Telescoping Missile Air Inlet for Structural Integrity
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Solution Overview
Problem
Cannon-fired missiles face structural weaknesses due to air intake openings that are vulnerable to high G-forces and turbulence, and existing designs struggle to balance space, weight, and engine efficiency for extended range.
Innovation Solution
A missile with a selectively opening air inlet system featuring a telescoping mechanism with slidable arms that transitions from a closed to an open position post-launch, allowing air flow into a gas turbine engine while maintaining structural integrity and minimizing weight and space constraints.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If air intake openings are provided in the missile body to allow air flow to the turbine engine, then the engine can operate efficiently, but the structural strength of the missile is compromised due to points of weakness in the missile skin
Solution Approach 1:
The air inlet is designed as a telescoping mechanism that can transition between retracted and extended positions. During launch, the inlet is retracted to maintain structural integrity and withstand high G-forces. After launch, the inlet extends to provide adequate air flow to the turbine engine, thus dynamically adapting the structure to different operational phases.
Solution Approach 2:
The air inlet system is segmented into movable telescoping components rather than a fixed opening. This segmentation allows the missile body to maintain its structural continuity during critical phases while enabling air intake functionality when needed, separating the structural and functional requirements in different operational states.
2Strength
If the air inlet is kept closed during launch to maintain structural integrity, then the missile can withstand high G-forces, but the engine cannot receive air for operation
Solution Approach 1:
The telescoping air inlet is pre-configured in a retracted position before launch to ensure structural integrity during high-G phases. After launch, the inlet is extended to enable engine operation. This preliminary positioning strategy ensures that structural requirements are met first, followed by operational requirements.
Solution Approach 2:
The air inlet transitions from a static closed design to a dynamic telescoping mechanism that can change its configuration based on operational needs, allowing the system to satisfy both structural strength requirements during launch and air intake requirements during flight.
3Device complexity
If a fixed air inlet design is used, then the structure is simpler, but the missile cannot adapt to different flight phases requiring both structural integrity and air flow
Solution Approach 1:
The air inlet system employs telescoping mechanisms that allow it to change its configuration between retracted and extended states, enabling adaptation to different flight phases while maintaining a relatively compact and integrated design that does not excessively increase overall system complexity.
Data Source
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AI summary
Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.