Multi-Stage Kinetic Missile Architecture for TOW Compatibility
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Solution Overview
Problem
Existing hyper-velocity kinetic energy missiles are incompatible with the TOW platform due to size, weight, and guidance constraints, making it difficult to retrofit KE technology for effective use with existing TOW launch containers and platforms, especially against modern composite armor.
Innovation Solution
A 'missile in a missile' architecture with a first stage flight missile cruising at sub-sonic velocities for guidance and a second stage KE-rod penetrator that boosts to hyper-velocity just before impact, reducing propellant weight and simplifying guidance, allowing the missile to fit within TOW constraints while maintaining effective KE performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the missile is boosted to hyper-velocity over the entire effective range to target, then the KE performance is maximized, but the missile becomes heavy and requires a different guidance system that is incompatible with CLOS
Solution Approach 1:
The missile is divided into two distinct stages: a flight missile that carries the KE-rod penetrator and is guided by CLOS at sub-sonic velocities, and a separate boost motor that is ignited only in the final seconds before impact to accelerate the penetrator to hyper-velocity. This segmentation allows each component to optimize its function without compromising the other.
Solution Approach 2:
The flight missile is guided to the target area using CLOS guidance at controlled sub-sonic velocities, establishing the correct trajectory and positioning before the hyper-velocity boost phase. This preliminary guidance action ensures the penetrator is on the correct path before the final acceleration, combining the benefits of controlled guidance with hyper-velocity impact.
2Speed
If the missile is made heavy to achieve hyper-velocity, then the KE performance improves, but the missile cannot fit within the TOW launch container constraints
Solution Approach 1:
The boost motor and propellant are contained within the body structure of the flight missile, with the KE-rod penetrator positioned inside the kill missile assembly. This nested configuration allows the heavy hyper-velocity components to be packaged within the size constraints of the TOW launch container while maintaining the necessary mass for KE performance.
Solution Approach 2:
The missile system is segmented into modular components (flight missile, boost motor, KE-rod penetrator) that can be efficiently packaged within the launch container. The separation of the boost motor from the main flight phase allows the propellant mass to be concentrated in a compact configuration that fits within TOW constraints.
3Speed
If the missile uses smokey propellants for hyper-velocity, then the KE performance is maximized, but the operator's vision of the target is occluded
Solution Approach 1:
The CLOS guidance and target acquisition are completed during the sub-sonic flight phase before the boost motor is ignited. The operator maintains visual contact and guidance control throughout this phase, and only after the target is locked on does the hyper-velocity boost phase begin, minimizing the time during which smoke could interfere with vision.
Solution Approach 2:
The flight phase is segmented into a guidance phase (sub-sonic, clear visibility) and an impact phase (hyper-velocity, smokey propellant). This temporal segmentation ensures that the period of maximum operator visibility coincides with the guidance phase, while the smokey propellant is used only in the final seconds before impact when guidance is no longer required.
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 multi-stage design satisfies physical, operational, and guidance constraints of TOW platforms, enabling effective targeting and penetration of modern composite armor without requiring significant modifications to the infrastructure, while minimizing propellant usage and maintaining operator control during guidance.
Implementation Method 1
a flight motor to accelerate the kill missile to a velocity greater than Mach 0.6 and less than Mach 1.5
Implementation Method 2
a boost motor to accelerate the KE-rod penetrator to velocities greater than Mach 3 and typically hyper-velocities
Implementation Method 3
The principle of the kinetic energy penetrator is that it uses its kinetic energy, which is a function of mass and velocity, to force its way through armour
Data Source
Figure 1a~1b
Figure 2a~2b
Figure 3
AI summary
A multi-stage hyper-velocity kinetic energy missile (HVKEM) uses a 'missile in a missile' architecture in which the HVKEM includes a 1st stage flight missile and a 2nd stage kill missile that includes a KE-rod penetrator. The flight missile cruises at a relatively low velocity (less than Mach 1.5, typically less than Mach 1) to conserve propellant (weight) and to allow for effective guidance and maneuvering until the missile is in close proximity to the target. When the missile is within the lethal range of the KE- rod penetrator, the kill missile separates and boosts to a much higher velocity (greater than Mach 3, typically greater than Mach 5) and flies unguided to impact the target in less than a second. Waiting to boost the KE-rod until "the last second" reduces the total propellant (weight) needed to deliver the KE-rod on target and simplifies the guidance. The missile may be configured for use with different platforms and different guidance systems but is particularly well suited for use with the existing base of TOW launch containers and platforms satisfying all of the physical, operational and CLOS guidance constraints while maintaining the performance of the KE-rod penetrator.