Solid Propellant Divert System with Extinguishable Hot Gas Generator
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Solution Overview
Problem
Conventional divert and attitude control systems for flight vehicles, such as those used in missile defense systems, face limitations in operating time, energy management, mass, and divert distance, necessitating the development of a more efficient and capable system for on-demand, multi-pulse operations.
Innovation Solution
A divert and attitude control system (DACS) utilizing solid propellant that can be repeatedly extinguished and reignited, with the propellant being ignited by hot gas from the attitude control system, allowing for extended operation and reduced mass, and featuring a pneumatically linked attitude control system and divert system for continuous thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of moving object
If conventional divert and attitude control systems are used, then the system structure is simple, but the operating time is limited
Solution Approach 1:
The solid propellant is repeatedly ignited and extinguished in periodic cycles, with each cycle consisting of an ignition phase that generates hot gas and an extinction phase that allows propellant cooling. This periodic operation enables extended total operating time while using a single propellant charge, avoiding the need for continuous ignition systems.
Solution Approach 2:
The system maintains continuous readiness for ignition by keeping the propellant in a reusable state. After extinction, the propellant is quickly reconditioned and ready for the next ignition cycle, ensuring continuous operational capability without interruption or need for replacement.
2Weight of moving object
If separate igniters are used in the divert system, then the ignition capability is reliable, but the mass increases
Solution Approach 1:
The attitude control system's hot gas generation capability is made multi-functional by using it to ignite the divert system's solid propellant. The same hot gas source serves both attitude control operations and divert operations, eliminating the need for separate igniters in the divert system.
Solution Approach 2:
The attitude control system serves the divert system by providing the ignition source using its own hot gas output. The divert system utilizes the attitude control system's resources (hot gas) for its ignition needs, creating a self-sufficient integrated operation that reduces overall system mass.
3Use of energy by moving object
If the solid propellant is continuously burning, then the thrust is continuous, but the energy consumption is high
Solution Approach 1:
The solid propellant operates in periodic cycles of ignition and extinction rather than continuous burning. During the extinction phase, energy consumption is minimized while the propellant cools and prepares for the next ignition. The periodic thrust pulses provide sufficient propulsion without the continuous energy drain of continuous combustion.
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 system provides continuous attitude and divert control for an extended period, enhancing the capabilities of flight vehicles by increasing operational time and reducing mass, while eliminating the need for separate igniters in the divert system.
Implementation Method 1
A divert and attitude control system (DACS) utilizing solid propellant that can be repeatedly extinguished and reignited, with the propellant being ignited by hot gas from the attitude control system
Implementation Method 2
the solid propellant is extinguished by rapid depressurization
Data Source
AI summary
Various implementations of an extinguishable, solid propellant divert system for a flight vehicle are disclosed. Also disclosed are methods for using the divert system to control the flight of a flight vehicle. In one implementation, a divert system includes a hot gas generator pneumatically linked to one or more divert thrusters and an extinguishment valve. The extinguishment valve can be opened to rapidly depressurize the hot gas generator and extinguish the solid propellant burning inside. In another implementation, a method of controlling the trajectory of the flight vehicle includes repeatedly igniting and extinguishing the solid propellant in a hot gas generator and using the hot gas to provide divert thrust for the flight vehicle.