Dual-Heater Propellant Pressurization for Rocket Engines
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Solution Overview
Problem
Conventional pressurization devices for rocket propellant tanks cannot maintain sufficient pressure during ballistic stages, as they rely on engine combustion heat, which is not available during inactive stages, leading to complex heat exchanger structures and inefficient pressure management.
Innovation Solution
A dual-heater system where a primary heater uses engine combustion heat to vaporize propellant during propulsion stages, and a secondary heater, independent of engine operation, maintains pressure during ballistic stages using an electric heater with a simple and lightweight design.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a heat exchanger uses the heat of combustion from the engine to heat and vaporize propellant, then the desired temperature and pressure can be obtained during propulsion stages, but the structure becomes complex with a multiplicity of heat exchange surfaces
Solution Approach 1:
The heat exchange function is divided into two separate heaters: a primary heater that uses engine combustion heat during propulsion stages, and a secondary heater that operates independently during ballistic stages. This segmentation allows each heater to be simpler in structure while maintaining the required temperature control functionality across different operational phases.
Solution Approach 2:
The system dynamically switches between the primary heater (engine-dependent) and secondary heater (independent) based on the operational stage. During propulsion stages, the primary heater is activated; during ballistic stages, the secondary heater takes over. This dynamic operation allows the use of simpler heat exchange surfaces optimized for specific conditions rather than requiring a complex system that handles all conditions simultaneously.
2Stress or pressure
If pressurization devices rely on engine combustion heat, then efficient pressurization is achieved during propulsion stages, but pressure cannot be maintained during ballistic stages when the engine is inactive
Solution Approach 1:
The pressurization system is designed with dual functionality: the primary heater provides efficient pressurization using engine combustion heat during propulsion stages, while the secondary heater provides independent pressurization capability during ballistic stages. This multi-functionality ensures the system can maintain propellant tank pressure across all operational phases, adapting to different engine states without requiring separate systems.
Solution Approach 2:
The secondary heater acts as an intermediary pressurization device that bridges the gap during ballistic stages when the primary heater cannot operate. It provides the necessary heat input to maintain propellant pressure and temperature, ensuring the system can transition smoothly between propulsion and ballistic stages without pressure loss.
3Use of energy by moving object
If heat exchangers are designed to optimize heat recovery from engine combustion, then energy efficiency is improved, but the devices become heavier and more complex
Solution Approach 1:
The heat recovery function is segmented into two distinct heating systems with different weight characteristics. The primary heater is optimized for high heat recovery efficiency during propulsion stages when engine combustion is available, while the secondary heater is designed with lower weight for operation during ballistic stages. This segmentation allows each component to be optimized for its specific operational context rather than requiring a single heavy system to handle all scenarios.
Solution Approach 2:
The system changes operational parameters by switching between two different heating modes. During propulsion stages, the primary heater operates at high heat recovery efficiency with higher weight utilization. During ballistic stages, the system transitions to the secondary heater with different thermal parameters and lower weight characteristics. This parameter change allows the system to optimize the weight-efficiency trade-off dynamically based on operational requirements.
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 dual-heater system ensures consistent propellant tank pressure across all stages, allowing for quick engine restarts and efficient thrust management, with reduced complexity and weight, while the secondary heater maintains pressure during inactive engine periods.
Implementation Method 1
the primary heater uses the heat of combustion from the engine
Implementation Method 2
heating and vaporizing to the desired pressure
Implementation Method 3
a secondary heater having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater in order to heat the propellant
Data Source
AI summary
The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.