Search

EP-4467468-B1 - ELECTRICAL UMBILICAL SYSTEM FOR SPACE LAUNCH VEHICLE, USING ELECTROMAGNET

EP4467468B1EP 4467468 B1EP4467468 B1EP 4467468B1EP-4467468-B1

Inventors

  • LEE, JEONG CHAN
  • MOON, Keun Hwan
  • CHOI, JONG HWI
  • CHOI, GO EUN

Dates

Publication Date
20260506
Application Date
20230316

Claims (6)

  1. An electrical umbilical system using an electromagnet for a space launch vehicle, the system comprising: a launch vehicle unit (10) and a connection module (20) provided in the launch vehicle unit (10) capable of flying by thrust; and a tower unit (30) and an umbilical unit provided in the tower unit (30) by which the launch vehicle unit (10) is supported upright, and being capable of being electrically connected to the connection module (20), wherein the umbilical unit comprises: a supply module capable of being electrically connected to the connection module (20); a connection drive module (120) coupled to the tower unit (30) and configured to connect the supply module to the connection module (20); a weight body (130) coupled to the tower unit (30) so that the weight body (130) is capable of moving up and down; a drive line (150) configured to connect the supply module with the weight body (130); and a guide roller coupled rotatably to the tower unit (30) and configured to support the drive line (150), wherein whether the connection module (20) and the supply module are coupled to each other is determined depending on whether at least any one of the connection module (20) and the supply module is magnetized by electricity, wherein the system further comprises: a cable cutting module (170) configured to cut the drive line (150) when the connection module (20) and the supply module are maintained to be coupled to each other in response to a launch operation of the launch vehicle unit (10).
  2. The system of claim 1, wherein the connection module (20) comprises: a connection connector (21) comprising a connection terminal (22) that is electrically conductive, a connection coupling member (24) configured to cover the connection terminal (22) so that a portion of the connection terminal (22) is exposed, and a connection insulating means (23) configured to insulate the connection terminal (22) from the connection coupling member (24); and a connection cable (25) connected to the connection terminal (22), and the supply module comprises: a supply connector (110) comprising a supply terminal (111) that is electrically conductive to be electrically connected to the connection terminal (22), a supply coupling member (113) configured to cover the supply terminal (111) so that a portion of the supply terminal (111) is exposed, and a supply insulating means (112) configured to insulate the supply terminal (111) from the supply coupling member (113); and a supply cable connected to the supply terminal (111), wherein at least one of the connection coupling member (24) and the supply coupling member (113) is magnetized by electricity applied thereto.
  3. The system of claim 1 or claim 2, further comprising: a static buffering module (160) configured to buffer a load acting on at least one of the weight body (130), the drive line (150), and the connection drive module (120) in response to falling of the weight body (130).
  4. The system of claim 3, wherein the static buffering module (160) comprises at least one of: a weight buffering part (160a) configured to elastically support the weight body (130) in the tower unit (30) in response to the falling of the weight body (130); a bracket buffering part (160b) configured to elastically support the supply module in the connection drive module (120) in response to the falling of the weight body (130); and an abnormal buffering part (160c) configured to elastically support the drive line (150) in the tower unit (30) in response to the falling of the weight body (130).
  5. The system of claim 1 or 2, wherein an electrical connection part (11) is formed to be recessed in the launch vehicle unit (10), with the electrical connection part (11) allowing the connection module (20) to be mounted therein and the supply module to be inserted therein through an entrance thereof, and the cable cutting module (170) comprises a cable cutter (171) disposed upright at a side of the entrance of the electrical connection part (11).
  6. The system of claim 5, wherein the cable cutter (171) is coupled to the launch vehicle unit (10) so that the cable cutter (171) is capable of moving up and down, and the cable cutting module (170) further comprises a cutter drive part (172) configured to move the cable cutter (171) up and down.

Description

Technical Field The present disclosure relates to an electrical umbilical system using an electromagnet for a space launch vehicle and, more particularly, to an electrical umbilical system using an electromagnet for a space launch vehicle, the electrical umbilical system applying an electromagnetic method to fix an umbilical unit to a connection module provided in a launch vehicle unit up to a required time point and to separate the umbilical unit from the connection module in response to a launch operation of the launch vehicle unit so that a normal retrieval operation of the umbilical unit or an abnormal retrieval operation of the umbilical unit is stably performed. Background Art Generally, a rocket is installed on a rocket launcher when preparing for launch, and is then connected to the ground through an umbilical cable to receive power and various control signals from the ground. The umbilical cable is connected to the rocket so that the umbilical cable is automatically removed from the rocket when the rocket is launched. One end of the umbilical cable is fixed to the ground, and a cable retrieval apparatus is installed on the rocket launcher so that the umbilical cable separated from the rocket is quickly retrieved to the ground. The cable retrieval apparatus is usually powered by a motor or hydraulic device. However, in order to separate an umbilical cable from a rocket and retrieve the umbilical cable according to a prior art, a cable retrieval apparatus is operated by electric force. Accordingly, when power is not supplied properly during rocket launch, the umbilical cable cannot be quickly retrieved, there is a high risk that the unretrieved umbilical cable may collide with the fuselage or wings of the rocket being launched and damage the rocket, and the cable retrieval apparatus is not only complex in structure due to electrical configuration thereof, but is expensive. A prior art document includes Korean Patent Application Publication No. 10-2005-0061185 (published on June 22, 2005, invention title: UMBILICAL CABLE RETRIEVAL APPARATUS OF ROCKET). The CN 106,740,212 A discloses an electric car charging system. The electric car charging system comprises an electricity supply unit, a connection unit and an electric car body. The electricity supply unit is installed at the top of a garage and electrically connected with the connection unit. The connection unit is connected with an electric car. A charge couple of the electric car is located at the top of the electric car. The connection unit comprises a first magnetic joint and a second magnetic joint, the first magnetic joint is electrically connected with the electricity supply unit, and the second magnetic joint is installed at the charge couple of the electric car. The electric car charging system does not occupy any aboveground space, the existing garage can be reconstructed conveniently, the cost is low, and the whole charging process is completely and automatically controlled without manual repeated operation. The US 2020/180455 A1 discloses a cable retrieving system for a charging station adapted for recharging an electric vehicle, the charging station comprising an electric cable and a plug for enabling an electrical connection with the electric vehicle, the system comprising a mechanical wire having a first end secured to the electric cable and a second end; an enclosure comprising an opening suitable for the mechanical wire and a pulling mechanism located in the enclosure, the pulling mechanism comprising a weight member located in the enclosure and mounted on a portion of the mechanical wire to thereby create a pulling force on the mechanical wire to thereby pull the electric cable towards the charging station. The US 2015/153135 A1 discloses an umbilical cable disconnect device. The umbilical cable disconnect device includes a base having an opening configured to receive an umbilical cable, a cutter extending into the opening of the base, and a spacer component disposed in the opening between the cutter and the umbilical cable. The spacer component maintains separation of the cutter and the umbilical cable prior to disconnect of the umbilical cable. The cutter is operable to penetrate the spacer component in response to displacement of the disconnect device relative to the umbilical cable to facilitate cutting of the umbilical cable by the cutter to disconnect the umbilical cable. Document JP 2019001193 A discloses according to its abstract an umbilical connection device comprising: an internal connector provided to a flying body R; and an external connector 2 provided at a tip of an umbilical cable A. The external connector 2 includes an electric magnet 3 adsorbing on a side of the flying body R while being connected to the internal connector 1. Disclosure Technical Problem The present disclosure has been made to solve the above problems occurring in the prior art, and is intended to propose an electrical umbilical system using an elec