Missile Midcourse Guidance Using Predictive Trajectory Planning
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Solution Overview
Problem
Supersonic missiles face significant fuel consumption challenges when flying at high speeds and altitudes, limiting their range and requiring robust flight planning to avoid enemy defenses, especially when performing evasive maneuvers.
Innovation Solution
The application of Model Predictive Control (MPC) for missile guidance, known as Model Predictive Guidance (MPG), which predicts and optimizes multiple trajectories based on control variables to minimize fuel consumption and ensure mission success by varying flight altitudes and avoiding enemy defenses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If supersonic flight at high speeds (Mach 3+) is employed to cover long ranges, then the missile can engage targets at extended distances, but fuel consumption increases significantly limiting the range
Solution Approach 1:
The patent implements dynamic flight path optimization by continuously calculating and adjusting the missile's trajectory using Model Predictive Control. The system dynamically varies flight parameters including altitude, speed, and course adjustments based on real-time conditions to minimize fuel consumption while maintaining supersonic performance over long ranges
Solution Approach 2:
The patent changes physical parameters of flight by ascending to high altitudes (above 15-20 km) where air density is lower, reducing aerodynamic drag and fuel consumption. The system also varies speed parameters and thrust control to optimize the balance between maintaining supersonic speed and conserving fuel for extended range
2Length of moving object
If the missile ascends to high altitudes (20 km) to reduce fuel consumption and extend range, then the range can be increased by up to a factor of 10, but the air becomes too thin causing the engine to stall due to insufficient dynamic pressure
Solution Approach 1:
The patent employs dynamic altitude control where the missile adjusts its flight altitude in real-time based on engine performance parameters and atmospheric conditions. The system maintains altitude within an optimal range (above 15-20 km for fuel efficiency) while ensuring minimum dynamic pressure is maintained for engine operation, preventing stall conditions
Solution Approach 2:
The patent implements feedback control by continuously monitoring engine parameters (dynamic pressure, thrust, altitude) and adjusting the flight path accordingly. The Model Predictive Control system uses this feedback to modify future trajectory predictions, ensuring the missile maintains sufficient dynamic pressure for engine operation while optimizing for fuel-efficient high-altitude flight
3Reliability
If evasive maneuvers are performed at supersonic speeds to avoid intercepting missiles, then the missile's ability to avoid detection and interception is significantly enhanced, but fuel consumption increases many times compared to subsonic maneuvers
Solution Approach 1:
The patent performs preliminary optimization of the flight path using Model Predictive Control to anticipate and plan for evasive maneuvers. The system calculates optimal trajectory adjustments in advance, preparing the missile with sufficient fuel reserves and optimized flight parameters to execute evasive maneuvers at supersonic speeds when necessary, rather than making unplanned high-cost maneuvers
Solution Approach 2:
The patent changes flight parameters (altitude, speed, thrust) to optimize for both range and evasive capability. By maintaining higher altitudes and optimizing speed profiles, the system reduces the fuel cost of evasive maneuvers while preserving supersonic performance, allowing effective evasion with reduced fuel consumption compared to low-altitude subsonic flight
Data Source
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AI summary
The invention relates to a method for midcourse guidance of a missile (2) which is driven by a thrust-controlled engine (4) for engaging a target (14). To achieve fuel-efficient guidance of a missile (2) to the target (14), it is proposed that in a planning cycle a) a prediction of a possible trajectory (18) of the missile (2) is created using a predictor (48) and the trajectory (18) is evaluated (62), b) further predictions of possible trajectories (18) of the missile (2) to the target (14) are calculated by multiple variations (68) of control variables of the missile (2), with the trajectories (18) being evaluated each time (62), and c) based on the evaluations, one of the trajectories (18) of the missile (2) is selected, and a first segment (22) of this trajectory (18) is flown and the planning cycle is repeated multiple times for subsequent segments (22).