Carrier Platform Reversible Transfer Mechanism for Stealth UAV Launch
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Solution Overview
Problem
Existing carrier platforms face challenges in accommodating missiles with large control surface elements due to stealth requirements, leading to issues with installation space and the inability to return missiles to the launcher after launch preparation is aborted.
Innovation Solution
A carrier platform with a reversible transfer mechanism for missiles and control surface elements, allowing the control surface elements to be folded in for compact storage and unfolded for launch, while enabling the missile to be returned to the launcher if needed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If missiles are accommodated in a shaft-like receiving device to maintain stealth properties, then the stealth characteristics are improved, but the mounting system requires sufficiently large dimensions that may not be available due to installation space constraints
Solution Approach 1:
The control surface elements are divided into multiple segments that can be folded independently. The first control surface element has a first segment and a second segment, while the second control surface element has a third segment and a fourth segment. This segmentation allows the control surfaces to be folded into a compact configuration for stealth mode while maintaining full functionality when deployed.
Solution Approach 2:
The control surface elements are designed with dynamic folding capability, transitioning between extended and folded states. The reversible folding mechanism allows the control surfaces to adapt their configuration based on operational requirements, being extended for flight control and folded for compact storage in the receiving device.
2Volume of stationary object
If missiles with fold-out control surface elements are used to reduce mounting system dimensions, then the installation space requirement is reduced, but the control surface elements cannot be folded back in, preventing the missile from being returned to the launcher
Solution Approach 1:
The control surface elements incorporate a reversible folding mechanism that allows bidirectional movement between extended and folded states. The first and second control surface elements can be folded out from the missile body for flight operation and then folded back in, enabling the missile to be returned to the launcher for reuse or storage.
Solution Approach 2:
The design enables recovery of the missile system by allowing control surface elements to be folded back into the missile body after use. This reversibility prevents permanent deployment of control surfaces, allowing the missile to be recovered and returned to the launcher, thereby extending the operational lifecycle of the missile system.
3Volume of stationary object
If the receiving device is designed to accommodate missiles with control surface elements folded in, then the installation space is optimized, but the missile cannot be transferred back to the launcher if a launch sequence is aborted
Solution Approach 1:
The control surface elements are equipped with dynamic folding mechanisms that enable reversible transitions between extended and folded configurations. When a launch sequence is aborted, the control surfaces can be folded back into the missile body, allowing the missile to be transferred back to the launcher and restoring the system to its initial state.
Solution Approach 2:
The control surface elements change their spatial configuration parameter by folding in and out. This parameter change enables the missile to adapt its dimensions for different operational states, allowing compact storage in the receiving device while maintaining the capability for reversible transfer to and from the launcher.
Data Source
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AI summary
A launching platform (1) for launching or dropping an unmanned aerial vehicle (2) at a target, comprising: a shaft-like receiving device (4) for receiving at least one aerial vehicle (2) that can be launched or dropped at a target, wherein at least one control surface element (2.1) is arranged or formed on the aerial vehicle (2), which is reversibly transferable into an operating position and into a non-operating position; a transfer device (5) associated with the receiving device (4), which is configured to transfer the or an aerial vehicle (2) from a first position arranged inside the shaft-like receiving device (4) to a second position arranged outside the shaft-like receiving device (4), or vice versa, wherein the or a further transfer device (6) is provided, the at least one control surface element (2.1) when transferring the missile or missile (2) from the first position to the second position from the non-operational position to the operational position, and/or the or a further transfer device (6) is provided to transfer at least one control surface element (2.1) from the operational position to the non-operational position when transferring the missile or missile (2) from the second position to the first position.