Aircraft SSPC Switchable Bypass for Inductive Voltage Protection
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Solution Overview
Problem
Aircraft solid state power controllers (SSPCs) face damage from high inductive voltages induced when switching off inductive loads, which can damage the SSPC and other connected components.
Innovation Solution
Incorporating a switchable bypass with a second bypass diode and a bypass switch, controlled by a bypass controller, to divert and dissipate inductive voltages before switching off the solid state power switching device, and deactivating the bypass after a predetermined time to prevent overshooting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the solid state power switching device is used to switch off inductive loads, then the electric power supply can be controlled and interrupted, but high inductive voltages are induced that may damage the switching device and other connected components
Solution Approach 1:
A bypass diode is introduced as an intermediary component connected in parallel with the solid state power switching device. When the switching device turns off inductive loads, the bypass diode provides a safe path for the induced current to flow, protecting the switching device from voltage damage while allowing controlled power interruption
Solution Approach 2:
The bypass diode is pre-configured and connected before switching operations occur. When inductive voltage is generated during load switching, the bypass diode is already in position to immediately divert the harmful voltage, preventing damage before it can affect the switching device
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
The solution enables SSPCs to reliably switch large electric powers and voltages without damage, ensuring durability and preventing damage to connected components by effectively managing induced voltages.
Implementation Method 1
The first bypass diode has a first node, which is electrically connected to the input node of the solid state power switching device, and a second node, which is electrically connected to the control node of the solid state power switching device
Implementation Method 2
The second bypass diode and the bypass switch are electrically connected with each other in a serial configuration so that an electric bypass current flowing through the second bypass diode is controllable by switching the bypass switch between a low resistance state ('on-state') and a high resistance state ('off-state')
Data Source
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AI summary
An aircraft solid state power controller (5) for controlling electric power in an aircraft (24) comprises: a solid state power switching device (10) for switching the electric power, the solid state power switching device (10) comprising an input node (10a), an output node (10b) and a control node (10c); a first bypass diode (12) electrically connected between the input node (10a) of the solid state power switching device (10) and the control node (10c) of the solid state power switching device (10); and a switchable bypass (8) electrically connected between the input node (10a) of the solid state power switching device (10), and he output node (10b) of the solid state power switching device (10). The switchable bypass (8) comprises a second bypass diode (16) and a bypass switch (18). An electric bypass current (Ibypass) flowing through the second bypass diode (16) is switchable by switching the bypass switch (18) on and off. The aircraft solid state power controller (5) further comprises a bypass controller (20), which is configured for switching the bypass switch (18) on and off.