Reusable launch vehicle comprising non-separable fairing opening / closing structure, and operating method thereof

Abstract

The present invention relates to a reusable launch vehicle, which transports cargo from the ground to a space orbit or outer space, and then returns to the ground so as to be reusable like an aircraft, and, more specifically, to a non-separable fairing opening / closing structure for a reusable launch vehicle, and the reusable launch vehicle comprising same, the structure enabling reuse of even a fairing that is separated from the launch vehicle.

Description

Reusable launch vehicle including non-separable fairing opening and closing structure and method of operating the same

[0001] The present invention relates to a reusable launch vehicle that can transport cargo from the ground to space orbit or space and then return to the ground and be reused like an aircraft, and more specifically, to a reusable launch vehicle including a non-separable fairing opening / closing structure that enables the fairing separated from the launch vehicle to be reused, and a method for operating the same.

[0002]

[0003] A Reusable Launch Vehicle (RLV) is the opposite of a conventional expendable space launch vehicle, and refers to a reusable launch vehicle, like an aircraft. While the first stage of a conventional space launch vehicle is typically abandoned at sea, the first stage of a reusable launch vehicle is used to land a previously used rocket on Earth and launch it again.

[0004] In particular, considering that the price of the first stage launch vehicle, where rocket thrust is concentrated, accounts for a significant portion of the total cost, the cost-saving effect of launch vehicle reuse is significant.

[0005] Meanwhile, the payload fairing, a component of the launch vehicle, is a structure used to protect the payload mounted on the space launch vehicle from the effects of dynamic pressure and aerodynamic heating during the launch vehicle's flight in the atmosphere. It is made of lightweight yet durable materials and is manufactured to withstand the harsh conditions of the space launch vehicle's flight. It can also provide the function of maintaining a clean room environment for sensitive payloads such as precision instruments. After the launch vehicle exits the atmosphere, the payload fairing is typically separated into two pieces using a pyrolysis device and pyro and pneumatic pushers, and is detached from the launch vehicle, exposing the payload to space. Therefore, the payload fairing is typically destroyed by burning up in the atmosphere or crashing into the ocean.

[0006] As described above, conventional fairings are disposable parts designed to be separated into two pieces and detached from the launch vehicle using a pyrotechnic device when the launch vehicle has reached a sufficiently high altitude. Even if the launch vehicle is reused through a reusable launch vehicle, the cost of remanufacturing and reassembling the fairing accounts for a significant portion of the cost.

[0007] Fairings are expensive parts that are lightweight and meet numerous requirements, made of lightweight metals such as aluminum or fiber-reinforced composite materials. Even when using reusable launch vehicles, there was the problem of additional costs ranging from tens of millions to billions of won to remanufacture a pair of fairings.

[0008] To solve the above problems, a technology has recently been disclosed to load a parachute onto a fairing, land the fairing on the open sea, and use a recovery ship to recover and reuse the fairing. However, since a parachute and control device must be applied to the fairing, it is inefficient in terms of the structural cost of the launch vehicle, and additional problems arise, such as the cost of operating a ship to recover a pair of fairings, and the complexity of the overall operation system of the launch vehicle.

[0009]

[0010] The present invention has been devised to solve the above problems, and the purpose of the present invention is to provide a reusable launch vehicle including a non-separable fairing opening / closing structure that enables reuse by preventing the fairing of the reusable launch vehicle from being separated from the launch vehicle, and a method for operating the same.

[0011] More specifically, the present invention provides a reusable launch vehicle and a method of operating the same, including a non-separable fairing opening / closing structure in which a fairing is connected to the launch vehicle through an opening / closing means, opens when a payload is separated, and closes after the payload is separated, thereby allowing the fairing to return together with the launch vehicle.

[0012]

[0013] According to one embodiment of the present invention, a reusable launch vehicle comprises a first stage rocket having a propellant and a combustion chamber therein, a second stage rocket mounted on an upper side of the first stage rocket and including a payload, and a fairing that opens when the second stage rocket is separated, wherein the reusable launch vehicle comprises a hinge joint that hinges the fairing and the first stage rocket, and the fairing opens when the second stage rocket is separated and closes after the second stage rocket is separated, so as to remain connected to the first stage rocket when the reusable launch vehicle is recovered.

[0014] In addition, the pairing is formed by a single pairing unit or a combination of a plurality of pairing units separated along the circumferential direction, and the lower portion of the pairing unit is hingedly connected to the upper portion of the first stage rocket through the hinge joint.

[0015] In addition, the pairing unit and the first stage rocket (100) are connected via an actuator, and the pairing is controlled to open or close by driving the actuator via the control unit.

[0016] In addition, the actuator includes a first hinge-joint portion coupled to the inner surface of the fairing unit; a second hinge-joint portion coupled to a second-stage rocket mounting portion provided on the upper side of the first-stage rocket; and a drive shaft having one side hinge-joint to the first hinge-joint portion and the other side hinge-joint to the second hinge-joint portion, wherein the drive shaft changes its length by a control signal from the control unit to open and close the fairing unit.

[0017] In addition, the actuator includes a first hinge-joint portion coupled to the inner surface of the fairing unit; a second hinge-joint portion coupled to the inner surface of the upper side of the first stage rocket; and a drive shaft having one side hinge-joint to the first hinge-joint portion and the other side hinge-joint to the second hinge-joint portion, wherein the drive shaft changes its length by a control signal from the control unit to open and close the fairing unit.

[0018] In addition, the actuator includes a first hinge-joint portion coupled to an outer surface of the fairing unit; a second hinge-joint portion coupled to an upper outer surface of the first stage rocket; and a drive shaft having one end hinge-joint to the first hinge-joint portion and the other end hinge-joint to the second hinge-joint portion, wherein the drive shaft changes its length by a control signal from the control unit to open and close the fairing unit.

[0019] Additionally, the fairing includes a fixing means provided between the fairing and the first stage rocket or between the fairing unit and an adjacent fairing unit so as to maintain the closed state when closed.

[0020] A method for operating a reusable launch vehicle according to one embodiment of the present invention comprises the steps of igniting an engine of a first stage rocket for takeoff; operating an actuator through a control unit to open a plurality of fairing units coupled through a hinge joint radially outward; separating a second stage rocket from a first stage rocket while the plurality of fairing units are open; and returning the reusable launch vehicle to the ground.

[0021] In addition, the operating method further includes a step of closing the fairing by operating an actuator through a control unit to close a plurality of open fairing units after separating the second stage rocket from the first stage rocket.

[0022] In addition, the operating method further includes a step of fixing the fairing and the first stage rocket through a fixing means so that the fairing and the first stage rocket are maintained in a coupled state before the launch vehicle takes off; and a step of releasing the fixing of the fairing and the first stage rocket through the fixing means before opening the plurality of fairing units radially outward.

[0023] In addition, the above operating method further includes a step of fixing the fairing and the first stage rocket through a fixing means before the launch vehicle returns.

[0024]

[0025] The reusable launch vehicle including the non-separable fairing opening / closing structure of the present invention with the above-described configuration and the operating method thereof enable the fairing to be closed without being separated from the first-stage launch vehicle after separation of the second-stage launch vehicle in an open state, thereby returning to the ground together with the first-stage launch vehicle, thereby enabling the reuse of expensive fairings, thereby reducing the expensive additional cost and time for remanufacturing the fairings and assembling them into the launch vehicle.

[0026] Non-detachable fairings do not require the complex mechanical components or electrical systems required to detach and detach from the launch vehicle, simplifying the design and reducing manufacturing costs and time. Furthermore, they reduce the launch vehicle's total weight and increase space utilization, facilitating its operation and maintenance.

[0027] In addition, since fairing debris and other hazards caused by conventional fairing separation methods do not affect the launch vehicle or the surrounding area, it has the effect of greatly improving the stability and reliability of the space launch vehicle and preventing the generation of space debris.

[0028] In addition, since no separate configuration is required for fairing recovery, it is efficient in terms of the structural cost of the launch vehicle and has the effect of reducing the cost of operating the recovery means.

[0029] Therefore, if the fairing is reused as well as the first stage booster in a reusable launch vehicle, it can have the effect of drastically reducing the cost per launch.

[0030]

[0031] Figure 1 is a front perspective view of a reusable launch vehicle including a fairing opening / closing structure according to one embodiment of the present invention.

[0032] Figure 2 is a front perspective view of a reusable launch vehicle when the fairing is closed according to the first embodiment of the present invention and an enlarged view of the fairing opening and closing structure.

[0033] Figure 3 is a front perspective view of a reusable launch vehicle when the fairing is opened according to the first embodiment of the present invention and an enlarged view of the fairing opening and closing structure.

[0034] Figure 4 is a front perspective view of a reusable launch vehicle when the fairing is closed according to the second embodiment of the present invention and an enlarged view of the fairing opening and closing structure.

[0035] Figure 5 is a front perspective view of a reusable launch vehicle and an enlarged view of the fairing opening and closing structure when the fairing is opened according to the second embodiment of the present invention.

[0036] Figure 6 is an enlarged front perspective view of a reusable launch vehicle illustrating a fairing opening / closing structure and an operating method of a reusable launch vehicle including the same according to one embodiment of the present invention.

[0037] Figure 7 is a drawing showing the flight operation stages of a reusable launch vehicle.

[0038] <Explanation of symbols>

[0039] 1000: Reusable launch vehicle

[0040] 100: 1st stage rocket

[0041] 120: 2nd stage rocket mount

[0042] 150: Nozzle

[0043] 200: Pairing

[0044] 2000: Two-stage rocket

[0045] 400: Hinge joint

[0046] 500, 600: Actuator

[0047] 510, 610: First hinge joint

[0048] 520, 620: Second hinge joint

[0049] 550, 650: Drive shaft

[0050]

[0051] Hereinafter, an embodiment of the present invention as described above will be described in detail with reference to the drawings.

[0052] FIG. 1 is a front perspective view of a reusable launch vehicle (1000) including a fairing (200) opening / closing structure according to one embodiment of the present invention.

[0053] As illustrated, the reusable launch vehicle (1000) includes a first stage rocket (100) having a first space (101) formed therein, which houses an oxidizer tank, a fuel tank, and a combustion chamber. A second stage rocket mounting portion (120) is provided on the upper side of the first stage rocket (100), on which a second stage rocket (2000) having a payload coupled thereto is mounted, and a nozzle (150) for injecting propellant gas combusted in the combustion chamber is provided on the lower side.

[0054] In addition, a second space (201) is formed on the upper side of the first stage rocket (100) to accommodate the second stage rocket (2000) so that the second stage rocket (2000) is not exposed to the outside, and a fairing (200) that opens when the second stage rocket (2000) is separated is provided.

[0055] At this time, the fairing (200) of the reusable launch vehicle (1000) is opened when the second stage rocket (2000) is separated through a hinge connection with the first stage rocket (100), and is closed when the reusable launch vehicle (1000) is recovered after the second stage rocket (2000) is separated. Hereinafter, the detailed configuration of the reusable launch vehicle (1000) having the above configuration will be described in detail with reference to the drawings.

[0056]

[0057] FIG. 2 shows a front perspective view and an enlarged view of the fairing (200) opening and closing structure of a reusable launch vehicle (1000) according to the first embodiment of the present invention when the fairing (200) is closed, and FIG. 3 shows a front perspective view and an enlarged view of the fairing (200) opening and closing structure of a reusable launch vehicle (1000) according to the first embodiment of the present invention when the fairing (200) is opened.

[0058] As illustrated, the fairing (200) is formed with a second space (201) to accommodate a second stage rocket (2000) mounted on the top of the first stage rocket (100), and the upper portion is formed in a streamlined shape with a diameter that becomes narrower as it goes upward, and the lower portion is formed open. The fairing (200) having the above shape is composed of a pair of fairing units (210), and the lower portion of each fairing unit (210) can be hingedly connected to the upper portion of the first stage rocket (100) through a hinge joint (400). Therefore, the pair of fairing units (210) are normally maintained in a closed state to form the fairing (200), and when the second stage rocket (2000) is separated, each fairing unit (210) is configured to unfold radially outward. In addition, the pairing unit (210) and the first stage rocket (100) may be connected via an actuator (500) and configured to be controlled for unfolding or closing by driving the actuator (500) via a control unit. In addition, the pairing (200) may further include a fixing means capable of maintaining the closed state when closed, and for example, a pneumatic latch or a pyrolysis separator may be applied.

[0059] Meanwhile, the actuator (500) is configured to include a first hinge-joint portion (510) coupled to the inner surface of the fairing unit (210), a second hinge-joint portion (520) coupled to a second-stage rocket mounting portion (120) provided on the upper side of the first-stage rocket (100), and a drive shaft (550) having one side hinge-joint to the first hinge-joint portion (510) and the other side hinge-joint to the second hinge-joint portion (520). The drive shaft (550) is configured to open and close the fairing unit (210) by varying its length according to a control signal of the control unit, and may be, for example, an electric linear actuator or a double-acting pneumatic actuator. The second stage rocket mounting portion (120) is fixed to the upper side of the first stage rocket (100), and when the second stage rocket (2000) is separated, the second stage rocket (2000) is configured to detach from the second stage rocket mounting portion (120).

[0060] Accordingly, when the length of the drive shaft (550) increases, the upper end of the fairing unit (210) is opened radially outward to form an open space in which the second stage rocket (120) can be separated, and when the length of the drive shaft (550) decreases, the upper ends of a pair of fairing units (210) can be configured to be coupled to each other in contact to seal the upper opening of the first stage rocket (100). Since the second hinge joint (520) is provided in the second stage rocket mounting portion (120), the drive shaft (550) can be prevented from interfering with the upper end of the first stage rocket (100) when the actuator is operated to open the fairing unit (210), and there is an advantage in that the size of the second hinge joint (520) can be minimized.

[0061] Meanwhile, the second stage rocket (2000) can be mounted on the second stage rocket mounting portion (120) fixed to the upper side of the first stage rocket (100) so that the upper part is accommodated inside the fairing (200). Through the above, the present invention has the effect of reducing the length of the rocket since no guide is needed for separating the second stage rocket (2000), and further reducing the length of the first stage rocket (100) since the second stage rocket (2000) is arranged in the fairing space. In particular, since the upper part of the second stage rocket (2000) is arranged close to the upper part of the fairing (200), a certain range of free space is formed in the horizontal direction when the second stage rocket (2000) is separated, so that interference with the fairing (200) does not occur, and thus safe separation can be expected.

[0062]

[0063] FIG. 4 shows a front perspective view and an enlarged view of the fairing (200) opening and closing structure of a reusable launch vehicle (1000) according to a second embodiment of the present invention when the fairing (200) is closed, and FIG. 5 shows a front perspective view and an enlarged view of the fairing (200) opening and closing structure of a reusable launch vehicle (1000) according to a second embodiment of the present invention when the fairing (200) is opened.

[0064] As illustrated, the pairing (200) is composed of a pair of pairing units (210), and the lower end of each pairing unit (210) can be hingedly connected to the upper end of the first-stage rocket (100) via a hinge joint (400). In addition, the pairing unit (210) and the first-stage rocket (100) can be connected via an actuator (600) so that the opening or closing can be controlled by driving the actuator (500) via a control unit.

[0065] At this time, the actuator (600) is configured to include a first hinge-joining portion (610) coupled to the inner surface of the pairing unit (210), a second hinge-joining portion (620) coupled to the upper inner surface of the first stage rocket (100), and a driving shaft (650) of which one side is hinge-joined to the first hinge-joining portion (610) and the other side is hinge-joined to the second hinge-joining portion (620). The driving shaft (650) is configured to open and close the pairing unit (210) by varying its length according to a control signal of the control unit, and may be, for example, an electric linear actuator or a double-acting pneumatic actuator.

[0066] Accordingly, when the length of the drive shaft (650) increases, the upper end of the pairing unit (210) is opened radially outward to form an open space in which the two-stage rocket (120) can be separated, and when the length of the drive shaft (650) decreases, the upper ends of a pair of pairing units (210) can be configured to contact each other and be coupled to seal the upper opening of the one-stage rocket (100).

[0067] Since the first and second hinge joints (610)(620) are provided on the inner surface of the fairing unit (210) and the inner surface of the first stage rocket (100), damage to the first and second hinge joints (610)(620) can be prevented, and the aerodynamic load of the reusable launch vehicle (1000) can be reduced. In other words, air resistance and moment due to aerodynamic force can be reduced.

[0068] In another embodiment, the first and second hinge joints (610) (620) may be provided on the outer surface of the fairing unit (210) and the outer surface of the first stage rocket (100). The above embodiment has the advantage of ease of assembly and manufacturing even when considering the increased aerodynamic load of the reusable launch vehicle (1000).

[0069]

[0070] Hereinafter, the operating method of the reusable launch vehicle (1000) according to the first and second embodiments of the present invention having the above configuration will be described with reference to the drawings.

[0071] FIG. 6 is an enlarged front perspective view of a reusable launch vehicle (1000) showing an opening / closing structure of a fairing (200) according to one embodiment of the present invention and an operating method of a reusable launch vehicle (1000) including the same, and FIG. 7 is a drawing showing the overall flight operation steps of a reusable launch vehicle (1000).

[0072] First, a step (S10) is performed to ignite the engine of the first stage rocket (100) of the reusable launch vehicle (1000) to take off, and a step (S20) is performed to increase the altitude by accelerating using propulsion.

[0073] Next, a step (S20) is performed to release the latch that secures the fairing (200) after the reusable launch vehicle (1000) passes through the atmosphere. In the above step, as illustrated in FIG. 6a, the two-stage rocket (2000) including the payload remains connected to the two-stage rocket mounting portion (120) of the one-stage rocket (100), and the fairing (200) remains closed.

[0074] Next, a step (S40) is performed to open a pair of pairing units (210) connected through a hinge joint (400) radially outward by operating a drive shaft (550, see FIGS. 2 to 5) through a control unit as shown in FIG. 6b.

[0075]

[0076] Next, as illustrated in Fig. 6c, a step (S50) is performed to separate a second-stage rocket (2000) from a first-stage rocket (100) using a separate pusher while a pair of pairing units (210) are open. The second-stage rocket (2000) separated from the first-stage rocket (100) generates thrust through ignition.

[0077]

[0078] Next, as illustrated in FIG. 6d, a step (S60) is performed to close a pair of open pairing units (210) by operating a drive shaft (550) via a control unit to close the pairing (200). In addition, a step (S70) is performed to change the direction of the reusable launch vehicle (1000) to a posture suitable for base landing.

[0079]

[0080] Next, the fixed latch is re-secured to maintain the closed state of the pairing, and a step (S80) is performed to return the reusable launch vehicle (1000) to the ground.

[0081]

[0082] Next, the operation method is terminated by performing a step (S90) of reducing the speed of the reusable launch vehicle (1000) by re-igniting the engine as landing approaches and a step (S100) of settling the reusable launch vehicle (1000) on the station.

[0083]

[0084] The technical concept of the present invention should not be construed solely based on the aforementioned embodiments. The scope of application is diverse, and various modifications can be made by those skilled in the art without departing from the spirit of the invention as claimed in the claims. Therefore, such improvements and modifications, as long as they are obvious to those skilled in the art, fall within the scope of protection of the present invention.

Claims

1. A reusable launch vehicle comprising a first stage rocket having a propellant and combustion chamber inside, a second stage rocket mounted on the upper side of the first stage rocket and containing a payload, and a fairing that opens when the second stage rocket is separated. The above reusable projectile is, It includes a hinge joint that hinge-joins the above fairing and the first stage rocket, A reusable launch vehicle, wherein the fairing opens when the second stage rocket is separated, closes after the second stage rocket is separated, and remains connected to the first stage rocket when the reusable launch vehicle is recovered.

2. In paragraph 1, The above pairing is formed by a single pairing unit or a combination of multiple pairing units separated along the circumferential direction, The above pairing unit, A reusable launch vehicle, wherein the lower portion is hingedly connected to the upper portion of the first stage rocket through the hinge joint.

3. In paragraph 2, The above pairing unit and the first stage rocket (100) are connected through an actuator, The above pairing is, A reusable launch vehicle, the opening or closing of which is controlled by the driving of the actuator through the control unit.

4. In paragraph 3, The above actuator, A first hinge joint coupled to the inner surface of the above pairing unit; A second hinge joint coupled to a second stage rocket mounting portion provided on the upper side of the first stage rocket; and A drive shaft having one side hingedly connected to the first hinge joint and the other side hingedly connected to the second hinge joint, The above drive shaft, A reusable launch vehicle that opens and closes the pairing unit by varying the length according to a control signal from the control unit.

5. In paragraph 3, The above actuator, A first hinge joint coupled to the inner surface of the above pairing unit; A second hinge joint coupled to the upper inner surface of the first stage rocket; and A drive shaft having one side hingedly connected to the first hinge joint and the other side hingedly connected to the second hinge joint, The above drive shaft, A reusable launch vehicle that opens and closes the pairing unit by varying the length according to a control signal from the control unit.

6. In paragraph 3, The above actuator, A first hinge joint coupled to the outer surface of the above pairing unit; A second hinge joint coupled to the upper outer surface of the first stage rocket; and A drive shaft having one side hingedly connected to the first hinge joint and the other side hingedly connected to the second hinge joint, The above drive shaft, A reusable launch vehicle that opens and closes the pairing unit by varying the length according to a control signal from the control unit.

7. In paragraph 3, The above pairing can be maintained in a closed state when closed, A reusable launch vehicle comprising a fixing means provided between the fairing and the first stage rocket or between the fairing unit and an adjacent fairing unit.

8. In the method of operating a reusable projectile, The stage of takeoff by igniting the engine of the first stage rocket; A step of operating an actuator through a control unit to open a plurality of pairing units coupled through a hinge joint radially outward; A step of separating the second stage rocket from the first stage rocket while multiple fairing units are open; and A step of returning the above reusable launch vehicle to the ground; A method of operating a reusable launch vehicle, comprising:

9. In paragraph 8, The above operating method is, A step of separating the second stage rocket from the first stage rocket and then operating an actuator through a control unit to close a plurality of open fairing units to close the fairing; A method of operating a reusable launch vehicle, further comprising:

10. In paragraph 9, The above operating method is, A step of fixing the fairing and the first stage rocket using a fixing means so that the fairing and the first stage rocket are maintained in a combined state before the launch vehicle takes off; and A step of releasing the fairing and the fixing of the first stage rocket through the fixing means before opening the plurality of pairing units radially outward; A method of operating a reusable launch vehicle, further comprising:

11. In paragraph 10, The above operating method is, A step of fixing the fairing and the first stage rocket using a fixing means before returning the launch vehicle; A method of operating a reusable launch vehicle, further comprising:

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