Dual-Function Motor for Launch Vehicle Propulsion Stage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing reusable propulsion stages for launch rockets face challenges in minimizing payload loss due to the added mass of electric duct blowers and associated components, which are necessary for controlled landing but increase the overall weight and reduce payload capacity.
Innovation Solution
A propulsion stage with a dual-function motor that can drive both the rotor assemblies and the fuel pump, allowing for the use of a single motor to power both systems, thereby reducing mass and weight. This design includes a switchable clutch system that enables the motor to be coupled either to a rotor drive or a fuel pump, optimizing energy use during ascent and descent phases.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If electric duct blowers and associated components are added for controlled landing, then landing control capability is improved, but payload capacity deteriorates due to increased mass
Solution Approach 1:
The motor is designed to perform multiple functions: driving the rotor assembly for controlled landing and driving the fuel pump for propellant delivery. This multi-functionality eliminates the need for separate dedicated components, reducing overall system mass while maintaining both landing control capability and propellant supply function
Solution Approach 2:
The patent combines the motor functions by merging the rotor drive motor and fuel pump drive motor into a single motor unit. This consolidation integrates two previously separate systems into one, reducing the number of components and associated mass, thereby improving payload capacity while preserving landing control functionality
2Reliability
If additional control nozzles and fuel reserves are provided for controlled landing, then landing reliability is improved, but device complexity and mass increase
Solution Approach 1:
The single motor serves dual purposes: controlling the rotor assembly for landing stability and operating the fuel pump for engine function. This multi-functionality maintains landing reliability through the rotor control system while avoiding the need for additional dedicated landing components that would increase system complexity
3Weight of moving object
If a single motor is used to drive both rotor assembly and fuel pump, then mass is reduced, but device complexity increases due to switchable clutch system
Solution Approach 1:
The switchable clutch system enables dynamic reconfiguration of the motor's power transmission path. The clutch can switch between connecting the motor to the rotor assembly for landing control and connecting to the fuel pump for propellant delivery. This dynamic switching capability allows a single motor to serve multiple functions while maintaining system manageability through controlled connectivity changes
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-function motor design reduces the overall mass of the propulsion stage, minimizing payload loss while enabling efficient energy use during both ascent and descent phases, thereby enhancing the rocket's performance and range.
Implementation Method 1
each of which can be driven by a rotor drive which comprises at least one motor
Implementation Method 2
to which liquid propellant can be supplied from at least one propellant tank by means of at least one associated fuel pump
Implementation Method 3
at least one recoil propulsion unit which acts predominantly parallel to the longitudinal axis
Implementation Method 4
A plurality of rotor assemblies is provided, each of which can be driven by a rotor drive
Data Source
AI summary
A propulsion stage for a launch rocket, the propulsion stage comprising: a rocket body having a longitudinal axis; at least one recoil propulsion unit acting substantially parallel to the longitudinal axis, wherein a liquid propellant is supplyable to the at least one recoil propulsion unit from at least one propellant tank through at least one fuel pump; and a plurality of rotor assemblies, each drivable by a rotor drive including at least one motor, wherein the at least one motor of at least one of the rotor drives is configured to selectively drive at least one of the rotor assemblies and/or the at least one fuel pump of the at least one recoil propulsion unit.