Payload fairing opening and closing device for a space launch vehicle

Abstract

A payload fairing opening and closing device according to one embodiment of the present invention is a payload fairing opening and closing device for a space launch vehicle comprising a main body and a payload fairing having a left fairing and a right fairing connected to the main body, wherein the device comprises: a first actuator that is retractable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the left fairing; a second actuator that is retractable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the right fairing; a first hinge portion that connects the left fairing to the main body rotatably relative to the main body and prevents the left fairing from being separated from the main body; and a second hinge portion that connects the right fairing to the main body rotatably relative to the main body and prevents the right fairing from being separated from the main body.

Description

Technology Field

[0001] The present invention relates to a payload fairing opening and closing device for a space launch vehicle, and more specifically, to a payload fairing opening and closing device for a space launch vehicle that enables the reuse of the payload fairing in order to increase the economic efficiency of the space launch vehicle. Background Technology

[0002] 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.

[0003] 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.

[0004] FIGS. 10 and 11 illustrate a payload fairing opening device disclosed in Korean Registered Patent Publication No. 10-0591799 as an example of such a space launch vehicle payload fairing. For reference, FIGS. 10 and 11 correspond to FIGS. 4 and FIGS. 5 of the said Korean Registered Patent Publication, respectively. For convenience 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.

[0005] 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).

[0006] A conventional space launch vehicle with this configuration will, after arriving at the destination, activate a pyro device (20) to expose the payload inside the payload fairing and separate the left and right openings (12, 13).

[0007] 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.

[0008] However, the pyro, which is a payload fairing separation device, is single-use and cannot be reused, and the existing payload fairing is a structure that is completely separated from the launch vehicle (main body) after the mission is completed and discarded, so reuse was not considered, which caused a decrease in the economic efficiency of reusable launch vehicles. Prior art literature

[0009] Korean Registered Patent Publication No. 10-0591799 (June 13, 2006) The problem to be solved

[0010] The present invention is intended to solve the problems of the prior art as described above, and the objective of the present invention is to provide a payload fairing opening and closing device for a space launch vehicle that can maximize the economic efficiency of the launch vehicle by enabling the reuse of the payload fairing. means of solving the problem

[0011] To achieve the above objective, a payload fairing opening and closing device according to one embodiment of the present invention is a payload fairing opening and closing device for a space launch vehicle comprising a main body and a payload fairing having a left fairing and a right fairing connected to the main body, wherein the device comprises: a first actuator that is retractable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the left fairing; a second actuator that is retractable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the right fairing; a first hinge portion that connects the left fairing to the main body rotatably relative to the main body and prevents the left fairing from being separated from the main body; and a second hinge portion that connects the right fairing to the main body rotatably relative to the main body and prevents the right fairing from being separated from the main body.

[0012] Additionally, the first hinge portion comprises a first main body hinge portion fixed to the main body, a first pairing hinge portion fixed to the left pairing, and a first pin connecting the first main body hinge portion and the first pairing hinge portion so that the first main body hinge portion and the first pairing hinge portion can rotate relative to each other, and the second hinge portion comprises a second main body hinge portion fixed to the main body, a second pairing hinge portion fixed to the right pairing, and a second pin connecting the second main body hinge portion and the second pairing hinge portion so that the second main body hinge portion and the second pairing hinge portion can rotate relative to each other.

[0013] In addition, the first pin is fixed to the first pairing hinge portion, and the second pin is fixed to the second pairing hinge portion.

[0014] In addition, it is characterized by including a first rotary actuator capable of applying rotational force to the first pin, and a second rotary actuator capable of applying rotational force to the second pin.

[0015] In addition, the vertical separation surface of the left pairing is provided with a plurality of spaced-apart protrusions, and the vertical separation surface of the right pairing is provided with a plurality of grooves corresponding to the positions of the plurality of protrusions.

[0016] In addition, each of the first actuator and the second actuator is characterized as being either a single-acting actuator or a double-acting actuator. Effects of the invention

[0017] The payload fairing opening and closing device of a space launch vehicle according to an embodiment of the present invention having the above-described configuration has the following effects.

[0018] When the payload fairing opens and closes, the actuator and rotary actuator restrain a part of the payload fairing, thereby suppressing elastic deformation of the payload fairing (structural panel part) due to separation force, so stable opening and closing behavior can be achieved.

[0019] In addition, the path of the opening and closing behavior of the payload fairing can be restricted, making it easy to reassemble after the closing behavior, which can reduce contamination inside the payload fairing during the recovery process of the reusable projectile and increase the economic efficiency of reuse.

[0020] In addition, the reliability of reassembly between the left and right pairings can be increased through the protrusions and grooves provided on the vertical separation surfaces of the left and right pairings, respectively, during the closing motion of the pairings.

[0021] In addition, the reuse of the payload fairing of a reusable projectile can be increased by implementing the opening and closing mechanism of the payload fairing using actuators, rotary actuators, etc., without applying a one-time separation mechanism using conventional pyrobolts, etc.

[0022] Meanwhile, the present invention also includes other effects that can be expected from the above-described configuration, although not explicitly stated. Brief explanation of the drawing

[0023] FIG. 1 shows a space launch vehicle including the main configuration of a payload fairing opening and closing device according to one embodiment of the present invention. Figure 2(a) is a view of the space launch vehicle of Figure 1 seen through the inside of the left fairing, and Figure 2(b) is a view of the space launch vehicle of Figure 1 seen through the inside of the right fairing. Figure 3(a) shows the first fairing hinge portion of the space launch vehicle of Figure 1, and Figure 3(b) shows the second fairing hinge portion of the space launch vehicle of Figure 1. Figure 4 shows the protrusion of the left pairing of Figure 1. Figure 5 shows the groove of the right pairing of Figure 1. FIG. 6(a) shows a single-acting actuator of the payload fairing opening and closing device of FIG. 1, and FIG. 6(b) shows a double-acting actuator of the payload fairing opening and closing device of FIG. 1. FIG. 7(a) shows a first rotary actuator mounted on the left pairing of a payload pairing opening and closing device according to another embodiment of the present invention, and FIG. 7(b) shows a second rotary actuator mounted on the right pairing. FIG. 8 is a view of a space launch vehicle equipped with the payload fairing opening and closing device of FIG. 7, seen from the inside of the fairing. FIG. 9 is a view of the interior of the fairing of a space launch vehicle equipped with a payload fairing opening and closing device capable of opening and closing motions using only a rotary actuator without an actuator, as shown in FIG. 8. FIGS. 10 and FIGS. 11 show an example of a conventional space launch vehicle payload fairing separation device. FIG. 12 shows an example of a known separation spring assembly for opening a projectile fairing. Specific details for implementing the invention

[0024] Hereinafter, embodiments of the present invention are described in detail with reference to the attached drawings so that those skilled in the art can implement the invention. However, the present invention may be embodied in various different forms and is not limited to the embodiments described herein. Furthermore, it should be noted that terms such as "first," "second," etc. in this specification do not indicate order but are intended to distinguish components having the same name from one another. Also, the terms "left" and "right" are merely terms used to distinguish one side from the other and are not intended to actually specify the left and right sides. Additionally, since the present invention relates to a separation structure of a space launch vehicle, descriptions of other components of the space launch vehicle unrelated thereto are omitted to avoid obscuring the point of the invention.

[0025] FIGS. 1 to 4 illustrate schematic diagrams of a space launch vehicle equipped with a payload fairing opening and closing device according to one embodiment of the present invention (hereinafter referred to as the "first embodiment"). For convenience of explanation, these drawings are shown with the right fairing in an open state. Meanwhile, although the present embodiment illustrates the payload fairing being provided with two fairings (left and right), the number of these fairings may be increased within the scope of the technical concept of the present invention.

[0026] The payload fairing opening and closing device of the present invention is a payload fairing opening and closing device that can be used in a space launch vehicle comprising a main body (1) and a payload fairing (2) having a left fairing (21) and a right fairing (22) connected to the main body (1), and as a main component, comprises a first actuator (31), a second actuator (32), a first hinge part (41), and a second hinge part (42).

[0027] One end of the first actuator (31) is rotatably fixed relative to the main body (1), and the other end is rotatably fixed relative to the left pairing (21), and is extendable.

[0028] The second actuator (32) has one end rotatably fixed relative to the main body (1) and the other end rotatably fixed relative to the right pairing (22), and is extendable.

[0029] These actuators (31, 32) can have one end pin-coupled to the payload pairing and the other end pin-coupled to the projectile body.

[0030] For example, the first actuator (31) and the second actuator (32) may each be either a single-acting actuator or a double-acting actuator.

[0031] As shown in FIG. 6(a), the single-acting actuator has one port (300) in the actuator and is equipped with a return spring (301) inside. Through this configuration, when closing the payload fairing, the fluid supplied through the port (300) is discharged again to cause the return spring (301) to expand, thereby shortening the actuator, and conversely, when opening the payload fairing, the fluid is supplied through the port (300) to cause the return spring (301) to compress, thereby extending the actuator.

[0032] As shown in FIG. 6(b), the double-acting actuator has two ports (302, 303) on the actuator. Through this configuration, when closing the payload pairing, fluid is supplied through the port (303) on one side (right) to shorten the actuator, and conversely, when opening the payload pairing, fluid is supplied through the port (302) on the other side (left) to extend the actuator.

[0033] As shown in FIG. 1, the first hinge part (41) connects the left pairing (21) to the main body (1) so as to be rotatable relative to the main body (1), and prevents the left pairing (21) from being separated from the main body (1).

[0034] Specifically, as shown in FIG. 3 (a), the first hinge portion (41) comprises a first main body hinge portion (411) fixed to the main body (1), a first pairing hinge portion (412) fixed to the left pairing (21), and a first pin (413) connecting the first main body hinge portion (411) and the first pairing hinge portion (412) so as to be rotatable relative to each other.

[0035] As shown in FIG. 1, the second hinge part (42) connects the right pairing (22) to the main body (1) so that it can rotate relative to the main body (1), and prevents the right pairing (22) from being separated from the main body (1).

[0036] Specifically, the second hinge portion (42) comprises, as shown in FIG. 3 (b), a second main body hinge portion (421) fixed to the main body (1), a second pairing hinge portion (422) fixed to the right pairing (22), and a second pin (423) connecting the second main body hinge portion (421) and the second pairing hinge portion (422) so as to be rotatable relative to each other.

[0037] Meanwhile, as illustrated in FIGS. 4 and 5, a plurality of protrusions (212) are spaced apart on the vertical separation surface (211) of the left pairing (21), and a plurality of grooves (222) may be provided on the vertical separation surface (221) of the right pairing (22) at positions corresponding to the positions of the plurality of protrusions (212) of the left pairing (21). Through this, when the left and right pairings (21, 22) are separated from each other and then closed again, the protrusions (212) of the left pairing (21) perform a kind of guide pin function and are inserted into the grooves (222) of the right pairing (22), thereby stably implementing the closing behavior of the left and right pairings (21, 22). For example, the grooves (222) may have a shape that is open toward the inside of the right pairing (22).

[0038] The payload fairing opening and closing device according to the first embodiment described above can open the payload fairing by extending the first actuator (31) and the second actuator (32) to rotate the left fairing (21) and the right fairing (22), respectively, relative to the main body (1) when the space launch vehicle intends to separate a payload such as a satellite at a predetermined orbit and time. Then, after the satellite is separated, the payload fairing can be closed by shortening the first actuator (31) and the second actuator (32) to rotate the left fairing (21) and the right fairing (22), respectively, relative to the main body (1).

[0040] Hereinafter, a payload pairing opening and closing device according to another embodiment of the present invention (hereinafter referred to as the "second embodiment") will be described with reference to FIGS. 7 and 8. For reference, the description of configurations identical to those of the payload pairing opening and closing device of the first embodiment described above will be omitted or simplified, and the description will focus on the configurations that differ.

[0041] As illustrated in FIG. 7, in the payload pairing opening and closing device of the second embodiment, the first pin (413) is fixed to the first pairing hinge part (412), and the second pin (423) is fixed to the second pairing hinge part (422). Through this, when the first pin (413) rotates, it rotates in conjunction with the first pairing hinge part (412), and the second pin (423) rotates in conjunction with the second pairing hinge part (422).

[0042] Additionally, the payload pairing opening and closing device of the second embodiment includes a first rotary actuator (51) capable of applying rotational force to the first pin (413) and a second rotary actuator (52) capable of applying rotational force to the second pin (423). Examples of rotary actuators (51, 52) may include an electric motor, a hydraulic rotary actuator, an electro-hydraulic actuator, etc.

[0043] These first and second rotary actuators (51, 52) may be provided together with the first and second actuators (31, 32) described above, or provided alone.

[0044] That is, as shown in FIG. 8, the first and second actuators (31, 32) may be provided, and the first and second rotary actuators (51, 52) may also be provided in the hinge portion (41, 42). In this case, the first and second actuators (31, 32) may be relatively smaller compared to the first embodiment.

[0045] Alternatively, as illustrated in FIG. 9, the first and second rotary actuators (51, 52) may be provided alone without the first and second actuators (31, 32) described above. In this case, the requirements for power, etc., of the first and second rotary actuators (51, 52) may be appropriately set considering the load requirements when the payload pairing is opened and closed.

[0046] If necessary, a known separation spring assembly for opening a projectile fairing (not shown) may be additionally used, taking into account the load requirements during opening. FIG. 12 illustrates an example of a known separation spring assembly for opening a projectile fairing disclosed in Korean Registered Patent No. 10-2115433. FIG. 12 (a) and (b) correspond to FIG. 1 and FIG. 14 of the aforementioned Korean Registered Patent, respectively, and are illustrated as they are without modification of drawing numbers, etc. Such a separation spring assembly functions to separate the first separation body (S1) and the second separation body (S2) by the compression force of the spring pushing the push rod away from the housing (110) while the housing (110) is coupled to the first separation body (S1) and the second separation body (S2) are coupled to the push rod end support (S2). Since this is irrelevant to the scope of the present invention, further explanation regarding this is omitted.

[0047] The payload fairing opening and closing device of the second embodiment having the configuration described above can open the payload fairing by rotating the left fairing (21) and the right fairing (22) relative to the main body (1) by extending the first and second actuators (31, 32) respectively and operating the first and second rotary actuators (51, 52) at the same time when the space launch vehicle intends to separate a payload such as a satellite at a predetermined orbit and time.

[0048] And after the satellite is separated, the first and second actuators (31, 32) are shortened respectively, and at the same time the first and second rotary actuators (51, 52) are operated, so that the left pairing (21) and the right pairing (22) are rotated relative to the main body (1) respectively, thereby closing the payload pairing.

[0049] If the load requirement during opening is small and the first and second rotary actuators (51, 52) are provided alone, the first and second pins (413, 423) are rotated by these rotary actuators, thereby enabling the left and right pairings (21, 22) to open or close.

[0050] Additionally, depending on the load requirements during opening, a known separation spring assembly for opening a projectile fairing may be applied. Furthermore, a latch and a clamp may be applied to maintain the payload fairing after the closing and reassembly mechanism is completed.

[0051] Although preferred embodiments of the present invention have been described in detail above, the scope of the present invention is not limited thereto, and various modifications and improvements by those skilled in the art using the basic concept of the present invention as defined in the following claims also fall within the scope of the present invention. Explanation of the symbols

[0052] 1...Main body 2...Payload pairing 21...Left pairing, 22...Right pairing 31...1st actuator, 32...2nd actuator 41...1st hinge part 411...1st main body hinge part, 412...1st pairing hinge part 413...1st pin 42...2nd hinge part 421...2nd main body hinge part, 422...2nd pairing hinge part 423...2nd pin

Claims

Claim 1 A payload fairing opening and closing device for a space launch vehicle comprising a main body and a payload fairing having a left fairing and a right fairing connected to the main body, wherein the device comprises: a first actuator that is extendable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the left fairing; a second actuator that is extendable, with one end rotatably fixed relative to the main body and the other end rotatably fixed relative to the right fairing; a first hinge portion that connects the left fairing to the main body rotatably relative to the main body and prevents the left fairing from being separated from the main body; and a second hinge portion that connects the right fairing to the main body rotatably relative to the main body and prevents the right fairing from being separated from the main body. Claim 2 A payload fairing opening and closing device for a space launch vehicle, characterized in that, in claim 1, the first hinge portion comprises a first main body hinge portion fixed to the main body, a first pairing hinge portion fixed to the left pairing, and a first pin connecting the first main body hinge portion and the first pairing hinge portion so that the first main body hinge portion and the first pairing hinge portion can rotate relative to each other, and the second hinge portion comprises a second main body hinge portion fixed to the main body, a second pairing hinge portion fixed to the right pairing, and a second pin connecting the second main body hinge portion and the second pairing hinge portion so that the second main body hinge portion and the second pairing hinge portion can rotate relative to each other. Claim 3 A payload fairing opening and closing device for a space launch vehicle according to claim 2, characterized in that the first pin is fixed to the first fairing hinge portion and the second pin is fixed to the second fairing hinge portion. Claim 4 A space launch vehicle payload fairing opening and closing device according to claim 3, characterized by including a first rotary actuator capable of applying rotational force to the first pin, and a second rotary actuator capable of applying rotational force to the second pin. Claim 5 A payload fairing opening and closing device for a space launch vehicle according to claim 1, characterized in that a plurality of spaced-apart protrusions are provided on the vertical separation surface of the left fairing, and a plurality of grooves are provided on the vertical separation surface of the right fairing in correspondence with the positions of the plurality of protrusions. Claim 6 A payload fairing opening and closing device for a space launch vehicle according to claim 1, wherein each of the first actuator and the second actuator is one of a single-acting actuator and a double-acting actuator. Claim 7 A space launch vehicle comprising a payload fairing opening and closing device according to any one of paragraphs 1 to 6.

Images