Rocket Motor Thrust Adjustment Device for Dynamic Propulsion Control
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Solution Overview
Problem
Conventional rocket motors have a fixed propulsion capability, which limits their adaptability to changing field conditions, such as varying payload weights or required trajectories, in applications like the U.S. Army's anti-personnel obstacle breaching system, where dynamic thrust adjustment is necessary.
Innovation Solution
A rocket motor with a thrust adjustment device that can change the direction and pressure of the gas flow, allowing field operators to select different thrust modes by positioning a valve to divert gas through various paths, thereby adjusting the net forward thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a fixed propulsion capability is used in conventional rocket motors, then the structure is simple and reliable, but the adaptability to changing field conditions deteriorates
Solution Approach 1:
The patent applies the dynamics principle by making the thrust capability adjustable rather than fixed. The thrust adjustment device includes a valve that can be positioned in multiple positions to divert propellant gas flow, allowing the rocket motor to dynamically adapt its thrust output to different field conditions such as varying payload weights or required trajectories.
Solution Approach 2:
The patent implements universality by designing a single rocket motor that can perform multiple thrust levels and functions. The thrust adjustment device enables the same motor to accommodate different payload weights and trajectories, making one motor universally applicable to various tactical situations rather than requiring multiple specialized motors.
2Adaptability or versatility
If a thrust adjustment device is added to allow dynamic thrust modification, then the adaptability improves, but the device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the propellant gas flow into different paths using a valve mechanism. The valve can divert a portion of the propellant gas flow away from the primary nozzle, creating segmented flow paths that allow independent control of thrust magnitude without requiring multiple complete propulsion systems.
Solution Approach 2:
The patent uses an intermediary device (the valve and thrust adjustment mechanism) to mediate between the fixed propellant combustion and the variable thrust requirement. This intermediary component allows smooth transition between different thrust levels by controlling gas flow diversion, adding minimal complexity while enabling continuous thrust adjustment.
3Reliability
If the nozzles are positioned at the forward end for towing applications, then dynamic stability improves and payload damage is reduced, but the thrust adjustment mechanism becomes more complex
Solution Approach 1:
The patent applies local quality by positioning the nozzles at the forward end of the rocket motor specifically for towing applications. This localized configuration improvement enhances dynamic stability and protects the payload from hot exhaust gases without requiring changes to the entire motor structure, thereby minimizing the complexity added by the thrust adjustment device.
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 flexible operation by accommodating different payload weights and trajectories, increasing the utility of a single rocket motor in various tactical situations by allowing adjustable thrust, reducing collateral damage and improving operational flexibility.
Implementation Method 1
A propellant is provided in a rocket motor. The propellant is configured to generate gas upon ignition
Implementation Method 2
One or more nozzles are arranged to receive and direct the gas in a first direction
Implementation Method 3
A thrust adjustment device is arranged to receive a portion of the gas. The thrust adjustment device is configured to change the direction of flow of at least a portion of the gas
Implementation Method 4
The thrust adjustment device is configured to change a pressure of the gas within the housing during operation
Data Source
AI summary
A rocket having a motor with a user adjustable thrust is provided. The rocket includes a main cylinder containing a rocket propellant, the propellant configured to generate gas during operation and one or more nozzles arranged to direct the gas in a first direction. A thrust adjustment device is arranged to receive a portion of the gas, the thrust adjustment device configured to change the direction of flow of at least a portion of the gas.