reasonable adjustment of flight events by considering the condition of solar altitude angles in the designing process of a flight program, and meanwhile, flight-control operation can be simplified. The discharging time of a storage battery in the period of orbit-transferring ignition can be shortened by designing the flight program according to the method, so that the load power in the power-supplying period of the storage battery is reduced, therefore the discharging depth of the storage battery is reduced, the energy-source safety of the satellite is ensured, and a launch window is not limited by solar illumination angles.

Description

technical field [0001] The invention relates to a method for improving the safety of orbit change of an inclined orbit satellite, which can ensure the safety of energy and thermal control during satellite orbit change, and is mainly used during flight control of inclined orbit satellites. Background technique [0002] Generally, the geosynchronous orbit satellite has a low sun altitude angle after launch into orbit, and the sun illumination angle (the angle between the sun's rays and the projection of the sun's rays on the satellite's orbital plane) is small during orbit change ignition, which meets the power supply demand of the satellite. Therefore, the flight program design during the orbit change generally does not need to consider the problem of energy shortage. The common flight program design method during the orbit change is: according to the orbit change strategy and the tracking arc section, arrange the earth capture sequentially and establish the earth pointing att...

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Application Information

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IPC IPC(8): B64G1/10
Inventor 马利杨慧王金刚潘宇倩刘涛张孝功鲍恩竹陈少华
Owner BEIJING INST OF SPACECRAFT SYST ENG
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