RCS Micro-Rocket Modules for Missile Orientation Control
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Solution Overview
Problem
Conventional missiles and rockets designed for vertical launch follow ballistic trajectories, lacking the ability to adjust orientation post-launch for more effective targeting at lower altitudes, especially under unfavorable conditions like severe wind or unstable launch platforms.
Innovation Solution
A reaction control system (RCS) comprising micro-rocket modules and a controller, which can be retrofitted to air vehicles to provide control moments for altering orientation, allowing for desired trajectory changes post-launch, including swinging to a horizontal orientation, without significant modifications to the vehicle.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional missiles are launched vertically following ballistic trajectories, then the missile structure remains simple and launch infrastructure is minimal, but the missile cannot adjust orientation post-launch for effective targeting at lower altitudes
Solution Approach 1:
The control system is segmented into multiple independent micro-rocket modules (typically 4-6 modules) arranged around the missile nose. Each module can be independently activated to provide specific control moments, allowing flexible trajectory adjustment without requiring a complex integrated control system. This segmentation enables the missile to achieve orientation control while maintaining relatively simple individual module designs.
Solution Approach 2:
Micro-rocket modules serve as intermediary propulsion elements between the main missile engine and the guidance system. These modules provide the necessary control forces by firing in specific sequences and directions, mediating between the simple ballistic trajectory and the desired adjusted trajectory without requiring complex control mechanisms within the missile body itself.
2Adaptability or versatility
If micro-rocket modules are added to the missile nose for orientation control, then trajectory adjustment capability is improved, but the overall length and diameter of the missile increase
Solution Approach 1:
The micro-rocket modules are nested within or mounted on the existing missile nose structure. The modules are positioned within the conical nose section or on its surface, utilizing the existing spatial envelope. This nesting approach allows the control system to be integrated without significantly extending the missile's overall length or diameter, as the modules share the space already allocated for the nose cone.
Solution Approach 2:
The micro-rocket modules are designed to be selectively activated rather than continuously operating. By firing only when and where needed for trajectory correction, the system achieves orientation control without requiring permanent structural modifications that would increase missile dimensions. The dynamic activation strategy allows the same physical configuration to serve multiple mission requirements.
3Reliability
If the missile is designed for vertical launch only, then the launch infrastructure remains simple, but the missile cannot operate effectively under unfavorable conditions like severe wind or unstable launch platforms
Solution Approach 1:
The micro-rocket modules are pre-positioned and pre-configured on the missile before launch. The control system is pre-programmed with sequences for correcting various launch deviations. When unfavorable conditions are detected, the system executes pre-planned correction maneuvers by activating specific modules in predetermined sequences, allowing the missile to compensate for wind, platform instability, or other adverse conditions without requiring complex real-time decision-making infrastructure.
4Adaptability or versatility
If the missile trajectory is extended to allow orientation adjustment, then targeting flexibility is improved, but the flight time and exposure to detection increase
Solution Approach 1:
The micro-rocket modules operate in periodic, pulsed sequences rather than continuous firing. Short bursts of thrust from individual modules are timed to provide maximum orientation change with minimum energy expenditure. This periodic activation allows the missile to quickly adjust its trajectory and maintain desired orientation without prolonged exposure to detection, minimizing the time penalty while achieving targeting flexibility.
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
Enables air vehicles to achieve desired orientations, such as between 0° to 50° relative to horizontal, enhancing targeting capabilities, reducing range, and allowing operation under adverse launch conditions, while conserving overall length and diameter, and enabling launch from existing silos without modifications.
Implementation Method 1
A reaction control system (RCS) comprising micro-rocket modules and a controller, which can be retrofitted to air vehicles to provide control moments for altering orientation
Data Source
AI summary
A reaction control system (RCS) is provided for use with an air vehicle having a nose portion and a center of gravity aft of the nose portion. The RCS includes a belt element configured for selectively securing the RCS to the nose portion, and also includes a plurality of micro-rocket modules affixed to the belt element, each micro-rocket module being configured for being selectively activated to provide corresponding control moments to the air vehicle when secured to the nose portion thereof. A corresponding air vehicle, and a method for modifying an air vehicle, are also provided.