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- Autonomous Relative Orbit Determination for Satellite Formation Flying on basis of Orbit Element Differences 基于轨道根数差的卫星编队自主定轨研究
- relative orbit element 相对轨道根数
- relative orbit elements 相对轨道要素
- relative orbital element 相对轨道要素
- J2 perturbation makes the relative orbit drift in the in-track direction, nutation or procession. J2摄动对相对轨道的影响分为相对轨道构形的漂移、相对轨道平面的章动和进动。
- Finally,the relative orbit trajectory and the corresponding changes were analyzed with respect to the J2 perturbation. 最后;针对J2摄动分析了卫星编队相对轨道构形的变化以及相对轨道构形的漂移量和转动量.
- The general relative orbit dynamics equation and GPS orbit observational equation onboard for spacecraft formation flying have been developed. 同时文章也提出了用GPS伪距测量信息实现卫星编队飞行的建立和保持的自主导航控制方法。
- With the method, the accuracy of c a rrier phase-based relative orbit determination may attain the order of a few de cimeter from the results calculated by using data collected from GPS/DR onboard TOPEX/POSEIDON. 该方法应用于TOPEX/PO SEIDON卫星星载GPS实测数据 ,可得到分米级的定轨精度
- The major semiaxis a and p of the relative orbital motion are known. 我们知道其相对轨道运动的主要半长轴a和周期p。
- This paper investigates the least maneuver velocity through the tolerable apolune and other lunar orbit elements. 另外，第一次近月制动失败后，卫星飞行大约15小时将飞离月球影响球。
- Abstract Based on Gauss perturbation equation, the variation equation of orbit elements under both J2 and atmosphere perturbation is derived. 摘要 基于高斯摄动方程，推导了卫星在同时考虑J2摄动和大气阻力摄动情况下的轨道要素变化方程。
- First, the locally optimal control laws are derived for each modified equinoctial orbital element. 研究了近地小推力转移轨道的制导问题,给出了一种基于局部最优控制律的自主制导算法。
- Abstract The variation equation of the satellite orbit elements under both J2 and drag perturbations was derived based on the Gauss perturbation equation. 摘要 基于高斯摄动方程，推导了卫星在同时考虑J2和大气摄动情况下的轨道根数变化方程。
- relative orbit utilization ratio 相对轨道利用率
- inter-satellite relative orbit determination 星间相对定轨
- The brief note gave the orbital elements of the hypothetical planet. 那张纸上写了那颗假想行星的轨道参数。
- In a printer, the removable type element. 印刷机上可拆卸的打印部件。
- The tidal solutions obtained from SLR and satellite altimetry are used to compute the secular changes in the Moon's orbit elements and the Earth rotation rate in the ecliptic reference system. SLR和卫星测高的潮汐解被用来计算月球轨道根数相对黄道坐标系的长期变化和地球自转速率的长期变化。
- The spacecraft is in orbit around the moon. 该航天器在绕月球轨道运行。
- Aiming at this situation,satellite motion was described by nonsingular orbit elements and the corresponding impulsive control model for a near round reference satellite formation is derived. 针对高斯摄动方程在描述近圆轨道时其近地点幅角和平近点角存在奇异性的问题,采用非奇异轨道要素描述卫星轨道运动,推导了适用于近圆参考轨道编队的非奇异轨道要素脉冲控制模型。
