Compression Spring Cam Wing Deploy Initiator

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Solution Overview

Problem

Existing mechanical wing deploy initiators for missiles and rockets are bulky and complex, leading to increased production costs and a higher likelihood of failure due to the need for numerous components and insufficient deployment force to break through frangible wing covers.

Innovation Solution

A mechanical compression spring wing deploy initiator that uses a cam driven by linear compression springs to exert a higher deployment force with fewer parts, reducing bulkiness and complexity, and providing sufficient energy to break through frangible covers.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Force

If a torsion spring mechanism with multiple parts is used to assist wing deployment, then the deployment force is sufficient to break through frangible covers, but the device becomes bulky and complex with increased production cost and likelihood of failure

Engineering Contradiction:

Improvedeployment forceVSAvoidnumber of parts

Core Design Contradiction:

ForceVSDevice complexity

Solution Approach 1:

The patent combines multiple separate torsion spring mechanisms into a single integrated compression spring assembly. The cam mechanism integrates the function of multiple levers and springs into one coordinated system, reducing the total part count from 65 components to a significantly smaller number while maintaining sufficient deployment force to break through frangible covers.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The compression spring assembly serves multiple functions simultaneously: it stores deployment energy, provides the forcing mechanism to break frangible covers, and integrates the cam mechanism to coordinate wing deployment. This multi-functionality eliminates the need for separate dedicated springs and lever arms for each wing, reducing overall device complexity.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Force

If explosives are used to push wings through frangible covers, then deployment force is sufficient, but safety concerns and chemical stability issues arise during storage

Engineering Contradiction:

Improvedeployment forceVSAvoidsafety and chemical stability

Core Design Contradiction:

ForceVSObject-affected harmful factors

Solution Approach 1:

The patent replaces the chemical explosive system with a mechanical compression spring system. The compression springs store mechanical energy that is released to provide the necessary deployment force, eliminating all safety and chemical stability concerns associated with explosives while maintaining sufficient force to break through frangible covers.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Device complexity

If centrifugal force from spinning is used to deploy wings, then no additional mechanism is needed, but the force is insufficient to penetrate frangible slot covers

Engineering Contradiction:

Improvedeployment mechanismVSAvoidcentrifugal force

Core Design Contradiction:

Device complexityVSForce

Solution Approach 1:

The compression springs are pre-compressed during weapon assembly to store deployment energy before launch. This preliminary action ensures that when the wings need to deploy, sufficient force is already available to break through the frangible covers, rather than relying solely on the centrifugal force generated during spinning which occurs after launch.

Inventive Principle:

Principle #10Preliminary action

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 achieves enhanced wing deploy performance with reduced complexity and cost, exerting 10 lb of push force on each wing after 0.3 inches of travel, compared to the torsion spring design's 6-7 lb, and effectively breaking through frangible covers without the use of explosives.

Implementation Method 1

uses one or more compression springs to drive a cam between the stowed guidance wings, thereby forcing the guidance wings outward through the frangible covers

Methodology Applied

Scientific EffectCompression spring: Spring

Implementation Method 2

The invention uses one or more compression springs to drive a cam between the stowed guidance wings, thereby forcing the guidance wings outward

Methodology Applied

Scientific EffectCam mechanism: Cam

Implementation Method 3

The deployment force is delivered at or near the ends of the guidance wings, thereby providing greater leverage than the co-pending torsion spring design

Methodology Applied

Scientific EffectMechanical advantage: Mechanical Advantage

Implementation Method 4

forcing the guidance wings outward through the frangible covers of the wing deployment slots

Methodology Applied

Scientific EffectFracture mechanics: Fracture Mechanics

Data Source

PatentUS8754352B2Compression spring wing deployment initiator

Publication Date: 2014.06.17 BAE SYSTEMS INFORMATION ANDELECTRONIC SYSTEMS INTEGRATION INC

AI summary

A wing deploy initiator for deploying guidance wings of a rocket or missile, such as the APKWS, provides enhanced wing deploy performance with reduced complexity, cost, and likelihood of failure. The invention includes a cam which is driven between the stowed guidance wings by at least one compression spring, thereby forcing the guidance wings outward through slots in the fuselage of the rocket or missile. Oblique flat sides of the cam can push against beveled edges on the wings. The cam can be attached to spring mandrels, and the cam and mandrels can pass through a retaining plate as the springs decompress. Embodiments can exert sufficient push force to enable the wings to break through frangible slot covers. An embodiment applicable to the APKWS includes only 13 parts, and can exert up to 10 lb push force on each wing after 0.3 inches of wing travel.