Selectable Force Gas Generator for Dynamic Ejection
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Solution Overview
Problem
Conventional bomb rack systems have a preset ejection force that is inflexible and can result in insufficient separation or tumbling of weapons due to rapid changes in flight conditions, and they are costly, heavy, and prone to maintenance issues.
Innovation Solution
A selectable force gas generator (SFGG) with gas-generating propellant cells embedded in a honeycomb structure, allowing for dynamic adjustment of ejection force based on flight parameters through an electrical initiator and signal switching matrix, preventing sympathetic detonation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a preset ejection force is used in conventional bomb rack systems, then the system is simple and inexpensive, but the ejection force cannot adapt to rapid changes in flight conditions causing insufficient separation or tumbling
Solution Approach 1:
The patent applies the dynamics principle by making the ejection force adjustable rather than fixed. The gas generator system allows dynamic selection of ejection force levels based on real-time flight conditions, transforming a static system into a dynamic one that can adapt to changing operational requirements.
Solution Approach 2:
The patent implements parameter changes by varying the ejection force parameter according to flight conditions. The system can select different ejection force levels (e.g., 1,000 lbs, 2,000 lbs, 3,000 lbs) based on aircraft acceleration, pitch rate, and other flight parameters, allowing optimal performance across different operational envelopes.
2Reliability
If conventional bomb rack systems are used, then the equipment is reusable and structurally sound, but the systems are costly, heavy, and require regular inspections and maintenance
Solution Approach 1:
The patent applies the disposable principle by using a single-use gas generator system that is discarded after one use, eliminating the need for reusable mechanical structures. This approach trades the reliability of reusable systems against the simplicity and weight savings of single-use systems, as the gas generator contains all necessary components in a lightweight configuration.
Solution Approach 2:
The patent replaces heavy mechanical ejection systems with a chemical gas generation system. Instead of using complex mechanical springs, pistons, and linkages, the system uses a gas generator that produces gas to drive a simple piston, significantly reducing weight while maintaining reliability.
3Strength
If conventional bomb rack systems are used, then the structure is robust and reusable, but they are subject to fatigue, material corrosion, and other long term effects
Solution Approach 1:
The patent eliminates concerns about fatigue and corrosion by using a disposable gas generator system. The single-use design means the system is not subjected to repeated stress cycles or environmental degradation, thereby avoiding the long-term durability issues affecting reusable conventional systems.
Solution Approach 2:
The patent applies the discarding principle by designing the gas generator to be discarded after single use. This eliminates the need for maintenance and recovery of reusable components, as the entire system is disposed of after one operation, avoiding issues related to service life and durability.
4Adaptability or versatility
If a single gas-generating propellant cell is used, then the system is simple, but it cannot provide selectable ejection forces for different flight conditions
Solution Approach 1:
The patent applies segmentation by dividing the gas generation system into multiple independent propellant cells (e.g., five cells arranged in a pattern). Each cell can be independently activated, allowing the system to select different combinations of cells to achieve various ejection force levels while maintaining a manageable structural configuration.
Solution Approach 2:
The patent implements partial action by activating only the necessary number of propellant cells to achieve the required ejection force. The system can fire one cell for low force, two cells for medium force, and so on, up to five cells for maximum force, providing selective ejection capability without requiring all cells to be present in the final assembly.
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
Enables effective and reliable ejection of airborne stores by dynamically adjusting the ejection force to match changing flight conditions, reducing the risk of tumbling and extending the operational envelope of the delivering aircraft while being lighter and more maintainable.
Implementation Method 1
The fire wire transmits a firing signal that causes the propellant packet to produce gas
Implementation Method 2
The cap has a tip that blocks the orifice of the jacket and the thickness of the jacket is sufficient to withstand rom increased outer pressure in the gas collection chamber to prevent sympathetic detonation of the propellant packet
Data Source
AI summary
A selectable force gas generator (SFGG) includes support material of honeycomb structure and a gas collection chamber contained in a housing. Gas-generating propellant cells are partially embedded in the support material. Each of the gas-generating propellant cells includes a steel jacket having a convex portion exposed to the gas collection chamber. The steel jacket has an orifice through the convex portion. Each propellant cell includes a propellant packet contained in the jacket. Each propellant cell includes a fire wire electrically connectable to an electrically-fired initiator and electrically connected to the propellant packet. The fire wire transmits a firing signal that causes the propellant packet to produce gas. A cap is positioned between the propellant packet and the jacket. The cap has a tip that blocks the orifice of the jacket and the thickness of the jacket is sufficient to prevent sympathetic detonation of the propellant packet.