Rocket Attitude Control via Thrust Vector Integration
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Solution Overview
Problem
Existing rocket vehicle attitude control systems require a large number of thrusters to maintain precise control, which increases fuel consumption and complexity, particularly when achieving roll moments.
Innovation Solution
A rocket vehicle equipped with a variable-vector main thruster and a controller that allows the main thruster to compensate for roll moments by adjusting its thrust direction, enabling the use of only one attitude control thruster on the leeward side to reduce fuel consumption and improve efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional attitude control systems use pairs of attitude control thrusters for roll control, then precise attitude control is maintained, but fuel consumption increases and system complexity increases
Solution Approach 1:
The patent combines the functions of attitude control thrusters and main thruster into an integrated system. The main thruster, equipped with thrust vector control capability, shares the workload of attitude control with the attitude control thrusters. This merging of functions allows the system to achieve the same attitude control precision using fewer thruster firings, thereby reducing fuel consumption while maintaining control reliability
Solution Approach 2:
The main thruster is designed with multi-functionality, serving both as the primary propulsion source and as an attitude control actuator through thrust vector control. This universal design allows the main thruster to compensate for reduced attitude control thruster activity, enabling fuel-efficient operation while maintaining precise attitude control capability
2Use of energy by moving object
If fewer attitude control thrusters are fired, then fuel consumption is reduced, but attitude control precision may deteriorate
Solution Approach 1:
The integrated control system continuously monitors the vehicle's attitude state and dynamically adjusts the thrust vectoring commands based on real-time feedback. This feedback mechanism ensures that when fewer attitude control thrusters are fired, the main thruster's thrust vectoring provides precise compensation, maintaining attitude control precision while reducing overall fuel consumption
3Use of energy by moving object
If thrust vector control is used to compensate for reduced thruster activity, then fuel efficiency improves, but control system complexity increases
Solution Approach 1:
The control system merges the propulsion control and attitude control functions into a single integrated controller. This integration allows the system to coordinate main thruster thrust vectoring with attitude control thruster firing in a unified manner, achieving fuel efficiency without requiring separate complex control systems for each function
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 approach reduces fuel use by approximately 10% and minimizes unexpected forces due to jet interaction, enhancing the rocket's kinematic performance while maintaining precise control.
Implementation Method 1
a main thruster coupled to the fuselage, wherein the main thruster provides forward thrust to the rocket vehicle
Implementation Method 2
pairs of attitude control thrusters for providing roll moments in opposite directions
Implementation Method 3
the main thruster is a vector control thruster that allows variation in thrust direction of the main thruster; and wherein the controller changes the thrust direction of the main thruster to compensate for the lateral moment
Data Source
Figure 1~2
Figure 3~4
Figure 5~7
AI summary
A rocket vehicle (10) includes a controller (18) that integrates operation of a variable-vector main thruster (12) and attitude control thrusters (16). When the main thruster (12) is firing and roll is commanded, the controller (18) can provide roll moment by firing only a single attitude control thruster (16), while changing the thrust vector of the main thruster (12) to offset any pitch/yaw moments induced by the firing of the single attitude control thruster (16). The single attitude control thruster (16) may be a thruster on the leeward side of the rocket vehicle (10). Since there is a lower wall pressure on the leeward side of the rocket vehicle (10), the thruster efficiency is improved by accomplishing roll by use of a single thruster (16) (which may be one of a pair of thrusters used to achieve roll in one direction). A significant reduction in fuel use may be accomplished.