Steerable Missile Nose Tilted by Electromagnet and Gravity
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Solution Overview
Problem
Existing steerable missile systems face challenges in achieving precise control with limited space, high costs, and high energy consumption, particularly in small missile designs where complex mechanical components and actuators are not feasible.
Innovation Solution
The use of electromagnets as actuators, combined with elastic restoring elements and aerodynamic fin-like ribs, allows for cost-effective, low-energy, and compact control of the missile nose, enabling precise tilting and trajectory changes without the need for complex mechatronic systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If complex mechatronic steering machines and actuators are used to achieve precise missile control, then steering precision is improved, but device complexity and cost increase significantly
Solution Approach 1:
The patent replaces complex mechatronic actuators with a purely mechanical tilting mechanism. The missile nose is tilted by gravity acting on a movable mass, controlled by simple electromagnetic coils that generate Lorentz forces in a magnetic field. This substitution eliminates complex mechanical steering machines while achieving sufficient steering precision through aerodynamic forces generated by the tilted nose.
Solution Approach 2:
The patent changes the control parameter from direct mechanical actuation to electromagnetic field control. By applying voltage to electromagnetic coils, a magnetic field is generated that interacts with a movable mass to tilt the missile nose. This parameter change from mechanical to electromagnetic control simplifies the actuation system while maintaining steering capability.
2Measurement precision
If high-quality mechatronic actuators are used for nose tilting, then steering accuracy is improved, but energy consumption increases
Solution Approach 1:
The patent replaces energy-intensive mechatronic actuators with a passive gravitational tilting mechanism controlled by low-power electromagnetic coils. The movable mass tilts the nose under gravity when released, requiring minimal energy input from the coils, which only need to generate small Lorentz forces to initiate or reverse the tilting motion.
Solution Approach 2:
The patent employs periodic or pulsed electromagnetic activation to control the tilting mechanism. The coils are activated briefly to shift the movable mass and initiate nose tilting, then deactivated to allow gravity to complete the motion. This periodic action reduces average energy consumption compared to continuous actuation.
3Volume of moving object
If compact actuators are used to reduce installation volume, then space efficiency is improved, but actuating speed may be compromised
Solution Approach 1:
The patent replaces compact but slow mechatronic actuators with a gravitational mechanism that leverages the full force of gravity for rapid nose tilting. The movable mass, when released, tilts the nose quickly under gravitational acceleration, achieving high actuating speed without requiring large-volume high-power motors.
Solution Approach 2:
The patent positions the movable mass in advance at a location where its gravitational force will produce the desired nose tilting direction. When voltage is applied to the coils, the pre-positioned mass immediately exerts gravitational force to tilt the nose, reducing the time required for actuation compared to systems that must first build up mechanical force.
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
This solution provides robust, temperature-independent, and long-term storage capabilities, achieving high actuating speed and precision in steering the missile with a simple design, reducing costs and space requirements while maintaining effective control over pitch and yaw axes.
Implementation Method 1
the actuator or actuators in the missile according to the invention are formed by simple electromagnets
Implementation Method 2
the provision of an electromagnet as an actuator makes it possible to achieve an effective inclination of the nose of the missile
Implementation Method 3
the electromagnet acts against the force of an associated elastic restoring element, preferably a restoring spring
Implementation Method 4
the missile nose is provided with longitudinally extending and radially extending fin-like ribs, the missile nose is given aerodynamic control surfaces which can increase tilting of the missile nose initiated by an electromagnet as an actuator by aerodynamic forces acting on the ribs
Data Source
Figure 1~5
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Figure 7
AI summary
The guidable missile has a tubular body (1) and a tilt-movable missile nose (2) attached at the body, where an actuator is formed by multiple electromagnets (30,34). The missile nose is provided with radially extending flow-like ribs running in longitudinal direction. The electromagnets are operated against a force of an arranged elastic resetting element (39,39'), particularly a reset spring.