Aircraft External Store Matching for Sensor Integration
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Solution Overview
Problem
Aircraft external stores, such as fuel tanks and sensors, impose drag penalties and alter aerodynamic properties, increasing moment of inertia and changing mass distribution, making it difficult to achieve optimal mounting and certification, especially in space-constrained nose areas.
Innovation Solution
A method for configuring a sensor system with a store and payload to match the aerodynamic properties, moments of inertia, and mass distribution of certified external stores, using a Ram Air Turbine for power and a wireless transceiver for communication, allowing the system to be mounted externally without separate certification by matching the characteristics of existing certified stores.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If sensor systems are mounted externally on aircraft, then sensing capabilities are improved, but aerodynamic properties are altered and drag increases
Solution Approach 1:
The sensor system is designed to replicate the aerodynamic properties, moments of inertia, and mass distribution of a certified external store. By copying these physical characteristics, the sensor system can be mounted externally without requiring separate certification, as it behaves aerodynamically like an already-approved store configuration
Solution Approach 2:
The design process involves measuring and matching specific physical parameters (aerodynamic properties, moments of inertia, mass distribution) of the sensor system to those of a certified external store. This parameter matching allows the sensor system to integrate seamlessly with the aircraft's existing certification
2Measurement precision
If multiple sensors are mounted on aircraft forebody, then measurement capabilities are improved, but space availability deteriorates
Solution Approach 1:
Instead of mounting sensors in the constrained forebody area, the invention moves the sensor system to external mounting locations on the aircraft. This dimensional transition from internal to external mounting provides abundant space for multiple sensors while maintaining measurement capabilities
3Quantity of substance
If external stores are carried by aircraft, then payload capacity is improved, but moment of inertia increases reducing roll rates
Solution Approach 1:
The sensor system is configured to match the moments of inertia of a certified external store, ensuring that the rotational dynamics characteristics are preserved. This allows the aircraft to carry the sensor system without experiencing degraded roll rates, as the moment of inertia parameters are replicated from the certified store configuration
4Reliability
If sensor systems are certified for aircraft mounting, then reliability is improved, but device complexity and certification costs increase
Solution Approach 1:
The sensor system is designed with universal characteristics by matching the aerodynamic properties and physical parameters of a certified external store. This multi-functionality approach allows the sensor system to serve as both a sensing platform and a certified external store, eliminating the need for separate certification processes
Solution Approach 2:
By copying the certification-relevant parameters (aerodynamic properties, moments of inertia, mass distribution) from an already-certified external store, the sensor system inherits the certification status of the reference store, reducing integration complexity and costs
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
Enables the mounting of sensor systems on aircraft without additional certification, reducing integration costs and complexity, minimizing power loading, and allowing for self-powered and wireless communication, while maintaining aerodynamic compatibility with existing stores.
Implementation Method 1
The second payload may further comprise a power source (e.g. a Ram Air Turbine) for at least partially powering the sensor and/or a projecting means.
Data Source
Figure 1~2
AI summary
A method of providing apparatus comprising: providing a first store and a first payload on or in the first store, the first store being for mounting to the outside of an aircraft (4); acquiring aerodynamic properties, moments of inertia, and the mass distribution of the first store and first payload; providing a second store (8) and a second payload, the second payload being on or in the second store (8), the second store (8) being for mounting to the outside of the aircraft (4), the second payload being different to the first, the second payload comprising a sensor (12) and/or a projecting means; and configuring the second store (8) and the second payload such that the aerodynamic properties, moments of inertia, and mass distribution of the second store (8) and the second payload are substantially the same as those of the first store and first payload.