Steerable Rotating Projectile With In-Flight Mass Redistribution
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Solution Overview
Problem
Existing systems for controlling the flight path and steering of rotating projectiles, such as Frisbees and aerobies, face challenges in efficiently altering the pitch moment and aerodynamics due to gyroscopic stabilization, making it difficult to achieve stable and maneuverable flight paths.
Innovation Solution
The system employs a mechanism to vary the moment of inertia and control aerodynamics during flight by altering the mass distribution or using fluidic mass to adjust the pitch moment, combined with power management for sustained control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If gyroscopic stabilization is used to maintain stable flight, then flight stability is improved, but maneuverability and the ability to alter pitch moment deteriorate
Solution Approach 1:
The patent employs movable masses that can be dynamically repositioned within the projectile during flight. These masses are mounted on movable platforms or carriages that can shift position along the rotation axis or radially, allowing real-time adjustment of the center of gravity and moment of inertia. This dynamic reconfiguration enables the projectile to alter its pitch moment and aerodynamic characteristics mid-flight, achieving maneuverability while maintaining gyroscopic stabilization through controlled mass redistribution
Solution Approach 2:
The patent changes key physical parameters of the rotating projectile during flight by moving masses to different positions. By altering the radial position or axial location of movable masses, the system modifies the moment of inertia and center of gravity position. These parameter changes allow the projectile to adjust its pitch moment and aerodynamic behavior, enabling course correction and maneuvering without compromising the stabilizing gyroscopic effects
2Ease of operation
If mass distribution is altered to control pitch moment, then aerodynamic control is improved, but device complexity increases
Solution Approach 1:
The patent divides the projectile into distinct functional segments: a stationary housing and movable mass carriers mounted on separate platforms. These segmented components can independently move relative to each other along predefined tracks or guides, allowing pitch moment control through relative positioning. The segmentation enables simplified control mechanisms compared to moving entire mass assemblies, reducing overall system complexity while maintaining aerodynamic control capability
Solution Approach 2:
The patent introduces movable platforms or carriages as intermediary elements between the fixed projectile structure and the controllable masses. These intermediaries provide guided motion paths and simplify the mechanical connection requirements, allowing masses to be repositioned with reduced complexity. The intermediary platforms act as mediators that translate control inputs into precise mass positioning for pitch moment adjustment
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 approach allows for more stable and maneuverable flight paths by mitigating gyroscopic effects, enabling precise control over the projectile's trajectory.
Implementation Method 1
gyroscopic stabilization
Implementation Method 2
rotating projectile
Implementation Method 3
aerodynamics
Implementation Method 4
drag on the exterior surface(s)
Implementation Method 5
vary the moment of inertia
Implementation Method 6
displace a set of balanced masses or fluidic mass to a different radial position, thereby changing a center of gravity position
Implementation Method 7
gravitational force
Data Source
AI summary
A method of controlling a gyroscopically-stabilized projectile, comprising a control system producing a control signal, a rotating aerodynamic shell, and a reaction mass system responsive to the control signal, the method comprising: imparting rotational and translational kinetic energy to induce gyroscopic stabilization of the projectile about a gyroscopic axis and a movement of the projectile along a flight path; interacting the shell with surrounding air while moving, to induce aerodynamic forces; generating the control signal from the control system; and altering a state of the reaction wheel system selectively in dependence on the control signal, to alter the flight path.