Staged Ion Thruster System for Small Satellite Propulsion
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Solution Overview
Problem
Current propulsion technologies for small satellites are difficult to miniaturize, limiting the size, weight, and power of spacecraft, and lack a capable miniaturized propulsion system for high Δν maneuvers and high-precision attitude control without relying on reaction wheels.
Innovation Solution
The development of a staged ion propulsion thruster system with detachable ion thruster layers and a shared voltage source, allowing for sequential activation and jettisoning of thruster layers to extend operational lifetime and reduce dry mass, while maintaining compactness and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If current propulsion technologies are used for small satellites, then propulsion capability is achieved, but the system size, weight, and power requirements increase
Solution Approach 1:
The ion propulsion system is divided into multiple detachable ion thruster layers that can be sequentially activated and jettisoned. Each layer contains ion thrusters, propellant tanks, and associated components as separate modular units, allowing the spacecraft to carry multiple propulsion stages without permanently increasing operational mass
Solution Approach 2:
spent ion thruster layers are jettisoned after their propellant is depleted or they complete their operational mission. This discarding approach reduces the dry mass of the spacecraft over time, improving the thrust-to-mass ratio and enabling longer operational lifetimes without carrying unnecessary dead weight
2Duration of action of moving object
If ion thruster layers are made detachable for sequential operation, then operational lifetime is extended, but device complexity increases
Solution Approach 1:
The thruster system is segmented into standardized modular layers with uniform interfaces for electrical, propellant, and structural connections. This segmentation allows complex multi-stage operation to be achieved through simple repetition of identical modular units rather than designing and managing unique complex systems
Solution Approach 2:
Each ion thruster layer is designed as a universal module that can perform the same propulsion function independently. The standardized interfaces and identical design across all layers allow any layer to replace another, simplifying the control system and reducing the complexity of managing multiple different thruster types
3Power
If multiple ion thruster layers are stacked, then propulsion capability is enhanced, but the volume and area of the spacecraft increase
Solution Approach 1:
Multiple ion thruster layers are stacked vertically one on top of another in a nested configuration, similar to nested dolls. This vertical stacking allows multiple propulsion systems to occupy the same horizontal footprint, enhancing propulsion capability without significantly increasing the spacecraft's planar area or overall volume
Solution Approach 2:
The propulsion system transitions from a horizontal or distributed layout to a vertical stacked arrangement. By utilizing the vertical dimension for layer stacking, the system packs multiple thruster layers into a compact space, reducing the spacecraft's horizontal footprint while maintaining enhanced propulsion 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
This solution provides high Δν propulsion and increased operational lifetimes for small satellites, reducing costs and complexity by enabling efficient exploration of near Earth objects and deep space missions with reduced dry mass and mechanical complexity.
Implementation Method 1
The voltage source applies a voltage differential to the ion thruster layer to emit ions when the ion thruster layer is connected to the propellant source and/or the voltage source
Data Source
AI summary
Spacecraft thruster systems are disclosed. In some instances, a spacecraft thruster system may include stacked ion thrusters and/or ion thruster layers. The ion thrusters and/or ion thruster layers may be sequentially activated and jettisoned from the thruster system after use.