Auxiliary Air-Vehicle Propulsion with Dual-Drive Compressor Jets
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Solution Overview
Problem
Air vehicles face safety concerns due to the weight and drag increases associated with auxiliary propulsion systems, which also reduce passenger space and range, while existing systems fail to efficiently provide lift and thrust forces during engine failures or abnormal conditions.
Innovation Solution
An auxiliary propulsion apparatus with an engine, generator, compressor, battery, and nozzle devices, including clutches and a controller, that selectively engages power transmission to provide lift and thrust forces using pressurized gas, minimizing weight and drag, and optimizing space for passengers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If an auxiliary propulsion apparatus is provided to improve safety during engine failure, then safety and reliability are improved, but weight of the air vehicle increases
Solution Approach 1:
The auxiliary propulsion system merges the engine-driven compressor and generator-driven compressor into a single integrated system. The engine is connected to a compressor via a first clutch, and the generator is connected to another compressor via a second clutch, allowing either power source to drive compression functions. This merging reduces redundant components and overall system weight while maintaining reliability during engine failure.
Solution Approach 2:
The compressor system is designed with multi-functionality to serve both the auxiliary propulsion system and the air conditioning system. The same compressor can be driven by either the engine or the generator, and it provides pressurized gas for both thrust generation during engine failure and cabin cooling during normal operation, reducing the need for separate dedicated components.
2Power
If an auxiliary propulsion apparatus is added to provide auxiliary thrust, then flight performance is improved, but drag of the fuselage increases
Solution Approach 1:
The exhaust gas jetting function is extracted from the main engine system and separated into a dedicated auxiliary propulsion system. The exhaust gas from the engine or generator-driven compressor is directed through nozzles positioned at the rear of the fuselage to generate thrust, separating the auxiliary propulsion function from the main engine to minimize interference with aerodynamic flow and reduce fuselage drag.
3Stability of the object's composition
If auxiliary propulsion components are mounted to provide lift and thrust, then flight stability is improved, but space for passengers is reduced
Solution Approach 1:
The auxiliary propulsion components are nested within existing structural spaces of the air vehicle. The compressor, generator, and fuel tank are arranged to utilize available space in the fuselage, with the generator mounted on the engine and the fuel tank positioned in the lower part of the fuselage. The exhaust gas nozzles are integrated into the rear fuselage structure, minimizing intrusion into passenger cabin space while maintaining flight stability.
4Duration of action of moving object
If auxiliary propulsion system is implemented to extend range, then duration of flight is improved, but weight and complexity increase
Solution Approach 1:
The system employs dynamic clutch mechanisms that can selectively engage or disengage power transmission paths between the engine, generator, and compressors. The first clutch connects the engine to the compressor, while the second clutch connects the generator to the compressor. This dynamic configuration allows the system to adapt to different operational modes (engine-driven or generator-driven) without requiring permanent complex mechanical linkages, thereby extending range while managing complexity.
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
The system efficiently provides lift and thrust forces to improve air vehicle stability and flight performance, ensuring increased range and reduced passenger space reduction, while enabling safe operation during engine failures or abnormal conditions.
Implementation Method 1
a compressor (5) configured to be driven by the engine (1) or the generator (3)
Implementation Method 2
at least one nozzle device configured to jet pressurized gas supplied from the compressor, to an outside of the fuselage
Implementation Method 3
a generator (3) configured to be driven using power from the engine (1)
Implementation Method 4
a battery (7) configured to store electricity generated by the generator (3)
Data Source
AI summary
An auxiliary propulsion apparatus of an air vehicle may include an engine mounted in a fuselage of the air vehicle, a generator configured to be driven using power from the engine, a compressor configured to be driven by the engine or the generator, a battery configured to store electricity generated by the generator, an electricity distributor connected to the generator, the battery and the main propulsion apparatus and configured to distribute electricity generated by the generator to the battery and to a main propulsion apparatus, and at least one nozzle device configured to jet high-pressure gas, supplied from the compressor, to an outside of the fuselage.