Spacecraft Attitude Control via Deployable Elongated Member
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Solution Overview
Problem
Existing attitude control systems for spacecraft, such as reaction wheel assemblies and control moment gyroscopes, suffer from issues like excess vibrations, reliability concerns, and electromagnetic interference, and they require fuel, which increases the spacecraft's weight and reduces its operational time.
Innovation Solution
The proposed Multifunctional Structures for Attitude Control (MSAC) system uses deployable structures with embedded actuators to change the attitude of a spacecraft by deflecting and altering the length of an elongated member, thereby controlling the spacecraft's attitude without continuous spinning or sliding parts, fuel, or significant electromagnetic interference.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If reaction wheel assemblies or control moment gyroscopes are used for attitude control, then the spacecraft can maintain orientation, but excess vibrations and jitters are transmitted to the spacecraft
Solution Approach 1:
The patent replaces traditional mechanical attitude control systems (reaction wheels, control moment gyroscopes) with a magnetic field-based system using magnetorque coils. This substitution eliminates the mechanical rotating components that generate vibrations and jitters, while maintaining attitude control functionality through electromagnetic interaction with the Earth's magnetic field.
Solution Approach 2:
The patent introduces magnetic fields as an intermediary between the spacecraft and the external environment for attitude control. By using magnetorque coils to generate magnetic moments that interact with the Earth's magnetic field, the system achieves torque generation without direct mechanical moving parts, thereby eliminating vibration transmission to the spacecraft structure.
2Ease of operation
If reaction thrusters are used for attitude control, then the spacecraft can change orientation, but fuel is consumed which increases weight and reduces operational time
Solution Approach 1:
The patent replaces chemical propulsion systems (reaction thrusters requiring fuel) with an electromagnetic system using magnetorque coils. This substitution eliminates the need for propellant mass, significantly reducing spacecraft weight while maintaining attitude maneuverability through interaction with the Earth's magnetic field.
Solution Approach 2:
The patent changes the fundamental operating parameter from chemical energy consumption (fuel) to electromagnetic energy consumption. By utilizing the Earth's magnetic field as an external resource, the system achieves continuous attitude control without consuming onboard mass, thereby extending operational time and reducing initial weight.
3Duration of action of moving object
If magnetic torque coils are used for attitude control, then the spacecraft can operate without fuel, but electromagnetic interference is generated that affects sensitive payloads
Solution Approach 1:
The patent applies local quality by strategically positioning magnetorque coils and sensitive payloads in different spatial locations on the spacecraft. By separating the electromagnetic actuation components from sensitive instruments and using directional coil configurations, the system minimizes electromagnetic interference exposure to payloads while maintaining effective attitude control.
Solution Approach 2:
The patent uses the Earth's magnetic field as an external intermediary for attitude control, allowing the spacecraft to generate control torques without requiring high-power onboard electromagnetic transmitters. This approach reduces the intensity of electromagnetic fields generated by the spacecraft itself, thereby minimizing interference with sensitive payloads while maintaining operational capability.
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 MSAC system provides reliable and precise attitude control with reduced vibrations and electromagnetic interference, eliminates the need for fuel, and increases the operational time of the attitude control system, while also reducing the spacecraft's weight and volume.
Implementation Method 1
The plurality of actuators are configured to deflect the angular position of the elongated member relative to the axis, and to alter the length of the elongated member
Implementation Method 2
The plurality of actuators are configured to deflect a position of the elongated member, and to alter a mass moment of inertia of the elongated member
Data Source
AI summary
A structure for changing the attitude of a spacecraft is provided including an elongated member and a plurality of actuators coupled to the elongated member. The elongated member is coupled to the spacecraft. The elongated member has a length and an angular position relative to an axis. The plurality of actuators are configured to deflect the angular position of the elongated member relative to the axis and to alter the length of the elongated member.