Multiple-Impulse Solid Fuel Rocket Motor for KKV Divert Control
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Solution Overview
Problem
Current kinetic kill vehicle (KKV) systems for intercepting ballistic missile re-entry vehicles face challenges in achieving precise navigation due to the complexity and cost of divert and attitude control systems (DACS) with multiple nozzles and gas supply systems, which increase the CEP (circular error probable) and reduce the probability of collision.
Innovation Solution
The use of multiple-impulse solid fuel rocket motors with independently ignitable combustion chambers and a common nozzle, where each chamber contains solid fuel propellant charges and igniters, allows for precise thrust control by selectively igniting and pressurizing each chamber, reducing the complexity and cost of the DACS while improving navigation accuracy.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If independent liquid fuel rocket motors or common gas supply systems with piping, valves, and actuators are used to control thrust to multiple divert nozzles, then the divert and attitude control system can achieve precise trajectory control, but the system complexity and cost increase significantly
Solution Approach 1:
The patent merges multiple combustion chambers into a single integrated engine assembly with a common nozzle. The combustion chambers are arranged in a cluster configuration where they share common structural elements, fuel supply systems, and exhaust pathways, eliminating the need for separate piping, valves, and actuators for each nozzle while maintaining independent thrust control capability
Solution Approach 2:
The common nozzle structure serves multiple functions: it acts as the exhaust outlet for all combustion chambers, provides structural support for the entire engine assembly, and enables coordinated thrust vectoring for both divert and attitude control functions. This multi-functional design reduces the overall component count and system complexity
2Ease of operation
If multiple nozzles with independent gas supply systems are used for divert control, then the KKV can maneuver precisely to intercept the target, but the navigation accuracy (CEP) deteriorates due to system complexity
Solution Approach 1:
The engine assembly is segmented into multiple independently controllable combustion chambers, each capable of being ignited or extinguished independently. This segmentation allows for fine-grained thrust control where individual chambers can be activated to produce precise maneuvering forces while the shared nozzle provides structural stability and reduces overall system complexity
3Adaptability or versatility
If complex piping, valves, and actuators are installed to meter fuel or exhaust gas to multiple nozzles, then the divert subsystem can control thrust direction and magnitude, but the cost and complexity of the KKV increase
Solution Approach 1:
The patent combines multiple fuel supply lines into a common fuel manifold that distributes propellant to all combustion chambers. Similarly, the exhaust gases from all chambers are directed through a shared nozzle, eliminating the need for separate piping, valves, and actuators for each nozzle while maintaining independent thrust control capability through electronic ignition management
Solution Approach 2:
The patent replaces complex mechanical metering systems (piping, valves, actuators) with an electronic control system that manages ignition and combustion of individual chambers. This substitution eliminates numerous mechanical components while maintaining precise thrust control through electronic timing and sequencing of chamber ignition
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 solution enhances the precision of KKV navigation, reducing the CEP and increasing the probability of collision with the target re-entry vehicle, thereby improving the effectiveness of intercept missions.
Implementation Method 1
each chamber contains solid fuel propellant charges and igniters
Data Source
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AI summary
There is disclosed a vehicle and methods for maneuvering the vehicle. The vehicle may include a plurality of multiple-impulse rocket motors, each of which comprises a plurality of independently ignitable solid fuel propellant charges, and a processor that generates at least one command to ignite at least one solid fuel propellant charge of at least one of the plurality of multiple-impulse rocket motors.