Missile Launcher Container With Thermal Protection
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Solution Overview
Problem
Existing missile launchers are not versatile enough to accommodate both large and small missiles, requiring separate launchers for different sizes, and deformable lids used to prevent shockwave damage imperfectly seal after use.
Innovation Solution
A multiple container design for missile launchers, featuring a bottom with resealable lids and a partition dividing it into tubes, equipped with thermal protection and deformable caps with elastic blades, allowing the launcher to adapt to both large and small missiles by ensuring effective sealing and protecting adjacent lids from thermal radiation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single launcher is designed to accommodate both large and small missiles, then the launcher becomes versatile, but the container structure becomes more complex
Solution Approach 1:
The container is divided into multiple independent tubes within a single container structure, with each tube capable of holding missiles of different sizes. The partition walls between tubes can be selectively removed or adjusted to accommodate various missile diameters, allowing one container to replace multiple dedicated containers while maintaining structural integrity through modular segmentation.
Solution Approach 2:
The container design incorporates universal features including adjustable partition walls, deformable lids with elastic blades that adapt to different pressure conditions, and thermal protection systems that work across all tubes. This multi-functional design allows the same container structure to safely launch different missile types without requiring dedicated containers for each missile size.
2Object-affected harmful factors
If deformable lids with elastic blades are used to prevent shockwave damage, then protection is provided, but the lids fail to seal perfectly after use
Solution Approach 1:
The lid design incorporates elastic blades that change their physical parameters dynamically - remaining rigid during normal operation for sealing, becoming deformable during missile launch to absorb shockwaves, and returning to sealed position after launch. The elasticity of the blades is carefully calibrated to provide sufficient deformation for shockwave protection while maintaining adequate sealing force after pressure equalization.
Solution Approach 2:
The deformable lid structure is pre-designed with elastic blades that can absorb and dissipate shockwave energy before it reaches the missile or damages the container structure. The elastic blades act as a cushioning element that deforms under extreme pressure and then gradually returns to its original position, providing both protection during launch and sealing afterward through controlled elastic recovery.
3Object-affected harmful factors
If thermal protection means are added to protect adjacent lids, then thermal damage is reduced, but the device complexity increases
Solution Approach 1:
The thermal protection function is merged with existing structural components rather than adding separate protection systems. The partition walls between tubes are designed to serve both structural separation and thermal shielding functions. The deformable lids themselves incorporate thermal protection through their material selection and geometric design, eliminating the need for additional dedicated thermal protection components.
Solution Approach 2:
Thermal protection is applied locally where most needed - the partition walls adjacent to missile tubes receive enhanced thermal shielding, while areas not exposed to direct thermal radiation require minimal protection. The lid structures incorporate thermal protection features specifically at the downstream end where hot gases exit, rather than uniformly across all surfaces, optimizing protection while minimizing added complexity.
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
Enables the simultaneous launch of both large and small missiles from a single launcher, maintaining the elasticity of deformable lids for effective sealing and reducing thermal damage, making the launcher versatile and improving sealing efficiency.
Implementation Method 1
a stack of elastic blades and tearable downstream sealing membranes. The elastic blades are preferably rectangular and are held on their periphery between upstream and downstream support frames. Each elastic blade is made up of several triangular petals made from a thin flexible and elastic metal plate. In their rest position, the petals are contiguous and thus obstruct the orifice of the lid of the bottom of the container. When the propellant gases are ejected from the missile, an overpressure tears the sealing membranes and deforms the petals by flexing around a rounded inner edge of the lower support frame. The edges of the petals move away from each other and create a passage putting the interior of the container in communication with the plenum via the adapter. Once the missile is fired, the pressure inside the container decreases. The petals return elastically to their rest position, in abutment against the grid, and close the orifice of the lid.
Implementation Method 2
When the downstream cover opens, the propulsion gases which are hot and for which the speed of sound is around 1000 m/s, encounter gases present in the plenum which are cold and for which the speed of sound is of the order of 300 m/s. This results in a shock wave regime at the interface between the hot and cold gas masses. This phenomenon lasts between 100 and 150 ms, the time for the cold gases to propagate out of the plenum through the extraction chimney, and results in a sharp increase in temperature and pressure in the plenum, when missile fire.
Implementation Method 3
the bottom of the container is provided, on the downstream side, with thermal protection means capable of protecting each adjacent cover from the incident thermal radiation flux emitted when a cover is opened under the effect of the propulsion gases of a missile
Data Source
Figure 1
Figure 2~3
Figure 4~6
AI summary
The container (17) has a base (55) provided with several reclosable covers (56) and a partition (50) separating the container in to multiple tubes (51a, 51b). Each tube receives a missile, and the cover is arranged opposite to the tube. The cover is opened under pressure of missile propulsion gas contained in the corresponding tube and closed again after the ejection of the missile. The base has thermal protection unit to protect the covers from incident thermal radiation flow emitting during opening of the cover.