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首页> 外文期刊>Journal of guidance, control, and dynamics >Iterative Pseudostate Method for Trans-fer Trajectory Design of Interplanetary Orbiter Missions
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Iterative Pseudostate Method for Trans-fer Trajectory Design of Interplanetary Orbiter Missions

机译：行星际轨道飞行器弹道设计的迭代伪态方法

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摘要

For an interplanetary orbiter mission, a proposed method based on the pseudostate technique identifies the four distinct transfer trajectory design options available for an opportunity with the parking orbit inclinations fixed. Though design options (1-1) and (1-2) differ by about 0.06 deg in the departure right ascension of ascending node and about 0.07 deg in the departure argument of periapsis, they result in completely different arrival parking orbit angles [RAAN, AOP]: 1) [68.1,115.2], and 2) [242.9,314.9]. The proposed method derives its merit in clearly capturing the marginal difference in the departure hyperbolic orbit characteristics. Further, the numerical method cannot identify these design options without additional boundary condition on arrival hyperbola when the patched conic design is used as the initial guess. On the other hand, each of the proposed design options, when used as initial guess for numerical refinement, converges to the corresponding arrival geometry, thus generating four distinct numerical designs. The improvement in the transfer trajectory design using the proposed method is very significant when considering that the interplanetary transfers are highly sensitive to the departure hyperbolic orbit characteristics. The differences in the departure parking orbit angles (viz., RAAN and AOP) and between the proposed and V-infinity tuned patched conic designs are about 0.6 and 0.3 deg, respectively, for the minimum energy opportunity of 2018. This difference is because of inclusion of the sun's gravity within the pseudosphere in the proposed method. The proposed design reduces the deviation in target conditions. The closest approach altitude achieved from different design options of the proposed method ranges from 1965 to 11,457 km, as compared to the V-infinity tuned patched design that results in about 1811,560 km upon numerical propagation (improvement by about 95%). The deviation in the time of periapsis is also greatly reduced by about 95%. The designs obtained using the proposed method are very close to the numerical designs. The time taken for numerical refinement of the proposed design is only 8 s, whereas the V-infinity tuned patched conic design using additional arrival information takes about 420 s. Also, the computation time taken by the proposed method to generate designs for departure epochs spanning one year is 0.1 s, which is comparable to the 0.08 s taken by the V-infinity tuned patched conic method.
机译：对于行星际轨道飞行任务，一种基于伪状态技术的建议方法可识别出四个固定的转移轨迹设计选项，这些选项可用于固定轨道倾斜度的机会。尽管设计方案（1-1）和（1-2）在上升节点的出发权提升中相差约0.06度，在根尖脱离的出发论点中相差约0.07度，但它们导致完全不同的到达驻车轨道角[RAAN， AOP]：1）[68.1,115.2]和2）[242.9,314.9]。所提出的方法的优点在于可以清楚地捕捉到出发双曲轨道特性的边际差异。此外，当将贴片圆锥设计用作初始猜测时，数值方法无法在没有到达双曲线的附加边界条件的情况下识别这些设计选项。另一方面，每个建议的设计选项在用作数值细化的初始猜测时，会收敛到相应的到达几何形状，从而生成四个不同的数值设计。考虑到行星际转移对离场双曲轨道特性高度敏感，使用所提出的方法对转移轨迹设计的改进非常重要。对于2018年的最低能量机会，出发停车轨道角度（即RAAN和AOP）以及拟议的和V无限调谐的贴片圆锥设计之间的差异分别约为0.6和0.3度。之所以如此，是因为在拟议的方法中将太阳引力包含在拟球体内。提出的设计减少了目标条件下的偏差。与V-infinity调谐的修补设计相比，通过数值传播，大约1811,560 km（改进了约95％），从拟议方法的不同设计选项中获得的最接近进场高度为1965至11,457 km。围手术期的时间偏差也大大减少了约95％。使用所提出的方法获得的设计与数值设计非常接近。拟议的设计进行数值精修所需的时间仅为8 s，而使用附加到达信息的V-无穷大调谐贴片圆锥设计大约需要420 s。而且，所提出的方法生成跨度为一年的出发时间段的设计所花费的计算时间为0.1 s，这与V-infinity调谐补丁圆锥法所花费的0.08 s可比。

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  • 来源
    《Journal of guidance, control, and dynamics》 |2016年第12期|2794-2804|共11页
  • 作者

    S. P. Parvathi; R. V. Ramanan;

  • 作者单位

    Indian Institute of Space Science and Technology,Trivandrum 695 547, Kerala, India;

    Indian Institute of Space Science and Technology,Trivandrum 695 547, Kerala, India;

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