Divert and Attitude Control System Valve Arrangement
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Solution Overview
Problem
Existing Divert and Attitude Control Systems (DACS) for vehicles, particularly interceptor missiles, are cumbersome due to the large number of valves required for trajectory and attitude control, leading to increased mass, size, cost, and pyrotechnic safety concerns, with suboptimal valve placement affecting performance and maneuverability.
Innovation Solution
A DACS system with two sets of four valves arranged symmetrically around the center of gravity, each set capable of generating independent lateral thrusts in non-aligned directions, allowing for instantaneous corrections and reducing the individual thrust and power requirements of each valve, while simplifying the system design and improving safety.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple valves are used for trajectory and attitude control, then control precision is improved, but device complexity and mass increase
Solution Approach 1:
Each valve in the four-valve arrangement can perform multiple functions: trajectory correction by firing individual valves, and attitude control (roll, pitch, yaw) by firing combinations of valves. This multi-functionality eliminates the need for separate valve systems for different control purposes, reducing overall system complexity while maintaining precise control capabilities.
Solution Approach 2:
The patent combines trajectory deviation control and attitude control functions into a single integrated valve system. By positioning four valves at specific locations around the vehicle and using selective firing patterns, the system merges what would traditionally require separate valve assemblies, thereby reducing device complexity and mass.
2Volume of moving object
If valves are positioned inside the thruster body, then space is saved, but pyrotechnic safety deteriorates
Solution Approach 1:
The valves are extracted from the interior of the propellant block and positioned on its external surface. This extraction removes the pyrotechnic hazard of having ignition sources and valve mechanisms embedded within the propellant mass, significantly improving safety during assembly, handling, and operation while maintaining compact overall vehicle dimensions.
3Length of moving object
If valves are located close to propellant, then system compactness is improved, but operating time is limited due to high temperatures
Solution Approach 1:
A thermal barrier or insulating layer is introduced between the propellant block and the valve assembly. This intermediary protects the valves and surrounding structures from excessive heat transfer during propellant combustion, enabling the system to maintain compact dimensions while extending the duration over which the propulsion system can operate safely.
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 enables rapid and precise trajectory and attitude corrections with reduced mass and cost, improved steering precision, and enhanced pyrotechnic safety by distributing thrusts across two sets of valves, allowing for identical valve usage and a single propellant block for solid propellant systems.
Implementation Method 1
a plurality of valves capable of generating lateral thrusts by being placed in communication with the thruster body
Data Source
Figure 1~2
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Figure 6~7
AI summary
The invention relates to an in-flight attitude control and direct thrust flight control system which includes a propulsion body (20) and a plurality of valves capable of generating sidewise thrust when placed in communication with the propulsion body. The valves are distributed into two sets of valves (24, 26) spaced apart from one another towards the front and towards the rear of the propulsion body, in a substantially symmetrical manner relative to the centre of gravity of the vehicle, located on a longitudinal axis (A) thereof. Each set includes a first pair of valves generating thrust in opposite directions, along axes that are not aligned and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions, along axes that are not aligned and are parallel to a second axis, the first and second axes being separate and perpendicular to the longitudinal axis of the vehicle.