Detachable Grid Fin Missile Control System
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Solution Overview
Problem
Existing missile control systems face challenges in achieving low-speed guidance control and stability during launch, particularly when intercepting low-altitude threats, due to the limitations of traditional control surfaces and thrust vector control systems, which are often heavy, costly, and inefficient at low speeds.
Innovation Solution
A detachable aerodynamic missile control system featuring a grid fin interstage assembly with movable grid fins that provide increased drag and lift, coupled to the aft portion of the missile, and an articulation control system to control the orientation of the grid fins, allowing for rapid pitch-over and stability during low-speed flight, while being lightweight and compatible with existing missile designs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If control surfaces are sized for high speed use, then high speed control authority is improved, but low speed effectiveness deteriorates
Solution Approach 1:
The control surfaces are designed to be movable and adjustable in size. At high speeds, the control surfaces are extended to provide sufficient control authority. At low speeds, the control surfaces are retracted or reduced in size to maintain effectiveness without excessive weight and drag. This dynamic adjustment resolves the contradiction between high speed control authority and low speed effectiveness.
2Reliability
If control surfaces are sized for low speed use, then low speed effectiveness is improved, but device weight increases
Solution Approach 1:
The control surfaces are designed to be movable and adjustable in size. At low speeds, the control surfaces are extended to provide sufficient control authority. At high speeds, the control surfaces are retracted or reduced in size to minimize weight and drag. This dynamic adjustment resolves the contradiction between low speed effectiveness and device weight.
3Reliability
If movable nozzle systems are used for thrust vector control, then low speed guidance control is improved, but device complexity and weight increase
Solution Approach 1:
The invention extracts the thrust vector control function from the main engine nozzle and implements it through a separate, simpler movable nozzle system that can be independently controlled. This extracted subsystem provides low speed guidance control without the complexity of integrating movable mechanisms into the main propulsion system, resolving the contradiction between low speed guidance control and device complexity.
4Stability of the object's composition
If jet vanes are placed in the missile exhaust flow, then low speed stability is improved, but missile motor performance deteriorates
Solution Approach 1:
The invention introduces an intermediary flow path that allows the jet vanes to be positioned in the exhaust flow for stability control while maintaining a separate clean flow path for the majority of the propellant. This intermediary arrangement enables the jet vanes to provide low speed stability without significantly interfering with the main propellant flow and motor performance.
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 system enables rapid pitch-over and enhanced stability at low speeds, reducing the risk of overshooting targets and optimizing intercept trajectories, without the need for costly modifications to existing missile systems, and can be easily retrofitted to various missile types.
Implementation Method 1
the grid fins providing increased drag and lift to allow pitch-over when deployed
Implementation Method 2
the grid fins providing increased drag and lift to allow pitch-over when deployed
Implementation Method 3
an articulation control system configured to control an orientation of the grid fins and to link with a control system of the missile
Data Source
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AI summary
Provided is a detachable aerodynamic missile stabilizing system (130) for a missile (100) flying at low flight speeds. The system (130) includes a housing (134) adapted to couple to the missile (100). Extending outward from the housing (134) is at least one grid fin (136). Specifically the grid fin (136) extends from the housing (134) such that it is transverse to a longitudinal axis (110) of the housing (134) and the missile (100). The grid fin (136) provides a plurality of apertures (144). The apertures (144) are parallel to the longitudinal axis (110) of the housing (134) and the missile (100). A coupler (138) is adapted to detachably couple the housing (134) to the missile (100). A method of use is also provided.