Deformable Missile Rocket Motor Case for Launch Tube Volume Optimization
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional submarine-launched ballistic missiles are limited by the circular cross-sectional shape of launch tubes, which restricts the number of missiles that can be carried and the propellant loading, thereby reducing the range of the missiles.
Innovation Solution
A rocket motor case with a non-circular transverse cross-sectional shape, such as elliptical, that deforms into a circular shape upon ignition, allowing for increased propellant loading and efficient use of launch tube space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If partitioned launch tubes are used to carry multiple missiles, then the number of missiles per submarine increases, but the diameter of circular cross-section missiles is constrained, limiting propellant loading and range
Solution Approach 1:
The patent applies asymmetry by changing the missile cross-section from a conventional circular shape to an elliptical shape. This asymmetric geometry allows the missile to fit more efficiently into the partitioned circular launch tube, maximizing the use of available space. The elliptical cross-section enables greater propellant loading volume while maintaining compatibility with the partitioned tube configuration, thus resolving the contradiction between carrying multiple missiles and maintaining sufficient propellant capacity.
Solution Approach 2:
The patent utilizes dimensionality change by transitioning from a two-dimensional circular cross-section to an elliptical cross-section with different dimensional proportions. This dimensional adjustment allows the missile to optimize its space utilization within the constrained circular launch tube environment, enabling increased propellant volume without compromising the ability to fit multiple missiles in partitioned tubes.
2Adaptability or versatility
If circular cross-section missiles are used in partitioned launch tubes, then launch tube compatibility is maintained, but significant unused cross-sectional volume results, reducing propellant capacity
Solution Approach 1:
The elliptical cross-section introduces asymmetry that better conforms to the circular launch tube geometry when partitioned. This asymmetric shape eliminates the significant unused volume that occurs with circular missiles, allowing the missile to occupy more of the available cross-sectional area while maintaining adaptability to the launch tube configuration.
Solution Approach 2:
The patent employs dynamics by designing the missile case to be flexible and deformable. The missile is launched in an elliptical cross-section that optimizes space utilization in the partitioned tube, then deforms to a circular cross-section during flight to maintain aerodynamic performance. This dynamic shape transformation resolves the contradiction between maximizing launch tube volume usage and maintaining flight compatibility.
3Volume of moving object
If non-circular cross-section missiles are used, then propellant loading volume increases, but structural design and manufacturing complexity increases
Solution Approach 1:
The patent utilizes flexible shells by designing the missile case as a deformable structure that can transition between elliptical and circular cross-sections. This flexible case design simplifies manufacturing compared to rigid non-circular structures, as the flexibility allows the case to be formed more easily and to adapt its shape during flight, reducing manufacturing complexity while maintaining the volume advantages of non-circular geometry.
Solution Approach 2:
The dynamic shape-changing capability simplifies manufacturing by allowing the use of more conventional materials and construction methods for the case, which can be designed to deform predictably. Rather than requiring complex rigid non-circular structures, the dynamic approach uses materials and designs that naturally facilitate shape transformation, reducing manufacturing 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
This configuration enables about 25% to 45% more propellant to be accommodated, significantly increasing the range of missiles by optimizing the use of launch tube volume.
Implementation Method 1
a rocket motor case containing a propellant grain and having at least a portion of initial, non-circular transverse cross-sectional shape, which may be flexed into a second, different transverse cross-section responsive to application of internal pressure from ignition of a propellant grain therein
Data Source
AI summary
A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a missile component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.