Integrated Propulsion and Attitude Control System for Interceptors
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional attitude control systems (ACS) for interceptors are bulky, heavy, and costly due to the need for separate propulsion and control mechanisms, making them impractical for small, lightweight counter-missile missiles that require efficient maneuverability and compact design.
Innovation Solution
An integrated propulsion and attitude control system using a common pressure vessel with fixed main and attitude control nozzles, where propellant burn creates high-pressure gas for both propulsion and attitude control, eliminating the need for servo motors and reducing system size, weight, and cost.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional separate propulsion and attitude control mechanisms are used, then reliable attitude control is achieved, but system weight and complexity increase significantly
Solution Approach 1:
The patent combines the propulsion system and attitude control system into a single integrated architecture. The rocket motor serves dual purposes: generating thrust for propulsion while simultaneously providing high-pressure gas to attitude control nozzles for maneuvering. This merging eliminates separate ACS mechanisms (such as reaction control systems or aerodynamic surfaces), thereby reducing weight while maintaining control reliability through unified system operation.
Solution Approach 2:
The rocket motor is designed to perform multiple functions: it generates thrust for forward motion and simultaneously serves as the gas source for attitude control nozzles. The single propellant charge provides both propulsion energy and control energy, making the propulsion system universal for both primary motion and secondary maneuvering functions, thus eliminating dedicated ACS weight.
2Power
If conventional separate propulsion and attitude control mechanisms are used, then adequate thrust is provided, but system cost and complexity increase
Solution Approach 1:
The patent merges propulsion and attitude control into a single integrated system where the rocket motor and its propellant serve both functions. This eliminates the need for separate ACS mechanisms, reducing the number of components, simplifying system architecture, and lowering overall system complexity while maintaining adequate thrust for both propulsion and maneuvering.
Solution Approach 2:
The propulsion system is designed with universal functionality to provide both primary thrust and attitude control. The same propellant charge and pressure vessel serve dual purposes, eliminating redundant systems and reducing overall device complexity while ensuring adequate power for all flight phases.
3Productivity
If compact design is implemented for small interceptors, then maneuverability efficiency improves, but available space for separate ACS mechanisms decreases
Solution Approach 1:
The patent eliminates the need for separate ACS volume by merging attitude control functions into the propulsion system. The rocket motor's high-pressure gas directly feeds attitude control nozzles, removing the need for dedicated ACS tanks, valves, and actuators. This integration maximizes the use of available volume for maneuverability efficiency in compact interceptor designs.
Solution Approach 2:
The propulsion system serves dual functions, providing both thrust and attitude control from the same volume. The propellant charge and pressure vessel are universally used for both propulsion and maneuvering, eliminating the need for separate ACS volume and enabling compact interceptor design with efficient maneuverability.
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 integrated system enables a compact, lightweight, and inexpensive ACS that provides full 3-axis attitude control, consuming less than 10% of the propellant energy for control, while maintaining necessary thrust and maneuverability for engaging threats like MANPADS.
Implementation Method 1
Rocket propellant is ignited and burns creating a high-pressure gas
Implementation Method 2
main nozzles that convert the high-pressure gas into a high-velocity gas
Implementation Method 3
gas is expelled in a generally axial direction to propel the interceptor
Implementation Method 4
expel the high-velocity gas in generally radial directions offset from the interceptor Cg to change the attitude of the interceptor
Data Source
AI summary
An interceptor is provided with an integrated propulsion and attitude control system (ACS) in which propellant burn forms a common pressure vessel for high-pressure gas. An aft port in the rocket motor directs gas through one or more main nozzles that expel high-velocity gas in a generally axial direction to propel the interceptor. A forward port directs gas through one or more attitude control nozzles that expel high-velocity gas in a generally radial direction to control the attitude of the interceptor. The main nozzle(s) and stabilization fins are fixed, there is no servo control to the main nozzles or fins to affect attitude control. The use of a common pressure vessel enables an integrated propulsion and ACS that can be compact, lightweight and inexpensive.