固体轨控发动机作为飞行器轨道控制的关键执行机构，其推力性能直接决定轨道控制精度。当前推力性能设计依赖工程经验，仅满足预设推力调节范围要求，对喉栓型面关键参数与推力响应之间的强非线性关系考虑不足，参数的极小偏差可能导致极大的推力偏差，制约推力精确调控的效率与准确性，亟需开展面向推力响应线性化与精确匹配的喉栓型面关键参数精细化设计。为此，建立轨控发动机燃气阀参数化数值仿真模型，通过优化拉丁超立方设计生成喉栓型面关键参数样本，计算各组样本在不同喉栓位移下的推力响应；采用径向基函数分别建立不同位移下推力关于喉栓型面关键参数的快速预示模型；在此基础上，以推力输出线性度及其与目标推力曲线的匹配精度为优化目标，结合非精确搜索策略对喉栓型面关键设计参数进行迭代寻优，实现了面向推力线性匹配的喉栓型面重构。设计结果表明，喉栓型面优化后，在2-10 mm位移调控范围内，推力响应与喉栓位移高度线性匹配，设计推力与需求推力偏差的均方根误差降低96%，验证了所提方法的有效性。所构建的喉栓型面优化设计框架，为推力线性匹配和精确调控提供理论与方法支撑。

As a key actuator for spacecraft orbit control, the thrust performance of a solid divert control motor (SDCM) directly determines the accuracy of orbit control. The thrust design of SDCMs generally relies on engineering experience. Existing designs can satisfy the prescribed thrust regulation range, but the strong nonlinear relationship between the key parameters of the pintle contour and thrust response is insufficiently considered. Small deviations in these parameters may lead to large deviations in thrust response, limiting the efficiency and accuracy of precise thrust regulation. Therefore, the key geometric parameters of the pintle contour must be refined to linearize the thrust response and achieve accurate thrust matching. To this end, a parametric numerical simulation model of the gas valve of the solid divert control motor was established. Samples of the key pintle contour parameters were generated using an optimal Latin hypercube design, and the thrust responses of each sample at different pintle displacements were calculated. Subsequently, radial basis functions (RBFs) were used to construct rapid prediction models of thrust with respect to the key pintle contour parameters separately at different displacements. On this basis, the key design parameters were iteratively optimized using an inaccurate search strategy, with thrust-output linearity and matching accuracy relative to the target thrust curve defined as the optimization objectives, thereby enabling the reconstruction of the SDCM pintle contour for linear thrust matching. The design results demonstrate that the optimized pintle contour enables a highly linear thrust response with respect to pintle displacement over a regulation range of 2-10 mm, reducing the root mean square error (RMSE) between the designed and required thrust by 96% and thereby validating the effectiveness of the proposed method. The optimization-based design framework developed in this study provides theoretical and methodological support for linear thrust matching and precise thrust regulation.