共查询到19条相似文献,搜索用时 390 毫秒
1.
2.
3.
一种提高导航卫星星座自主定轨精度的方法研究 总被引:1,自引:0,他引:1
针对近地导航卫星仅利用星间测距进行自主定轨时,因无法消除星座整体旋转误差而导致长期自主定轨精度不高的问题,提出了利用拉格朗日导航卫星星座与近地导航卫星星座联合仅利用星间测距进行自主定轨的方法。建立了拉格朗日轨道导航卫星星座和近地导航卫星星座联合仅利用星间测距进行自主定轨的动力学模型和观测模型。利用扩展Kalman滤波(EKF)算法和星间测距信息实现了拉格朗日轨道导航星座与近地导航星座的长期自主定轨。以4颗拉格朗日卫星组成的导航星座与12颗GPS卫星组成的近地导航星座作为仿真对象进行了仿真分析,仿真结果表明本文仅利用星间测距的联合自主定轨方法可以有效提高导航卫星星座的长期自主定轨精度。 相似文献
4.
5.
针对中低轨道卫星,对平面内卫星半长轴α、偏心率e和近地点幅角w联合调整,以及平面外轨道倾角调整等进行了理论推导.用α,e,w联合修正法对初始轨道捕获、轨道保持和轨道倾角调整进行的仿真实验结果表明,用α,e,w同时修正可实现高精度的平面内轨道调整。另外,平面外倾角调整应尽可能在近地点和远地点完成,以使对升交点赤经的影响最小。 相似文献
6.
7.
低轨卫星星座的拓扑设计是天地一体化网络部署中较为重要的一环。在低轨卫星网络中,如何设计星座拓扑来提升卫星网络的稳定性与传输性能,是亟待解决的问题。提出一种基于轨道覆盖带方法的低轨持续全覆盖卫星星座设计方法,通过该方法构建低轨卫星星座,满足覆盖性能,可有效减少卫星切换的次数。基于构建的星座拓扑,制定邻轨k最近邻星的反向缝建链策略,优化设计链路长度和链路持续时长,获取网络传输性能与稳定性的平衡。仿真结果表明:通过上述方法设计出的星座,在满足对地持续全覆盖性能的情况下,相较于轨道覆盖带方法切换次数减少10%;邻轨k最近邻星策略相较于最短建链策略,拓扑稳定性能提升79.62%,使网络拓扑稳定性与传输性能达到更优的平衡。 相似文献
8.
9.
针对期望覆盖重数为偶数重时连续覆盖Walker星座的构型设计问题,提出一种基于覆盖带理论的构型设计方法。首先分析同轨道卫星组成覆盖带时的构型设计特例,随后将结论推广,改进了传统Walker星座的构型表征形式并提出覆盖带构型参数。基于轨道参数的相平面映射,给出了异轨卫星组成覆盖带时特征宽度的计算方法。通过分析相平面上覆盖带的拼接情况,给出了轨道倾角的优化策略和偶数重覆盖任意纬度的Walker星座设计步骤。所提出方法能显著提高构型枚举效率,且能满足不同纬度范围的覆盖需求。仿真表明,该方法能减少约10%覆盖所需的卫星数量,并能通过调整构型参数进一步优化轨道面数量。 相似文献
10.
11.
12.
A new scheme for refueling satellite constellation is proposed in this paper. Compared with the traditional research, where the satellite refueling is implemented through spacecraft rendezvous and docking, the new pattern studied here is based on formation flying, and it is more feasible, safer and more reliable. On the grounds of the proposed pattern, two refueling strategies are studied. The first is called single supplier refueling (SSR) based on formation flying. In this scenario, one fuel-sufficient satellite called a supplier, departs from its parking orbit, and after a series of orbit maneuvers, arrives at the target constellation that consists of multiple fuel-deficient satellites called workers. It then transfers equal fuel to each worker within the prescribed mission time. The second strategy is called double suppliers refueling (DSR) based on formation flying. This time two suppliers take charge of refueling half of the workers respectively in the same way as SSR. Using a genetic algorithm, the orbit of a supplier with a minimum consumption of fuel can be obtained once the mission time is fixed. Simulation results indicate that DSR is superior to SSR and that this dominance will be more distinct as the number of workers increases and the mission time decreases. 相似文献
13.
This paper analyses the fuel consumption of interferometric radar missions employing small satellite formations like, e.g., Cross-track Pendulum, Cartwheel, CarPe, or Trinodal Pendulum. Individual analytic expressions are provided for each of the following contributions: separation from a simultaneously injected master satellite, formation set-up, orbit maintenance, formation maintenance, and distance maintenance. For this, a general system of equations is derived describing the relative motion of the small satellites in a co-rotating reference frame. The transformation into Keplerian elements is carried out. To evaluate fuel consumption, three master satellites are assumed in different orbital heights, which are typical for Earth observation missions. The size of the exemplarily analysed formations is defined by remote sensing aspects and their respective fuel requirements are estimated. Furthermore, a collision avoidance concept is introduced, which includes a formation separation and formation set-up after a desired time period. 相似文献
14.
Tetsuo Yasaka 《Acta Astronautica》1992,26(12):867-874
Tumble Orbit Transfer, which is an effective method of re-orbiting inoperative satellites is described. This is done by an independent service vehicle equipped with a long arm and a grapple mechanism on top of it. After grappling the target satellite, the service vehicle orients its axis perpendicular to the orbit velocity vector. Then a thruster is activated to give an impulse on the service vehicle, which simultaneously causes velocity change and tumbling of the combined system. Since the angular momentums of two masses are exchanged periodically, separation at a selected instance will bring each mass into different orbits, one with a higher energy and the other with a lower. Separation soon after the impulse application puts the target satellite into an elliptical orbit, and separation after a half orbital period puts it into a higher circular orbit, assuming the original orbit is circular. The amount of total impulse is exactly half of that required in a conventional method. In case the service vehicle returns to the original orbit after injecting the target into the new orbit. The required total impulse is further reduced to one-third maximum. Another important feature of this method is the ease of capturing. Because the dominant force during and after the impulse application is tension through the arm, bending rigidity in the capture mechanism is not required. Therefore, a simple grapple will be enough for this maneuver. Small fuel requirements and simple capturing make this method attractive for transferring orbiting objects, and only this will provide a method of re-orbiting inoperative satellites of arbitrary shape. 相似文献
15.
卫星采用运载火箭上面级发射入轨期间,经历了由大椭圆轨道至圆轨道的过程,飞行姿态经历了变轨、慢旋、分离后巡航等多个阶段。在太阳翼展开前,卫星要经历比自身变轨更为恶劣的高低温环境及能源紧张等供电风险。在分离时刻的太阳翼碰撞或干涉安全性也需要重点关注和分析。针对北斗三号一箭双星采用上面级直接入轨方式的特点,分析了卫星与上面级间的供电和热设计接口,并从双星分离安全性角度考虑,分析影响卫星与上面级接口安全性的主要要素,并对应用和验证情况进行总结。 相似文献
16.
对于当代同步轨道通信卫星来说,星载设备寿命一般都高于星载燃料使用寿命,因此卫星设计寿命都是以星载燃料消耗殆尽为依据的。卫星轨道保持不仅是卫星测控任务的重要工作之一,同时也是星载燃料消耗的主要途径。文中从卫星平经度漂移量、测站定轨精度、星载推进器推力误差、卫星南北机动对东西方向耦合等多方面探讨同步轨道通信卫星E/W轨道保持策略,介绍一种细化轨道控制区间、估算偏心率控制圆半径范围的方法。 相似文献
17.
18.