Gimbaled Electric Thrusters for Spacecraft Attitude and Orbit Control
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Solution Overview
Problem
Existing spacecraft propulsion systems, particularly chemical and hybrid systems, are costly, hazardous, and require complex design and handling, limiting their use and efficiency in satellite operations.
Innovation Solution
The use of an electric propulsion system with independently movable thrusters and a gimbaled platform, eliminating the need for chemical propulsion systems, allowing for attitude and orbit control, and reducing mass and launch costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If chemical propulsion systems are used, then thrust is achieved through chemical reactions, but the systems are costly, hazardous, and require complex design and handling
Solution Approach 1:
The patent replaces chemical propulsion systems with electric propulsion systems. Instead of using chemical reactions to generate thrust, the invention uses electric fields and magnetic fields to accelerate ions or plasma, eliminating hazardous chemicals while maintaining propulsion capability. This substitution resolves the contradiction by removing hazards and complexity associated with chemical handling while preserving the essential thrust generation function.
Solution Approach 2:
The patent changes the fundamental operating parameters of the propulsion system from chemical reactions to electrical and magnetic field interactions. By transitioning from chemical to physical field-based propulsion, the system achieves safer operation with reduced complexity. The electric propulsion system uses controlled electrical fields to ionize propellant and generate thrust, eliminating the need for complex chemical storage, handling, and reaction management infrastructure.
2Ease of manufacture
If chemical propulsion systems are used, then thrust is achieved through chemical reactions, but processing and launch costs are increased
Solution Approach 1:
The patent substitutes chemical propulsion with electric propulsion, replacing hazardous chemical processing with safer electrical field generation. This eliminates the need for specialized chemical handling facilities, storage infrastructure, and safety protocols, thereby reducing processing costs while improving operational safety. The electric propulsion system uses standard electrical components and field generation mechanisms that are cheaper and safer to manufacture and deploy.
3Adaptability or versatility
If electric propulsion systems with gimbaled platforms are used, then attitude and orbit control is enabled, but the device complexity increases
Solution Approach 1:
The patent implements a multi-functional electric propulsion system where the same electric thrusters and gimbaled platforms serve multiple purposes: attitude control, orbit correction, and momentum management. By making the propulsion system universal for all control functions, the patent reduces overall system complexity compared to having separate dedicated systems for each function. The electric propulsion system's versatility allows a single integrated design to handle diverse control requirements.
Solution Approach 2:
The patent employs gimbaled platforms that can dynamically adjust the orientation of electric thrusters relative to the spacecraft body. This dynamic positioning capability allows the same physical thruster to contribute to different control moments by changing its pointing direction, thereby achieving versatile attitude and orbit control without requiring multiple fixed-position thrusters for each function, thus managing complexity while enhancing adaptability.
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 satellite mass, extends mission life, and lowers processing and launch costs while enabling efficient repositioning and maneuvering in space without hazardous materials, thus enhancing operational safety and efficiency.
Implementation Method 1
Thrust is achieved by acceleration of propellants. Propellants may be accelerated substantially by pressure differences (cold or hot gas systems), chemical reactions (including catalytic decomposition, e.g. hydrazine monopropellant systems, hypergolic bipropellant reactions, solid rockets, etc.), and electrical and magnetic interactions (including ion propulsion systems, stationary plasma systems, Hall effect thrusters, magneto-plasma thrusters, etc., (e.g., electric propulsion)).
Data Source
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AI summary
Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame, a power source coupled to the frame and a payload coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus.