Deployable Tail Flap for High-G Projectile Terminal Maneuvers
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Solution Overview
Problem
Existing systems for achieving high-G maneuvers in projectiles, particularly spin-stabilized supersonic projectiles, are impractical, ineffective, and unreliable, especially for small projectiles, as they struggle with gas containment and mass ejection mechanisms, and fail to maintain maneuvering capability at long ranges or against rapidly maneuvering targets.
Innovation Solution
A deployable flap mechanism on the projectile's tail, activated by a pyrotechnic event, allows for altering the flight path to intercept moving targets, featuring a steering assembly with a flap that extends radially and angularly to provide increased aerodynamic lift for precise terminal maneuvers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed flap is used for steering, then the structure is simple and reliable, but the maneuverability and G-force generation are insufficient for engaging maneuvering targets at long ranges
Solution Approach 1:
The flap is designed to be deployable rather than fixed, allowing it to transition from a stowed position during cruise to an extended position during terminal maneuvers. This dynamic configuration enables the projectile to achieve high G-forces (potentially exceeding 10G) when needed while maintaining a simple fixed-flap structure during normal flight, thus resolving the contradiction between maneuverability and structural simplicity.
Solution Approach 2:
The steering assembly is segmented into multiple components: a fixed flap portion and a deployable flap portion that can be independently controlled. This segmentation allows the system to use only the necessary components for each phase of flight, providing adaptability for different maneuvering requirements while keeping the overall structure manageable through modular design.
2Reliability
If existing high-G maneuver systems are used, then some maneuver capability is achieved, but they are impractical, ineffective, and unreliable for spin-stabilized supersonic projectiles
Solution Approach 1:
The patent replaces complex mechanical maneuvering systems with a simpler deployable flap mechanism that relies on aerodynamic forces rather than complex mechanical actuators. The flap deployment is controlled by a release mechanism that can be triggered by various means (electronic, pyrotechnic, mechanical), eliminating the need for complex continuous mechanical actuation systems and improving reliability in spin-stabilized supersonic projectiles.
3Force
If the flap is extended to increase maneuverability, then G-force generation improves, but drag increases and flight stability may be compromised
Solution Approach 1:
The deployable flap remains retracted during cruise flight to minimize drag and maintain flight stability, then extends only during terminal maneuvers when high G-forces are needed. This dynamic deployment strategy ensures that the harmful effect of drag is minimized while still achieving the desired force generation when required, resolving the contradiction between force generation and drag reduction.
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 deployable flap mechanism enables projectiles to achieve abrupt trajectory changes, increasing G-forces for accurate targeting, even at long ranges or against evasive targets, by deploying a flap that provides enhanced aerodynamic lift and maneuverability.
Implementation Method 1
In some embodiments, the predetermined event is a pyrotechnic event. In some embodiments, the pyrotechnic event is activation of a pyrotechnic charge.
Implementation Method 2
a flap movable from a first position in which the flap does not extend radially beyond the body to a second position in which the flap extends radially beyond the body and at an angle relative to the longitudinal axis
Data Source
AI summary
A tail for a projectile includes a body having a longitudinal axis. A steering assembly is secured to the body. The steering assembly includes a flap movable from a first position in which the flap does not extend radially beyond the body to a second position in which the flap extends radially beyond the body and at an angle relative to the longitudinal axis, and a flap release mechanism. A projectile including a tail according to the present disclosure is also provided.