Auxiliary Platform for High Altitude Aircraft Ascent
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Solution Overview
Problem
Conventional high-flying aircraft designed for long missions in the stratosphere carry unnecessary mass and have oversized engines due to the need for ascent capabilities, leading to inefficiencies and increased costs, as they must balance short ascent durations with prolonged mission durations.
Innovation Solution
An auxiliary device is detachably coupled to the aircraft for ascent, providing independent propulsion and releasing at a predetermined altitude, allowing the aircraft engine to be optimized for stratospheric operation, reducing weight and cost, and featuring a non-electrical or electrical drive with stabilization and reusable return capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the aircraft uses its own propulsion for ascent into the stratosphere, then the aircraft can reach the mission altitude, but the aircraft carries unnecessary mass and has an oversized engine for the actual mission
Solution Approach 1:
The ascent function is segmented from the mission function by introducing a separate auxiliary device with its own drive. The auxiliary device provides propulsion during ascent, while the aircraft engine is optimized solely for stratospheric operation, eliminating the need for an oversized engine that would be required if the aircraft performed both ascent and mission functions.
Solution Approach 2:
The ascent capability is extracted from the aircraft system and placed into a separate auxiliary device. This allows the aircraft to be designed with minimal weight for its primary mission, while the auxiliary device carries the propulsion systems needed for ascent.
2Productivity
If the aircraft engine is optimized for stratospheric operation, then the aircraft achieves better efficiency during mission, but the aircraft cannot perform ascent without additional propulsion
Solution Approach 1:
The propulsion system is segmented into two independent components: the aircraft engine optimized for stratospheric operation and the auxiliary device with its own drive for ascent. This segmentation allows each component to be optimized for its specific function without compromise.
3Reliability
If the auxiliary device remains attached to the aircraft during the long mission, then the aircraft has redundant propulsion, but the aircraft carries more mass than necessary
Solution Approach 1:
The auxiliary device is detachably coupled to the aircraft, allowing it to be present during ascent when needed and absent during the mission when unnecessary. This local quality of detachability enables the system to have redundant propulsion during the critical ascent phase while minimizing mass during the extended mission phase.
4Power
If the auxiliary device provides high power for ascent, then the aircraft can reach stratosphere, but the auxiliary device consumes significant energy during operation
Solution Approach 1:
The auxiliary device performs the energy-intensive ascent operation before the mission begins, reaching the stratosphere where the aircraft can then operate efficiently for extended periods. By completing the high-energy task beforehand, the system avoids continuous high energy consumption during the mission phase.
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 approach enables optimal aircraft design for stratospheric operations, reducing weight and cost by using the auxiliary device's higher power for ascent, allowing the aircraft engine to operate efficiently during the mission, and enabling multiple uses of the auxiliary device.
Implementation Method 1
the drive can be an internal combustion engine, in which case fuel required for operation is stored or contained in a reservoir of the auxiliary device
Implementation Method 2
the drive can also include an electric motor, which is fed from an energy store of the auxiliary device
Implementation Method 3
after detaching the auxiliary device from the aircraft, it can be separated from the high-flying aircraft based solely on gravity
Implementation Method 4
such a stabilizing means can include one or more controllable wings and/or a controllable auxiliary drive and/or a direction-changing arrangement
Data Source
Figure 1~2
AI summary
The invention relates to an auxiliary device (20) for a high-flying aircraft (10). The auxiliary device (20) comprises an aircraft-independent drive (21) for the ascent of the aircraft (10) into the stratosphere, said aircraft being detachably coupled with the auxiliary device (20), and can be detached from the aircraft (10) at the latest when a predetermined mission height is reached.