Vehicle system
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Solution Overview
Problem
Existing airborne thermal and power systems for aircraft payloads face limitations in efficiency and versatility, particularly in providing reliable power and thermal management across various applications.
Innovation Solution
A system incorporating a gas turbine engine as a work providing device, capable of powering and cooling payloads through a refrigerant cycle thermal conditioning system, utilizing a phase change material for thermal energy storage and a power generation device to supply electrical power, with the option of multiple engines and pod configurations for enhanced performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a gas turbine engine is used as a work providing device to generate electrical power and provide thermal conditioning, then power and thermal management efficiency are improved, but device complexity increases
Solution Approach 1:
The patent combines multiple functions (power generation, thermal conditioning, electrical power supply) into a single integrated gas turbine engine system. The engine simultaneously drives a generator for electrical power and provides compressed air for thermal conditioning, eliminating the need for separate systems and improving overall efficiency while managing complexity through functional integration.
Solution Approach 2:
The gas turbine engine serves multiple purposes: it generates mechanical power to drive the generator, provides compressed air for the thermal conditioning system, and can operate across various altitudes and airspeeds. This multi-functionality improves productivity by maximizing the utilization of a single complex device rather than requiring multiple simpler systems.
2Temperature
If a refrigerant cycle thermal conditioning system with phase change material is implemented, then thermal management capability is improved, but device complexity increases
Solution Approach 1:
The patent utilizes phase change material within the thermal conditioning system to absorb and release thermal energy during phase transitions (e.g., liquid to solid). This enables effective thermal management and temperature control for the payload, improving thermal conditioning capability while the phase change process itself simplifies the overall thermal control mechanism by providing passive thermal regulation.
3Adaptability or versatility
If the system is designed to operate across various altitudes and airspeeds, then adaptability is improved, but reliability may worsen due to varying operational conditions
Solution Approach 1:
The gas turbine engine is designed to dynamically adapt to varying operational conditions including different altitudes and airspeeds. The engine's performance characteristics change with ambient conditions, allowing the system to maintain reliability across a wide range of environments. The dynamic nature of the gas turbine enables it to optimize combustion and power output based on real-time atmospheric conditions.
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
This solution enables efficient power generation and thermal management for aircraft payloads, allowing for flexible operation across different altitudes and airspeeds, and supports the use of directed energy systems by maintaining system temperatures and providing intermittent power.
Implementation Method 1
a gas turbine engine as a work providing device
Implementation Method 2
power generation device to supply electrical power
Implementation Method 3
refrigerant cycle thermal conditioning system, utilizing a phase change material for thermal energy storage
Implementation Method 4
phase change material for thermal energy storage
Implementation Method 5
phase change material for thermal energy storage
Implementation Method 6
thermal conditioning system powered by the work providing device
Data Source
Figure 1~2
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AI summary
An apparatus comprising an aircraft having one or more propulsion engines and an external pod and including a turbine apart from the one or more propulsion engines, the turbine in power communication with an electrical generator and a heat exchange system that includes a phase change heat exchanger, the aircraft further including an implement in thermal communication with the heat exchange system.