Rocket Landing Control Using Gimbal and Fin Force Coordination
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Solution Overview
Problem
Existing rocket control systems face challenges in continuously controlling horizontal translational motion during landing operations without increasing manufacturing and operation costs, particularly due to inactive periods caused by the balance between lift and thrust components.
Innovation Solution
A rocket control system incorporating a gimbal actuator, a fin actuator, a measurement unit, and a control unit that dynamically controls the steering angles of the gimbal mechanism and the attitude control fin to generate direct forces perpendicular to the velocity vector, thereby maintaining control over horizontal translational motion without attitude changes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional thrusters are added to solve the inactive period problem, then continuous horizontal control is achieved, but body weight and manufacturing costs increase
Solution Approach 1:
The patent makes the rocket body itself perform multiple functions: it generates both lift (aerodynamic force) and horizontal thrust components by coordinating attitude changes with engine gimbal adjustments. This eliminates the need for separate dedicated thrusters while achieving continuous horizontal control capability.
Solution Approach 2:
The patent combines the lift generation function and thrust direction control function into a unified control system that coordinates attitude changes with engine steering. This merging of functions allows the existing rocket components to work together to provide continuous horizontal control without adding separate thruster systems.
2Reliability
If additional thrusters are added to solve the inactive period problem, then continuous horizontal control is achieved, but manufacturing costs increase
Solution Approach 1:
The patent makes the rocket body itself perform multiple functions: it generates both lift (aerodynamic force) and horizontal thrust components by coordinating attitude changes with engine gimbal adjustments. This eliminates the need for separate dedicated thrusters while achieving continuous horizontal control capability.
Solution Approach 2:
The patent combines the lift generation function and thrust direction control function into a unified control system that coordinates attitude changes with engine steering. This merging of functions allows the existing rocket components to work together to provide continuous horizontal control without adding separate thruster systems.
3Ease of operation
If attitude change control is used during landing, then horizontal path control is achieved, but an inactive period occurs when lift and thrust components balance
Solution Approach 1:
The patent dynamically adjusts the control strategy by coordinating real-time attitude changes with engine gimbal angle adjustments. This dynamic coordination ensures that the horizontal control force remains non-zero throughout the landing process, eliminating the static inactive period that occurs when lift and thrust simply balance each other.
Solution Approach 2:
The patent changes the control parameters from simple attitude angle adjustments to coordinated adjustments of both attitude angle and engine gimbal angle. This parameter expansion allows the control system to maintain horizontal force generation even when vertical forces balance, eliminating the inactive period.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution enables continuous control of horizontal translational motion, ensuring accurate rocket landing operations while avoiding inactive periods and maintaining cost-effectiveness by not requiring additional thrusters.
Implementation Method 1
the aerodynamic force proportional to this angle of attack a acts on the rocket body. This aerodynamic force includes a component perpendicular to the velocity vector V of the rocket, which is called 'lift'.
Implementation Method 2
thrust T acts on the rocket body by a jet produced by an engine
Data Source
AI summary
Provided is a method of controlling horizontal translational motion of a rocket without changing the attitude of the body and without increasing manufacturing costs and operation costs. This allows for accurate execution of rocket landing operation. A rocket control system includes a gimbal actuator that controls a steering angle of a gimbal mechanism located on a lower side of the body of the rocket with respect to the center of gravity; a fin actuator that controls a steering angle of an attitude control fin located on an upper side of the body of the rocket with respect to the center of gravity; a measurement unit that measures a physical quantity related to motion of the body of the rocket; and a control unit that controls the gimbal mechanism and the attitude control fin according to a result of measurement by the measurement unit to control horizontal translational motion of the rocket.