Aircraft Payload Pod With Integrated Power and Thermal Conditioning
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Solution Overview
Problem
Existing airborne thermal and power systems for payloads aboard vehicles face inefficiencies and limitations in providing reliable power and thermal management, particularly in varying altitudes and airspeeds, and across different applications.
Innovation Solution
A system comprising a gas turbine engine as a work providing device, coupled with a thermal conditioning system using a refrigerant cycle and phase change materials, which powers and cools payloads aboard aircraft, including directed energy weapons, by utilizing bleed air and fuel from the aircraft engines, and featuring a pod configuration for efficient heat exchange and power distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing airborne thermal and power systems are used, then power and thermal management can be provided to payloads, but the systems face inefficiencies and limitations in varying altitudes and airspeeds
Solution Approach 1:
The system dynamically adjusts the operation of the gas turbine engine and thermal conditioning equipment based on real-time altitude and airspeed conditions. The engine operates as a dynamic power source that can modulate its output to match the varying thermal and power demands of the payload across different flight conditions, resolving the contradiction between reliability and adaptability.
Solution Approach 2:
The system changes operational parameters including engine speed, refrigerant flow rate, and heat exchange efficiency based on altitude and airspeed. By adjusting these parameters dynamically, the system maintains reliable power and thermal management performance while adapting to varying flight conditions.
2Power
If a gas turbine engine is used for power generation, then efficient power can be provided, but system complexity increases
Solution Approach 1:
The gas turbine engine serves multiple functions: it generates electrical power for the payload, provides bleed air for the thermal conditioning system, and can be integrated with the aircraft's existing propulsion system. This multi-functionality reduces overall system complexity despite the engine's inherent complexity, as it consolidates multiple subsystems into a single integrated power and thermal management platform.
Solution Approach 2:
The system merges the power generation and thermal management functions into a single integrated architecture where the gas turbine engine drives both the electrical generator and the thermal conditioning equipment. This consolidation reduces the number of separate components and simplifies system integration while maintaining high power generation efficiency.
3Temperature
If thermal conditioning system with refrigerant cycle is used, then effective cooling can be achieved, but energy consumption increases
Solution Approach 1:
The thermal conditioning system uses bleed air from the gas turbine engine as its primary energy source, making the system self-sufficient. The refrigerant cycle is driven by the engine's own exhaust or intermediate stage air, eliminating the need for separate power consumption for cooling. This self-service approach achieves effective temperature control while minimizing additional energy consumption beyond what the engine already produces.
Solution Approach 2:
The refrigerant acts as an intermediary medium that transfers heat from the payload to the bleed air from the gas turbine engine. This heat exchange process enables effective cooling by using the temperature differential between the hot bleed air and the refrigerant, achieving thermal management without direct energy consumption from the payload's power supply.
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, maintaining system temperatures and providing reliable operation across different conditions, including during the use of directed energy systems, by leveraging the gas turbine engine and thermal energy storage.
Implementation Method 1
a gas turbine engine as a work providing device, coupled with a thermal conditioning system
Implementation Method 2
utilizing bleed air and fuel from the aircraft engines
Implementation Method 3
thermal conditioning system using a refrigerant cycle and phase change materials
Implementation Method 4
featuring a pod configuration for efficient heat exchange
Implementation Method 5
refrigerant cycle
Implementation Method 6
refrigerant cycle
Implementation Method 7
phase change materials, which powers and cools payloads
Implementation Method 8
leveraging the gas turbine engine and thermal energy storage
Data Source
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AI summary
A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.