Powder Monopropellant Rocket Motor for Continuous Thrust Control
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Solution Overview
Problem
Existing liquid and solid propellant rocket motors face challenges such as heavy and complex tank designs, cryogenic storage requirements, safety and logistical complications, and limited throttle-ability, leading to inefficient production and launch processes.
Innovation Solution
A rocket motor powered by a powder monopropellant composed of micro or nano-sized particles, utilizing a separate container and a unitary feeder-combustor for combustion, which simplifies the process and allows for continuous thrust control and efficient energy generation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If liquid propellant rocket motors use separate fuel and oxidizer tanks with pumps, then propulsion function is achieved, but device complexity and weight increase
Solution Approach 1:
The patent combines fuel and oxidizer into a single liquid monopropellant composition that contains both components in the same tank, eliminating the need for separate fuel and oxidizer tanks and their associated pumps. This merging of components directly reduces device complexity while maintaining propulsion function.
Solution Approach 2:
The liquid monopropellant serves multiple functions: it acts as both fuel and oxidizer, eliminates the need for separate storage systems, and provides continuous thrust control capability. This multi-functionality resolves the contradiction by achieving propulsion power without the complexity of dual-tank systems.
2Quantity of substance
If cryogenic temperatures are used to store liquid fuel and oxidizer, then volumetric efficiency improves, but weight and thermal insulation requirements increase
Solution Approach 1:
The patent changes the temperature parameter from cryogenic to ambient storage conditions by using a stable liquid monopropellant composition. This parameter change eliminates the need for heavy thermal insulation and cryogenic tank design, reducing tank weight while maintaining volumetric efficiency through the liquid state of the propellant.
3Device complexity
If solid composite propellant is used, then device complexity is reduced, but continuous throttle-ability is lost
Solution Approach 1:
The patent employs a liquid monopropellant system that allows dynamic control of thrust through variable flow rates to the combustion chamber. This dynamic capability enables continuous throttle-ability unlike solid propellants, while the single-component liquid system maintains simpler device complexity compared to dual-tank liquid systems.
4Reliability
If extensive quality assurance testing is performed on solid propellant, then reliability improves, but production time and cost increase
Solution Approach 1:
The patent uses commercially available liquid chemicals as monopropellant components that can be purchased ready-to-use without extensive manufacturing and testing processes. This approach eliminates the need for time-intensive solid propellant mixing, casting, and curing procedures while maintaining reliability through the use of stable, well-characterized chemical components.
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 powder monopropellant system reduces weight and complexity, enables stable storage at room temperature, eliminates the need for cryogenic tanks, and allows for continuous thrust control and efficient energy use, improving volumetric efficiency and reducing launch vehicle drag.
Implementation Method 1
combustion takes place in a powder-fed feeder-combustor which is separate from the container that houses the powder monopropellant
Implementation Method 2
The combustion results in hot exhaust emitted at high pressure, which propels the rocket
Data Source
AI summary
A system for generating hot, high-pressure exhaust gas for thrust includes an energetic powder monopropellant, wherein each particle of powder is comprised of a combination of oxidizer and fuel in a ratio suitable for combustion; and a rocket motor for combusting the monopropellant, said rocket motor comprising a container for storing the monopropellant, and a unitary feeder-combustor, wherein the unitary feeder-combustor is configured to feed the powder monopropellant from the container and to combust the powder monopropellant therein without consumption of air, thereby generating hot, high-pressure exhaust gas, generating thrust.