Auxiliary Flight Display With Virtual Horizon for Spatial Disorientation
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Solution Overview
Problem
Pilots may suffer from spatial disorientation during emergencies such as turbulence or harsh weather, leading to a momentary loss of control of the aircraft, especially for inexperienced pilots, due to the inability to observe correct external information through the windshield.
Innovation Solution
An aircraft auxiliary display system that includes a central processing unit, sensing module, and electro-optical visual unit, which displays virtual aerial and terrestrial environment images based on pitch, roll, and yaw angle thresholds, providing pilots with essential flight information and reference points to prevent disorientation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If pilots rely on external visual observation through the windshield during emergencies, then they can obtain natural reference points, but they may suffer from spatial disorientation when external information is unavailable
Solution Approach 1:
The patent introduces a head-mounted display device as an intermediary between the pilot and the external environment. This device provides virtual reference points (horizon lines, terrain features, obstacle indicators) that mediate the pilot's spatial perception when direct visual observation is unreliable or unavailable, thereby preventing spatial disorientation without requiring actual external visual references
Solution Approach 2:
The system creates virtual copies of external reference elements (horizon, terrain, obstacles) and presents them through the head-mounted display. These copied visual references allow pilots to maintain spatial orientation by viewing synthesized imagery that represents the external environment, even when the actual external view is obscured or misleading
2Loss of information
If pilots observe a large number of instruments to determine flight information, then they can acquire flight data, but it increases the complexity of information processing and response time
Solution Approach 1:
The patent merges multiple flight information sources (instruments, sensors, navigation data) into a single integrated virtual display presented through the head-mounted device. Instead of requiring pilots to scan multiple separate instruments, all critical flight information is combined and presented in one unified visual interface, reducing cognitive load and information processing complexity
Solution Approach 2:
The system transitions flight information from traditional two-dimensional instrument panels to a three-dimensional virtual space that overlays directly in the pilot's field of view. This dimensional change allows pilots to perceive flight parameters spatially rather than scanning across flat surfaces, reducing the mental effort required to process and integrate multiple data sources
3Loss of time
If pilots need to quickly acquire flight information during emergencies, then response time is reduced, but the system must provide sufficient reference points without external interference
Solution Approach 1:
The system pre-configures virtual reference points and flight information displays that are immediately available when activated. During normal operation, the system can pre-load and prepare spatial references, so that when an emergency occurs, pilots receive pre-prepared visual aids without delay, enabling immediate response while maintaining reliable spatial orientation
Solution Approach 2:
The head-mounted display system continuously provides feedback to the pilot by updating virtual reference points and flight information in real-time based on aircraft state changes. This continuous feedback loop ensures that pilots always have current, accurate spatial references regardless of how quickly the situation evolves, maintaining reliability while enabling rapid response
Data Source
AI summary
An aircraft auxiliary display system for avoiding spatial disorientation includes a central processing unit (CPU), a sensing module, an activation display unit and an electro-optical visual unit. The CPU includes a storage unit and is electrically connected to the activation display unit. The sensing module is electrically connected to the CPU and includes a flight data sensing unit. The activation display unit is electrically connected to the electro-optical visual unit.