Linear Motor Geometry for Persistent Current Magnets
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Solution Overview
Problem
Current electromagnetic launch apparatuses face technical hurdles in achieving efficient payload delivery to orbital and sub-orbital velocities, including high costs and the need for large power supplies and fast-acting switching systems, which have limited their adoption for both terrestrial and extra-terrestrial applications.
Innovation Solution
A linear motor apparatus utilizing superconducting materials in persistent current mode, with a primary assembly generating a constant magnetic field and a secondary assembly designed to travel along the primary, allowing for the acceleration of payloads without the need for sliding current pickups or quenching, and enabling the use of arbitrarily small power supplies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If conventional electromagnetic launch apparatus are used, then payloads can be accelerated to high velocities, but the cost is high and large power supplies with fast-acting switching systems are required
Solution Approach 1:
The primary assembly is divided into multiple primary segments that can be independently controlled. Each segment contains conductors arranged to generate magnetic fields in specific regions, allowing the launch apparatus to accelerate the secondary assembly in discrete stages without requiring a single large, complex power supply system
Solution Approach 2:
The launch process uses periodic activation of primary segments, where current is applied to successive segments in sequence as the secondary assembly progresses through the tube. This periodic action replaces the need for fast-acting switching systems by using a simpler sequential activation approach
2Ease of operation
If sliding current pickups are used for the secondary assembly, then current can be transferred during motion, but the system becomes more complex and less reliable
Solution Approach 1:
The invention extracts and eliminates the sliding current pickup system entirely from the secondary assembly. Instead of attempting to transfer current to a moving component, the system uses electromagnetic induction where the moving secondary assembly generates current in itself through its interaction with the magnetic fields from the primary segments
Solution Approach 2:
The mechanical sliding contact system is replaced with an electromagnetic field-based current generation system. The secondary assembly, containing conductors and magnets, generates the necessary current through its motion through the magnetic fields, eliminating mechanical wear and contact issues
3Productivity
If quenching or switching of the primary assembly is required during launch, then the launch cycle can be controlled, but the system complexity and maintenance requirements increase
Solution Approach 1:
The primary assembly is designed with segments that can be dynamically activated in sequence during the launch cycle. Each primary segment can be independently controlled to provide magnetic fields at the appropriate positions as the secondary assembly moves through the tube, enabling controlled acceleration without quenching or switching
Solution Approach 2:
The primary segments are pre-positioned and pre-configured with their conductors and magnets in specific arrangements. This preliminary configuration allows the system to simply activate pre-positioned segments in sequence rather than requiring dynamic switching or quenching operations during the launch cycle
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 solution enables the efficient acceleration of small payloads to high velocities, offering lower costs, greater control flexibility, and reduced maintenance requirements, making it suitable for satellite assembly, maintenance, and space station resupply, while being safer and potentially more efficient than chemical systems.
Implementation Method 1
The present invention provides an electromagnetic launch apparatus including a primary assembly and a secondary assembly, where the secondary assembly is designed to be accelerated by the primary assembly down a length of the primary assembly in response to electromagnetic fields in the primary assembly and the secondary assembly
Implementation Method 2
The motor is well-suited as electromagnetic payload launch apparatus or as a projectile launch apparatus because sliding current pickups are not needed for the secondary assembly, the power supply can be arbitrarily small, and no quench or other switching of the primary assembly is necessary during a launch of a payload
Implementation Method 3
The present invention provides an electromagnetic launch apparatus including a primary assembly having a left element and a right element, each element having a longitudinal slot herein and a secondary assembly comprising a closed loop designed to travels down the longitudinal slots and upon which a payload can be coupled
Data Source
AI summary
An electrically powered launcher is disclosed that can accelerate small payloads to orbital velocities. The invention uses a novel geometry to overcome limitations of other design, and allows full exploitation of existing superconducting materials.