Integrated Actuation System for Missile Thrust Vector Control
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Solution Overview
Problem
Ballistic missiles face challenges with complex and heavy systems for thrust vector and attitude control, which increase weight, size, and integration difficulties, and introduce single-point failure risks due to separate power sources and components.
Innovation Solution
A projectile with an integrated actuation system that directs propellant from a storage reservoir through both internal and external outlets to control thrust vector and attitude, using a propulsion booster and nozzle to produce pressurized gases and additional thrust, thereby simplifying system integration and reducing weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate thrust vector control and attitude control systems are used, then control functions are achieved, but device complexity and weight increase
Solution Approach 1:
The patent combines separate thrust vector control actuators and attitude control actuators into a single integrated actuation system. This integration merges multiple control functions into one unified system, reducing the number of separate components while maintaining both thrust vectoring and attitude control capabilities throughout the missile flight trajectory.
Solution Approach 2:
The integrated actuation system performs multiple functions: it provides thrust vector control during propulsion stage burn and initial flight vector alignment, and subsequently provides attitude control for pitch, yaw, and roll adjustments. This multi-functional approach eliminates the need for separate control systems while achieving all required control objectives.
2Ease of operation
If separate power sources are used for propulsion and control systems, then independent operation is achieved, but weight and integration difficulty increase
Solution Approach 1:
The patent merges the power sources by integrating the attitude control system into the propulsion stage power source. The propulsion stage motor provides power during burn, and after propulsion stage separation, the same motor continues to provide power for attitude control maneuvers, eliminating the need for separate batteries or power sources.
Solution Approach 2:
The propulsion stage motor serves dual purposes: it provides thrust during the propulsion stage burn and subsequently provides electrical power for attitude control after stage separation. This multi-functional power source reduces overall system weight by eliminating redundant power sources while maintaining operational independence through sequential function transition.
3Reliability
If multiple separate control systems are integrated, then control capabilities are achieved, but assembly integration difficulty increases
Solution Approach 1:
The patent merges multiple control systems into a single integrated actuation system with unified mounting structures and common power connections. This integration simplifies assembly by reducing the number of separate mounting operations and electrical connections required, while maintaining all necessary control capabilities through the multi-functional actuator design.
4Weight of moving object
If separate control systems are used, then functional redundancy is reduced, but single point failure risk increases
Solution Approach 1:
The integrated actuation system is designed with internal redundancy and fail-safe mechanisms. By combining control functions into a unified system with common power and control electronics, the patent reduces the number of potential failure points while maintaining reliability through sophisticated control algorithms that can detect and compensate for failures within the integrated system.
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 actuation system enhances mission flexibility, reduces weight and complexity, eliminates single-point failures, and improves reliability by combining thrust vector and attitude control into a single system, using propellant for both thrust and power generation, thus optimizing performance and manufacturing efficiency.
Implementation Method 1
a propulsion booster for producing pressurized gases
Implementation Method 2
a nozzle for expelling the pressurized gases produced by the booster
Implementation Method 3
The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster
Implementation Method 4
The integrated actuation system also selectively directs the propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce additional thrust at an external periphery of the projectile, thus diverting the projectile
Data Source
AI summary
A projectile includes a propulsion booster for producing pressurized gases, a nozzle for expelling the pressurized gases produced by the booster, and a supplementary integrated actuation system. The integrated actuation system selectively directs propellant from a storage reservoir of the integrated actuation system through an interiorly-located outlet of the integrated actuation system located at the nozzle and into the nozzle, thus changing a direction of the pressurized gases expelled by the booster. The integrated actuation system also selectively directs propellant from the storage reservoir through a peripherally-located outlet of the integrated actuation system, to produce thrust at an external periphery of the projectile, thus diverting the projectile. The integrated actuation system may also selectively direct propellant to a nozzle actuation system for positioning the nozzle, to a stage separation system for separating portions of the projectile, or to a power generator for generating electric power for the projectile.