Orbital maneuver technology of temporary networked satellites for earth exploration

临时组网卫星应急对地勘查的轨道机动技术

¹ Xi′an Satellite Control Center, Xi′an 710043, China
² Northwestern Polytechnical University, Xi′an 710072, China

Received: 9 October 2021

Abstract

It is very difficult to achieve effective coverage of hot-spot target in a short time period by earth perturbation for orbital maneuver, because the coverage gap of the temporary multi-satellites network in certain period of time is too large. In this paper, it is assumed that wave beam type of the satellite-payload sensor is a simple conic, the beam center of the satellite payload under the maximum lateral pendulum is calculated based on the precise ephemeris, and according to the projection ellipse of the payload wave beam on the ground, the coverage ability of the satellite payload on the ground target direction is obtained. Then the satellite is designed to encounter the ground target in the nodal period between the satellite passing the ground target and the latitude circle. The orbital maneuver control variables are calculated from the change of nodal period, and the optimal orbital maneuver control variables are selected from a specified time period. At last, the orbit maneuver in covering the target in a specified time period is achieved and the maximum revisit interval is greatly shortened.

摘要

针对多星以多类型载荷临时联合进行快速勘查存在某些时段勘查覆盖间隙过大、以地球摄动力长时间进行轨道机动难以短时实现对热点目标的有效覆盖等问题，提出基于精密星历计算出卫星在最大侧摆条件下的载荷波束中心，并假设载荷传感器波束类型为简单圆锥，依据载荷波束在地面的投影椭圆给出载荷在地面目标方向的覆盖能力；以卫星过地面目标同纬度圈的交点周期变化来设计卫星与地面目标相遇，由卫星相遇所需交点周期的变化计算出卫星轨道机动控制量；根据勘查需求从指定时间段内筛选出最小轨道机动控制量，从而实现在指定时段内以轨道机动覆盖目标，缩短了多星联合勘查的最大重访间隔。