Hall Effect Thruster Solar Power Direct Coupling
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Solution Overview
Problem
Conventional solar powered spacecraft power systems are inefficient and heavy due to the need for large power management and distribution (PMAD) systems to handle peak power demands of Hall effect thrusters, leading to reduced thrust and extended transit times as the solar array ages.
Innovation Solution
Connecting the electric propulsion system directly to the solar photovoltaic array and periodically adjusting operating parameters to operate at the maximum available output power, eliminating the need for a PMAD system and reducing power losses, size, and weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If a large PMAD system is used to handle peak power demands of Hall effect thrusters, then the spacecraft can supply required power to the EP on demand, but the PMAD system becomes large and heavy
Solution Approach 1:
The patent extracts the electric propulsion load from the conventional PMAD system architecture by connecting the Hall effect thruster directly to the solar photovoltaic array through a dedicated power processing unit. This separation allows the main PMAD system to be reduced in size since it no longer needs to handle the full peak power demand of the thruster, while the dedicated power processing unit handles only the thruster's power needs efficiently.
2Power
If the PMAD system is designed to handle peak power for EP, then power can be supplied on demand, but the system must also dissipate excess power when EP is not demanding, requiring extra size and weight
Solution Approach 1:
The patent extracts the electric propulsion power processing function from the main PMAD system, creating a dedicated power processing unit that handles the thruster's power demands independently. This eliminates the need for the main PMAD system to be oversized for both peak EP power and excess power dissipation, as the dedicated unit can efficiently manage the thruster's variable power needs without requiring large dissipation capabilities in the main system.
3Reliability
If peak power tracking lowers voltage as the solar array ages, then operational stability margin is preserved, but the thruster does not receive all available power, reducing thrust and extending transit time
Solution Approach 1:
The patent implements a feedback control system in the dedicated power processing unit that continuously monitors the solar array's output characteristics and adjusts the power delivered to the thruster accordingly. This feedback mechanism allows the system to operate at the maximum power point of the solar array at any given time, adapting to aging effects while maintaining optimal thrust performance, rather than using conservative fixed voltage reduction strategies.
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 enhances efficiency, reduces mass and costs, and maintains the solar array at peak power, ensuring the thruster operates at maximum available power, thereby increasing thrust and reducing spacecraft transit times.
Implementation Method 1
power is generated by a solar photovoltaic array (SP)
Implementation Method 2
the EP load such as Hall effect thrusters
Data Source
AI summary
A solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array in parallel with the spacecraft power system; the electric propulsion system including a Hall effect thruster, a thruster power supply for driving the thruster; a sensor for sensing the power output of the solar array and a controller responsive to the power output of the solar array and configured to periodically adjust an operating parameter of the thruster to operate the thruster at the maximum available output power of the solar array including comparing a previous solar array output power level with a later solar array output power level, and incrementing the operating parameter with a positive value if the later is greater and with a negative value if the later is lesser; a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array, and a power management and distribution system connected to the solar photovoltaic array for distributing power to one or more bus loads and payloads.