Aircraft External DC Power Voltage Check for Accurate Indication
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Solution Overview
Problem
Conventional aircraft external power indicators fail to accurately indicate available and in-use power due to insufficient or excessive voltage, leading to user confusion and potential system malfunctions.
Innovation Solution
A voltage check system with a relay sensor and check switch ensures that power is within a suitable range before activating indicators and allowing power distribution, preventing under-voltage and over-voltage conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional indicators are used to show external power availability, then the system is simple and easy to operate, but the indicators may activate at insufficient voltage causing false indications or burn out at excessive voltage
Solution Approach 1:
The voltage check system performs preliminary voltage verification before activating indicators or allowing power distribution. The check switch is configured to close only when voltage falls within the acceptable range (18-32 volts DC), preventing false indications and indicator burnout by ensuring voltage compliance before system activation.
Solution Approach 2:
The voltage check system acts as an intermediary between the external power source and the aircraft electrical system. It includes a check switch that mediates power flow, closing only when voltage is within acceptable ranges, thereby protecting indicators and preventing false indications without requiring complex monitoring circuitry.
2Reliability
If the voltage check system is added to monitor power voltage, then indicator accuracy and system reliability are improved, but the device complexity increases
Solution Approach 1:
The voltage check system performs preliminary voltage verification before allowing power distribution or indicator activation. By checking voltage conditions in advance and only closing the check switch when voltage is within 18-32 volts DC, the system ensures reliable operation without requiring complex continuous monitoring circuitry throughout the electrical system.
Solution Approach 2:
The voltage checking function is extracted as a separate, dedicated check switch mechanism rather than being integrated into the main power distribution circuitry. This standalone voltage check system handles monitoring and protection functions independently, simplifying the overall system architecture while maintaining high reliability.
3Adaptability or versatility
If external power is allowed to activate at lower voltage, then the system is more adaptable to different power sources, but the power distribution circuit may not function properly causing user confusion
Solution Approach 1:
The check switch performs preliminary voltage verification before allowing power distribution circuit activation. It closes only when voltage is within the acceptable range (18-32 volts DC), ensuring that sufficient power is available to operate the aircraft's electrical systems properly, thereby preventing user confusion from incomplete system activation.
Solution Approach 2:
The system defines specific voltage threshold parameters (18-32 volts DC) that must be met for power distribution activation. By establishing these parameter boundaries, the system maintains adaptability to different external power sources while ensuring minimum voltage requirements are satisfied for proper system operation and accurate status indication.
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
Ensures accurate indication of available and in-use power, preventing system confusion and malfunctions by ensuring voltage compliance, thus enhancing reliability and user understanding.
Implementation Method 1
A voltage relay sensor can be configured to activate a check switch when a proper voltage is supplied to the sensor
Implementation Method 2
The voltage relay sensor can include any suitable circuitry, logic, software, or the like configured to check an electrical source voltage
Implementation Method 3
If the external power is outside the suitable voltage range, then the voltage relay sensor does not allow power to an electrical power distribution circuit (EPDC) or to either of two indicators
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
An external power supply system (100) for an aircraft includes a power receptacle (101) configured to connect to an external power source (105) to provide external power, a power switch (107) operative to switch between a battery power source (109) and the external power source (105), and a voltage check system (111) configured to prevent at least one of under-voltage or over-voltage of an aircraft electrical system (113). The voltage check system (111) includes a voltage relay sensor (111a) configured to determine if the external power is within a suitable voltage range and a check switch (111b) operatively connected to the voltage relay sensor (111a), wherein if the external power is within a suitable voltage range, the voltage relay sensor (111a) activates the check switch (111b) to allow external power to the aircraft electrical system (113), and wherein if the external power is outside the suitable voltage range, then the voltage relay sensor (111a) does not allow power to the aircraft electrical system (113).