Heat-resistant device, attachment device, spacecraft, and deployment control method

Abstract

To reduce a thermal load in re-entry of the atmosphere even in a spacecraft mounted with a loaded article, and recover the spacecraft.SOLUTION: A heat-resistant device is provided in a spacecraft which is mounted with a loaded article and charged to space, and is developed in re-entry into the atmosphere of the spacecraft after separation of the loaded article from the spacecraft. The spacecraft has an attachment for connecting the spacecraft body and the loaded article. The attachment has such a cylindrical shape that an opening is provided at the center on the loaded article side, and includes a tip member which projects from the opening in development and is positioned at a projection position, which is the tip of the spacecraft, a covering part which is connected to the tip member and covers a gap between the tip member positioned at the projection position in the development and the attachment, and a projection mechanism which projects the tip member and the covering part from a storage position where the tip member and the covering part are stored inside the attachment before development to the projection position where the tip member and the covering part project from the opening after the development.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] The present disclosure relates to a heat-resistant device, an attachment device, a spacecraft, and a deployment control method. [Background technology]

[0002] Conventionally, an autonomous recovery spacecraft equipped with a capsule cover has been known as a spacecraft that re-enters the atmosphere and is recovered (see, for example, Patent Document 1). This spacecraft is equipped with a capsule cover, and the capsule cover remains attached even after being inserted into outer space. Therefore, the capsule cover can ensure the heat resistance of the spacecraft even when it re-enters the atmosphere. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Publication No. 04-176799 Summary of the Invention [Problem to be solved by the invention]

[0004] Incidentally, spacecraft include multi-stage rockets that carry payloads such as satellites. In such spacecraft, a fairing covering the tip of the rocket is separated before the satellite is released in order to launch the satellite into space. However, since the spacecraft does not have a fairing after the satellite is released, it cannot withstand the thermal load generated during re-entry into the atmosphere, making it difficult to re-enter the atmosphere.

[0005] Therefore, an object of the present disclosure is to provide a heat-resistant device, an attachment device, a spacecraft, and a deployment control method that can reduce the thermal load during atmospheric re-entry and recover a spacecraft, even if the spacecraft is carrying a payload. [Means for solving the problem]

[0006] The heat-resistant device of the present disclosure is provided on a spacecraft that is launched into outer space while carrying a payload, and is deployed when the spacecraft re-enters the atmosphere after the payload is separated from the spacecraft, wherein the spacecraft has an attachment that connects the spacecraft main body to the payload, and the attachment is tubular with an opening at the center of the payload side, and is equipped with: a tip member that protrudes from the opening at the time of deployment and is located at a protruding position that becomes the tip of the spacecraft; a covering part that is connected to the tip member and covers a gap between the tip member and the attachment, which is located at the protruding position at the time of deployment; and a protrusion mechanism that protrudes from a stored position in which the tip member and the covering part are stored inside the attachment before deployment, to the protruding position in which the tip member and the covering part protrude from the opening after deployment.

[0007] The attachment device of the present disclosure comprises an attachment that connects the spacecraft body and the payload, and the above-mentioned heat-resistant device that is provided on the attachment.

[0008] The spacecraft of the present disclosure comprises a spacecraft body carrying a payload, an attachment connecting the spacecraft body and the payload, and the heat-resistant device described above.

[0009] The deployment control method of the present disclosure causes the heat-resistant device to execute the steps of outputting an activation signal to activate the protrusion mechanism after the load is separated, determining whether or not a detection signal has been input from the covering detection sensor after the activation signal has been output, and determining that deployment has been completed if a detection signal has been input from the covering detection sensor. [Effects of the Invention]

[0010] According to the present disclosure, even for a spacecraft carrying a payload, the thermal load during atmospheric re-entry can be reduced and the spacecraft can be recovered. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a diagram showing a spacecraft according to the first embodiment. [Figure 2] FIG. 2 is a diagram schematically illustrating the heat-resistant device according to the first embodiment. [Figure 3] FIG. 3 is an explanatory diagram of the heat-resistant device as viewed from below. [Figure 4] FIG. 4 is an explanatory diagram regarding the operation of the covering portion. [Figure 5] FIG. 5 is a top view showing an example of the covering portion. [Figure 6] FIG. 6 is an explanatory diagram showing an example of the operation of the heat-resistant device. [Figure 7] FIG. 7 is an explanatory diagram showing an example of the operation of the heat-resistant device. [Figure 8] FIG. 8 is an explanatory diagram showing an example of the operation of the heat-resistant device. [Figure 9] FIG. 9 is an explanatory diagram regarding the operation of the covering part of the heat-resistant device according to the second embodiment. [Figure 10] FIG. 10 is a top view showing an example of the covering portion. [Figure 11] FIG. 11 is a diagram schematically illustrating an attachment device according to the third embodiment. [Figure 12] FIG. 12 is an explanatory diagram regarding the operation of the covering part of the heat-resistant device according to the fourth embodiment. [Figure 13] FIG. 13 is a top view showing an example of a covering part of the heat-resistant device according to the fifth embodiment. [Figure 14] FIG. 14 is an explanatory diagram of the heat-resistant device as viewed from below. [Figure 15] FIG. 15 is a perspective view of an example of a reversing plate of a heat-resistant device. [Figure 16] FIG. 16 is a perspective view of an example of a reversing plate of a heat-resistant device. [Figure 17] FIG. 17 is an explanatory diagram of the operating part of the covering part. [Figure 18] FIG. 18 is an explanatory diagram regarding the operation of the covering portion. DETAILED DESCRIPTION OF THE INVENTION

[0012] Hereinafter, embodiments of the present disclosure will be described in detail with reference to the drawings. However, the present invention is not limited to these embodiments. Furthermore, the components in the following embodiments include those that are easily replaceable by those skilled in the art, or those that are substantially identical. Furthermore, the components described below can be combined as appropriate, and if there are multiple embodiments, the respective embodiments can also be combined.

[0013] [Embodiment 1] The spacecraft 1 of the present disclosure is a spacecraft that re-enters the atmosphere, and is, for example, the upper (second) stage of a multi-stage rocket (hereinafter referred to as rocket 1). Rocket 1 carries a payload P, which may be, for example, a satellite or a supply vehicle. A multi-stage rocket has a fairing attached to its tip that separates during launch. Therefore, rocket 1 travels through space without the fairing and then re-enters the atmosphere.

[0014] FIG. 1 is a diagram showing a spacecraft according to a first embodiment. FIG. 2 is a diagram showing a heat-resistant device according to the first embodiment. FIG. 3 is an explanatory diagram of the heat-resistant device as seen from below. FIG. 4 is an explanatory diagram relating to the operation of the covering part. FIG. 5 is a top view showing an example of the covering part. FIGS. 6 to 8 are explanatory diagrams showing an example of the operation of the heat-resistant device. The spacecraft will be described with reference to FIG. 1.

[0015] (Spacecraft) A rocket 1 as a spacecraft is launched into space. As shown in Fig. 1, the rocket 1 includes a rocket body 3, a payload support structure (PSS) 21 (hereinafter referred to as PSS 21), a payload attachment fitting (PAF) 22 (hereinafter referred to as PAF 22), and a heat-resistant device 23.

[0016] The rocket body 3 includes a frame 5, a fuel tank 6 supported on one side of the frame 5 (the upper side in FIG. 1), an oxidizer tank 7 supported on the other side of the frame 5 (the lower side in FIG. 1), a rocket engine 8 that burns fuel to generate thrust, and an air accumulator 10. The air accumulator 10 is capable of supplying pressurized working gas to the fuel tank 6 and the oxidizer tank 7.

[0017] The fuel tank 6 is, for example, a liquid hydrogen tank that stores liquid hydrogen as fuel and is formed in a cylindrical shape. The fuel tank 6 is capable of supplying liquid hydrogen toward the rocket engine 8 by receiving a supply of working gas from the gas accumulator 10. The oxidizer tank 7 is, for example, a liquid oxygen tank that stores liquid oxygen as an oxidizer and is formed in a cylindrical shape. The oxidizer tank 7 is capable of supplying liquid oxygen toward the rocket engine 8 by receiving a supply of working gas from the gas accumulator 10.

[0018] The rocket engine 8 is provided on the other side of the oxidizer tank 7, that is, on the opposite side of the fuel tank 6 across the oxidizer tank 7. The rocket engine 8 generates thrust by mixing and burning liquid hydrogen supplied from the fuel tank 6 and liquid oxygen supplied from the oxidizer tank 7.

[0019] The PSS 21 is a support for supporting the payload P, and is provided on one side of the fuel tank 6. The PSS 21 is formed in a cylindrical shape that tapers from the rocket body 3 side toward the payload P side. The interior of the PSS 21 is hollow. The other side of the PSS 21 is fixed to the rocket body 3, and the PAF 22 is connected to one side.

[0020] The PAF (attachment) 22 has the function of separating the load P and is provided on one side of the PSS 21. The other end of the PAF 22, which is connected to the PSS 21, is the same size as one end of the PSS 21. The PAF 22 is formed in a cylindrical shape that tapers from the PSS 21 side toward the load P side. The outer circumferential surface of the PAF 22 is continuous with the outer circumferential surface of the PSS 21. Furthermore, a circular opening is provided in the center of one end of the PAF 22. A tip member 31 of the heat-resistant device 23, which will be described later, protrudes through this opening. The PAF 22 has a hollow space inside. The other end of the PAF 22 is fixed to the PSS 21, and the load P is detachably mounted on one side.

[0021] (heat resistant equipment) Next, the heat-resistant device 23 will be described with reference to Figures 2 to 5. The heat-resistant device 23 is housed inside the PSS 21 and the PAF 22, and is deployed when the rocket 1 re-enters the atmosphere. The heat-resistant device 23 includes a tip member 31, a projection mechanism 32, a covering part 33, a covering detection sensor 34, and a control part 35.

[0022] The tip member 31 is a component that protrudes from the opening of the PAF 22 upon deployment and becomes the tip of the rocket 1. The tip member 31 is formed in a circular shape in a plan view and has a curved shape that is convex toward the payload side. The tip member 31 is a seamless component made of a single material, and its outer surface is a continuous surface. The tip member 31 is made of, for example, a heat-resistant material, such as ceramics, CMC (Ceramic Matrix Composites), or PICA (Phenolic Impregnated Carbon Ablators). Before deployment, the tip member 31 is housed inside the PSS 21 and PAF 22 in a stowed position. After deployment, the tip member 31 protrudes from the opening of the PAF 22 in a protruding position. The tip member 31 and a covering portion 33 (described later) are smaller than the opening of the PAF 22 in a plan view from one side when in the stowed position.

[0023] The ejection mechanism 32 is a mechanism for ejecting the tip member 31 from the stored position to the ejected position. The ejection mechanism 32 is provided inside the PSS 21 and the PAF 22, and is provided between the tip member 31 and the PAF 22 and the inner surface of the PAF 22. In other words, the ejection mechanism 32 ejects the tip member 31 using the PAF 22 and the portion connected to the PAF 22 as a fixed point. Before deployment, the ejection mechanism 32 holds the tip member 31 in midair at the stored position inside the PSS 21 and the PAF 22.

[0024] The protruding mechanism 32 includes a link portion 41, a locking portion 42, and a lock-release portion 43. As shown in FIG. 3, a plurality of link portions 41 are arranged at predetermined intervals along the circumferential direction of the tip member 31. The link portion 41 includes a link mechanism 41a that connects the tip member 31 and the PAF 22 and a biasing member 41b that biases the link mechanism 41a. One end of the link mechanism 41a is rotatably connected to the tip member 31, and the other end is rotatably connected to the PAF 22. The link mechanism 41a moves the tip member 31 to the protruding position by the biasing member 41b and fixes the tip member 31 in the protruding position by a latch or the like (not shown). The biasing member 41b is, for example, a compression spring and connects the link mechanism 41a to the inner circumferential surface of the PAF 22. The biasing member 41b biases the link mechanism 41a so as to move the tip member 31 toward the protruding position by contracting. The locking portion 42 locks the link mechanism 41a so that the tip member 31 is in the retracted position against the biasing force of the biasing member 41b. The locking portion 42 is, for example, a tension wire 42a, which restricts the link mechanism 41a toward the retracted position. In other words, the tension wire 42a positions the tip member 31 at the retracted position by expanding the compression spring. As shown in FIG. 3, the tension wire 42a includes a tension wire that bundles the link mechanisms 41a of the multiple link portions 41 arranged in the circumferential direction and a tension wire that restricts the link mechanism 41a toward the retracted position. The locking release portion 43 releases the locking of the link portion 41 by the locking portion 42. The locking release portion 43 is a device that cuts the tension wire 42a. The unlocking unit 43 may be, for example, a device that cuts the wire by electric heat, a device that releases the lock by releasing a pin puller, a device that cuts the wire by pyrotechnics, etc. The unlocking unit 43 is connected to the control unit 35, and performs the unlocking (wire cutting) operation based on an actuation signal output from the control unit 35.

[0025] When an actuation signal is input from the control unit 35, the protruding mechanism 32 releases the lock of the locking unit 42 by the lock release unit 43. As a result, the protruding mechanism 32 is released from the position restriction of the tip member 31 to the stored position by the locking unit 42, and the link unit 41 biases the tip member 31 to the protruding position.

[0026] The covering portion 33 is deployed after the tip member 31 moves to the protruding position, and covers the gap between the tip member 31 and the PAF 22 when the tip member 31 is in the protruding position. As shown in FIGS. 4 and 5 , the covering portion 33 includes a reversing plate member 51 and a flexible member 52. A plurality of reversing plate members 51 are arranged along the gap between the tip member 31 and the PAF 22. The reversing plate members 51 are plate-shaped extending from the tip member 31 toward the PAF 22 and have a curved shape following the outer periphery so as to close the gap. The reversing plate member 51 is connected to the outer periphery of the tip member 31 via a hinge 53. The reversing plate member 51 moves so that its front and back are reversed before and after deployment. Before reversing, the reversing plate member 51 is superimposed on the tip member 31. In other words, the front surface of the reversing plate member 51 faces the outer surface of the tip member 31, and the back surface of the reversing plate member 51 is exposed to the outside. As shown in Fig. 4, before inversion, the tip member 31 and the inversion plate member 51 superimposed thereon are smaller than the opening of the PAF 22 in a plan view from one side, and therefore can move to a protruding position from the opening of the PAF 22. After inversion, the inversion plate member 51 extends from the tip member 31 to the PAF 22, thereby covering the gap between the tip member 31 and the PAF 22. In other words, the front surface of the inversion plate member 51 is exposed to the outside, and the back surface of the inversion plate member 51 is positioned opposite the inside of the PAF 22. The inversion plate member 51 before inversion may be restrained by a restraining member such as a wire.

[0027] Furthermore, after reversal (deployment), the reversal plate member 51 overlaps with the tip component 31 so that its end connected to the tip component 31 is located on the PAF 22 side, and its end covering the PAF 22 is located on the tip component 31 side of the PAF 22. The flow direction of airflow A during re-entry is assumed to be from the tip component 31 toward the PAF 22, and as shown in FIG. 4, the upstream end of the reversal plate member 51 in the flow direction of airflow A flowing from the tip component 31 toward the PAF 22 is located inside and upstream of the tip component 31, and the downstream end of the reversal plate member 51 in the flow direction is located outside and downstream of the PAF 22. Therefore, the reversal plate member 51 does not have a portion that collides with the airflow A, and the airflow A flows along the surface of the reversal plate member 51. The end of the reversal plate member 51 connected to the tip component 31 via a hinge 53 may be U-shaped, as shown in FIG. 4. As a result, after deployment, a part of the reversal plate material 51 overlaps with the end of the tip member 31 so as to enter inside and on the upstream side, making it easier for the airflow A to flow along the surface of the reversal plate material 51.

[0028] The reversal plate 51 is made of a heat-resistant material, similar to the tip member 31, and examples of materials that can be used include ceramics, CMC (Ceramic Matrix Composites), and PICA (Phenolic Impregnated Carbon Ablators).

[0029] The flexible member 52 is a flexible member that covers the gap between adjacent reversal plate members 51. A heat-resistant material such as silica cloth or aluminum silica cloth is used for the flexible member 52. The flexible member 52 is connected to each of the reversal plate members 51 on both sides. The flexible member 52 moves together with the reversal plate members 51 so that the front and back are reversed before and after deployment.

[0030] In addition, the covering part 33 serves as an inversion mechanism for inverting the inversion plate material 51, and is configured as a mechanism for pulling the base part of the inversion plate material 51 on the hinge 53 side using a wire or a spring, etc., thereby inverting the inversion plate material 51 and the flexible member 52.

[0031] The coating detection sensor 34 detects whether the gap between the tip member 31 and the PAF 22 is covered by the coating portion 33. The coating detection sensor 34 is, for example, a touch sensor, and is provided at a location where the reversal plate 51 and the PAF 22 come into contact. The coating detection sensor 34 is connected to the control unit 35, and outputs a detection signal to the control unit 35.

[0032] The control unit 35 controls each part of the heat-resistant device 23. The control unit 35 may be a control device provided in the rocket 1. The control unit 35 includes, for example, an integrated circuit such as a CPU (Central Processing Unit). The control unit 35 executes deployment control of the heat-resistant device 23. After the payload P is detached, the control unit 35 outputs an activation signal to activate the protrusion mechanism 32, and determines that deployment is complete when a detection signal is input from the sheath detection sensor 34. Specifically, as the deployment control, the control unit 35 determines whether or not the payload P has been detached. If the control unit 35 determines that the payload P has been detached, the control unit 35 executes a step of outputting an activation signal to activate the protrusion mechanism 32. After outputting the activation signal, the control unit 35 executes a step of determining whether or not a detection signal has been input from the sheath detection sensor 34. If the control unit 35 determines that a detection signal has been input from the sheath detection sensor 34, the control unit 35 determines that deployment of the heat-resistant device 23 is complete.

[0033] Next, a series of operations of the heat-resistant device 23 will be described with reference to FIGS. 6 to 8. As shown in FIG. 6, before deployment, the heat-resistant device 23 has the tip member 31 located at a storage position inside the PAF 22. When an activation signal is input from the control unit 35, the heat-resistant device 23 activates the locking release unit 43. The heat-resistant device 23 releases the locking of the locking unit 42 by the locking unit 42. As a result, as shown in FIG. 7, the protrusion mechanism 32 releases the position restriction of the tip member 31 to the storage position by the locking unit 42, and the tip member 31 moves to the protruding position due to the bias of the link unit 41. Thereafter, the reversal plate member 51 and the flexible member 52 of the covering unit 33 of the heat-resistant device 23 are reversed, so that the covering unit 33 covers the gap between the tip member 31 and the PAF 22 as shown in FIG. 8.

[0034] In the first embodiment, the heat-resistant device 23 is provided on the rocket 1, but the PAF 22 and the heat-resistant device 23 may be provided as an integral attachment device.

[0035] In addition, in the first embodiment, the tip member 31 is moved from the retracted position to the protruding position by the protruding mechanism 32 including the link mechanism 41a, but any mechanism that moves the tip member 31 from the retracted position to the protruding position is not particularly limited to the protruding mechanism 32 of the first embodiment. The protruding mechanism may be, for example, a mechanism that uses an actuator, or an inflatable mechanism that operates by expanding its volume with a working gas.

[0036] In addition, in embodiment 1, a tension wire 42a is used as the locking portion 42, but it may also be a mechanism that can lock and unlock, such as a mechanism using an electromagnet, a mechanism using a shape memory alloy, or a mechanism using hydraulic chucking.

[0037] [Embodiment 2] Next, a second embodiment will be described with reference to Fig. 9 and Fig. 10. In the second embodiment, to avoid redundant description, only parts different from the first embodiment will be described, and parts having the same configuration as the first embodiment will be described using the same reference numerals. Fig. 9 is an explanatory diagram regarding the operation of the covering part of the heat-resistant device according to the second embodiment. Fig. 10 is a top view showing an example of the covering part.

[0038] The heat-resistant device 70 of the second embodiment is provided with a covering part 71 having a first reversal plate member 75 and a second reversal plate member 76 instead of the covering part 33 of the first embodiment. That is, the covering part 71 has a first reversal plate member 75 and a second reversal plate member 76. A plurality of first reversal plate members 75 are arranged along the gap between the tip member 31 and the PAF 22. Note that the first reversal plate member 75 is similar to the reversal plate member 51 of the first embodiment, and therefore a description thereof will be omitted.

[0039] The second reversal plate 76 covers the gap between adjacent first reversal plate members 75. A plurality of second reversal plate members 76 are provided, each between adjacent first reversal plate members 75. The second reversal plate member 76 has a plate shape extending from the tip member 31 toward the PAF 22, and like the first reversal plate member 75, has a curved shape following the outer periphery so as to close the gap. The second reversal plate member 76 is connected to the outer periphery of the tip member 31 via a hinge 77. The second reversal plate member 76 moves so that its front and back are reversed before and after deployment. Before reversal, the second reversal plate member 76 is overlapped with the tip member 31. In other words, the surface of the second reversal plate member 76 is positioned opposite the outer surface of the tip member 31, and the back surface of the second reversal plate member 76 is exposed to the outside. After the reversal, the second reversal plate 76 extends from the tip member 31 to the PAF 22, thereby covering the gap between the tip member 31 and the PAF 22 and also covering the gap between the first reversal plates 75. In other words, the front surface of the second reversal plate 76 is exposed to the outside, and the back surface of the second reversal plate 76 is positioned opposite the inside of the PAF 22.

[0040] As with the first reversal plate 75, after reversal (deployment), the upstream end of the second reversal plate 76 in the flow direction of the airflow A flowing from the tip member 31 side toward the PAF 22 side is located inside the tip member 31, and the downstream end in the flow direction is located outside the PAF 22. As shown in Fig. 9, the end connected to the tip member 31 may have a U-shaped portion connected via a hinge 77. This results in a portion of the reversal plate 76 overlapping with the end of the tip member 31 so as to enter the inside and upstream side after deployment, making it easier for the airflow A to flow along the surface of the reversal plate 76.

[0041] In the covering portion 71 of embodiment 2, the first reversal plate material 75 is inverted to cover the gap between the tip member 31 and the PAF 22, and then the second reversal plate material 76 is inverted to cover the gap between adjacent first reversal plate materials 75.

[0042] [Embodiment 3] Next, a third embodiment will be described with reference to Fig. 11. In the third embodiment, to avoid redundant description, only parts different from the first and second embodiments will be described, and parts having the same configuration as the first and second embodiments will be described with the same reference numerals. Fig. 11 is a diagram schematically illustrating an attachment device according to the third embodiment.

[0043] In the heat-resistant apparatus 80 of the third embodiment, the reversing mechanism 81 that reverses the reversing plate material 51 of the covering portion 33 is configured as shown in Fig. 11. Fig. 11 shows two reversing mechanisms 81a and 81b.

[0044] The reversing mechanism 81a is a mechanism connected to the protruding mechanism 32 that protrudes the tip member 31. The reversing mechanism 81a is a connecting member that connects the base portion of the reversing plate material 51 on the hinge 53 side with a part of the link mechanism 41a of the protruding mechanism 32. The reversing mechanism 81a reverses the reversing plate material 51 by pulling the base portion of the reversing plate material 51 as the link mechanism 41a moves toward the protruding position due to the biasing force of the biasing member 41b.

[0045] The reversal mechanism 81b includes a biasing member (not shown) provided at the base portion of the reversal plate material 51 on the hinge 53 side, a tension wire 85 that holds the reversal plate material 51 in the position before deployment against the biasing force of the biasing member, and a cutting device (not shown) that cuts the tension wire 85. When the tension wire 85 is cut by the cutting device, the reversal mechanism 81b releases the position restriction of the reversal plate material 51, and the reversal plate material 51 is reversed by the biasing force of the biasing member.

[0046] [Embodiment 4] Next, a fourth embodiment will be described with reference to Fig. 12. In the fourth embodiment, to avoid redundant description, only the parts different from the first to third embodiments will be described, and parts having the same configuration as the first to third embodiments will be described with the same reference numerals. Fig. 12 is an explanatory diagram regarding the operation of the covering part of the heat-resistant device according to the fourth embodiment.

[0047] In the heat-resistant device 90 of the fourth embodiment, the reversing mechanism 91 that reverses the reversing plate material 51 of the covering portion 33 is the mechanism shown in FIG. 12. The reversing mechanism 91 shown in FIG. 12 includes a string-like member 92 provided at the base portion of the reversing plate material 51 on the hinge 53 side, and a fastening mechanism 93 that tightens the string-like member 92. The string-like member 92 is arranged in a ring shape by being stretched across the circumferential direction of the tip member 31 to connect multiple reversing plate materials 51. The fastening mechanism 93 tightens the ring-shaped string-like member 92, thereby reducing the loop size of the string-like member 92. The reversing mechanism 91 reverses the reversing plate material 51 by reducing the loop size of the string-like member 92 using the fastening mechanism 93, thereby pulling the root portion of the reversing plate material 51 inward.

[0048] [Embodiment 5] Next, a fifth embodiment will be described with reference to Figs. 13 to 18. In the fifth embodiment, to avoid repetition, only the parts different from the first to fourth embodiments will be described, and parts having the same configuration as the first to fourth embodiments will be described using the same reference numerals. Fig. 13 is a top view showing an example of a covering part of a heat-resistant device according to the fifth embodiment. Fig. 14 is an explanatory diagram of the heat-resistant device as seen from below. Fig. 15 is a perspective view of an example of a reversing plate of the heat-resistant device. Fig. 16 is a perspective view of an example of a reversing plate of the heat-resistant device. Fig. 17 is an explanatory diagram of the operating part of the covering part. Fig. 18 is an explanatory diagram of the operation of the covering part.

[0049] The heat-resistant device 100 of the fifth embodiment has a covering part 101 obtained by adding an operating part 107 to the covering part 71 of the second embodiment. That is, the covering part 101 has a first reversal plate member 105, a second reversal plate member 106, and the operating part 107. The first reversal plate member 105 and the second reversal plate member 106 are partially different from the first reversal plate member 75 and the second reversal plate member 76 of the second embodiment, and therefore only the different parts will be described.

[0050] The first reversal plate member 105 and the second reversal plate member 106 form an overlapping portion where their ends in the circumferential direction of the tip member 31 overlap. As shown in FIG. 13, the first reversal plate members 105 and the second reversal plate members 106 are alternately arranged in the circumferential direction of the outer periphery of the tip member 31. As shown in FIG. 16, the first reversal plate member 105 and the second reversal plate member 106 are fitted together at the overlapping portion. Furthermore, the first reversal plate member 105 and the second reversal plate member 106 are fitted together at the overlapping portion so that their surfaces are connected to each other after deployment. At this time, the overlapping portion of the first reversal plate member 105 and the second reversal plate member 106 forms a labyrinth seal 109 by fitting together.

[0051] The first reversal plate 105 and the second reversal plate 106 are connected to the outer periphery of the tip member 31 via hinges 108. As shown in FIG. 15 , the hinges 108 are provided on the surfaces of the first reversal plate 105 and the second reversal plate 106, respectively, and are arranged closer to the tip member 31. The hinges 108 are provided on an axis of symmetry I on the surface of the tip member 31, about which the shapes are symmetrical. The axis of symmetry I is an axis extending from the tip member 31 to the PAF 22.

[0052] 17 and 18, the actuating unit 107 is provided at the center inside the tip member 31. The actuating unit 107 has a motor 110, a first actuating wire 111, a second actuating wire 112, a first winding mechanism 115, and a second winding mechanism 116.

[0053] The motor 110 is a drive source, and is connected to the control unit 35, and its drive is controlled by the control unit 35. The motor 110 is a motor that can rotate forward and backward, rotating in the forward direction when the first reversible plate material 105 is reversing, and rotating in the reverse direction when the second reversible plate material 106 is reversing. The motor 110 drives when the first operating wire 111 is wound by the first winding mechanism 115, and also drives when the second operating wire 112 is wound by the second winding mechanism 116. A reduction gear is provided on the output shaft of the motor 110 according to the required drive torque and rotation speed.

[0054] A first operating wire 111 connects the motor 110 and the first reversing plate member 105. The first operating wire 111 is connected to the motor 110 via a first winding mechanism 115. A wire guide 117 (see FIG. 18 ) that guides the first operating wire 111 is provided between the motor 110 and the first reversing plate member 105. The first operating wire 111 is provided along the wire guide 117.

[0055] The second actuation wire 112 connects the motor 110 and the second reversal plate member 106. The second actuation wire 112 is connected to the motor 110 via a second winding mechanism 116. Similar to the first actuation wire 111, a wire guide 117 (not shown) that guides the second actuation wire 112 is provided between the motor 110 and the second reversal plate member 106. The second actuation wire 112 is provided along the wire guide 117.

[0056] The first winding mechanism 115 is attached to the rotating shaft of the motor 110, and winds up the first operating wire 111 when the motor 110 rotates in the forward direction. The first winding mechanism 115 has a forward rotation latch 121 and a forward rotation pulley 122 that rotates together with the forward rotation latch 121. The forward rotation latch 121 rotates when the motor 110 rotates in the forward direction, but does not rotate when the motor 110 rotates in the reverse direction. The first operating wire 111 is wound around the forward rotation pulley 122.

[0057] The second winding mechanism 116 is attached to the rotary shaft of the motor 110 and winds the second operating wire 112 when the motor 110 rotates in reverse. The second winding mechanism 116 is provided coaxially with the first winding mechanism 115. The second winding mechanism 116 has a reverse latch 124 and a reverse pulley 125 that rotates together with the reverse latch 124. The reverse latch 124 rotates when the motor 110 rotates in reverse, but does not rotate when the motor 110 rotates in forward. The second operating wire 112 is wound around the reverse pulley 125.

[0058] Next, the operation of the covering unit 101 will be described with reference to FIG. 18 . When the first reversing plate 105 and the second reversing plate 106 are deployed, the control unit 35 rotates the motor 110 of the actuation unit 107 in the forward direction. When the motor 110 rotates in the forward direction, the forward rotation pulley 122 rotates in the forward direction together with the forward rotation latch 121, thereby winding up the first actuation wire 111. When the first actuation wire 111 is wound up, the base portion of the first reversing plate 105 is pulled, causing the first reversing plate 105 to reverse. Thereafter, although not shown in the drawings, the control unit 35 rotates the motor 110 of the actuation unit 107 in the reverse direction. When the motor 110 rotates in the reverse direction, the reverse rotation pulley 125 rotates in the reverse direction together with the reverse rotation latch 124, thereby winding up the second actuation wire 112. When the second actuation wire 112 is wound up, the root portion of the second reversal plate 106 is pulled, causing the second reversal plate 106 to reverse.

[0059] As described above, the heat-resistant device 23, the attachment device, the spacecraft 1, and the deployment control method described in this embodiment can be understood, for example, as follows.

[0060] The heat-resistant device 23 according to the first aspect is provided on a spacecraft (rocket 1) that is launched into outer space while carrying a payload P, and is deployed when the spacecraft re-enters the atmosphere after the payload P is separated from the spacecraft. The spacecraft has an attachment (PAF 22) that connects the spacecraft main body (rocket main body 3) and the payload P. The attachment has a cylindrical shape with an opening at the center on the payload P side, and is equipped with a tip member 31 that protrudes from the opening at the time of deployment and is located at a protruding position that becomes the tip of the spacecraft, a covering part 33 that is connected to the tip member 31 and covers the gap between the tip member 31 and the attachment, which is located at the protruding position at the time of deployment, and a protrusion mechanism 32 that protrudes from a storage position where the tip member 31 and the covering part 33 are stored inside the attachment before deployment to a protruding position where the tip member 31 and the covering part 33 protrude from the opening after deployment.

[0061] According to this configuration, even in a spacecraft carrying a payload, the tip member 31 can be protruded and the gap between the tip member 31 and the attachment can be covered with the covering part 33. Therefore, even when the spacecraft re-enters the atmosphere after the payload P is separated, the thermal load can be reduced by the tip member 31 and the covering part 33, making it possible to recover the spacecraft.

[0062] As a second aspect, in the heat-resistant device 23 according to the first aspect, the tip member 31 has a curved surface shape that is convex toward the load P side.

[0063] According to this configuration, the shape of the tip member 31 can be made suitable for reducing the thermal load during re-entry into the atmosphere.

[0064] As a third aspect, in the heat-resistant device 23 according to the first or second aspect, the protrusion mechanism 32 is provided between the tip member 31 and the attachment, and the tip member 31 is held in the air inside the attachment.

[0065] According to this configuration, the tip member 31 and the protruding mechanism 32 can be housed and held inside the attachment without being provided on the spacecraft body, and therefore the heat-resistant device 23 can be placed without affecting the spacecraft body.

[0066] As a fourth aspect, in the heat-resistant device 23 relating to any one of the first to third aspects, the protrusion mechanism 32 has a link portion 41 that connects the tip member 31 and the attachment and biases it toward the protruding position, a locking portion 42 that locks the tip member 31 in the storage position against the bias of the link portion 41, and an unlocking portion 43 that releases the locking by the locking portion 42.

[0067] According to this configuration, by releasing the locking by the locking portion 42 with the locking release portion 43, the tip member 31 can be protruded by the biasing force of the link portion 41. Therefore, the tip member 31 can be protruded by the protrusion mechanism 32 having a simple configuration.

[0068] As a fifth aspect, in the heat-resistant device 23 relating to any one of the first to fourth aspects, the covering portion 33 is provided on the tip member 31 side and has a reversing plate material 51 that is reversed from the tip member 31 side to the attachment side when deployed.

[0069] According to this configuration, by reversing the reversible plate member 51, the gap between the tip member 31 and the attachment can be easily covered.

[0070] As a sixth aspect, in the heat-resistant device 23 according to the fifth aspect, after the reversal plate material 51 is deployed, the upstream end in the flow direction of the air flow A flowing from the tip member 31 side toward the attachment side is located inside the tip member 31, and the downstream end in the flow direction is located outside the attachment.

[0071] According to this configuration, the airflow A can flow along the surface of the reversal plate material 51 without colliding with the reversal plate material 51.

[0072] As a seventh aspect, in the heat-resistant device 23 according to the fifth aspect, the reversing plate materials 51 are arranged in a row along the gap formed between the tip member 31 and the attachment, and the covering portion 33 further has a flexible flexible member 52 that covers the gap between adjacent reversing plate materials 51.

[0073] According to this configuration, the flexible member 52 can suitably cover the gaps formed between the reversal plate members 51 .

[0074] As an eighth aspect, in the heat-resistant device 23 according to the fifth aspect, the reversal plate material 51 has a plurality of first reversal plate materials 75, 105 arranged in a line along the gap formed between the tip member 31 and the attachment, and a plurality of second reversal plate materials 76, 106 arranged between adjacent first reversal plate materials 75, 105.

[0075] According to this configuration, by reversing the first reversible plate members 75, 105 and the second reversible plate members 76, 106, the gap between the tip member 31 and the attachment can be easily covered.

[0076] As a ninth aspect, in the heat-resistant device 23 according to the eighth aspect, the overlapping portion between the first reversal plate material 105 and the second reversal plate material 106 is a labyrinth seal 109 formed by fitting them together.

[0077] According to this configuration, it is possible to prevent the airflow A from flowing in from the overlapping portion between the first reversal plate material 105 and the second reversal plate material 106.

[0078] As a tenth aspect, in the heat-resistant device 23 relating to the eighth aspect, the covering part 101 further has an operating part 107 that inverts the first inversion plate material 105 and the second inversion plate material 106, and the operating part 107 includes a motor 110 as a driving source, a first operating wire 111 that connects the motor 110 and the first inversion plate material 105, a second operating wire 112 that connects the motor 110 and the second inversion plate material 106, a first winding mechanism 115 that winds up the first operating wire 111 when the motor 110 rotates forward, and a second winding mechanism 116 that winds up the second operating wire 112 when the motor 110 rotates reversely.

[0079] According to this configuration, the forward and reverse rotation of the motor 110 can be used to reverse the first reversible plate material 105 and the second reversible plate material 106 .

[0080] As an eleventh aspect, the heat-resistant device 23 according to any one of the first to tenth aspects further includes a coating detection sensor 34 that detects the coating of the gap between the tip member 31 and the attachment by the coating portion 33, and a control unit 35 to which the coating detection sensor 34 is connected, and the control unit 35 outputs an activation signal to activate the protrusion mechanism 32 after the load P is detached, and when a detection signal is input from the coating detection sensor 34, determines that deployment is complete.

[0081] According to this configuration, it is possible to detect that the deployment of the heat-resistant device 23 has been completed.

[0082] The attachment device according to the twelfth aspect comprises an attachment that connects the spacecraft body and the payload P, and a heat-resistant device 23 according to any one of the first to eleventh aspects that is provided on the attachment.

[0083] According to this configuration, it is possible to provide a device in which the heat-resistant device 23 and the attachment are integrated.

[0084] A spacecraft according to a thirteenth aspect comprises a spacecraft main body carrying a payload P, an attachment connecting the spacecraft main body to the payload, and a heat-resistant device 23 according to any one of the first to eleventh aspects.

[0085] According to this configuration, by deploying the heat-resistant device 23, the spacecraft can re-enter the atmosphere, making it possible to make the spacecraft recoverable.

[0086] The deployment control method of the 14th aspect causes the heat-resistant device 23 of the 11th aspect to execute the steps of outputting an activation signal to activate the protrusion mechanism 32 after the load P is detached, determining whether or not a detection signal has been input from the covering detection sensor 34 after the activation signal is output, and determining that deployment is complete if a detection signal has been input from the covering detection sensor 34.

[0087] According to this configuration, it is possible to detect that the deployment of the heat-resistant device 23 has been completed. [Explanation of symbols]

[0088] 1. Rocket 3. Rocket body 5 frames 6 fuel tank 7. Oxidizer Tank 8. Rocket Engine 10 Air Storage Tank 21 PSS 22 PAF 23 Heat resistant equipment 31 Tip member 32 Ejection mechanism 33 Covering section 34 Coverage detection sensor 35 Control Unit 41 Link section 42 Locking part 43 Unlocking part 51 Reversed board 52 Flexible member 53 Hinge 70 Heat-resistant device (embodiment 2) 71 Covering part 75 First Reversed Plate 76 Second Reversed Plate 80 Heat-resistant device (embodiment 3) 81 Reversal mechanism 90 Heat-resistant device (embodiment 4) 91 Reversal mechanism 92 String-like member 100 Heat-resistant device (embodiment 5) 101 Covering part 105 First Reversed Plate 106 Second Reversed Plate 107 Operating unit 109 Labyrinth Seal 110 Motor 111 first actuation wire 112 second actuation wire 115 First winding mechanism 116 Second winding mechanism P Load A. Airflow

Claims

1. 1. A heat-resistant device that is provided on a spacecraft that is launched into outer space while carrying a payload, and that is deployed when the spacecraft re-enters the atmosphere after the payload is separated from the spacecraft, comprising: the spacecraft has an attachment that connects the spacecraft body to the payload, The attachment has a cylindrical shape with an opening at the center on the load side, a tip member that protrudes from the opening during deployment and is located at a protruding position that becomes the tip of the spacecraft; a covering portion connected to the tip member and covering a gap between the tip member located at the protruding position when deployed and the attachment; a protrusion mechanism that protrudes the tip member and the covering portion from a storage position in which the tip member and the covering portion are stored inside the attachment before deployment to a protrusion position in which the tip member and the covering portion protrude from the opening after deployment.

2. 2. The heat-resistant device according to claim 1, wherein the tip member has a curved surface that is convex toward the load side.

3. the protruding mechanism is provided between the tip member and the attachment, 2. The heat-resistant device according to claim 1, wherein the tip member is held in the air inside the attachment.

4. The protruding mechanism includes: a link portion that connects the tip member and the attachment and biases them toward the protruding position; a locking portion that locks the tip member at the storage position against the biasing force of the link portion; The heat-resistant device according to claim 1 , further comprising: an unlocking portion that unlocks the locking portion.

5. The heat-resistant device according to claim 1 , wherein the covering portion is provided on the tip member side and has a reversible plate member that is reversed from the tip member side to the attachment side when deployed.

6. The heat-resistant device described in claim 5, wherein, after deployment, the upstream end of the reversing plate in the flow direction of the airflow flowing from the tip member side toward the attachment side is located inside the tip member, and the downstream end in the flow direction is located outside the attachment.

7. A plurality of the reversing plates are arranged along a gap formed between the tip member and the attachment, The heat-resistant device according to claim 5 , wherein the covering portion further comprises a flexible member that covers a gap between adjacent reversal plates.

8. The inverted plate material is A plurality of first reversal plates are arranged along a gap formed between the tip member and the attachment; The heat-resistant device according to claim 5 , further comprising: a plurality of second inversion plates disposed between adjacent first inversion plates.

9. The heat-resistant device according to claim 8, wherein the overlapping portion of the first reversal plate and the second reversal plate is fitted together to form a labyrinth seal.

10. The covering portion is Further comprising an operating unit that inverts the first inversion plate material and the second inversion plate material, The actuation unit is a motor serving as a drive source; a first actuation wire connecting the motor and the first reversal plate; a second actuation wire connecting the motor and the second reversal plate; a first winding mechanism that winds the first operating wire when the motor rotates forward; 9. The heat-resistant device according to claim 8, further comprising: a second winding mechanism that winds the second operating wire when the motor rotates in reverse.

11. a coating detection sensor that detects the coating of the gap between the tip member and the attachment by the coating portion; a control unit to which the coating detection sensor is connected, The heat-resistant device according to claim 1, wherein the control unit outputs an activation signal to activate the protrusion mechanism after the load is separated, and determines that deployment is complete when a detection signal is input from the covering detection sensor.

12. an attachment that connects the spacecraft body and the payload; An attachment device comprising: a heat-resistant device according to any one of claims 1 to 11 provided on the attachment.

13. a spacecraft body carrying a payload; an attachment that connects the spacecraft body and the payload; A spacecraft comprising the heat-resistant device according to any one of claims 1 to 11.

14. The heat-resistant device according to claim 11, outputting an actuation signal to actuate the ejection mechanism after the load is released; a step of determining whether or not a detection signal is input from the coating detection sensor after outputting the activation signal; and determining that deployment is complete when a detection signal is input from the cover detection sensor.

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