Missile Guidance Vertical Flight Angle Control
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Solution Overview
Problem
Current missile systems lack the capability to guide a horizontally flying missile with a shaped charge to pass a predetermined distance above a target, combining target seeker technology with inertial navigation for precise altitude adjustment.
Innovation Solution
A gamma-ref calculation unit calculates a reference value for the vertical flight direction angle based on desired passage height, elevation angle, line-of-sight rotation, and missile velocity, allowing the missile to adjust its flight path to pass above the target at a specific height using an inertial navigation system and target seeking mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If conventional missile guidance systems are used to guide missiles to targets, then direct impact is achieved, but the missile cannot pass at a predetermined distance above the target
Solution Approach 1:
The guidance system changes the control parameter from direct impact angle to passage height, using a new reference value calculation that incorporates desired passage height (hdes) as a key parameter. This allows the missile to maintain a predetermined distance above the target while still achieving effective engagement
Solution Approach 2:
The system dynamically adjusts the vertical flight direction angle reference value (γref) based on real-time parameters including elevation angle (σ), line-of-sight rotation ({dot over (σ)}), and missile velocity (V). This dynamic adaptation enables the missile to consistently maintain desired passage height despite variations in flight conditions
2Object-affected harmful factors
If the missile is guided to pass at a predetermined distance above the target, then effective engagement against protected targets is achieved, but the guidance system complexity increases
Solution Approach 1:
The guidance system uses feedback from the inertial navigation system and target seeking mechanisms to continuously monitor and adjust the vertical flight direction angle. This feedback loop ensures the missile maintains the desired passage height while engaging protected targets effectively
Solution Approach 2:
The guidance system combines target seeking capabilities with inertial navigation data to accomplish both direct hit and fly-over missions using the same hardware platform. This multi-functionality reduces the need for separate specialized systems
3Ease of operation
If the missile velocity and line-of-sight rotation vary, then flight conditions change, but maintaining consistent passage height becomes difficult
Solution Approach 1:
The reference value for vertical flight direction angle is dynamically calculated based on current flight conditions including velocity (V) and line-of-sight rotation ({dot over (σ)}). This dynamic calculation ensures the missile maintains desired passage height despite variations in flight parameters
Solution Approach 2:
The system continuously monitors flight direction angle (γ) and compares it with the calculated reference value (γref), providing feedback control that maintains consistent passage height even when velocity or line-of-sight rotation changes
Data Source
AI summary
A missile guidance system and method for guiding a missile, mainly horizontally flying, to pass a target at a desired passage height.