单差PPP相位偏差估计方法及有效性分析

针对常规浮点解精密单点定位收敛时间长的问题,分析了PPP模型中模糊度不具备整数性质的原因,采用方向数据统计的计算方法,以单差模糊度为研究对象,对相位偏差进行了建模估计。算例从精密单点定位单差模糊度固定、定位精度以及收敛速度等方面对相位偏差改正的有效性进行了分析,结果表明,经相位偏差改正后的PPP模糊度固定成功率、收敛速度有了明显提高,定位精度较浮点解提高了一个量级。     

卫星10 N推力器复合材料支架的研制

文章阐述了卫星10N推力器复合材料支架的技术要求、工艺方案、研制和振动试验.10N推力器支架是封闭的盒形结构,受力状态复杂,尺寸公差要求高.采用缝合-树脂转移成型(RTM)组合工艺,保证了精度;选用水溶性芯模,解决了脱模难题.与原铸镁支架相比,复合材料支架的重量减轻了35％、制造工时缩短了80％、成本节约了20％.产品通过了鉴定级正弦和随机振动试验;振动试验后经超声波无损检测证实,支架无损伤,满足卫星发射阶段的力学环境要求.     

以VSCMG为执行器的航天器姿态机动自适应动态滑模控制

针对刚体航天器姿态机动控制问题,结合变速控制力矩陀螺(VSCMG)执行器的特性,提出一种自适应动态滑模控制律,提高了姿态机动控制的扰动抑制能力和鲁棒性。此控制律采用自适应方法对扰动力矩进行估计,通过给出控制力矩变化率并对其积分得到控制力矩,以此削弱切换控制的抖振对控制力矩时间连续性的影响,从而改善系统的动态性能。仿真分析显示该控制律能够在扰动力矩作用下实现刚体航天器的快速姿态机动,并且有效减弱了滑模控制的抖振现象。     

On the Precession of Saturn

The precession of Saturn under the effect of the gravity of the Sun, Jupiter and planet’s satellites has been investigated. Saturn is considered to be an axisymmetric (A = B) solid body close to the dynamically spherical one. The orbits of Saturn and Jupiter are considered to be Keplerian ellipses in the inertial coordinate system. It has been shown that the entire set of small parameters of the problem can be reduced to two independent parameters. The averaged Hamiltonian function of the problem and the integrals of evolutionary equations are obtained disregarding the effect of satellites. Using the small parameter method, the expressions for the precession frequency and the nutation angle of the planet’s axis of rotation caused by the gravity of the Sun and Jupiter are obtained. Considering the planet with satellites as a whole preceding around the normal to the unmovable plane of Saturn’s orbit, the satellites effect on the Saturn rotation is taken into account via the corrections in the formula for the undisturbed precession frequency. The satellites are shown to have no effect on the nutation angle (in the framework of the accepted model), and the disturbances from Jupiter to make the main contribution to the nutation angle evolution. The effect of Jupiter on the nutation angle and the precession period is described with regard to the attraction of satellites.     

On the features of long-term evolution of a high-apogee orbit of the SPECTR-R spacecraft

The practical tasks related to qualitative investigation of long-term evolution of high-apogee orbits of artificial Earth satellites (AES), for which the main perturbing factors are gravitational perturbations from the Moon and the Sun, are considered. Attention is given to the problem of the ballistic lifetime of similar orbits, and the issues associated with possibilities of the correction of orbits for ensuring the required duration of their ballistic lifetime are considered. The orbit of the SPECTR-R spacecraft launched in July of 2011 is considered as an example.     

基于遗传算法的多星座选星方法

提出了一种基于遗传算法的选星方法,该方法能够准确、快速地实现多个全球导航卫星系统(GNSS)下选星颗数大于4的选星。经过大量试验确定了遗传算法选星的选择、交叉、变异等关键参数,并通过在交叉和变异中穿插染色体优选过程克服了遗传算法的选星结果容易陷入局部最优的缺点。以不同GNSS星座个数和不同选星颗数下的选星仿真校验了所设定遗传参数的有效性和可靠性。仿真结果表明,利用遗传算法可以高效、准确地实现选星,该方法特别适用于多星座多选星颗数的情况。     

双组元统一推进系统优化改进技术进展

不断提高推进剂在轨管理效率,是应用卫星对推进系统的基本要求,也是推进系统的重要发展方向。推进剂剩余量在轨高精度测量和并联贮箱均衡排放主动控制,是提高推进剂在轨管理效率的重要技术手段。针对我国SAST-5000卫星平台双组元统一推进系统,开展了气体注入压力激励方法的关键技术攻关,并取得重要进展。研究结果表明：改良型气体注入压力激励法的推进剂剩余量在轨测量精度达到-0.68%-0.66%,并联贮箱均衡排放控制措施将被动调节的不均衡度控制在优于1.13%,主动纠偏措施还可进一步提高并联贮箱排放推进剂的同步性。     

地球同步轨道卫星群在轨加注任务规划

以地球同步轨道卫星群为研究对象,开展“多对多”在轨加注任务规划问题研究。首先建立了任务规划的数学模型,该任务规划属于多目标规划问题,求解过程中需要解决TSP问题。其次,给出了该规划问题的求解方法及流程,采用遗传算法进行求解并设计了相应的遗传算子。最后,选取了14颗地球同步轨道卫星作为目标星进行求解,并在小角度近似条件下对计算结果进行了分析,计算结果验证了算法的有效性。     

Evaluation of a satellite constellation for active debris removal

This paper analyzes an example of a three-dimensional constellation of debris removal satellites and proposes an effective constellation using a delta-V analysis that discusses the advisability of rendezvousing satellites with space debris. Lambert?s Equation was used to establish a means of analysis to construct a constellation of debris removal satellites, which has a limit of delta-V injection by evaluating the amount of space debris that can be rendezvoused by a certain number of removal satellite. Consequently, we determine a constellation of up to 38 removal satellites for debris removal, where the number of space debris rendezvoused by a single removal satellite is not more than 25, removing up to 584 pieces of debris total. Even if we prepare 38 removal satellites in their respective orbits, it is impossible to remove all of the space debris. Although many removal satellites, over 100 for example, can remove most of the space debris, this method is economically disproportionate. However, we can also see the removal satellites are distributed nearly evenly. Accordingly, we propose a practical two-stage strategy. The first stage is to implement emergent debris removal with the 38 removal satellites. When we find a very high probability of collision between a working satellite and space debris, one of the removal satellites in the constellation previously constructed in orbit initiates a maneuver of emergent debris removal. The second stage is a long-term space debris removal strategy to suppress the increase of space debris derived from collisions among the pieces of space debris. The constellation analyzed in this paper, which consists of the first 38 removal satellites, can remove half of the over 1000 dangerous space debris among others, and then the constellation increases the number of the following removal satellites in steps. At any rate, an adequate orbital configuration and constellation form is very important for both space debris removal and economic efficiency. Though the size of constellation of debris removal satellites would be small originally, such a constellation of satellites should be one of the initial constellations of removal satellites to ensure the safety of the future orbital environment.     

近地轨道卫星的地影预报算法

针对传统地影预报算法计算量大,不适合星载计算机进行地影时刻自主预报的问题,提出一种地影预报星上算法。通过构造降维坐标系将卫星进出地影过程转换为“星-地-日”平面内的几何问题;基于常数变易法推导出阴影条件的隐式解析公式,其方程系数可由实时轨道参数确定。为简化计算,将星上算法设计为双层结构：构造迭代算法,依据实时轨道参数可精确预报卫星在每个节点上的地影时刻;而在任意两个节点之间采用解析算法进行近似预报。仿真结果表明,星上算法的预报精度高且计算量小,适合星载计算机进行地影时刻自主预报。     

协同优化在卫星多学科设计优化中的初步应用

探讨以遗传算法为优化上具的协同优化方法在卫星总体优化设计中的应用以及各学科间耦合关系。首先对基本协同优化方法的流程及特点进行了探讨，然后以对地观测卫星总休优化设计为对象，研究如何利用协同优化方法建立此问题的优化模型。研究结果表明，融合了遗传算法的协同优化方法能够有效地解决对地观测卫星总休优化设计，学科间耦合设计变量以及耦合状态变量的一致性误差均接近0．01％。     

Luni-solar perturbations in the extended phase space representation of the Vinti problem

Perturbation theory is applied to the Vinti problem—motion about an oblate spheroid—to include the gravitational effects of the sun and moon. The problem is formulated using the extended phase space method which introduces a new independent variable similar to the true anomaly. The disturbing Hamiltonian H₁ for third bodies is of order J₂² (second order) and the final goal is a theory including second order short and long period terms and third order secular terms. The current paper however carries the development only to the second order in the secular terms and the first order in the periodic terms. Problems of including the higher orders are discussed. Therefore, in the development of H₁ all terms of order 10^?9 or larger are retained. The lunar emphemeris retains terms to e′² in the lunar eccentricity. The perturbation analysis is carried out by means of Lie series and is developed through the first order only which is consistent with the final accuracy desired. The generating function W₁ is obtained and separated into the long period, short period and secular terms. From W₁ the coordinates are defined from the Lie series by means of a transformation equation. These coordinates are non-singular for small eccentricity and inclination. Because of the complexity of the equations all algebraic computations were accomplished by means of a computerized Poisson series manipulator developed at the Naval Research Laboratory.     

星座设计中的安全性问题研究

如何避免星座中卫星之间发生碰撞是星座安全性设计需要考虑的重要问题,给出了预测星座中卫星发生碰撞的一种方法,提出保证星座安全性需要考虑的三个问题并研究了如何避免星座中工作卫星、备份卫星和寿命终止卫星与工作卫星发生碰撞的措施。     

基于实验室定标和均匀景统计的相对辐射定标方法

提出了一种基于实验室定标和均匀景统计的定标方法,并应用于CBERS-02卫星遥感图像相对辐射校正。首先分析宽视场成像仪(Wide Field Imager,WFI)实验室基础定标系数;然后结合均匀景的定标方法,生成一组新的相对辐射定标系数;最后评价WFI图像相对辐射校正的效果。结果表明:文章提出的定标方法有效,可以较好地解决宽幅遥感图像辐射校正问题,同时为遥感卫星相对辐射校正提供了一种新的途径。     

敏捷成像卫星调度的改进量子遗传算法

针对敏捷成像卫星调度问题中解空间大,选择任务的搜索空间和确定任务观测时间的搜索空间分别是离散域和连续域的难题。建立了多种决策变量混合的敏捷成像卫星调度模型,提出一种改进的量子遗传算法对其求解,改进的量子遗传算法采用二进制与实数杂合的编码方式,降低染色体的基因位编码数目,提高了搜索效率,有效适应了敏捷成像卫星调度问题中离散与连续混合的解空间;以杂合编码为基础,设计对应的观测函数将敏捷成像卫星调度问题的解映射到相位空间,从而将量子优化机制引入敏捷成像卫星调度问题中,利用量子遗传算法在相位空间搜索的特性解决敏捷成像卫星解空间大、解空间离散与连续并存的问题。最后,通过不同规模的仿真校验对算法的调度效果进行测试和分析。结果表明,所提改进的量子遗传算法在收敛速度和方案收益方面都有较好的表现,能够满足敏捷成像卫星调度的需要。     

“北斗+5G”联合定位与误差校正技术

在边坡、城市峡谷、高架等复杂的公路交通定位环境中,存在海量多样的定位需求与复杂的定位环境,北斗信号穿越建筑空间时强度被削弱,产生严重的信号反射和衍射,使得北斗卫星信号难以到达和有效使用,系统可用率下降,无法提供可靠的定位服务。结合第五代移动通信网络（5G）系统高密度部署的特点,提出了一种北斗+5G联合定位模型以及基于最小二乘残差Helmert后验加权的误差校正方法。在复杂公路交通环境中,可以改善可见卫星数少的问题,优化卫星的几何构型,提高用户终端定位精度,能够为用户终端提供高精度、全天候、连续、实时的定位服务。实验表明,北斗+5G联合定位模型能够大幅提升复杂公路交通环境下的定位性能。     

基于约束满足的多星对区域目标观测活动协同

多星对区域目标观测活动的协同问题是卫星任务规划与调度领域的新问题。讨论了采用多星协同模式观测区域目标的必要性，描述了协同问题的研究内容。基于约束满足理论，建立了多星协同问题的约束优化问题模型，提出了一种禁忌算法与约束传播相结合的求解机制。最后，以仿真算例验证了模型与算法的正确性和优化性能。     

一种多普勒域走动校正的斜视SAR成像算法

为了解决时域校正走动带来的方位空变性问题,提出了一种在方位多普勒域走动校正的斜视合成孔径雷达（SAR）成像算法。文中利用级数反演理论,将斜距公式展开至三次项,推导出SAR回波信号的两维频谱表达式。再从两维频谱出发,提出了基于两维频谱匹配滤波的斜视SAR成像算法。该算法考虑到距离空变性问题,提出先在两维频域进行走动校正和相位预滤波,接着在距离多普勒域进行线性频率变标的处理方法,经过距离脉压和方位脉压能够得到聚焦良好的SAR图像。此外,该方法与距离徙动（RMA）算法相比可以有效地降低需要处理的数据量。最后,临近空间SAR仿真实验证明本文提出方法的可行性和有效性。     

The dynamics of the space shuttle orbiter with a flexible payload

The Space Shuttle Orbiter will be used as an orbital base for near-term space operations. Its payloads will range from compact satellites to large, flexible antennas. This paper addresses the problem of the dynamics and control of the Orbiter with a flexible payload. Two different cases are presented as examples. The first is a long, slender beam which might be used as an element in a large orbiting structure. The second is a compact satellite mounted on a spin table in the Orbiter payload bay. The closed loop limit cycles are determined for the first payload and the open loop eigenvalues are calculated for the second. Models of both payloads are mechanized in a simulation with the Shuttle on-orbit autopilot. The vehicle is put through a series of representative maneuvers and its behavior analyzed. The degree of interaction for each payload is determined and strategies are discussed for its reduction.     

Orbview系列卫星介绍

文章介绍美国轨道成像公司研制并已经发射的Orbview-1和Orbview-2卫星和将要发射的Orbview-3和Orbview-4卫星的特性参数。