JP6502842B2 - How to assemble a fairing - Google Patents

Description

  The present invention relates to a method of assembling a fairing.

  A rocket for launching a spacecraft (payload) such as a satellite is provided with a fairing for protecting the spacecraft. The fairings are connected by fastening bolts having a pair of fairing separators having a separating function. And, when separated from the rocket, the fairing separates from the rocket by the pairing of the fairing separated bodies being separated and craniotomized.

  Patent Document 1 discloses an operation of assembling a fairing having such a pair of fairing separation bodies (fairing pieces) to a rocket at a launch space of the rocket. In the assembling operation disclosed in Patent Document 1, after the payload is mounted on the tip of the rocket, one fairing piece is attached to the tip of the rocket via a craniotomy mechanism. Thereafter, the other fairing piece is attached to the tip of the rocket via a craniotomy mechanism, and the tip of the rocket and the pair of fairing pieces are coupled by a fastening bolt or the like.

JP 2011-235793 A

  In the assembling work of the fairing disclosed in the above-mentioned Patent Document 1, since the operation of attaching the craniotomy mechanism to the tip of the rocket is carried out in the launch site, the working time becomes long, and the assembling work of the fairing (assembly work) There is a problem that the cost of

  An object of the present invention is to solve the above-mentioned conventional problems, and it is an object of the present invention to provide a fairing assembling method capable of shortening the working time and reducing the cost of fairing assembly work at the launch site. .

  A method of assembling a fairing according to the present invention is a method of assembling a fairing comprising a front end and a rear end attached to a front end of a rocket and configured to perform a split craniotomy, the spacecraft at the front end of the rocket The rear end is placed on a mounting adapter for connecting the two, and the mounting adapter and the rear end are coupled by a first fastening member having a separating function, and a craniotomy mechanism is provided between the mounting adapter and the rear end. Step A of attaching, step B of fixing the spacecraft to the mounting adapter, and step of mounting the tip end on the rear end and combining the rear end and the tip by a second fastening member And C.

  By this, it is possible to attach the craniotomy mechanism, which has conventionally been mounted at the launch site, at a factory that manufactures a fairing, it is possible to shorten the working time at the launch site, and thus reduce the cost of assembly work. be able to.

  According to the method of assembling the fairing of the present invention, the working time at the launch site can be shortened, and hence the cost of the assembling work can be reduced.

FIG. 1 is a schematic view showing the fairing according to Embodiment 1 attached to a rocket. FIG. 2A is a schematic view showing a schematic configuration of a craniotomy mechanism of the fairing shown in FIG. FIG. 2B is a schematic view showing a schematic configuration of a craniotomy mechanism of the fairing shown in FIG. FIG. 2C is a schematic view showing a schematic configuration of a craniotomy mechanism of the fairing shown in FIG. FIG. 3A is a schematic view showing a schematic configuration of a connector of the fairing shown in FIG. FIG. 3B is a schematic view showing a schematic configuration of a connector of the fairing shown in FIG. FIG. 3C is a schematic view showing a schematic configuration of a connector of the fairing shown in FIG. FIG. 4A is a process chart schematically showing an assembly operation of the fairing according to the first embodiment. FIG. 4B is a process chart schematically showing an assembly operation of the fairing according to the first embodiment. FIG. 5 is a schematic view showing a state in which the fairing of Modification 1 of Embodiment 1 is mounted on a rocket. FIG. 6 is a schematic view showing the fairing according to the second embodiment mounted on a rocket. FIG. 7A is a process chart schematically showing an assembly operation of the fairing according to the second embodiment. FIG. 7B is a process chart schematically showing an assembly operation of the fairing according to the second embodiment. FIG. 7C is a process chart schematically showing an assembly operation of the fairing according to the second embodiment. FIG. 7D is a process chart schematically showing an assembly operation of the fairing according to the second embodiment.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In all the drawings, the same or corresponding parts are denoted by the same reference numerals, and redundant description will be omitted. Further, in all the drawings, components for explaining the present invention are extracted and illustrated, and the other components may be omitted. Furthermore, the present invention is not limited to the following embodiments.

Embodiment 1
[Structure of fairing]
FIG. 1 is a schematic view showing the fairing according to Embodiment 1 attached to a rocket. 2A, 2B, and 2C are schematic views showing a schematic configuration of a craniotomy mechanism of the fairing shown in FIG. 1, and FIG. 2A is a schematic diagram showing a state before disaggregation of the fairing. 2B is a schematic view showing a state in which the fairing is in a separated craniotomy, and FIG. 2C is a schematic view showing a state in which the fairing is in a separated craniotomy. 3A to 3C are schematic views showing a schematic configuration of the connector of the fairing shown in FIG. 1, FIG. 3A is a schematic view showing a state before separation and craniotomy of the fairing, and FIG. 3B is a fairing FIG. 3C is a schematic view showing a state during separation and craniotomy, and FIG. 3C is a schematic view showing a state after fairing and separation and craniotomy.

  In FIG. 1, the vertical direction of the fairing is shown as the vertical direction in the figure. Moreover, in FIGS. 2A to 3C, part of the fairing is omitted.

  As shown in FIG. 1, the fairing 100 according to the first embodiment includes a cylindrical rear end 101 and a conical front end 102, and the rear end 101 is coupled to the mounting adapter 300. In the state, the tip of the rocket 200 is attached. Further, the fairing 100 has the rear end portion 101 and the front end portion 102 arranged in this order. That is, the rear end portion 101 is positioned downward, and the leading end portion 102 is positioned upward.

  Also, the fairing 100 is configured to be divided along the traveling direction of the rocket 200 (vertical direction in the figure). Specifically, two fairing pieces 100a and 100b are configured to be separated and craniotomized.

  The dividing surfaces of the fairing piece 100a and the fairing piece 100b in the vertical direction constitute a bonding surface 100c, and the radial dividing surfaces of the fairing piece 100a and the fairing piece 100b and the mounting adapter 300 are a bonding surface 100d. Configure

  Moreover, the joint surface 100c of the fairing piece 100a and the fairing piece 100b is couple | bonded (connected) by the 1st fastening member 11 mentioned later. Furthermore, the joint surface 100 d between the fairing piece 100 a and the fairing piece 100 b and the mounting adapter 300 is also coupled (connected) by the first fastening member 11.

  In the first embodiment, a mode in which the joining surface 100d of the fairing piece 100a and the fairing piece 100b and the mounting adapter 300 is joined by the first fastening member 11 is adopted, but the present invention is not limited thereto. A mode may be adopted in which fastening is performed using a fastening member different from the first fastening member 11.

  The mounting adapter 300 is formed in a substantially frustum shape. The upper bottom portion of the mounting adapter 300 is provided with a navigation body side connection portion to which the space navigation body 400 such as a satellite is connected, and the lower bottom portion of the mounting adapter 300 is connected with the tip portion of the rocket 200. Rocket side connections are provided.

  Further, a cylindrical rear end portion 101 is mounted on the mounting adapter 300. Specifically, for example, an outwardly projecting flange may be provided on the lower outer periphery of the mounting adapter 300, and the rear end 101 may be mounted on the upper surface of the flange. The mounting adapter 300 and the rear end portion 101 (i.e., the joint surface 100d) are coupled (connected) by a first fastening member 11 having a separation function.

  The first fastening member 11 may be configured of, for example, a frangible bolt type separation mechanism. Specifically, the first fastening member 11 cuts notched bolts (bolts having grooves (notches) for facilitating cutting) and nuts for fastening the mounting adapter 300 and the rear end portion 101, and nuts, and the notched bolts. It may be composed of a pyrotechnic product. In this case, the flange formed on the inner peripheral surface side of the mounting adapter 300 and the flange formed on the inner peripheral surface side of the rear end portion 101 are fastened with a notched bolt and a nut. The pyrotechnic article is disposed in the vicinity of the notched bolt and the nut.

  Further, at the mounting adapter 300 and the rear end portion 101, a craniotomy mechanism having a hinge member 21 and a craniotomy member 22 and a connector 23 for electrically connecting the spacecraft 400 and the rocket 200 are disposed. The craniotomy mechanism will now be described in detail with reference to FIGS. 2A-2C and the connector 23 will be described in detail with reference to FIGS. 3A-3C.

  As shown in FIGS. 2A to 2C, the hinge member 21 is attached to the outer peripheral surface of the mounting adapter 300 and the outer peripheral surface of the rear end portion 101 so as to straddle the joint surface 100d. Specifically, the hinge member 21 has a first hinge portion 21a and a second hinge portion 21b, and the first hinge portion 21a is attached to the outer peripheral surface of the mounting adapter 300, and the rear end portion is mounted. The second hinge portion 21 b is attached to the outer peripheral surface of the 101.

  The first hinge portion 21a is provided with a hinge pin, and the second hinge portion 21b has a fitting portion that fits with the hinge pin when the fairing piece 100a and the fairing piece 100b are in a coupled state. Provided (none shown). The hinge pin is configured to be released from the fitting portion when the fairing piece 100a or the fairing piece 100b is opened to a predetermined angle (see Japanese Patent Laid-Open No. 2000-185699).

  In the first embodiment, the pair of hinge members 21 may be attached to the mounting adapter 300 and the rear end portion 101 so as to face each other across the axial center of the fairing 100. In other words, assuming that the position at which one of the hinge members 21 is attached (the position in the circumferential direction about the axial center of the fairing 100) of the pair of hinge members 21 is 0 °, the other hinge member The 21 is mounted at the 180 ° position. In the following description, the position at which one hinge member 21 is attached is 0 °, and the arrangement position of the other members will be described.

  In the first embodiment, two pairs of hinge members 21 may be attached to the mounting adapter 300 and the rear end portion 101. In this case, the pair of hinge members 21 are attached so as to face each other across the axial center of the fairing 100. That is, even if one pair of hinge members 21 are attached at 2 ° and 178 °, respectively, and the other pair of hinge members 21 are attached at −2 ° and −178 °, respectively. Good.

  The craniotomy member 22 is attached to the outer peripheral surface of the mounting adapter 300 and the outer peripheral surface of the rear end portion 101 so as to straddle the joint surface 100 d as with the hinge member 21. Specifically, the craniotomy member 22 has a first fixing portion 22a, a second fixing portion 22b, and a spring portion 22c. The upper end portion of the spring portion 22c is swingably fixed to the mounting adapter 300 by the second fixing portion 22b, and the lower end portion abuts on the first fixing portion 22a having a recess to press the recess It is arranged as.

  In addition, when the fairing piece 100a and the fairing piece 100b are coupled, the craniotomy member 22 is fixed to the mounting adapter 300 and the rear end portion 101 in a state where the spring portion 22c is compressed. The spring portion 22c is configured to extend when the piece 100a and the fairing piece 100b are separated and opened.

  Furthermore, when the fairing piece 100a and the fairing piece 100b are opened to a predetermined angle, the lower end portion of the spring portion 22c is disengaged from the first fixing portion 22a (the contact with the first fixing portion 22a is released) And the fixing of the mounting adapter 300 and the rear end portion 101 is released.

  In the first embodiment, the craniotomy member 22 is attached near the joint surface 100c of the fairing piece 100a and the fairing piece 100b. Specifically, in the vicinity of the joint surface 100c of the fairing piece 100a, a pair of craniotomy members 22 are attached so as to face each other. More specifically, for example, one craniotomy 22 is mounted at a position of 88 ° and the other craniotomy 22 is mounted at a position of -88 °. Similarly, in the vicinity of the joint surface of the fairing piece 100b, a pair of craniotomy members 22 are attached so as to face each other.

  As shown in FIGS. 3A to 3C, the connector 23 has a first connector 23 a attached to the other end of the cable 24 a whose one end is connected to the rocket 200 via the mounting adapter 300, and one end is a fairing 100. And a second connector 23b attached to the other end of the cable 24b connected to the. The first connector 23 a and the second connector 23 b are connected when the fairing 100 is assembled, and electrically connect the fairing 100 and the rocket 200.

  The first connector 23 a is fixed to the side surface of the mounting adapter 300. The second connector 23 b is attached to a support member 25 fixed to the inner peripheral surface of the rear end portion 101 by a lanyard 26. The lanyard 26 is configured to have a slack portion (play portion) when the fairing piece 100 a and the fairing piece 100 b are in a coupled state.

  Then, when the fairing piece 100a and the fairing piece 100b are separated and opened, the connector 23 is configured such that the slack of the lanyard 26 disappears and the second connector 23b is pulled out from the first connector 23a.

  Further, as shown in FIG. 1, the rear end portion 101 fastens the panel 27 with a panel 27 having a honeycomb sandwich structure in which CFRP (carbon-back reinforced plastic) or an aluminum plate or the like is bonded to both surfaces of the honeycomb core. A fastening member (for example, a bolt and a nut) 28 is provided. The rear end portion 101 is formed in a cylindrical shape by fastening a plurality of curved panels 27 with a fastening member 28.

  Similarly, the front end portion 102 includes a panel 29 having a honeycomb sandwich structure in which an aluminum plate or the like is adhered to both surfaces of a honeycomb core, and a fastening member (for example, a bolt and a nut) 30 for fastening the panel 29. . The distal end portion 102 is formed in a substantially conical shape by fastening a plurality of curved panels 29 with a fastening member 30.

  The front end portion 102 is placed on the upper end portion of the rear end portion 101, and the joint surface between the rear end portion 101 and the front end portion 102 is coupled (fastened) by the second fastening member 12. The second fastening member 12, the fastening member 28, and the fastening member 30 may be configured by the same member, or may be configured by different members. For example, when each fastening member is formed of a bolt and a nut, the second fastening member 12, the fastening member 28, and the fastening member 30 may have the same size of the bolt and the nut, and the sizes of the bolt and the nut May be different from one another.

  In the first embodiment, the rear end portion 101 and the front end portion 102 are formed of a plurality of panels, but the present invention is not limited to this. For example, the rear end portion 101 may be configured by a pair of semi-cylindrical panels (each formed by a single panel), and similarly, the tip end portion 102 may be a pair of panels ( It may consist of a panel which has the shape which cut a cone to axial direction.

[Separate craniotomy of fairing]
Next, the separation craniotomy of the fairing 100 according to the first embodiment will be described with reference to FIGS. 1 to 3C.

  When the rocket 200 is launched and reaches a predetermined altitude (space), a controller (not shown) controls each device to separate the spacecraft 400 from the rocket 200. Specifically, the pyrotechnic article of the first fastening member 11 is actuated to cut the notched bolt.

  Thereby, the connection of the joining surface 100c of the fairing piece 100a and the fairing piece 100b is released, and the connection of the joining surface 100d of the fairing piece 100a, the fairing piece 100b, and the mounting adapter 300 is released. It is divided into a piece 100a and a fairing piece 100b. Moreover, the spring part 22c of the craniotomy member 22 is extended by dividing the fairing 100 into the fairing piece 100a and the fairing piece 100b (refer FIG. 2A and FIG. 2B).

  Then, the fairing piece 100 a and the fairing piece 100 b are respectively separated from each other centering on the hinge member 21. At this time, as shown in FIG. 3B, the slack of the lanyard 26 disappears along with the craniotomy of the fairing piece 100a and the fairing piece 100b.

  Then, when the fairing piece 100a and the fairing piece 100b are opened up to a predetermined angle, as shown in FIG. 3C, the second connector 23b is pulled out of the first connector 23a. Further, as the craniotomy of the fairing piece 100a and the fairing piece 100b progresses, the craniotomy member 22 is released from the mounting adapter 300 (see FIG. 2C), and the first hinge portion 21a and the second hinge portion 21b separate.

  Thereby, the fairing piece 100 a and the fairing piece 100 b are separated from the rocket 200. The controller then separates the spacecraft 400 from the rocket 200 (loading adapter 300).

[How to assemble the fairing]
Next, a method of assembling the fairing 100 according to the first embodiment will be described with reference to FIGS. 1 to 4B.

  FIG. 4A and FIG. 4B are process diagrams schematically showing the assembly operation of the fairing according to the first embodiment.

  First, as shown in FIG. 4A, each of the rear end portion 101, the tip end portion 102, and the mounting adapter 300 is manufactured at a factory (Step Z). As described above, the rear end portion 101 arranges the plurality of panels 27 in a cylindrical shape, and fastens the respective panels 27 with the fastening members 28. When the rear end portion 101 is constituted by a pair of semi-cylindrical panels 27, these panels 27 are arranged to be cylindrical.

  Further, when the fairing piece 100 a and the fairing piece 100 b are separated and opened, the surface (joining surface 100 c) to be separated is coupled (connected) by the first fastening member 11. Further, the support member 25 is fixed to the inner peripheral surface of the rear end portion 101, and the second connector 23b is attached to the support member 25 by the lanyard 26. In addition, the first connector 23 a is fixed to the side surface of the mounting adapter 300.

  The tip portion 102 arranges a plurality of panels 29 and fastens each panel 29 with a fastening member 30 so as to be conical. Further, when separating and opening the fairing piece 100 a and the fairing piece 100 b, the surface to be separated (joint surface 100 c) is fastened by the first fastening member 11.

  Next, the rear end 101 suspended by a crane (not shown) is moved to the upper side of the mounting adapter 300, and thereafter, the rear end 101 is moved to the lower side and mounted on the mounting adapter 300. Then, the joint surface 100 d of the mounting adapter 300 and the rear end portion 101 is coupled (fastened) by the first fastening member 11, and the hinge member 21 and the craniotomy member 22 are attached to the mounting adapter 300 and the rear end portion 101. Further, the first connector 23a and the second connector 23b of the connector 23 are coupled (Step A).

  Specifically, the flange formed at the upper portion of the mounting adapter 300 and the flange formed at the lower portion of the rear end portion 101 are fastened with a notched bolt and a nut. At this time, the pyrotechnic product is also fastened with the notched bolt and the nut.

  Next, attach the second hinge part 21b to the outer peripheral surface of the rear end part 101, attach the hinge pin of the first hinge part 21a to the fitting part of the second hinge part 21b, and then mount the first hinge part 21a. Attach to

  Further, the craniotomy member 22 fixes the second fixing portion 22b to the rear end portion 101 and fixes the first fixing portion 22a to the mounting adapter 300 in a state in which the spring portion 22c is compressed and fixed by a pin not shown. And attached to the mounting adapter 300 and the rear end 101. Thereafter, the pin is removed from the craniotomy 22.

  Further, the second connector 23b is pushed into the first connector 23a to couple them.

  Next, as shown in FIG. 4B, the spacecraft 400 is mounted on the mounting adapter 300 of the assembly of the mounting adapter 300 and the rear end portion 101 at the launch range of the rocket 200 (step B).

  Next, the front end 102 suspended by a crane not shown is moved above the assembly of the mounting adapter 300 and the rear end 101, and then the front end 102 is moved downward to join the front end 102. Place on At this time, the tip end portion 102 is placed on the joined body so that the bonding surface 100 c of the rear end portion 101 and the bonding surface 100 c of the tip end portion 102 coincide with each other. Next, the joint surfaces of the rear end portion 101 and the front end portion 102 are coupled (fastened) by the second fastening member 12 (step C).

  Then, the fairing 100 assembled in this manner is mounted on the tip of the rocket 200, and the fairing 100 and the rocket 200 are coupled.

  In the assembling method of the fairing 100 according to the first embodiment configured as described above, the craniotomy mechanism (the hinge member 21 and the craniotomy member 22) conventionally attached at the launch site of the rocket 200 is It can be attached at the factory where the back end 101 is manufactured. Also, conventionally, the first connector 23 a and the second connector 23 b that have been coupled can be performed at a launch site of the rocket 200 in a factory that manufactures the rear end portion 101.

  For this reason, since it is not necessary to perform the installation work of the craniotomy mechanism performed conventionally, and the connection work of the connector 23 at the launch site, the work time at the launch site can be shortened, and the operation cost at the launch site Can be reduced. Therefore, the cost of the overall assembly operation of fairing 100 can also be reduced.

  Also, conventionally, the inside of the fairing 100 was accessed from the access door installed in the fairing 100 to perform the mounting operation of the craniotomy mechanism and the coupling operation of the connector 23. There is no need to install an access door because it is not necessary to This can reduce the manufacturing cost of the fairing.

  Further, in the assembly method of the fairing 100 according to the first embodiment, it is only necessary to place the front end portion 102 on the rear end portion 101 from above at the launch site, and positioning of the rear end portion 101 and the front end portion 102 Becomes easy. For this reason, in the launch site, the working time at the launch site can be shortened, as compared with the conventional assembling operation in which one pair of fairing pieces are disposed at the tip of the rocket.

  As a result, the working time at the launch site can be shortened, and the working cost at the launch site can be reduced. Therefore, the cost of the overall assembly operation of fairing 100 can also be reduced.

[Modification 1]
Next, a modified example of the fairing 100 according to the first embodiment will be described with reference to FIG.

  FIG. 5 is a schematic view showing a state in which the fairing of Modification 1 of Embodiment 1 is mounted on a rocket.

  As shown in FIG. 5, the fairing 100 of the first variation of the first embodiment is the same in basic configuration as the fairing 100 according to the first embodiment, but the configuration of the rear end portion 101 is different. Specifically, in the fairing 100 of the first modification, the rear end portion 101 is formed in a truncated cone shape, and the opening on the tip end 102 side is larger than the opening on the mounting adapter 300 side. It is formed.

  Even in the fairing 100 of the first modification configured as described above, the same assembling method as the fairing 100 according to the first embodiment can be applied to the assembling method. For this reason, when the assembling method of the fairing 100 according to the first embodiment is applied, even the fairing 100 according to the first modification exhibits the same function and effect as the fairing 100 according to the first embodiment.

Second Embodiment
[Structure of fairing]
FIG. 6 is a schematic view showing the fairing according to the second embodiment mounted on a rocket.

  As shown in FIG. 6, the basic structure of the fairing 100 according to the second embodiment is the same as that of the fairing 100 according to the first embodiment, but between the rear end portion 101 and the front end portion 102. The difference is that the intermediate portion 103 is further provided.

  The intermediate portion 103 is formed in a cylindrical shape, and has a panel 31 having a honeycomb sandwich structure in which an aluminum plate or the like is adhered to both surfaces of a honeycomb core, and a fastening member (for example, bolt and nut) 32 for fastening the panel 31. And.

  The joint surface of the rear end portion 101 and the intermediate portion 103 is connected (fastened) by the second fastening member 12, and the joint surface of the intermediate portion 103 and the tip end portion 102 is joined (fastened) by the third fastening member 13. ). In addition, the 2nd fastening member 12, the fastening member 32, and the 3rd fastening member 13 may be respectively comprised with the same member, and may be comprised with a different member. For example, when each fastening member is configured by a bolt and a nut, the second fastening member 12, the fastening member 32, and the third fastening member 13 may have the same size of the bolt and the nut, and the bolt and the nut The size of each may be different.

[How to assemble the fairing]
Next, a method of assembling the fairing 100 according to the second embodiment will be described with reference to FIGS. 6 and 7A to 7D.

  7A to 7D are process diagrams schematically showing an assembly operation of the fairing according to the second embodiment.

  First, as shown in FIG. 7A, similarly to the fairing 100 according to the first embodiment, the rear end portion 101, the tip end portion 102, the intermediate portion 103, and the mounting adapter 300 are manufactured at a factory. The middle portion 103 arranges the plurality of panels 31 in a cylindrical shape, and fastens the panels 31 with the fastening member 32. Further, when the fairing piece 100a and the fairing piece 100b are separated and opened, the surface (joining surface 100c) to be separated is coupled (connected) by the first fastening member 11 (step Z).

  Next, as shown in FIG. 7B, the rear end portion 101 is placed on the mounting adapter 300, and the joint surface of the mounting adapter 300 and the rear end portion 101 is coupled (fastened) by the first fastening member 11, The craniotomy member 22 is attached to the mounting adapter 300 and the rear end 101. Further, the first connector 23a and the second connector 23b of the connector 23 are coupled (Step A).

  Next, as shown in FIG. 7C, the tip 102 suspended by a crane (not shown) is moved above the intermediate part 103, and then the tip 102 is moved downward and placed on the intermediate part 103. . At this time, the tip end portion 102 is placed on the middle portion 103 so that the bonding surface 100 c of the middle portion 103 and the bonding surface 100 c of the tip end portion 102 coincide with each other. Then, the joint surfaces of the intermediate portion 103 and the distal end portion 102 are joined (fastened) by the third fastening member 13 to manufacture a joined body of the intermediate portion 103 and the distal end portion 102 (step C1).

  Next, as shown in FIG. 7D, the spacecraft 400 is mounted on the mounting adapter 300 of the stacked body of the mounting adapter 300 and the rear end portion 101 at the launch range of the rocket 200 (step B).

  Next, the joined body of the intermediate portion 103 and the tip end portion 102 suspended by a crane not shown is moved to the upper side of the joined body of the mounting adapter 300 and the rear end portion 101, and then the intermediate portion 103 and the tip end portion 102 are joined. The body is moved downward and placed on the assembly of the mounting adapter 300 and the rear end portion 101. At this time, the joined body of the intermediate portion 103 and the leading end portion 102 is mounted so that the joint surface 100c of the joined portion of the intermediate portion 103 and the leading end portion 102 and the joining surface 100c of the rear end portion 101 coincide with each other. It mounts on the joined object of part 101. Next, the joint surfaces of the rear end portion 101 and the middle portion 103 are coupled (fastened) by the second fastening member 12 (step C2).

  Then, the fairing 100 assembled in this manner is mounted on the tip of the rocket 200, and the fairing 100 and the rocket 200 are coupled.

  Even with the method of assembling the fairing 100 according to the second embodiment configured as described above, the same function and effect as the method of assembling the fairing 100 according to the first embodiment can be obtained.

  From the above description, many modifications or other embodiments of the present invention will be apparent to those skilled in the art. Accordingly, the above description should be taken as exemplary only, and is provided for the purpose of teaching those skilled in the art the best mode of carrying out the present invention. The structural and / or functional details may be substantially altered without departing from the spirit of the present invention.

  The assembly method of the fairing of the present invention is useful because the operation time can be shortened and the cost of the fairing assembly operation can be reduced at the launch site.

11 first fastening member 12 second fastening member 13 third fastening member 21 hinge member 21 a first hinge portion 21 b second hinge portion 22 open head member 22 a first fixed portion 22 b second fixed portion 22 c spring portion 23 connector 23 a first connector 23b second connector 24a cable 24b cable 25 support member 26 lanyard 27 panel 28 fastening member 29 panel 30 fastening member 31 panel 32 fastening member 100 fairing 100a fairing piece 100b fairing piece 100c joint surface 100d joint surface 101 rear end portion 102 Tip 103 Intermediate 200 200 Rocket 300 Adapter 400 Spacecraft

Claims (4)

A method of assembling a fairing comprising a front end and a rear end attached to a front end of a rocket and configured to be separated and cranioptally comprising:
The rear end is mounted on a mounting adapter for mounting a spacecraft at the tip of the rocket, and the mounting adapter and the rear end are coupled by a first fastening member having a separating function, and the mounting adapter and the rear Attaching a craniotomy between the ends;
A process B for fixing the spacecraft to the mounting adapter;
Placing the front end on the rear end and connecting the rear end and the front end by a second fastening member ;
Wherein step A is performed in the manufacturing plant of the fairing, the step B and the step C is Ru place at the launch site of the rocket assembly method of the fairing.
The fairing further includes an intermediate portion disposed between the rear end portion and the front end portion,
Step C places the tip on the middle part, couples the middle and the tip by a third fastening member, and manufactures a joined body of the middle and the tip. The method of assembling the fairing according to claim 1, comprising: a step C2 of placing the joined body on the rear end portion and joining the rear end portion and the joined body by the second fastening member. .   The method for assembling a fairing according to claim 2, wherein the step A to the step C2 are performed in the order of the step A, the step C1, the step B, and the step C2. The rear end portion is formed in a truncated cone shape,
The fairing according to any one of claims 1 to 3, wherein an opening on the tip end side in the rear end portion is formed to be larger than an opening on the mounting adapter side in the rear end portion. Assembly method.

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