Rocket Motor Void Propellant for Bomb Deployment
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Solution Overview
Problem
Bombs deployed from air vehicles at medium altitudes often lack sufficient speed to effectively penetrate targets due to insufficient time to transition from launch to dive orientation and accelerate, existing solutions like rocket motors being complex and costly.
Innovation Solution
A rocket motor with propellant that has an initial burning surface and a downstream void, exposing increased surface area as the propellant burns, providing a two-stage thrust profile for efficient bomb deployment, maintaining velocity and accelerating towards the target.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a rocket motor with constant thrust is used to increase launch speed, then the bomb can turn faster to reach dive orientation, but at medium altitudes the bomb still travels too slowly to provide sufficient penetration
Solution Approach 1:
The propellant structure is designed with a void space that causes the burning surface area to change dynamically during combustion. Initially, the burning surface is limited providing lower thrust for orientation change. As the propellant burns and exposes the void, the burning surface area increases significantly, providing higher thrust for target penetration. This dynamic thrust adjustment resolves the contradiction by adapting the thrust profile to the different phases of bomb flight without increasing device complexity.
2Speed
If a rocket motor provides constant high thrust throughout flight, then the bomb accelerates quickly towards the target, but the bomb cannot maintain proper velocity during the orientation change phase
Solution Approach 1:
The propellant combustion process is divided into two distinct periods through the void structure. In the first period, the burning surface is constrained providing lower thrust suitable for maintaining velocity during orientation change. In the second period, after the void is exposed, the burning surface area increases providing high thrust for acceleration towards the target. This periodic variation in thrust matches the different operational requirements of each flight phase.
3Force
If the propellant burning surface area is increased to provide higher thrust, then the bomb accelerates faster towards the target, but the bomb cannot effectively turn into dive orientation at medium altitudes
Solution Approach 1:
The propellant structure is segmented into different burning surface zones separated by a void space. The initial burning surface is designed to be relatively small to provide moderate thrust that allows sufficient time for orientation change. As combustion progresses and the void is exposed, a second larger burning surface is activated to provide high thrust for target acceleration. This segmentation of the burning surface resolves the contradiction by providing appropriate thrust levels at different times.
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 rocket motor imparts a low initial thrust for orientation change and a high thrust for target penetration, enhancing bomb speed and accuracy without increasing complexity or cost, suitable for medium altitude deployments.
Implementation Method 1
the propellant is burned, the void will be exposed, thereby increasing the surface area of the burning surface of the propellant to provide an increased thrust of the rocket motor
Data Source
AI summary
A bomb for deployment from an air vehicle includes a rocket motor for propelling the bomb. The rocket motor includes propellant which at least partially defines a void downstream of an initial burning surface. As the propellant is burned the void will be exposed, increasing the surface area of the burning surface of the propellant to increase the thrust of the rocket motor.