Missile Air Intake Cover Ejection Mechanism
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Solution Overview
Problem
Air intake covers for missiles often become stuck due to dirt accumulation or ice formation during storage and transit, requiring reliable ejection mechanisms that operate with sufficient force without increasing the missile's size or adapting launchers.
Innovation Solution
A self-contained air intake cover with a motive arrangement, including a linkage mechanism and pyrotechnic actuator, that moves from a locked to a removable configuration, ensuring reliable ejection without external modifications, using a cam and follower mechanism to push the cover outward and a ballast weight for predictable trajectory.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the cover ejection mechanism is designed to operate with sufficient force to break through dirt accumulation and ice formation, then the reliability of cover removal is improved, but the device complexity and space requirements increase
Solution Approach 1:
The cover and ejection mechanism are merged into a single integrated unit. The motive arrangement is contained within the cover itself, eliminating the need for separate external ejection mechanisms. This integration reduces overall device complexity while maintaining the required ejection force through the self-contained design.
Solution Approach 2:
The ejection mechanism is nested within the cover structure. The motive arrangement, including the linkage mechanism and actuator, is positioned inwardly of the cover surface, with components arranged in a compact nested configuration that fits within the limited space of the air intake cover while providing sufficient ejection force.
2Volume of moving object
If the motive arrangement is positioned inwardly of the cover surface, then the missile's size and launcher adaptation requirements are reduced, but the mechanism must operate through tighter spaces increasing complexity
Solution Approach 1:
The linkage mechanism employs dynamic motion paths that allow components to move through compact arcs and angles rather than straight lines. The mechanism transitions from a retracted position to an extended ejection position through a series of coordinated movements that maximize force application within the constrained inwardly-positioned space.
Solution Approach 2:
The ejection mechanism utilizes three-dimensional spatial arrangement rather than simple linear extension. Components are positioned at different depths and angles within the cover, allowing the linkage to achieve sufficient leverage and ejection force by moving through multiple dimensions rather than requiring extended linear space.
3Object-affected harmful factors
If the cover is locked flush with the missile surface during storage, then aerodynamic performance and protection are improved, but the ejection mechanism requires sufficient force to overcome locking and sticking
Solution Approach 1:
The locking mechanism is designed with preliminary release features that initiate the ejection sequence. Before full ejection force is applied, the linkage mechanism first disengages the locking arms from the locked position, reducing the initial force barrier. This preliminary action prevents the cover from becoming permanently stuck due to dirt or ice accumulation during storage.
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 solution ensures reliable and efficient removal of the air intake cover during flight, preventing debris ingress and ice formation, while maintaining compactness and reliability, even after prolonged storage, without requiring additional space or launcher adaptations.
Implementation Method 1
a motive arrangement, including a linkage mechanism and pyrotechnic actuator
Data Source
Figure 1a~1b
Figure 2
Figure 3
AI summary
A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a motive arrangement operable to move from a first configuration in which the cover is lockable to a missile, to a second configuration in which the cover is pushed outwardly from the missile. In the first configuration, the surface of the cover is flush with the surface of the missile and the motive arrangement is located inwardly of the cover surface. A missile provided with such a cover is also disclosed.