The invention belongs to the field of orbit control, and particularly relates to a method for converting a pulse orbit transfer sequence into a finite thrust orbit transfer sequence. The method comprises the following steps of: 1, determining the initial position, initial speed and initial mass of a spacecraft; 2, determining the position, the speed and the mass of the spacecraft at the pulse point; 3, according to the overall mass of the spacecraft, the specific impulse of the engine and the speed increment, determining the fuel consumption needed by orbit transfer this time; 4, determining the time required by the orbit transfer according to the fuel consumption required by the orbit transfer and the engine thrust; 5, converting the pulse quantity into finite thrust in a time period by adopting a discrete and integral mode; and 6, correcting the direction by taking the X-axis positive direction of the tnw coordinate system as a thrust direction. The accurate fuel consumption can be obtained in spacecraft orbit transfer pre-planning, the guidance precision is improved, the orbit transfer preparation cost is reduced, and the final guidance precision is improved.
本发明属于轨道控制领域,特别涉及一种脉冲轨道转移序列向有限推力轨道转移序列转换的方法,包括步骤一、确定航天器初始位置、初始速度和初始质量;步骤二、确定航天器的在脉冲点处位置、速度和质量;步骤三、根据航天器的整体质量、发动机比冲以及的速度增量,确定本次轨道转移所需要的燃料消耗量;步骤四、根据轨道转移所需的燃料消耗量以及发动机推力确定本次轨道转移所需要的时间;步骤五、采用离散、积分的方式将脉冲量转换为时间段内的有限推力;步骤六、采用tnw坐标系的X轴正方向作为推力方向进行方向修正。本发明能够在航天器轨道转移事前规划中得到准确的燃料消耗量、提高制导精度,降低轨道转移准备成本、提高最终的制导精度。
Method for converting pulse orbit transfer into limited thrust orbital transfer
一种脉冲轨道转移向有限推力轨道转移转换的方法
2021-03-09
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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