Carrier Rocket Wind Estimation via Apparent Acceleration
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Solution Overview
Problem
Carrier rockets without airflow measurement devices cannot perform rapid real-time estimation of wind speed information, leading to increased errors in their attitude control systems due to uncompensated wind interference.
Innovation Solution
A method and apparatus that iteratively updates a wind speed vector prediction using a transfer matrix and error calculations between predicted and measured rocket body apparent accelerations, without relying on airflow measurement data, to converge to a stable wind speed estimation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a carrier rocket is not equipped with an airflow measurement device, then the device complexity is reduced, but the ability to perform rapid real-time estimation of wind speed information deteriorates
Solution Approach 1:
The patent uses rocket body apparent acceleration as an intermediary parameter to indirectly estimate wind speed. Instead of directly measuring wind speed with complex airflow measurement devices, the system measures apparent acceleration (which is easier to obtain) and uses it as a mediator to infer wind speed information through the dynamic model and iterative algorithm.
Solution Approach 2:
The patent replaces the mechanical airflow measurement system with a computational approach. Instead of using physical airflow measurement devices that directly sense wind, the system uses mathematical models, transfer matrices, and iterative algorithms to compute wind speed from apparent acceleration data, substituting mechanical measurement with computational estimation.
2Reliability
If wind interference compensation is implemented, then attitude control error is reduced, but the requirement for real-time wind speed estimation increases system complexity
Solution Approach 1:
The patent implements a feedback mechanism where the estimated wind speed is continuously updated based on the difference between predicted and actual apparent acceleration. The iterative algorithm uses the error signal to adjust the wind speed estimation, creating a closed-loop feedback system that improves accuracy while using existing sensors.
Solution Approach 2:
The system uses its own existing sensors (accelerometers, navigation systems) and internal dynamic models to generate wind speed estimates without requiring external specialized equipment. The rocket's own flight data and apparent acceleration measurements are sufficient to self-determine wind conditions through the computational methodology.
Data Source
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AI summary
The present invention discloses a wind estimation method and apparatus for a carrier rocket, a device and a storage medium. The wind estimation method for a carrier rocket comprises: inputting rocket body state parameters and a wind speed vector predicted value into a preset apparent acceleration prediction model to obtain a rocket body apparent acceleration predicted value; calculating an error between the rocket body apparent acceleration predicted value and a rocket body apparent acceleration measured value; calculating an updated wind speed vector predicted value by using a preset transfer matrix and the error between the rocket body apparent acceleration predicted value and the rocket body apparent acceleration measured value; determining whether the updated wind speed vector predicted value converges to a preset range; and when the updated wind speed vector predicted value converges to a preset range, using the updated wind speed vector predicted value as a final wind speed vector predicted value; or when the updated wind speed vector predicted value does not converge to the preset range, using the updated wind speed vector predicted value as the next wind speed vector predicted value. In this way, a wind speed vector can be quickly estimated without relying on airflow measurement data.