Missile Vectored Thrust Steering at High Altitude
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Solution Overview
Problem
Missiles face challenges in maneuvering at high altitudes due to the reduced effectiveness of aerodynamic control surfaces in thinner air, limiting their ability to intercept high-altitude targets.
Innovation Solution
The integration of vectored thrust systems with movable control surfaces and a controller that shifts between high and low dynamic pressure modes during flight, allowing the missile to use vectored thrust for steering at high altitudes and control surfaces at lower altitudes, supplemented by a multiple-pulse rocket motor for acceleration and maneuvering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If control surfaces are used for steering at high altitudes, then the missile can maintain aerodynamic control, but the control effectiveness deteriorates due to thinner air
Solution Approach 1:
The patent combines aerodynamic control surfaces with a vectored thrust system to create a hybrid steering mechanism. The control surfaces handle low-altitude maneuvering where air density is sufficient, while the vectored thrust system takes over at high altitudes where aerodynamic control becomes ineffective. This merging allows the missile to maintain reliable steering across the entire altitude range.
Solution Approach 2:
The patent implements dynamic mode switching between high dynamic pressure mode (using control surfaces) and low dynamic pressure mode (using vectored thrust). The controller dynamically selects the appropriate steering mechanism based on real-time altitude and air density conditions, ensuring optimal control effectiveness throughout the flight envelope.
2Adaptability or versatility
If a single steering mechanism is used, then the device complexity is reduced, but the adaptability to different altitude conditions deteriorates
Solution Approach 1:
The patent creates a universal steering system that can operate effectively across diverse altitude conditions. The dual-steering architecture (control surfaces + vectored thrust) allows the missile to engage targets at various altitudes, from sea level to high-altitude ballistic trajectories, making the system versatile for multiple mission types.
Solution Approach 2:
The patent segments the steering function into two distinct systems: aerodynamic control surfaces for low-altitude operation and vectored thrust for high-altitude operation. Each subsystem is optimized for its specific operational regime, and the controller manages the segmentation by selecting the appropriate system based on flight conditions.
3Ease of operation
If control surfaces are used in thin air, then the structure remains simple, but the steering capability deteriorates
Solution Approach 1:
The vectored thrust system acts as an intermediary mechanism that bridges the gap where aerodynamic control surfaces become ineffective. In high-altitude thin air conditions, the vectored thrust provides the necessary steering authority that control surfaces alone cannot deliver, ensuring maintainable steering capability across all operational conditions.
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 the missile to effectively steer and intercept targets at higher altitudes where conventional control surfaces are inadequate, extending its operational range and capability to engage high-altitude targets.
Implementation Method 1
a thrust system that provides vectored thrust for steering the air vehicle
Implementation Method 2
Aerodynamic control from control surfaces loses effectiveness at high altitudes, where air is thinner
Data Source
AI summary
An air vehicle, such as a missile, for example an interceptor, includes control surfaces and a vectored thrust system, both used for steering the missile. A controller is operatively coupled to both steering mechanisms, and is configured to operate in a low dynamic pressure mode, which uses the vectored thrust system for at least part of the steering, only when the dynamic pressure is low, such as when the missile is at high altitude. At higher dynamic pressure, such as at lower altitude, the controller is configured to operate in a high dynamic pressure mode that uses only the control surfaces for steering. This allows the interceptor to operate at higher altitudes than interceptors that use only control surfaces for steering during flight. During flight for a high altitude interception the missile shifts from the high dynamic pressure mode to the low dynamic pressure mode.