Mechanical Aircraft HUD With Damped Weighted Disk Stabilization
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Solution Overview
Problem
Existing aircraft instrumentation systems do not effectively measure and display critical flight parameters such as roll, pitch, and slip angles in a manner that is visible and stable under varying flight conditions, particularly in dark environments.
Innovation Solution
A mechanical aircraft heads-up display system that includes a weighted disk structure with non-uniform mass distribution, fluid management for damping transient forces, and an accessory structure for displaying additional flight parameters, all integrated with a cockpit-mounted instrument structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a mechanical heads-up display system is used to measure and display flight parameters, then the measurement stability and visibility under varying flight conditions is improved, but the device complexity increases due to the weighted disk structure and fluid management system
Solution Approach 1:
The patent introduces a weighted disk structure as an intermediary mechanical element that responds to flight parameter changes. This disk, with its non-uniform mass distribution, serves as a mediator between the aircraft's motion and the display mechanism, translating complex flight dynamics into visible indicator positions without requiring direct electronic sensing of all parameters
Solution Approach 2:
The patent employs a fluid management system with damping fluid to stabilize the weighted disk structure during transient flight conditions. The fluid provides hydraulic damping that reduces oscillations and maintains measurement stability, allowing the mechanical display to remain reliable under varying flight conditions without requiring complex electronic stabilization systems
2Measurement precision
If a mechanical heads-up display system with weighted disk structure is used, then the visibility and stability of flight parameter measurement is improved, but the manufacturing precision requirements increase
Solution Approach 1:
The patent deliberately employs asymmetric mass distribution in the weighted disk structure. By positioning the center of gravity offset from the rotational axis, the disk naturally responds to flight parameter changes with predictable angular displacements. This asymmetric design converts complex multi-axis flight dynamics into simplified rotational movements that can be read by the display mechanism, maintaining measurement precision while avoiding the need for perfectly symmetric, high-precision components
Solution Approach 2:
The patent utilizes changes in the physical state and distribution of damping fluid within the weighted disk assembly to maintain measurement precision across varying flight conditions. The fluid's viscosity and distribution characteristics change in response to acceleration and orientation, providing automatic compensation that maintains measurement accuracy without requiring the mechanical components themselves to be manufactured with extremely tight tolerances
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
Provides stable and visible measurement of roll, pitch, and slip angles, along with other flight parameters, even under transient conditions and in low light, enhancing pilot awareness and control.
Implementation Method 1
The weighted disk structure (132) has a non-uniform mass distribution that offsets a center of mass of the weighted disk structure (132) from a center of rotation of the weighted disk structure (132)
Implementation Method 2
The weighted disk structure (132) has a non-uniform mass distribution that offsets a center of mass of the weighted disk structure (132) from a center of rotation of the weighted disk structure (132)
Implementation Method 3
fluid management for damping transient forces
Data Source
AI summary
The aircraft heads up display is an instrument for use with an aircraft. The aircraft heads up display is a mechanical structure. The aircraft heads up display measures: a) the roll angle of the aircraft; b) the pitch angle of the aircraft; and, c) the slip angle of the aircraft. The aircraft heads up display incorporates an instrument structure and an accessory structure. The instrument structure measures the roll angle, the pitch angle, and the slip angle of the aircraft. The accessory structure is an optional structure that forms an electric connection with the aircraft. The accessory structure displays other measured flight parameters of the aircraft.