Rotor-Assisted Launch Vehicle for Reusable Low-Noise Takeoff
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Solution Overview
Problem
Existing launch vehicles face challenges in achieving high reuse ratios due to the limitations of first propulsion stages, which typically burn out and cannot be reused, leading to inefficiencies in rocket fuel consumption and noise pollution during launch.
Innovation Solution
A launch vehicle design incorporating a rocket body with a main propulsion stage and a separate takeoff stage, equipped with electrically driven rotors that allow vertical takeoff and landing, reducing noise and fuel consumption, and enabling the stages to be reused through energy generation during descent using autorotation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional rocket propulsion systems are used for launch, then the rocket can achieve orbital velocity, but the first propulsion stage burns up and cannot be reused
Solution Approach 1:
The launch vehicle is divided into multiple independent stages: a reusable first propulsion stage equipped with both rocket engines and rotor drives, and a second propulsion stage for orbital insertion. This segmentation allows the first stage to be recovered and reused while the second stage completes the mission
Solution Approach 2:
The first propulsion stage is designed to be recovered after use rather than discarded. It performs its launch function, then returns to a landing site where it can be refurbished and reused for subsequent launches, significantly reducing fuel consumption and waste
2Force
If conventional rocket engines are used during launch, then the rocket achieves required thrust, but significant noise pollution is generated near the ground
Solution Approach 1:
The first propulsion stage combines two different propulsion systems: rocket engines for achieving orbital velocity and rotor drives (similar to helicopter rotors) for vertical takeoff and landing. This hybrid configuration allows the vehicle to use rotor drives during the noisy ground phase and switch to rocket engines in space where noise is not an issue
Solution Approach 2:
The rotor drives replace conventional rocket engines for the vertical takeoff and landing phases. These electrically-driven rotors produce significantly less noise than combustion-based rocket engines, reducing noise pollution near the ground while still providing sufficient thrust
3Device complexity
If the first propulsion stage is designed for single use, then the launch vehicle can be simpler in design, but the reuse ratio remains low
Solution Approach 1:
The first propulsion stage is designed with dynamic capabilities for controlled descent and precision landing. It can transition from horizontal flight after stage separation to vertical descent using its rotor drives, and finally to controlled landing on a designated site, enabling recovery and reuse
Solution Approach 2:
The first propulsion stage serves multiple functions: it provides initial vertical lift-off using rotor drives, transitions to rocket-powered horizontal flight for orbital insertion, then performs controlled descent and landing back on Earth. This multi-functionality enables reuse without significantly increasing overall system complexity
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 design allows for controlled landing and reuse of multiple stages, reducing fuel consumption and noise pollution, and enhancing the economic viability of space flights by enabling the stages to be recovered and prepared for subsequent flights.
Implementation Method 1
at least a portion of the rotor drives is operable in a generator mode where electrical energy is generatable during an autorotation of the outer rotors
Implementation Method 2
the portion of the rotor drives is configured to feed the electrical energy generated back into the power storage device
Implementation Method 3
a main propulsion stage drivable by a first reaction propulsion system acting substantially parallel to the longitudinal axis
Implementation Method 4
a separate takeoff stage coupled to or couplable to and decouplable from the rocket body or the propulsion stage, the takeoff stage including a plurality of outer rotors
Data Source
AI summary
A launch vehicle with a rocket body having a longitudinal axis which has at least one propulsion stage which can be driven by a reaction propulsion system acting predominantly parallel to the longitudinal axis, wherein the launch vehicle is provided with a plurality of rotors which can be driven by means of a respective rotor drive and whose respective rotor axis is aligned substantially parallel to the longitudinal axis of the rocket body, is characterized in that a separate takeoff stage is provided which is coupled or can be coupled to the rocket body and/or the propulsion stage, which is coupled to or can be coupled to and decoupled from the separate takeoff stage, which has the plurality of outer rotors, in that the outer rotors are arranged in the manner of a multi-copter radially outside the rocket body and surrounding the rocket body.