Electric Multicopter Take-Off Stage for Reusable Launch Vehicles
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Solution Overview
Problem
Existing launch vehicles face challenges in achieving high reuse rates due to the inefficiency and environmental impact of traditional rocket propulsion systems, particularly during launch and re-entry.
Innovation Solution
A launch vehicle design incorporating electrically powered rotors arranged in a multicopter configuration, allowing for vertical takeoff and landing, with energy storage to power the rotors, enabling controlled descent and reuse of stages by converting kinetic energy into electrical energy during descent.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional rocket propulsion systems are used for launch, then the vehicle can achieve space flight, but fuel consumption is high and noise is generated during launch
Solution Approach 1:
The launch vehicle is divided into a launch stage with electric rotors and a propulsion stage with rocket engines. The launch stage uses electric motors to lift the vehicle to a predetermined altitude where atmospheric density is sufficient for rotor operation, then the propulsion stage takes over for space flight. This segmentation allows each system to operate in its optimal environment, reducing overall fuel consumption.
Solution Approach 2:
Electrically powered rotor drives serve as an intermediary system between the ground and the rocket propulsion system. These rotors provide the initial lift to reach altitude and speed conditions where rocket engines can operate efficiently, acting as a bridge that reduces the energy demand on the main propulsion system.
2Productivity
If traditional rocket propulsion systems are used for launch, then the vehicle can achieve space flight, but noise is generated during launch
Solution Approach 1:
The launch process is segmented into two phases: initial ascent using electrically powered rotors that produce minimal noise, and subsequent space flight using rocket engines. By separating these functions, the noisy rocket propulsion is delayed until after the vehicle has cleared the noise-sensitive ground environment.
Solution Approach 2:
Electric motor-driven rotors act as an intermediary propulsion system during the initial launch phase, replacing traditional noisy rocket engines for the portion of flight that occurs in the noise-sensitive ground environment. This intermediary system enables quiet launch while still achieving space flight capability.
3Device complexity
If rocket stages are designed for single use, then the vehicle can be simpler in structure, but the reuse rate is low
Solution Approach 1:
The vehicle is segmented into reusable and disposable components. The launch stage with electric rotors and the propulsion stage with rocket engines are designed as reusable segments that can be recovered and reused, while only the upper payload stage may be disposable. This segmentation enables high reuse rates without requiring the entire vehicle to be complex and reusable.
Solution Approach 2:
The patent implements a system where launch and propulsion stages are recovered after use and reused for subsequent missions. The launch stage returns to the launch site and the propulsion stage returns to a recovery site, both being refurbished and reused. This recovering approach dramatically increases the reuse rate while maintaining reasonable structural complexity.
4Ease of operation
If energy storage devices are added to power rotor drives, then controlled descent is enabled, but the vehicle structure becomes more complex
Solution Approach 1:
The energy storage devices and rotor drives serve multiple functions: they provide lift during initial ascent, enable controlled descent for precision landing, and can be used for maneuvering. This multi-functionality justifies the added structural complexity by eliminating the need for separate systems for each function.
Solution Approach 2:
The rotor drives powered by energy storage devices enable the launch vehicle to perform its own controlled descent and precision landing without requiring external assistance such as parachutes or external recovery systems. The vehicle serves itself by using its own power and propulsion systems for the entire flight envelope including landing.
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
Reduces fuel consumption and noise during launch, facilitates controlled landing and reuse of propulsion stages, and enhances operational efficiency by utilizing energy generated during descent for subsequent operations.
Implementation Method 1
each of which has an electrically powered rotor drive
Implementation Method 2
The launch stage has a plurality of outer rotors, each of which has an electrically powered rotor drive and for which a respective power storage device is provided
Implementation Method 3
at least some of the rotor drives can be operated in a generator mode in which electrical energy can be generated during autorotation of the outer rotors
Data Source
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AI summary
The invention relates to a launch vehicle comprising a rocket body (2; 102) that has a longitudinal axis (Z, Z'), which rocket body has at least one propulsion stage (3; 103) that can be propelled by a jet propulsion means (36; 136) that acts predominantly in parallel with the longitudinal axis (Z, Z'), the launch vehicle being provided with a plurality of rotors that can be driven in each case by a rotor drive, the rotor axis of each rotor being oriented substantially in parallel with the longitudinal axis of the rocket body. The launch vehicle is characterised in that: a separate take-off stage (5; 105) is provided which is or can be coupled to the rocket body (2; 102) and/or the propulsion stage (3; 103), and uncoupled therefrom, which take-off stage comprises a plurality of external rotors (52); the external rotors (52) are situated radially outside and so as to surround the rocket body (2; 102) in the manner of a multicopter; the particular rotor drive (53) comprises at least one electric motor as a drive machine; the take-off stage (5; 105) is provided with at least one power storage means (58; 158) for storing electrical energy and for supplying electrical energy to the external rotor drives (53); and during autorotation of the external rotors (52) at least some of the rotor drives (53) can be operated in a generator mode in which electrical energy can be generated; and the relevant rotor drives (53) are designed to return the generated electrical energy into the particular associated power storage means (58; 158).