Spacecraft PCDU Microcontroller Battery Charging Flexibility

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Solution Overview

Problem

Conventional power control and distribution units (PCDUs) in spacecraft are complex and require many electronic components, limiting flexibility in battery charging procedures, which can be costly and difficult to change without hardware modifications.

Innovation Solution

A PCDU with a programmable and reprogrammable microcontroller that controls battery charging from solar arrays, allowing adaptive optimization of charging procedures based on mission-specific conditions and receiving parameters from a main computer.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If conventional PCDU with many electronic components is used, then power control function is achieved, but device complexity increases and flexibility is limited

Engineering Contradiction:

Improveflexibility in battery charging proceduresVSAvoidnumber of electronic components

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The microcontroller serves multiple functions: it controls battery charging procedures, monitors system parameters, and can be reprogrammed to adapt to different mission requirements. This single component replaces what would traditionally require multiple dedicated electronic components, thereby reducing overall device complexity while maintaining or enhancing flexibility in battery charging procedures

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The microcontroller is programmable and reprogrammable, allowing the PCDU to dynamically adapt its charging algorithms and parameters based on different mission profiles, battery types, and operational conditions. This dynamic reconfigurability provides high flexibility without requiring hardware changes or additional components

Inventive Principle:

Principle #15Dynamics

2Adaptability or versatility

If hardware modifications are made to change battery charging procedures, then charging flexibility is improved, but cost and difficulty increase

Engineering Contradiction:

Improvebattery charging procedure adaptabilityVSAvoidcost and difficulty of hardware changes

Core Design Contradiction:

Adaptability or versatilityVSEase of manufacture

Solution Approach 1:

The patent replaces the traditional hardware-based control approach with a software-based microcontroller system. Instead of modifying physical circuitry to change charging procedures, the system uses programmable logic that can be updated via software, eliminating the need for costly and difficult hardware modifications while maintaining full adaptability of charging procedures

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The microcontroller allows charging parameters such as current limits, voltage thresholds, and charging rates to be modified through software configuration rather than hardware changes. This enables easy adaptation to different battery types and mission requirements without incurring manufacturing costs or increasing system complexity

Inventive Principle:

Principle #35Parameter changes

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

Reduces complexity and enhances flexibility in battery charging, enabling efficient power management and adaptation to varying conditions without the need for costly hardware changes.

Implementation Method 1

The solar arrays are used to provide power to the spacecraft and may also be used to charge the batteries

Methodology Applied

Scientific EffectPhotovoltaic effect: Photovoltaic Effect

Data Source

PatentUS20230369876A1Microcontroller based solar array energy transfer battery charge control

Publication Date: 2023.11.16 LANTERIS SPACE LLC

AI summary

Technology is disclosed herein for a power control and distribution unit (PCDU) of a spacecraft that has a microcontroller to control battery charging from solar arrays. Using a microcontroller within the PCDU reduces the complexity of the PCDU. The microcontroller may be programmable and reprogrammable, which allows the charging of the battery to be adapted to various conditions. For example, the microcontroller can be programmed in accordance with the mission to optimize battery charging for that mission.