Projectile Flare Assembly with Dynamic Petal Actuation
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Solution Overview
Problem
Existing projectile flares face stability issues due to changes in static margin caused by events like jettisoning, leading to unstable flight, as the center of lift may no longer be sufficient to ensure stable flight.
Innovation Solution
A manipulable flare assembly mounted to a load-bearing structure with an actuating mechanism that provides selective relative rotation, allowing the flare assembly to transition from a non-deployed to a deployed configuration, featuring active and passive petals that deflect radially to control the center of lift and maintain stability through a cam profile that optimizes actuation force distribution.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If the flare assembly is deployed to move the center of lift rearward, then the static margin is improved and flight stability is enhanced, but the aerodynamic forces and drag increase
Solution Approach 1:
The flare assembly is designed to be dynamically deployable, transitioning from a stowed position during launch to a deployed position during flight. This dynamic configuration allows the system to optimize stability only when needed, rather than maintaining constant aerodynamic forces throughout the flight trajectory.
Solution Approach 2:
The system changes the geometric parameter of the flare assembly deployment, which alters the center of lift position and static margin. By controlling the deployment parameter, the system adjusts the aerodynamic characteristics to match different flight phases, improving stability when required while minimizing drag during other phases.
2Stability of the object's composition
If the petals are deployed to project into the air stream, then the center of lift moves rearward, but the drag increases
Solution Approach 1:
The petal deployment is a dynamic process controlled by the slide ring mechanism. The petals transition from an aligned (low drag) position to a projected (high stability) position based on flight conditions, allowing the system to optimize the trade-off between drag and stability at different flight phases.
Solution Approach 2:
The slide ring is designed with sufficient inertia to shift aft automatically in response to acceleration events, such as separation of the attached body. This preliminary action triggers petal deployment before manual intervention is needed, ensuring stability is established proactively when flight conditions change.
3Stability of the object's composition
If the slide ring is allowed to move aft to deploy petals, then the center of lift moves rearward, but the structural complexity increases
Solution Approach 1:
The slide ring mechanism is designed to deploy the petals automatically using the inertia generated during acceleration events. The system serves itself by converting the kinetic energy of separation into the deployment action, eliminating the need for external actuators, motors, or complex control systems.
Solution Approach 2:
The complex active control system is extracted and replaced with a passive inertial mechanism. The slide ring and detent system represents a simplified actuating mechanism that relies on physical principles rather than active control, reducing overall system complexity while maintaining functionality.
4Loss of energy
If the petals are kept aligned with the air stream, then drag is minimized, but the center of lift cannot move rearward to improve stability
Solution Approach 1:
The petal alignment is dynamic rather than static. During launch and stable flight phases, petals remain aligned with the air stream to minimize drag. Upon detection of acceleration events or instability, the petals dynamically reposition to project into the air stream, moving the center of lift rearward to restore stability.
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 effectively controls the center of lift, maintaining stability and overcoming aerodynamic forces by optimizing the radial displacement of the flare assembly, ensuring stable flight even after events that alter the static margin.
Implementation Method 1
a cam arrangement comprising at least one cam, the or each cam comprising a cam profile configured for providing a radial displacement for the flare assembly with respect to a longitudinal axis thereof responsive to the drive force being applied to the flare assembly via the cam arrangement
Implementation Method 2
such as to maintain external reaction forces on the flare assembly, generated responsive to the radial displacement, at a magnitude less than the drive force
Data Source
AI summary
Apparatus and method are provided for controlling a vehicle in motion through a fluid medium. A manipulable flare assembly is mounted to a load bearing structure, the structure being configured for mounting to the vehicle. An actuating mechanism has a rotational member operably associated with the flare assembly, the actuating mechanism being configured for selectively providing relative rotation between the rotational member and the load bearing structure. The actuating mechanism is configured for manipulating the flare assembly responsive to selective relative rotation between the rotational member and the load bearing structure. A vehicle is also provided incorporating the apparatus.