Nested Solid Propellant Tanks for Side Force Steering
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Solution Overview
Problem
Existing side force steering and attitude control systems for vehicles, particularly in interceptor missiles, face challenges in achieving independent thrust control between attitude correction and side force steering, leading to increased system size and mass.
Innovation Solution
A compact side force steering and attitude control system utilizing two nested solid propellant tanks, allowing independent feeding of attitude correction and side force steering modules, with each tank having a distinct combustion chamber and propellant structure, enabling optimized operating points and reduced inert mass.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If a single block of solid propellant is used to power both attitude correction valves and side force steering valves, then the system size is reduced, but independent thrust control between attitude correction and side force steering cannot be achieved
Solution Approach 1:
The single propellant block is segmented into two separate solid propellant charges, each contained in its own tank. The first charge powers the attitude correction valves while the second charge powers the side force steering valves, enabling independent control of each function while maintaining a compact integrated structure.
Solution Approach 2:
The two tanks containing separate propellant charges are arranged in a nested configuration where one tank is positioned within or adjacent to the other within the thruster body. This nesting approach allows independent propellant storage and combustion for each control function while minimizing the overall system volume.
2Adaptability or versatility
If distinct propellant blocks are used to independently feed attitude correction and side force steering valve sets, then independent thrust control is achieved, but the overall size of the DACS increases
Solution Approach 1:
The two separate propellant feeding systems are merged into a single integrated thruster body structure. The tanks are positioned and configured to share common structural support, mounting interfaces, and combustion chamber integration, thereby reducing the overall system size compared to completely separate arrangements.
Solution Approach 2:
The tanks are arranged in a nested configuration within the thruster body, with one tank positioned inside or adjacent to the other. This spatial arrangement minimizes the envelope volume required to accommodate both independent propellant systems while maintaining their functional independence.
3Ease of manufacture
If the same solid propellant block is used for both valve sets, then manufacturing is simplified, but operating points (pressure, combustion duration, ignition instants) cannot be independently optimized
Solution Approach 1:
The propellant system is segmented into two separate charges that can be manufactured to different specifications. Each charge can be formulated with different grain structures, densities, and combustion characteristics to optimize the operating points for its specific function, while both can be manufactured using similar processes.
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 allows for independent control of attitude correction and side force steering, optimizing operating conditions and reducing system size and mass, while maintaining balanced thrust and flow rates throughout the mission.
Implementation Method 1
a first solid propellant charge having at least one combustion face exposed at the second end of said first tank, the first tank being in communication with the first valve set; and a second solid propellant charge having at least one combustion face exposed at the second end of said second tank
Data Source
AI summary
An in-flight side force steering and attitude control system for a vehicle includes a thruster body and a plurality of valves distributed in first and second valve sets. The system further includes a first tank defined by a first cylindrical enclosure present at the center of the thruster body, the first tank containing a first solid propellant charge having at least one combustion face exposed at one end of the first tank, the first tank being in communication with the first valve set; and a second tank defined between the first cylindrical enclosure and a second cylindrical enclosure present around the first enclosure, the second tank containing a second solid propellant charge having at least one combustion face exposed at one end of the second tank, the second tank being in communication with the second valve set.