Hybrid Rocket Motor Bulkhead Access Passageways
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Solution Overview
Problem
Current rocket propulsion systems, including solid and liquid systems, face challenges such as high manufacturing costs, safety risks, and the potential for catastrophic failures due to inadvertent ignition, while hybrid systems offer advantages like higher specific impulse and safety but require improved access and control mechanisms.
Innovation Solution
A hybrid propulsion system with a structural configuration that includes a hybrid rocket motor case and a fuel tank connected by a bulkhead with access passageways, allowing for easy access to the interior regions without disassembly, and utilizing liquid oxidizer for thrust and attitude control, including injection mechanisms and conduits for controlling thrust vectors and pressure oscillations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If solid propellant systems are used, then thrust is produced through combustion, but the system is subject to safety risks including inadvertent ignition by mechanical shock and static electricity
Solution Approach 1:
The propulsion system is divided into separate solid fuel and liquid oxidizer components that are physically isolated from each other during storage and handling. The solid fuel is contained in a fuel grain while the liquid oxidizer is stored separately, preventing inadvertent mixing and ignition. This segmentation eliminates the safety risks associated with solid propellant systems where fuel and oxidizer are pre-mixed in solid form.
2Reliability
If liquid propulsion systems are used, then thrust is produced through combustion, but high performance pressurization systems are required which increase cost and maintenance
Solution Approach 1:
The liquid oxidizer serves a dual function: it acts as both the propellant for combustion and as the pressurization medium for fuel delivery. The oxidizer is stored under its own vapor pressure, which automatically pressurizes the fuel lines and delivers fuel to the combustion chamber without requiring separate high-performance pressurization pumps or systems. This self-service approach eliminates complex pressurization equipment while maintaining reliable thrust production.
3Reliability
If liquid propulsion systems are used, then thrust is produced through combustion, but exotic materials must be used for components which increases monetary cost
Solution Approach 1:
The system operates at lower temperatures and pressures compared to traditional liquid propulsion systems. By changing the operating parameters and using a liquid oxidizer with favorable properties (such as nitrogen tetroxide or dinitrogen tetroxide), the invention enables the use of conventional, readily available materials for combustion chamber and nozzle construction rather than requiring expensive exotic materials like refractory metals or specialized ceramics. This parameter change significantly reduces manufacturing costs while maintaining reliable thrust production.
4Productivity
If hybrid propulsion systems are used, then specific impulse is improved, but access to interior regions of motor case and fuel tank is difficult
Solution Approach 1:
Access ports are nested within the bulkhead structure that separates the fuel tank and motor case. The bulkhead incorporates recessed access ports with removable covers or doors that provide entry to the interior regions while maintaining the structural integrity and separation of the fuel and oxidizer systems. This nested design allows maintenance and inspection personnel to access critical components without disassembling the entire propulsion system, preserving the high specific impulse performance while improving ease of operation.
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
This configuration enhances safety, reduces manufacturing costs, and improves performance by allowing easy access and control over the propulsion system, increasing specific impulse and reducing the risk of failure, while providing flexible and efficient operation.
Implementation Method 1
The oxidizer and liquid fuel are mixed in the combustion chamber, where they react to produce gases under high temperature and high pressure
Implementation Method 2
The gases exhaust through a nozzle from the combustion chamber to thereby produce thrust
Data Source
AI summary
Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank.