An integrated algorithm to design the optimal ascent trajectory of a target Sun-synchronous orbit (SSO) for small-lift launch vehicles is studied in this paper. A general problem description is provided, including the specific pitch law designed for an ascent trajectory to SSO and the definitions of design variables and equality/inequality constraints. Then an integrated optimization scheme is introduced to solve this problem. In order to improve its efficiency, a preliminary determination method is to analytically generate two sensitive design variables related with the coast arc. With the help of the two design variables, an initial combination of design variables can be obtained by solving separately the optimization problems of two powered phases. Based on the predetermination method, an efficient integrated algorithm using hierarchical optimization is proposed. A simulation based on a type of small-lift Electron Rocket and Rutherford engine is performed using this hierarchical optimization algorithm and the feasibility and efficiency of this algorithm is evaluated. These systematic investigations on all the possible injected orbits give a full detail of launching capability for Electron Rocket.

本文研究了一种设计用于小举升运载工具的目标太阳同步轨道（SSO）最佳上升轨迹的集成算法。提供了一个一般性的问题描述，包括为SSO的上升轨迹设计的特定音高定律，以及设计变量和相等/不相等约束的定义。然后引入了集成优化方案来解决该问题。为了提高效率，一种初步的确定方法是分析性地生成与海岸弧有关的两个敏感设计变量。借助于两个设计变量，可以通过分别解决两个供电阶段的优化问题来获得设计变量的初始组合。根据预定方法，提出了一种利用层次优化的高效集成算法。使用该分层优化算法对基于小升程电子火箭和卢瑟福发动机的发动机进行了仿真，并评估了该算法的可行性和效率。这些对所有可能的注入轨道的系统研究提供了电子火箭发射能力的完整细节。