Orbit Attitude Control Device Using Acceleration Feedback
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Solution Overview
Problem
Existing orbit and attitude control systems for flying objects are vulnerable to mechanical errors, thermal expansions, and fuel uniformity issues, leading to deviations from intended courses and unstable combustion chamber pressures.
Innovation Solution
A system comprising multiple nozzles with controlled opening degrees, a control section for calculating and applying nozzle opening degree correction values based on combustion chamber pressure and acceleration measurements, ensuring robust attitude control and maintaining constant combustion chamber pressure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional thruster control method is used, then the system structure is simple, but the control is vulnerable to mechanical errors, thermal expansions, and fuel uniformity issues leading to course deviation
Solution Approach 1:
The patent implements feedback control by detecting the actual acceleration of the flying object and comparing it with the commanded acceleration. The difference (error) is used to generate correction values that adjust the opening degrees of the nozzles. This closed-loop feedback mechanism compensates for disturbances such as mechanical errors, thermal expansions, and fuel uniformity issues, thereby improving control robustness without significantly increasing system complexity
Solution Approach 2:
The patent replaces direct mechanical control of nozzle opening degrees with an acceleration-based control system. Instead of mechanically adjusting each nozzle based on complex calculations, the system uses acceleration sensors to detect actual motion and automatically adjusts nozzle openings based on detected acceleration errors. This substitution of mechanical control with sensor-based feedback simplifies the control mechanism while improving reliability
2Stability of the object's composition
If the opening degrees of nozzles are controlled based on commanded values only, then the control system is simple, but the combustion chamber pressure becomes unstable due to various disrupting factors
Solution Approach 1:
The patent uses acceleration feedback to indirectly control combustion chamber pressure stability. By detecting actual acceleration and comparing it with commanded acceleration, the system generates correction values that adjust nozzle opening degrees. This feedback loop ensures that the combustion process remains stable despite disruptions, as the system continuously adapts nozzle openings to maintain the desired thrust and pressure conditions
Solution Approach 2:
The control system automatically adjusts nozzle opening degrees based on detected acceleration errors without requiring external intervention. The system self-regulates by using the acceleration sensor feedback to generate correction values that are directly applied to the nozzle control, maintaining combustion stability through autonomous adaptation to changing conditions
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
The system achieves robust orbit and attitude control, resistant to disrupting factors, while maintaining stable combustion chamber pressure, thereby ensuring accurate and stable flight trajectories.
Implementation Method 1
A combustion gas is supplied to a plurality of nozzles included in a thruster from a common combustion chamber
Implementation Method 2
Each nozzle injects the combustion gas with an amount corresponding to the opening degree, and thereby an orbit attitude of the flying object is controlled
Implementation Method 3
a first axis acceleration sensor configured to detect a first axis acceleration which is an acceleration along the first axis direction
Data Source
AI summary
An orbit attitude control device includes a divert thruster including a plurality of nozzles. First group nozzles inject combustion gas in opposite directions along a first axis. Second group nozzles inject combustion gas in opposite directions along a second axis. A control section calculates correction values for opening degree commands based on a detection value of a pressure of the combustion chamber and a command value of the pressure, and corrects the opening degree command values by the correction values. The device further includes a first axis acceleration sensor for detecting acceleration along the first axis and a second axis acceleration sensor for detecting acceleration along the second axis. The correction values for the opening degrees of the first group nozzles are determined by a first axis acceleration, and the correction values for the opening degrees of the second group nozzles are determined by a second axis acceleration.