Guided Missile Steering via Transverse Thrust at High Altitude
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current guided missiles face limitations in range and effectiveness at higher altitudes due to decreasing air density, which reduces their ability to generate the required lateral acceleration for steering, limiting their operational range to altitudes below 30 km.
Innovation Solution
A guided missile design incorporating a double impulse engine as the first drive and a transverse thrust unit with Cartesian nozzles as the second drive, allowing for steering through a combination of longitudinal and transverse thrusts, enabling the missile to maintain agility and accuracy even at high altitudes by aligning the longitudinal axis with the velocity vector and generating necessary transverse acceleration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If aerodynamic control surfaces are used to steer the missile, then the missile can be controlled at lower altitudes, but the effectiveness decreases at higher altitudes due to decreasing air density
Solution Approach 1:
The patent introduces transverse thrust nozzles as an intermediary mechanism to supplement aerodynamic control surfaces. These nozzles provide direct thrust-based steering assistance when aerodynamic effectiveness is insufficient at high altitudes, bridging the control gap between low-altitude aerodynamic control and high-altitude operation requirements
Solution Approach 2:
The system dynamically changes the operational parameters of the control system by switching between aerodynamic control surfaces and transverse thrust nozzles based on altitude and air density conditions. At high altitudes where air density is low, the transverse thrust nozzles are activated to provide the necessary steering force that aerodynamic surfaces cannot generate alone
2Adaptability or versatility
If the missile is designed for high-altitude operation, then the operational range is extended, but the complexity of the drive and control system increases
Solution Approach 1:
The first drive unit is designed with multi-functionality, serving both as a longitudinal propulsion system and, when equipped with transverse thrust nozzles, as a steering system. This dual functionality eliminates the need for separate aerodynamic control surfaces in some configurations, reducing overall system complexity while maintaining high-altitude operational capability
Solution Approach 2:
The patent merges the propulsion and steering functions into a single integrated drive system. The transverse thrust nozzles are integrated with the longitudinal propulsion system, allowing both functions to be achieved through one unified drive unit rather than requiring separate systems for propulsion and control
3Adaptability or versatility
If transverse thrust nozzles are added to supplement aerodynamic control, then high-altitude steering is improved, but the manufacturing cost increases
Solution Approach 1:
Rather than equipping the missile with full aerodynamic control surfaces and separate steering systems, the patent applies transverse thrust nozzles selectively - only to the extent necessary to provide sufficient steering capability at high altitudes. This partial application approach achieves the required high-altitude performance while minimizing the additional manufacturing cost compared to a complete dual-system design
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 solution extends the operational range of guided missiles by ensuring they can be steered and accurately hit targets at higher altitudes, achieving direct hits against fast and maneuvering targets through improved dynamics and control, even when aerodynamic effectiveness is negligible.
Implementation Method 1
A first thrust along the longitudinal axis can be generated by the first drive
Implementation Method 2
a second thrust perpendicular to the longitudinal axis can be generated by the second drive
Implementation Method 3
the required lateral acceleration with aerodynamic lift guarantee
Data Source
Figure 1~2
Figure 3~4
AI summary
The invention relates to a guided missile (1) having a longitudinal axis (2) and comprising at least a first drive (3) with which a first thrust (100) can be generated along the longitudinal axis (2), and a second drive (4) with which a second thrust (200) can be generated perpendicular to the longitudinal axis (2), wherein the guided missile (1) is configured to control the second drive (4) activated by the first drive (3) in such a way that the guided missile (1) is steerable.