Embedded Command Modules for Manual Spacecraft De-orbit Control
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Solution Overview
Problem
Current spacecraft systems lack an effective means to safely de-orbit a geosynchronous satellite in the event of a dual Spacecraft Control Processor failure, as they rely on a single processor for thruster and solar wing control, leading to a critical need for an alternative control mechanism to manage de-orbiting without the costly addition of a third processor.
Innovation Solution
The implementation of Embedded Command Modules (ECMs) that can be directly commanded from a Central Command and Telemetry Unit, allowing manual ground control of latch valves, thruster valves, and solar wing drives, enabling the spacecraft to be maneuvered to a safe disposal orbit even in the absence of operational primary and redundant processors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single Spacecraft Control Processor is used to control thrusters and solar wings, then the system complexity is reduced, but the reliability for de-orbiting in case of processor failure deteriorates
Solution Approach 1:
The control system is segmented into two independent pathways: the primary Spacecraft Control Processor pathway and the alternative Embedded Command Modules pathway. Each pathway can independently control the thrusters and solar wings, allowing the system to maintain de-orbit capability even when one pathway fails. The Embedded Command Modules are distributed across different hardware platforms, providing spatial segmentation of control functions.
Solution Approach 2:
The system changes the operational parameter from single-processor control to dual-pathway control by activating Embedded Command Modules when the primary processor fails. This parameter change allows the system to transition between different control modes, maintaining reliability without permanently increasing system complexity.
2Reliability
If a third processor is added to provide backup de-orbit control, then the reliability for processor failure is improved, but the cost and mass of the system increase
Solution Approach 1:
The Embedded Command Modules are designed to perform multiple functions: they can control thrusters for de-orbiting, manage solar wing positioning, and operate latch valves. By making these command modules multi-functional, the system achieves backup control capability without adding dedicated single-purpose hardware, thereby minimizing mass and cost increases.
Solution Approach 2:
Instead of adding a complete third processor, the system creates simplified copies of essential control functions within the Embedded Command Modules. These modules replicate only the critical de-orbit control capabilities needed for failure scenarios, rather than duplicating the entire processor architecture, thus reducing the mass penalty.
3Extent of automation
If manual ground control is implemented for de-orbiting, then the autonomy requirement is reduced, but the operational complexity increases
Solution Approach 1:
The Embedded Command Modules are pre-configured with de-orbit control algorithms and parameters before spacecraft launch. This preliminary configuration includes pre-loaded orbital mechanics data, thruster firing sequences, and solar wing positioning commands. When processor failure occurs, these pre-prepared instructions can be executed with minimal ground intervention, reducing operational complexity during critical failure scenarios.
Data Source
AI summary
A system and method for controlling de-orbit of a spacecraft is presented. Embedded command modules are commanded directly from a central command and telemetry module. Latch valves, thruster valves, and solar wing drive of the spacecraft are operated in response to inputs to the embedded command modules. The spacecraft is maneuvered to a safe disposal orbit in response to commands from the central command and telemetry unit.