Aircraft-Mounted Launch Vehicle Casing for Thermal Protection
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Solution Overview
Problem
Existing methods for transporting launch vehicles on aircraft face issues such as exposure to extreme temperatures, damage from external objects, sensitivity to weather conditions, and thermomechanical stresses, as well as the need for complex release mechanisms that can interfere with the aircraft's center of gravity or cause contamination.
Innovation Solution
A casing is designed to be externally mounted on an aircraft, providing a protected environment for launch vehicles with temperature control, impact resistance, and a secure release mechanism, while minimizing mechanical interfaces with the aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If the launch vehicle is inserted inside the aircraft's nacelle, then the launch vehicle is protected from external environment, but the release mechanism becomes complex and may interfere with the fuselage hatch
Solution Approach 1:
The invention extracts the launch vehicle from the aircraft's internal nacelle and positions it in an external mounting configuration. The launch vehicle is mounted on a pylon structure that extends from the aircraft fuselage, allowing the vehicle to be transported externally while maintaining protection through a streamlined fairing rather than internal containment. This extraction resolves the contradiction by eliminating the complex internal release mechanism while maintaining environmental protection.
Solution Approach 2:
The invention introduces a fairing or streamlined cover as an intermediary element that protects the launch vehicle during transport. This fairing acts as a mediator between the external environment and the launch vehicle, providing aerodynamic protection and environmental shielding without requiring complex internal mounting or release mechanisms. The fairing can be easily detached or released without interfering with the aircraft's fuselage hatch.
2Device complexity
If the launch vehicle is mounted externally to the aircraft, then the release is simplified, but the launch vehicle is exposed to extreme temperatures and external environmental effects
Solution Approach 1:
The fairing serves as a protective intermediary that shields the launch vehicle from extreme temperatures and external environmental effects during external transport. This streamlined cover maintains a controlled thermal environment around the launch vehicle while allowing for simplified release mechanisms, as the fairing can be independently detached without complex internal release systems.
Solution Approach 2:
The invention employs dynamic thermal protection through the fairing design, which can be configured to provide thermal insulation during transport and quickly released when needed. The fairing's dynamic capability allows it to adapt to varying thermal conditions during flight while maintaining protection, resolving the contradiction between simplified release and thermal protection.
3Device complexity
If the launch vehicle is transported externally with fixing pylons, then the release mechanism is simplified, but the inert mass of the air-transported system increases considerably
Solution Approach 1:
The invention applies local quality optimization by designing the pylon mounting structure to provide strength and protection only where specifically needed, rather than uniformly across the entire launch vehicle. The fairing provides localized aerodynamic protection and thermal shielding at the critical exposed surfaces of the launch vehicle, reducing the overall mass required compared to full-enclosure internal mounting while maintaining necessary protection and simplifying release.
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 casing effectively protects launch vehicles from external conditions and reduces thermomechanical stresses, allowing secure transport and landing without detaching the vehicle, while maintaining aircraft stability and safety.
Implementation Method 1
The casing is designed to be externally mounted on an aircraft, providing a protected environment for launch vehicles with temperature control, impact resistance
Implementation Method 2
it is possible that an impact may occur with external objects, debris on the runway, birds, which could damage the launch vehicle
Data Source
Figure 1~5
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Figure 11~12
AI summary
The present invention relates to a casing intended to be externally applied, connected or fixed to the fuselage (2a) or to a wing (2b) of an aircraft (2) or to a central or wing station/hardpoint (6) of an aircraft (2), the casing entirely or partly delimiting a housing zone (HZ) of a super-orbital, orbital or sub-orbital launch vehicle (3).