Convertible Nozzle for Airbreathing Rocket Engine Integration
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Solution Overview
Problem
Traditional vertical takeoff vehicles for space travel face challenges with component stress, safety, reliability, and the expense and disposal difficulties of booster rockets, limiting reusability and efficiency.
Innovation Solution
A single-stage-to-orbit engine system with a convertible nozzle and ejector duct assembly that transitions between airbreathing and non-airbreathing operations, using a gas-turbine engine and rocket engine combination, allowing for horizontal takeoffs and landings without jettisoning components, and utilizing the same fuels for both modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If vertical takeoff is used to overcome vehicle inertia, then sufficient thrust is achieved, but tremendous stress is generated on components
Solution Approach 1:
The nozzle segment subassembly is made movable between open and closed positions to dynamically adapt the engine configuration. During airbreathing mode, the nozzle is in the open position to reduce stress on components by allowing exhaust gases to expand naturally, while during non-airbreathing mode, it closes to redirect thrust efficiently
Solution Approach 2:
The engine system changes operational parameters by switching between airbreathing and non-airbreathing modes. This allows the same engine to operate under different thrust and stress conditions, optimizing performance while minimizing component stress during various flight phases
2Speed
If booster rockets are used for space travel, then orbital insertion is achieved, but retrieval and disposal becomes difficult and expensive
Solution Approach 1:
The patent merges the airbreathing engine and rocket engine into a single integrated propulsion system. The nozzle segment subassembly serves dual functions by being reconfigurable, eliminating the need for separate disposable booster rockets and simplifying retrieval and disposal processes
Solution Approach 2:
The engine system achieves multi-functionality by combining airbreathing and non-airbreathing capabilities in one propulsion unit. The movable nozzle segment allows the same engine to perform both atmospheric flight and space propulsion, replacing multiple specialized components with a single universal system
3Adaptability or versatility
If the nozzle segment subassembly is movable between positions, then engine transition between modes is enabled, but device complexity increases
Solution Approach 1:
The nozzle is divided into segments that can move independently between open and closed positions. This segmentation allows for controlled transition between airbreathing and non-airbreathing modes while maintaining structural integrity and managing the complexity through modular design
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 solution reduces component stress, enhances safety and reliability, enables reusable systems, eliminates the need for booster rocket disposal, and optimizes fuel usage by allowing horizontal operations and efficient orbital travel without jettisoning components.
Implementation Method 1
a gas-turbine engine having a tailcone portion and a bypass duct
Implementation Method 2
a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine
Data Source
AI summary
An engine assembly includes a gas-turbine engine having a tailcone portion and a bypass duct, a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine, and a movable nozzle segment subassembly that is selectively engageable with the gas-turbine engine bypass duct in an open position and with the rocket engine combustion assembly in a closed position.