Impulse Propulsion With Counter-Rotating Tube Propellers
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Solution Overview
Problem
Current space propulsion systems face inefficiencies in specific impulse and thrust, leading to long mission times and high fuel consumption, with electric propulsion systems requiring months to reach desired orbits and chemical systems needing large fuel masses, while also limiting orbital maneuvers and being susceptible to space debris impacts.
Innovation Solution
A propulsion system utilizing counter-rotating longitudinal tubes with projectiles and propellers that convert translational movement into rotational movement, dissipating heat and using a non-isolated system design to achieve impulse thrust, reducing fuel consumption and increasing maneuverability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of substance
If electric propulsion is used to achieve high specific impulse, then fuel consumption is reduced, but mission time increases significantly
Solution Approach 1:
The propulsion system uses periodic impulse thrust generated by projectiles being accelerated and ejected from longitudinal tubes, creating pulsed propulsion rather than continuous thrust. This allows the system to achieve high delta-v with minimal propellant while maintaining reasonable transit times through repeated short bursts of acceleration
Solution Approach 2:
The system changes the physical state and parameters of projectiles (accelerating them to high velocities using electromagnetic or mechanical means) to generate impulse thrust. By varying projectile mass, velocity, and ejection frequency, the system optimizes both fuel efficiency and mission duration
2Loss of time
If chemical propulsion is used to achieve high thrust, then mission time is reduced, but fuel mass increases significantly
Solution Approach 1:
The propulsion system divides the thrust generation into multiple independent longitudinal tubes, each containing projectiles that can be accelerated and ejected independently. This segmentation allows for high instantaneous thrust when multiple tubes fire simultaneously while using minimal propellant mass compared to chemical systems
3Adaptability or versatility
If conventional propulsion systems are used, then orbital plane changes are possible, but fuel consumption becomes excessive
Solution Approach 1:
The propulsion system employs multiple pairs of longitudinal tubes that can be activated in different configurations and orientations. By selectively firing specific tubes at different times and angles, the system can perform various orbital maneuvers including plane changes with minimal propellant consumption
Solution Approach 2:
The system uses periodic impulse thrust from projectiles to achieve orbital plane changes through repeated small adjustments rather than large single burns, reducing overall fuel consumption while maintaining maneuverability
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 system reduces travel time to desired orbits and minimizes fuel requirements, enhances orbital maneuverability, and reduces the impact of space debris, offering a more efficient and versatile propulsion solution.
Implementation Method 1
Thanks to the viscosity of the fluid, the propeller is arranged to transform a translational movement of the projectile into a rotational movement
Implementation Method 2
another part will be transformed, depending on the nature of the braking device, either into heat or into electrical energy
Implementation Method 3
a heat dissipation device arranged to remove heat from the internal volume of the longitudinal tube containing the projectile and the propeller
Data Source
Figure 1
Figure 2
AI summary
The invention relates to a propulsion system comprising a motor comprising a pair of parallel longitudinal tubes (100), each longitudinal tube comprising a first end (10) and a second end (11) and delimiting an internal volume (12) filled with a fluid. Each longitudinal tube (100) comprises: - a projectile (200), configured to move longitudinally in the internal volume, securely attached to a propeller (201), - a mechanism for launching the projectile in the internal volume (12) from the first end, the propeller (201) being designed to convert a translational movement of the projectile (200) into a rotational movement, - a device for slowing the rotation of the projectile (200) in the internal volume (12), this device being positioned at the second end, - a device for returning the projectile (200) toward the first end, - a device for dissipating heat, the propellers of the longitudinal tubes being contrarotating.