Partitioned Solid Propulsion Chamber for Adjustable Thrust
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Solution Overview
Problem
Existing solid propulsion systems for short to medium range rockets and missiles have fixed thrust profiles, leading to high complexity, weight, and limited flexibility, making them unsuitable for varied operational scenarios.
Innovation Solution
A solid propulsion system with a combustion chamber subdivided into multiple partitions, allowing independent ignition and burn control of each propellant charge, enabling adjustable thrust profiles without moving parts or complex components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed thrust profile is used in simple solid rocket motors, then the structure is simple and weight is low, but the adaptability to different operational scenarios is limited
Solution Approach 1:
The combustion chamber is divided into multiple partitions (first partition, second partition, etc.), each containing separate propellant charges. This segmentation allows independent control of each partition's combustion, enabling variable thrust profiles without requiring complex mechanical moving parts. The partitions are separated by bulkheads that prevent cross-ignition, maintaining structural simplicity while achieving adaptability.
2Adaptability or versatility
If mechanically displaceable components are used to modify thrust, then variable thrust curves can be generated, but weight and structural complexity increase
Solution Approach 1:
The patent replaces mechanically displaceable components with a static partitioned structure. Instead of using moving parts to change combustion geometry, the invention uses fixed bulkheads to separate propellant charges, with ignition control achieved through electrical or chemical ignition systems. This substitution eliminates heavy mechanical mechanisms while maintaining thrust variability.
3Ease of operation
If multiple combustion chambers and nozzles are used to achieve variable thrust, then thrust control is possible, but device complexity and unladen weight become high
Solution Approach 1:
Multiple propellant charges in different partitions share a common combustion chamber and common nozzle. The bulkheads separate the propellant sources, but the exhaust gases from all partitions converge into a single nozzle. This merging approach reduces the number of nozzles and overall structural complexity while maintaining the ability to control thrust by selectively igniting different partitions.
4Adaptability or versatility
If propellant charges are separated into partitions, then independent ignition and adjustable thrust profiles are achieved, but the combustion chamber structure becomes more complex
Solution Approach 1:
The bulkheads separating partitions incorporate localized features such as ignition access channels, thermal insulation layers, and pressure equalization pathways. These local quality enhancements allow each partition to be independently controlled while maintaining overall structural integration. The bulkheads are not simple walls but contain specialized zones that enable the desired functionality without requiring complete structural redesign.
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 provides a lightweight, cost-effective, and reliable propulsion system with adjustable thrust profiles, enhancing flexibility and reducing complexity, while maintaining high overall thrust and minimizing susceptibility to errors.
Implementation Method 1
The partition is designed to protect a propellant in an associated partition from being ignited by another burning propellant in another partition. The partition wall can, for example, comprise thermal insulation.
Implementation Method 2
A propellant charge with reducing and oxidizing agents in solid form is usually carried along, which are reacted with one another.
Data Source
Figure 1~3
Figure 4~5
Figure 6~7
AI summary
The solid propellant (12) has a burning chamber (16) withy one partition (26a) and another partition (26b) that are separated from each other by a partition wall (24). Former partition has a propellant (28a), which is arranged to be ignited in latter partition independent from another propellant (28b). The partition wall has a plate stretching in longitudinal direction (L). The plate is connected at edges with an outer wall (20) of the burning chamber, so that the partitions are formed in wedge-shape or cylindrical segment shape. Independent claims are included for the following: (1) a method for operating a solid propellant; and (2) a missile.