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KR-20260067749-A - Payload fairing separation system with vertical separation part having no structural fastenings

KR20260067749AKR 20260067749 AKR20260067749 AKR 20260067749AKR-20260067749-A

Abstract

A payload pair separation device according to one embodiment of the present invention is a payload pair separation device for a space launch vehicle comprising a main body and a payload pair having a left pair and a right pair connected to the main body, wherein the device comprises a first hinge portion having one end connected to the main body and the other end connected to the left pair so that the left pair can rotate in a direction away from the central axis of the space launch vehicle, and a second hinge portion having one end connected to the main body and the other end connected to the right pair so that the right pair can rotate in a direction away from the central axis of the space launch vehicle after moving in the longitudinal direction of the space launch vehicle relative to the left pair, wherein the right pair is connected to the main body by a pyro device or a mechanical separation means, and the left pair is connected to the main body by the first hinge portion.

Inventors

  • 이종웅
  • 김희철
  • 임성준
  • 공철원

Assignees

  • 한국항공우주연구원

Dates

Publication Date
20260513
Application Date
20241106

Claims (11)

  1. A payload pair separation device for a space launch vehicle comprising a main body and a payload pair having a left pair and a right pair connected to the main body, A first hinge part, having one end connected to the main body and the other end connected to the left fairing, so that the left fairing can rotate in a direction away from the central axis of the space launch vehicle; and A second hinge part, one end of which is connected to the main body and the other end of which is connected to the right fairing, such that the right fairing can move along the longitudinal direction of the space launch vehicle relative to the left fairing and then rotate in a direction away from the central axis of the space launch vehicle. Includes, The above right pairing is connected to the main body by a pyro device or a mechanical separation means, and A payload pairing separation device characterized in that the above-mentioned left pairing is connected to the above-mentioned main body by the above-mentioned first hinge part.
  2. In paragraph 1, One or more left pair separation actuators, one end of which is fixed to the left pairing and the other end of which contacts the main body, and One or more right-pairing separation actuators, one end of which is fixed to the right-pairing and the other end of which contacts the main body. A payload pairing separation device characterized by further including
  3. In paragraph 2, The above right pairing separation actuator includes a first actuator and a second actuator installed spaced apart along the inner wall perimeter of the right pairing, and The extendable length of the first actuator is longer than the extendable length of the second actuator. A payload pairing separation device characterized by
  4. In Paragraph 3, There are two first actuators, and the second actuator is positioned between the two first actuators, and A payload pair separation device characterized in that the above-described left pair separation actuator includes a third actuator and a fourth actuator installed spaced apart along the inner wall perimeter of the above-described left pair.
  5. In paragraph 1, A payload fairing separation device characterized in that the right fairing is capable of sliding in the longitudinal direction of the space launch vehicle relative to the left fairing.
  6. In paragraph 5, The vertical separator of the above right pairing is First outer wall, A first flange extending from the first outer wall, and A plurality of first protrusions located apart from the first outer wall and spaced apart from each other in the longitudinal direction of the space launch vehicle on the bottom surface of the first flange Equipped with, The vertical separator of the above-mentioned left pairing is A second outer wall facing the first outer wall, A second flange extending from the second outer wall, and A plurality of second protrusions located apart from the second outer wall and spaced apart from each other in the longitudinal direction of the space launch vehicle on the upper surface of the second flange A payload pairing separation device characterized by having
  7. In paragraph 6, Before the right pairing and the left pairing are separated from each other, the first projection and the second projection maintain contact with each other, and When the right fairing moves relative to the left fairing along the longitudinal direction of the space launch vehicle and the contact between the first protrusion and the second protrusion is released, the right fairing rotates in a direction away from the central axis of the space launch vehicle, so that the right fairing and the left fairing can be separated from each other. A payload pairing separation device characterized by
  8. In Paragraph 7, A second projection located on the second nose tip of the above-mentioned left pairing is extended by a second length from the apex of the second nose tip in the direction where the main body is located and is located on a part of the second nose tip, A first projection located at the first nose tip of the above-mentioned right pairing extends from the apex of the first nose tip in the direction in which the main body is located by a first length longer than the second length. A payload pairing separation device characterized by
  9. In Paragraph 1, The second hinge portion includes a second main body hinge portion fixed to the main body and a right pairing hinge portion fixed to the right pairing, and The above right pairing hinge portion is equipped with left and right partition walls spaced apart from each other and a pin connecting the left and right partition walls to each other. The second main body hinge portion has a groove portion in which the right fairing hinge portion can slide in the longitudinal direction of the space launch vehicle, and an opening that is open in a direction away from the space launch vehicle so that the pin can escape. A payload pairing separation device characterized by
  10. In Paragraph 9, A payload pairing separation device characterized in that the second main body hinge portion further comprises a re-entry prevention member that prevents the pin from re-entering the groove portion after the pin has exited.
  11. In Paragraph 10, A payload pairing separation device characterized in that the above-mentioned re-entry prevention member comprises a bar and an elastic member that applies force to the bar in a direction such that the bar always blocks the groove.

Description

Payload fairing separation system with vertical separation part having no structural fastenings The present invention relates to a payload fairing separation device, and more specifically, to a space launch vehicle having a payload fairing separation structure in which there is no structural fastening in the vertical separation section of the payload fairing, and only one of the horizontal separation sections of the left and right payload fairings is connected to the main body of the launch vehicle using a pyro- or mechanical separation device, while the other side can be separated without using such devices. The payload fairing of a space launch vehicle is a protective cover located at the very top of the vehicle, primarily serving to protect the payload (such as satellites or exploration equipment). The payload fairing is designed to withstand the extreme pressure, temperature changes, and shocks that occur as the launch vehicle passes through the atmosphere, and it separates upon reaching space to allow the payload to enter orbit. When the space launch vehicle reaches a certain altitude, the payload fairing automatically separates and falls into space; it is designed to avoid affecting the payload by utilizing technologies such as explosive bolts, springs, and fatigue mechanisms as separation devices. FIGS. 18 and 19 illustrate a payload pairing opening device disclosed in Korean Registered Patent Publication No. 10-0591799 as an example of such a payload pairing opening device. For reference, FIGS. 18 and 19 correspond respectively to FIGS. 4 and FIGS. 5 of the said Korean Registered Patent Publication, and for the sake of explanation, the reference numerals used in the said Korean Registered Patent Publication have been used as they are without modification, and even if these reference numerals overlap with the reference numerals used in the description of the present invention below, they do not refer to the same components. A conventional space launch vehicle includes a left opening (12), a right opening (13), and a main body (11) of a payload fairing (10). In particular, the left opening (12) and the right opening (13), and the left and right openings (12, 13) and the main body (11) are all fixed to each other by a pyro device (20). A conventional space launch vehicle having this configuration will, after arriving at the destination, operate a pyro device (20) to expose the payload inside the payload fairing and separate the left and right openings (12, 13). Specifically, as shown in FIG. 19, by operating the ignition device (26) of the separation bolt (22) to detonate the gunpowder (29) of the gunpowder ball (28), the notch (23) of the body (24) is broken by the expansion force of the gas, thereby releasing the left and right openings (12, 13) of the payload fairing (10) from the connected state. In this way, to perform the function of separating the payload fairing, the existing space launch vehicle releases the structural coupling using a mechanical separation means that uses an explosive device such as a pyro (gunpowder), or a mechanical latch and a non-explosive actuator, for both the vertical separation unit in which the left opening (left payload fairing) and the right opening (right payload fairing) are combined, and the horizontal separation unit in which the left and right openings and the main body (e.g., a second stage launch vehicle) are combined. However, in the case of the pyro, which is a payload fairing separation device, it is single-use and cannot be reused, and mechanical devices have the problem of being complex in configuration and increasing the weight of the projectile. FIG. 1 is a schematic diagram of a payload fairing separation device of a space launch vehicle according to one embodiment of the present invention (before fairing separation). Figure 2 shows the first hinge portion of the payload pairing separation device of Figure 1. Figure 3 shows the state in which the right fairing of the space launch vehicle of Figure 1 has moved upward relative to the left fairing. Figure 4 shows the second hinge portion of the payload pairing separation device of Figure 1. Figure 5(a) shows the right pairing hinge part of the second hinge part of Figure 4, and Figure 5(b) shows the main configuration of the second main body hinge part of the second hinge part. Figure 6 shows the state in which the pin of the right pairing hinge part in the second hinge part of Figure 4 has slipped out of the groove part to the outside through the opening of the second main body hinge part. Figure 7(a) shows the coupling relationship between the left fairing and the main body of the space launch vehicle of Figure 1, and Figure 7(b) shows the coupling relationship between the right fairing and the main body of the space launch vehicle of Figure 1. FIG. 8 is a perspective view showing the main configuration of the right pairing of FIG. 1. Figure 9 (a) shows various cross-sections of the left fairing of Fi