A solid rocket trajectory optimization design method based on internal trajectory parameterization modeling

By using internal ballistic parameterized modeling and joint optimization design, the problem of insufficient range release of solid rockets was solved, enabling rapid optimization and efficient design, and improving rocket performance and development efficiency.

CN121637679BActive Publication Date: 2026-05-05XIAN MODERN CONTROL TECH RES INST
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Patent Information

Application Number
CN202610153128.4
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2026-02-03
Publication Date
2026-05-05
Estimated Expiration
2046-02-03

AI Technical Summary

Technical Problem

Existing solid rocket design methods fail to fully realize range potential, and have long development cycles and high testing costs. Traditional serial design methods result in internal ballistic parameter modifications relying on external ballistic feedback, leading to low iteration efficiency.

Method used

A method based on parameterized modeling of internal ballistics is adopted to construct a joint optimization model of internal and external ballistics. The model is solved using a sequential quadratic programming algorithm and the Gaussian pseudospectral method to optimize engine parameters and achieve joint optimization of internal and external ballistics.

Benefits of technology

It significantly improved the performance of solid rockets, shortened the development cycle, ensured the feasibility and effectiveness of the optimization results, and improved the rocket's carrying capacity through joint optimization design of internal and external trajectories.

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Abstract

This invention belongs to the field of commercial aerospace and solid rocket optimization, and discloses a solid rocket trajectory optimization design method based on internal ballistic parameterization modeling. The method includes: determining the structural and energy characteristic parameters of the solid rocket motor; designing different types of propellant grains and constructing their geometric models; determining the internal ballistic parameterization model of the motor; constructing a dynamic model for joint optimization of the internal and external trajectories of the solid rocket; based on the dynamic model, setting the optimization objective of the joint internal and external trajectory optimization problem and representing it with a performance index function, and setting the constraints of the joint internal and external trajectory optimization problem; discretizing the dynamic model, performance index function, and constraints, converting them into a nonlinear programming problem and solving it to obtain the optimization results corresponding to each type of propellant grain; determining the performance index corresponding to each type of propellant grain based on the optimization results, and using the performance index to determine the propellant grain as the optimal design scheme.
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