运载火箭时序协同设计与综控诸元自动生成

Collaborative Design and Automated Generation of Launch Vehicle Flight Sequences and Comprehensive Control Parameters

摘要:

针对运载火箭飞行时序多专业协同设计过程中时间基准分散、综控诸元人工生成易出错以及设计基准与飞行试验判读数据难以关联等问题，提出一种飞行时序协同设计与综控诸元自动生成方法。首先，采用基准事件对准机制，将不同专业子时序映射至统一的主时序时间轴；其次，构建以初始通道状态为共同起点的双路径独立状态演进算法，使紧急关机路径与全时序路径分别进行控制字状态计算，并保持通道状态在相邻特征时序段之间连续继承；然后，在执行硬件配置中预定义各I/O板控制字导出列表，使诸元序号由硬件接口模板确定，避免因当前时序中控制字缺项造成序号偏移；最后，通过固定版本引用和导出快照建立综控诸元与飞行试验判读数据之间的追溯关系。以某两级单芯级运载火箭为对象开展工程验证，系统自动生成综控诸元1070行，诸元序号与执行硬件接口模板一致。在相同输入数据条件下，与传统Excel人工整理方法相比，综控诸元生成及校核时间由56 h缩短至30 min，耗时缩短约99.1%，人工修改条目数由100余项降低至10项；在本次工程验证中，经人工复核，未发现诸元序号、控制字状态及版本不一致问题。结果表明，该方法能够提高飞行时序协同设计和综控诸元生成的效率、一致性与可追溯性，并为飞行试验时序自动判读提供统一设计基准。

Abstract:

To address the problems of dispersed time references in multidisciplinary collaborative design of launch vehicle flight sequences, error-prone manual generation of comprehensive control parameters, and difficulty in correlating design baselines with flight-test verification data, a collaborative flight-sequence design and automated comprehensive control parameter generation method is proposed. First, a baseline-event alignment mechanism is adopted to map sub sequences from different disciplines onto a unified master-sequence timeline. Second, a dual-path independent state-evolution algorithm is constructed with the initial channel state as the common starting point, enabling the emergency shutdown path and the full-sequence path to perform control-word state calculations independently while maintaining continuous channel-state inheritance between adjacent feature-sequence segments. Third, a control-word export list is predefined for each input/output board in the execution-hardware configuration, so that parameter indices are determined by the hardware interface template, thereby avoiding index shifts caused by missing control words in the current sequence. Finally, fixed-version references and export snapshots are used to establish traceability between comprehensive control parameters and flight-test verification data. Engineering validation was conducted using a two-stage launch vehicle without strap-on boosters. The system automatically generated 1,070 rows of comprehensive control parameters, with all parameter indices consistent with the execution-hardware interface template. Under the same input conditions, compared with the conventional Excel-based manual process, the total time required for parameter generation and checking was reduced from 56 h to 30 min, representing a reduction of approximately 99.1%, while the number of manual revisions decreased from more than 100 to 10. During the engineering review of the automatically generated results, no parameter-index, control-word-state, or version-consistency errors were identified. The results demonstrate that the proposed method improves the efficiency, consistency, and traceability of collaborative flight-sequence design and comprehensive control parameter generation, while providing a unified design baseline for automated flight-test sequence verification.