Reusable rocket return stage mass estimation method
By using periodic theoretical mass estimation and online deviation correction, and by using the rocket system's apparent acceleration information to correct engine performance deviations, the problem of inaccurate mass estimation during the rocket's reentry phase was solved, achieving high-precision mass estimation and reliable landing assurance.
CN122408549APending Publication Date: 2026-07-17BEIJING LANDSPACETECH CO LTD
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Patent Information
- Application Number
- CN202610355648.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-03-23
- Publication Date
- 2026-07-17
AI Technical Summary
Technical Problem
In existing technologies, deviations in engine performance lead to inaccurate estimation of the rocket's reentry phase mass, affecting the guidance accuracy and landing safety of the reentry phase.
Method used
By using periodic theoretical mass estimation, multi-segment overload information acquisition, and online deviation correction, the engine performance deviation is corrected using the rocket system's apparent acceleration information, thereby improving the accuracy of mass estimation.
Benefits of technology
It significantly improves the accuracy and robustness of rocket reentry mass estimation, ensuring reliable estimation under complex and highly dynamic environments and guaranteeing landing safety.
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Figure CN122408549A_ABST
Abstract
一种可复用火箭返回段质量估计方法，包括以下步骤：步骤S1，在火箭返回段的发动机工作期间，基于发动机工作参数周期性地估算火箭的理论质量；步骤S2，在所述发动机推力达到稳定工作状态后，于多个不同的采集时间点，分别采集对应时间段内的箭体系视加速度信息，并记录各所述采集时间点对应的由所述周期性理论质量估算步骤得到的理论质量；步骤S3，基于多组所述箭体系视加速度信息与对应理论质量，在线计算质量偏差，并根据所述质量偏差计算质量流量偏差，基于所述理论质量计算所述理论质量的总质量偏差，以得到初步修正后的质量估计值。该质量估计方法能够在线修正偏差，提高估计精度。
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