# US 12,006,068 B2 · Space launch system and method through electromagnetic pushing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,068 B2 - Document ID: US12006068B2 - Status: Granted - Kind: B2 - Application number: 17/580,727 - Filed: 2022-01-21 - Published: 2022-05-12 - Granted: 2024-06-11 - Earliest claimed: 2019-07-24 - Assignees: Naval University of Engineering - Applicants: Naval University of Engineering - Inventors: Weiming Ma; Yuxing Zhang; Mingyuan Zhang; Xiangming Zhang; Weichao Li; Xinlin Long; Chen Deng - Web page: https://patentgrep.com/patent/US12006068B2 ## CPC - B64G 1/002: {Launch systems} - F41B 6/006: {Rail launchers} - H02N 11/006: {Motors} - B60L 50/13: using AC generators and AC motors - B60L 2210/40: DC to AC converters - B60L 2220/42: with use of more than one motor - B60L 2220/50: Structural details of electrical machines - F02K 9/74: combined with another jet-propulsion plant - Y02T 10/7072: Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR - F41B: WEAPONS FOR PROJECTING MISSILES WITHOUT USE OF EXPLOSIVE OR COMBUSTIBLE PROPELLANT CHARGE; WEAPONS NOT OTHERWISE PROVIDED FOR (projectiles for fishing, e.g. fish-spears, A01K81/00; sports implements for throwing A63B65/00, e.g. boomerangs A63B65/08; stationary apparatus for projecting sports balls, e.g. tennis balls, A63B69/40; throwing or slinging toys A63H33/18; knives, axes B26B; projectiles or missiles other than those incorporating springs as projecting means F42B6/00) - H02N: ELECTRIC MACHINES NOT OTHERWISE PROVIDED FOR - B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A space launch system and method through electromagnetic pushing. The space launch system comprises an energy storage subsystem, an energy conversion subsystem, a linear motor subsystem, and a control maintenance subsystem. The space launch system converts the electric energy into an electromagnetic force. Through the electromagnetic force, a rocket is pushed to be accelerated to a certain speed along an electromagnetic launching track to realize the launching of the rocket. ## Claims ### Claim 1 A space launch system, comprising: an energy storage subsystem, configured to deliver stored energy to an energy conversion subsystem during rocket propulsion; the energy conversion subsystem, configured to convert the energy delivered by the energy storage subsystem into AC electric energy and output the AC electric energy to a linear motor subsystem; the linear motor subsystem, configured to receive the AC electric energy output by the energy conversion subsystem and generate an electromagnetic force that pushes a rocket to be accelerated to a certain speed within a certain distance; and a control maintenance subsystem, configured to send different control instructions respectively to the energy storage subsystem, the energy conversion subsystem and the linear motor subsystem and control the energy storage subsystem, the energy conversion subsystem and the linear motor subsystem to run according to predetermined programs. ### Claim 2 (depends on 1) The space launch system of claim 1, wherein the energy storage subsystem is further configured to absorb energy from a power supply system and store the energy during the interval of rocket propulsion. ### Claim 3 (depends on 2) The space launch system of claim 2, wherein the energy storage subsystem comprises n×m mutually independent power modules, n is a number of linear motors, and m is a number of phases of each of the linear motors. ### Claim 4 (depends on 3) The space launch system of claim 3, wherein each of the power modules is divided into p power units, and each of the power units is connected to a corresponding inverter unit in an inverter in the energy conversion subsystem. ### Claim 5 (depends on 4) The space launch system of claim 4, wherein each of the power units comprises a battery pack array and a charging cabinet, and the charging cabinet is a charging interface connected between the power supply system and the battery pack array. ### Claim 6 (depends on 5) The space launch system of claim 5, wherein each of the power units further comprises an energy storage switch cabinet, and the energy storage switch cabinet is connected between the battery pack array and the inverter unit. ### Claim 7 (depends on 1) The space launch system of claim 1, wherein the energy conversion subsystem comprises n×m mutually independent inverters, each of the inverters supplies power to one phase of one linear motor, n is a number of linear motors, and m is a number of phases of each of the linear motors. ### Claim 8 (depends on 7) The space launch system of claim 7, wherein each of the inverters comprises k inverter cabinets connected in parallel, and each of the inverter cabinets comprises p inverter units in cascade connection. ### Claim 9 (depends on 1) The space launch system of claim 1, wherein the linear motor subsystem comprises n linear motors and a rocket adapter, each of the linear motors comprises a stator and a rotor mounted on the stator, and the rocket adapter is connected to the rotors of the n linear motors. ### Claim 10 (depends on 9) The space launch system of claim 9, wherein stators of the n linear motors are unifonnly arranged along a circumferential direction of the rocket adapter. ### Claim 11 (depends on 9) The space launch system of claim 9, wherein stators of the n linear motors are unifonnly arranged along a radial direction of the rocket adapter, and n is an even number. ### Claim 12 (depends on 9) The space launch system of claim 9, wherein an angle between the stator of each of the linear motors and a horizontal plane is 0-90 degrees. ### Claim 13 (depends on 9) The space launch system of claim 9, wherein the stator of each of the linear motors adopts a sectional power supply manner. ### Claim 14 (depends on 1) The space launch system of claim 1, wherein the control maintenance subsystem comprises a top-level control facility, an energy storage control facility, an energy conversion control facility, and a linear motor control facility, and the top-level control facility, the energy storage control facility, the energy conversion control facility and the linear motor control facility are connected through a control ring; the top-level control facility is configured to provide a human-computer interaction control interface and send control instructions respectively to the energy storage control facility, the energy conversion control facility and the linear motor control facility; the energy storage control facility is configured to implement charging and discharging control on the energy storage subsystem according to a first received control instruction; the energy conversion control facility is configured to implement energy conversion control on the energy conversion subsystem according to a second received control instruction; and the linear motor control facility is configured to implement real-time control on a rotor motion, and control on the sectional power supply of stators of linear motors in the linear motor subsystem according to a third received control instruction. ### Claim 15 (depends on 14) The space launch system of claim 14, wherein the control maintenance subsystem further comprises an energy storage monitoring facility, an energy conversion monitoring facility, a linear motor monitoring facility and a management and maintenance facility, and the energy storage monitoring facility, the energy conversion monitoring facility, the linear motor monitoring facility and the management and maintenance facility are connected with each other through a health ring; the energy storage monitoring facility is configured to collect operational data of the energy storage subsystem and upload the operational data to the management and maintenance facility; the energy conversion monitoring facility is configured to collect operational data of the energy conversion subsystem and upload the operational data to the management and maintenance facility; the linear motor monitoring facility is configured to collect operational data of the linear motor subsystem and upload the operational data to the management and maintenance facility; and the management and maintenance facility is configured to analyze, display, store and query a health status and infonnation of the energy storage subsystem, the energy conversion subsystem and the linear motor subsystem according to the received data, and provide a maintenance test function. ### Claim 16 A space launch method, the method comprising: converting DC electric energy into AC electric energy; supplying the AC electric energy to a liner motor subsystem and converting the electric energy into an electromagnetic force through the linear motor subsystem; and pushing a rocket along an electromagnetic launching track through the electromagnetic force so as to accelerate the rocket to a certain speed; wherein: the linear motor subsystem comprises n linear motors and a rocket adapter, each of the linear motors comprises a stator and a rotor mounted on the stator, the stators of the n linear motors foini the electromagnetic launching track, the rocket adapter is connected to the rotors of the n linear motors, the rocket is mounted on the rocket adapter, the stators of the n linear motors are unifonnly arranged along a circumferential direction of the rocket adapter; or the stators of the n linear motors are unifonnly arranged along a radial direction of the rocket adapter, and n is an even number. ### Claim 17 (depends on 16) The method of claim 16, wherein an angle between the stator of each of the linear motors and a horizontal plane is 0-90 degrees.