JP4771470B2 - Propellant tank integrated structure panel - Google Patents

Description

  The present invention relates to a propellant tank integrated structure panel in which a structural panel constituting a structure of a spacecraft such as an artificial satellite and a planetary probe is integrated with a propellant tank.

  Spacecraft systems such as artificial satellites (meteorological / observation satellites, communication / broadcasting satellites, scientific satellites), planetary explorers, etc. are required to carry out the missions of the spacecraft. It consists of “bus equipment” required as a basic function. The bus device further includes subsystems such as a communication system, a power supply system, a propulsion system, an attitude control system, a structural system, and a thermal control system.

The spacecraft propulsion system includes an apogee engine 101, a thruster 102, and a propellant tank 103, 104 as shown in FIG. 10, but also includes valves, sensors, piping, etc. (not shown). 105. Usually, one to a plurality of propellant tanks 103 and 104 are mounted.
The propellant tank is required to withstand use at high pressure and to be as light as possible. For this reason, the propellant tank is often a spherical shape that has high rigidity and can be thinned, and occupies much of the internal space of the spacecraft.
In addition, as a prior art document regarding the propulsion system of a spacecraft, for example, there is Patent Document 1 below.

JP 2004-196138 A

By the way, in recent years, it has been desired that the propulsion system be modularized as a common bus from the viewpoints of cost reduction in the manufacture of spacecrafts and improvement in the degree of freedom for mounting mission equipment.
As the propulsion system common bus, it is desirable that the propulsion system is a propulsion system module equipped only on the bottom panel (structure panel) of the structure.
However, when there are two to three propellant tanks and the propellant tanks are arranged three-dimensionally with respect to the bottom panel (the propellant tank shown in FIG. 10 corresponds to this), the propellant tanks are spherical. For this reason, it is considered that it is structurally advantageous to support the propellant tank from the side panel with a support truss or the like, rather than supporting the propellant tank only with the bottom panel. When the propellant tank is supported by the bottom panel and the side panel, the propulsion equipment must be changed each time depending on the shape and arrangement of the mission equipment. On the other hand, when the arrangement and number of propellant tanks are specified, the degree of freedom of arrangement of mission equipment is limited.

  From the above, it is impossible to equip the propulsion system uniformly only on the bottom panel, and for this reason, it is difficult to configure the propulsion system module as a propulsion system common bus. For this reason, there has been a problem that it is difficult to improve the degree of freedom of installation of the mission equipment and to equip the propulsion system without being affected by the arrangement of the mission equipment.

  The present invention has been made in view of such a problem, and by configuring a propulsion system module as a propulsion system common bus in a spacecraft, the improvement in the degree of freedom of mounting mission equipment and the influence on the arrangement of mission equipment are affected. An object of the present invention is to provide a propellant tank integrated structure panel that can realize propulsion of the propulsion system that is not affected.

In order to achieve the above object, the propellant tank integrated structure panel according to the present invention employs the following means.
(1) That is, the propellant tank integrated structural panel according to the present invention is a propellant tank integrated structural panel in which a structural panel constituting a spacecraft structure and a propellant tank are integrated. An outer frame serving as a skeleton, and a propellant tank formed inside the outer frame, the propellant tank having a flat shape, and wall portions constituting both side portions of the propellant tank are respectively honeycombs The reinforcing plate is composed of a honeycomb panel composed of a core and a front plate and a back plate bonded to both sides of the honeycomb core, and a reinforcing member is provided in the propellant tank to connect the wall portions constituting the both side portions. It is characterized by that.

  As described above, since the spherical propellant tank, which has conventionally occupied a large area in the spacecraft structure, has a flat shape (flat plate) and is integrated with the structural panel, the propulsion system module is configured as a common propulsion system bus. be able to. As a result, it is possible to improve the degree of freedom of mounting the mission equipment and to implement the propulsion equipment that is not affected by the arrangement of the mission equipment.

Further, since the propellant tank is pressurized to supply the propellant to the propulsion device (thruster or apogee engine), the central portion of the propellant tank is deformed simply by having a flat shape. In order to suppress such deformation, the thickness of the shell of the flat tank is such that the stress acting on the shell (outer shell) of this flat tank is about the same as that of a spherical tank with the same internal volume. Is set, the mass becomes, for example, 100 times or more that of a spherical tank. This is not realistic at all.
Therefore, in the present invention, a reinforcing member is provided in the propellant tank to connect the wall portions constituting both side portions of the tank, and the wall portions are formed of a honeycomb panel. Since it comprised in this way, the deformation | transformation to the outer surface direction of the part in which the reinforcement member was provided is suppressed by the reinforcement member. Further, with the reinforcing member alone, the non-reinforcing portion (the portion between the reinforcing member and the reinforcing member) where the reinforcing member is not provided is swelled in the out-of-plane direction, but the wall of the propellant tank is lightweight. In addition, by configuring the honeycomb panel with excellent rigidity, deformation of the non-reinforced portion in the outer surface direction can be suppressed. As a result, the weight of the propellant tank integrated structure panel can be suppressed to the same level as the total weight of the conventional spherical tank and the bottom panel.

(2) In the propellant tank integrated structure panel according to (1), a plurality of the reinforcing members are radially arranged so as to partition the inside of the propellant tank into a plurality of small sections whose cross-sectional area decreases toward the center. It is characterized by being arranged.

  As described above, the reinforcing members are radially arranged so as to divide the inside of the propellant tank into a plurality of small sections whose cross-sectional area decreases toward the center. Since the reinforcing members are concentrated, the swelling at the center of the tank can be effectively suppressed.

(3) In the propellant tank integrated structure panel of (2), all the small sections communicate with each other in the outer peripheral portion of the propellant tank, and a gas for pressurization is provided in the outer peripheral portion of the propellant tank. A gas supply means for supplying the propellant is connected, and a discharge mechanism for discharging the propellant is connected to the central portion of the propellant tank.

As described above, since all the small sections communicate with each other in the outer peripheral portion of the propellant tank, it is not necessary to provide a gas supply means for each small section, and the configuration can be simplified. Such a form can be applied to a one-pack type in which the propellant that can be filled in the tank is one kind, and thus the propellant (fuel) is reacted with a catalyst to obtain a reaction gas. Alternatively, as will be described later, this propellant tank integrated structure panel can be made into a two-liquid type by having two stages and filling one side with fuel and filling the other with oxidant.
In addition, since a plurality of reinforcing members are radially arranged so as to partition the inside of the propellant tank into a plurality of small sections whose cross-sectional area decreases toward the center, the propellant is held by the surface tension, and the outer periphery of the tank By supplying the gas for pressurization from the part, the propellant can be pushed toward the center of the tank and discharged efficiently from the discharge mechanism connected to the center part.

(4) In the propellant tank integrated structure panel of (3), the inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other by a part of the plurality of reinforcing members. The plurality of small sections are formed in the large section, and in each of the large sections, all the small sections in the same large section communicate with each other at the outer periphery of the propellant tank,
A gas supply means for supplying a gas for pressurization is connected to the outer periphery of the propellant tank for each of the large compartments, and a propellant is supplied to the central portion of the propellant tank for each of the large compartments. A discharge mechanism for discharging is connected.

  Thus, since the inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other, a two-component propellant tank can be obtained. In addition, a gas supply means and a discharge mechanism are provided for each large compartment, and a plurality of small compartments are formed in the large compartment. can do.

(5) In the propellant tank integrated structure panel of (2) above, all the small sections communicate with each other in the outer peripheral portion of the propellant tank, and a gas for pressurization is provided in the central portion of the propellant tank. A gas supply means is connected to the outer periphery of the propellant tank, and one or more discharge mechanisms for discharging the propellant are connected to the outer periphery of the propellant tank.

As described above, since all the small sections communicate with each other in the outer peripheral portion of the propellant tank, it is not necessary to provide a gas supply means for each small section, and the configuration can be simplified.
In the case of a spin attitude stabilization type spacecraft that rotates and stabilizes its attitude, the propellant is subject to a centrifugal force much stronger than the surface tension, and the propellant is on the outer periphery of the propellant tank. Stick to. By disposing the gas supply means at the center and the discharge mechanism at the outer peripheral portion, the propellant is pushed out from the center toward the outer periphery, so that the propellant can be discharged efficiently without countering the centrifugal force.

(6) In the propellant tank integrated structure panel according to (5), the inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other by a part of the plurality of reinforcing members. The plurality of small sections are formed in the large section, and in each of the large sections, all the small sections in the same large section communicate with each other at the outer periphery of the propellant tank,
A gas supply means for supplying a pressurizing gas is connected to the central portion of the propellant tank for each of the large compartments, and a propellant is supplied to the outer peripheral portion of the propellant tank for each of the large compartments. A discharge mechanism for discharging is connected.

  Thus, since the inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other, a two-component propellant tank can be obtained. In addition, a gas supply means and a discharge mechanism are provided for each large compartment, and a plurality of small compartments are formed in the large compartment. can do.

(7) In the propellant tank integrated structure panel according to (4) or (6), the large section is obtained by equally dividing the interior of the propellant tank into four.

  Thus, since the inside of the propellant tank is equally divided into four, the center of gravity can be set to the center by alternately filling the fuel and the oxidant into the four sections.

(8) The propellant tank integrated structure panel is characterized in that the propellant tank integrated structure panel described in (3) or (5) above is stacked in two stages.

  In this way, the two-stage propellant tank-integrated structure panel can be used, and one side can be filled with fuel and the other side can be filled with an oxidant.

  According to the present invention, by configuring a propulsion system module as a propulsion system common bus in a spacecraft, it is possible to improve the degree of freedom of mounting mission equipment and to implement propulsion equipment that is not affected by the arrangement of mission equipment. Excellent effect is obtained.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

[First Embodiment]
FIG. 1 is a perspective view of a propellant tank integrated structure panel 10 according to a first embodiment of the present invention. FIG. 2 is a partially enlarged view of a cross section taken along line II in FIG. 3 is a cross-sectional view taken along line II-II in FIG.
This propellant tank integrated structural panel 10 is obtained by integrating a propellant tank 17 with a structural panel (for example, a lower panel) constituting a structure of a spacecraft such as an artificial satellite or planetary probe. The spacecraft in which the propellant tank integrated structure panel 10 of the present embodiment is used is assumed to be a three-axis attitude control method and the structure is a box type. For this reason, the propellant tank integrated structure panel 10 according to the present embodiment is configured in a rectangular shape as a whole.

As shown in FIGS. 1 to 3, the propellant tank integrated structural panel 10 includes an outer frame 12 that is a skeleton of the structural panel, and a propellant tank 17 formed inside the outer frame 12.
The outer frame 12 is a long frame member 13 (see FIG. 4 (a)) having a cross-sectional shape with two large and small U-shaped parts 13a and 13b back to back so that the large U-shaped part 13a is on the outside. A long beam member 14 having a similar cross-sectional shape at the four corners (but shorter than the frame member 13 constituting the rectangle) is obliquely attached to the four corners, thereby making its inner shape an octagon. Yes. The shape of the outer peripheral portion of the propellant tank 17 is determined by the shape inside the outer frame 12. As the material of the outer frame 12, for example, a titanium alloy or stainless steel can be used.
Moreover, the frame member 13 and the beam member 14 have a plurality of reinforcing plates 15 at intervals in the longitudinal direction of the frame member 13 and the beam member 14 inside the large U-shaped portion 13a.

  In this embodiment, the frame member 13 is formed by integrally molding two large and small U-shaped characters 13a and 13b. However, the two large and small U-shaped characters 13a and 13b are separately manufactured and joined by welding or the like. May be. Further, the inner shape of the outer frame 12 is not limited to an octagon, and may be a polygon of 7 or less or 9 or more.

As shown in FIG. 1, the propellant tank 17 has a flat shape. Moreover, in this embodiment, since the inner side of the outer frame 12 is octagonal as mentioned above, the propellant tank 17 is also octagonal. As shown in FIG. 2, the small U-shaped portion 13 b of the outer frame 12 constitutes the outer peripheral portion of the propellant tank 17.
In addition, as shown in FIG. 2, the wall portions constituting both surface portions of the propellant tank 17 are constituted by a honeycomb panel 19. The honeycomb panel 19 includes a honeycomb core 20 and a front plate 21 and a back plate 22 bonded to both surfaces of the honeycomb core 20. Here, the honeycomb core 20 refers to a structure in which a plurality of cells each having a cylindrical wall body having a hollow portion inside and open at both ends are arranged so as to be adjacent to each other through the wall body.
As the material of the honeycomb core 20, for example, an aluminum alloy can be used. For example, CFRP (Carbon Fiber Reinforced Plastics) or an aluminum alloy can be used as the material of the surface plate 21. As the material of the back plate 22, for example, a titanium alloy or stainless steel can be used.

As shown in FIGS. 2 and 3, the propellant tank 17 is provided with a plurality of reinforcing members 24 that connect the wall portions and suppress deformation in the out-of-plane direction of the tank. In the present embodiment, a plurality of reinforcing members 24 are arranged radially so as to partition the inside of the propellant tank 17 into a plurality of small sections whose cross-sectional area decreases toward the center. In the present embodiment, 24 small sections are formed by 24 reinforcing members 24. As a material of the reinforcing member 24, for example, a titanium alloy or stainless steel can be used.
The number of reinforcing members 24 is not limited to 24 and may be 23 or less or 25 or more.

As shown in FIG. 3, the small sections merge at the center of the tank. Moreover, the propellant tank 17 has the communication part 26 inside an outer peripheral part, as shown in FIG. Each small section communicates with an adjacent small section at the outer peripheral portion (radially outer end portion) of the propellant tank 17 through the communication portion 26. That is, all the small sections communicate with each other in the outer peripheral portion of the propellant tank 17.
Further, on the outer peripheral portion of the propellant tank 17, a pressurization gas supply pipe (gas supply means) 28 that supplies a pressurization gas for pushing out the propellant and discharging it toward an apogee engine or a thruster (not shown). Is connected.
As shown in FIG. 1, a discharge mechanism 30 that discharges the propellant toward the apogee engine or thruster is connected to the central portion of the propellant tank 17.

  In the propellant tank 17 configured as described above, when a pressurization gas is supplied from a pressurization gas supply pipe 28 connected to the outer peripheral portion, the pressurization gas is supplied to each small compartment via each communication portion 26. The pressure by acts. Then, since the reinforcing members 24 are arranged radially toward the center of the propellant tank 17, the propellant is pushed out toward the center and discharged toward the apogee engine or thruster (not shown) by the discharge mechanism 30. Is done.

  The propellant tank integrated structure panel 10 of the present embodiment can be applied to a one-pack type in which a propellant (fuel) is reacted with a catalyst to obtain a reaction gas because the propellant tank can be filled with only one type. . Alternatively, the two-stage propellant tank-integrated structure panel 10 may be two-packed by filling one side with fuel and filling the other with oxidant. This also applies to third to fourth embodiments described later.

  Next, an example of the manufacturing method of the propellant tank integrated structure panel 10 described above will be described.

(1) The long frame member 13 having a cross-sectional shape with two large and small U-shaped back-to-back as shown in FIG. 4A is rectangularized by welding or the like so that the large U-shaped portion 13a is on the outside. Assemble. Further, long beam members 14 having the same cross-sectional shape are obliquely attached to the four corners, and an outer frame 12 having an octagonal inner side as shown in FIG. 3 is manufactured.

(2) As shown in FIG. 4 (b), an I-type (H) composed of upper and lower flanges 32a and 32b whose width decreases from one to the other in the longitudinal direction and a web 32c that connects the upper and lower flanges. Mold) Manufacture the required number of cross-sectional parts 32. Of the I-shaped cross-section component 32, the upper and lower flanges 32a and 32b serve as (a part of) the back plate 22 described above, and the web 32c serves as the reinforcing member 24 described above. The number of I-shaped cross-section parts 32 varies depending on the number of reinforcing members 24 provided in the propellant tank 17 and is 24 in this embodiment.

(3) The flanges of the I-shaped cross-section component 32 are joined together by welding, the wide-side end of the flange portion of the I-shaped cross-sectional component 32, and the open-side end of the small U-shaped portion 13b of the frame member 13 And are joined by welding. Thus, an intermediate body with the back plate 22 attached to the outer frame 12 is manufactured.

(4) The honeycomb core 20 is bonded and fixed to the surface of the intermediate back plate 22 manufactured in (3) with an adhesive. In the present embodiment, the honeycomb core 20 also covers the small U-shaped portion 13b of the frame member 13 (and the beam member 14), and is also bonded and fixed to that portion. Further, the surface plate 21 is bonded to the surface of the honeycomb core 20 with an adhesive. In the present embodiment, the surface plate 21 also covers the large U-shaped portion 13a of the frame member 13 (and the beam member 14), and is also bonded and fixed to that portion.

(5) The discharge mechanism 30 is attached at an appropriate stage of the above (3) to (4).

Next, the operation and effect of the propellant tank integrated structure panel 10 configured as described above will be described.
According to the propellant tank integrated structure panel 10 described above, the spherical propellant tank that has conventionally occupied a large area in the spacecraft structure has a flat shape (flat plate shape) and is integrated with the structural panel. A propulsion system module can be configured as a system common bus. As a result, it is possible to improve the degree of freedom of mounting the mission equipment and to implement the propulsion equipment that is not affected by the arrangement of the mission equipment.

Further, since the propellant tank is in a high-pressure state in order to supply the propellant to the propulsion device (thruster or apogee engine), FIG. 5 (a) → (b ) As shown in FIG. (However, FIG. 5 (a)-(c) has shown the case where the propellant tank 17 is not an octagon but circular (disk shape) like said embodiment.)
In order to suppress such deformation, the thickness of the shell of the flat tank is such that the stress acting on the shell (outer shell) of this flat tank is about the same as that of a spherical tank with the same internal volume. Is set, the mass becomes, for example, 100 times or more that of a spherical tank. This is not realistic at all.

  Thus, in the present invention, the propellant tank 17 is provided with the reinforcing member 24 for connecting the wall portions constituting the both surface portions of the tank, and the wall portion is constituted by the honeycomb panel 19. Since it comprised in this way, the deformation | transformation to the outer surface direction of the part in which the reinforcement member 24 was provided by the reinforcement member 24 is suppressed. Further, with the reinforcing member 24 alone, the non-reinforcing portion (the portion between the reinforcing member 24 and the reinforcing member 24) where the reinforcing member 24 is not provided is swelled in the out-of-plane direction as shown in FIG. However, by forming the wall portion of the propellant tank 17 with the honeycomb panel 19 that is lightweight and excellent in rigidity, deformation of the non-reinforced portion in the outer surface direction can be suppressed. Thereby, the weight of the propellant tank integrated structure panel 10 can be suppressed to the same level as the total weight of the conventional spherical tank and the bottom panel.

  Further, the plurality of reinforcing members 24 are arranged radially so as to divide the inside of the propellant tank 17 into a plurality of small sections whose cross-sectional area decreases toward the center, so that the reinforcing member 24 is directed toward the center portion of the tank that tends to swell due to internal pressure. Since the reinforcing members are concentrated, the swelling at the center of the tank can be effectively suppressed.

In addition, since a plurality of reinforcing members are arranged radially as described above, the propellant is held by the surface tension, and the propellant is moved toward the center of the tank by supplying the pressurizing gas from the outer periphery of the tank. It is possible to efficiently discharge from the discharge mechanism 30 that is pushed in and connected to the central portion.
In other words, for example, a large number of pin-shaped members may be arranged as other types of reinforcing members. However, when such reinforcing members are used, the surface of the member is caused by surface tension in outer space (in a microgravity environment). Propellants are clinging to each other, making it difficult to discharge the propellants efficiently. If the reinforcing member 24 is disposed as in the present embodiment, the propellant is pushed into the center of the tank while peeling off the propellant from the surface of the reinforcing member, so that the propellant can be discharged efficiently.

  Further, since all the small sections communicate with each other in the outer peripheral portion of the propellant tank, there is no need to provide a pressurizing gas supply pipe for each small section, and the configuration can be simplified.

[Second Embodiment]
FIG. 6 is a cross-sectional view showing the configuration of the propellant tank integrated structure panel 10 according to the second embodiment of the present invention. Since the configuration other than the points described below is the same as that of the first embodiment, the description of the common points will be omitted as appropriate.
In the present embodiment, a single propellant tank integrated structure panel can be used as a two-component propellant tank. In the case of the two-component type, the propellant tank 17 needs to be partitioned into compartments that are spatially independent from each other so that the oxidant and the fuel are not mixed with each other. In the embodiment of FIG. 6, the interior of the propellant tank 17 is partitioned into four large sections 34 a to 34 d that are spatially independent from each other by some reinforcing members (these are indicated by reference numerals 24-1 to 24-4). ing. Each large section is obtained by equally dividing the inside of the propellant tank 17 into four.

In addition, a plurality of small sections are formed in each large section, and in each large section, all the small sections in the same large section communicate with each other at the outer peripheral portion of the propellant tank.
Further, a pressurized gas supply pipe (gas supply means) 28 is connected to the outer peripheral portion of the propellant tank 17 for each large section. Moreover, the discharge mechanism (not shown) mentioned above is connected to the center part of the propellant tank 17 for every large division.

  Thus, since the inside of the propellant tank 17 is partitioned into a plurality of large compartments spatially independent from each other, the two-component propellant tank 17 can be obtained. In addition, since a plurality of small sections are formed in the large section, the propellant can be efficiently discharged as described above even in the case of a two-pack type.

Among the large sections, for example, the upper right and lower left large sections 34b and 34d in FIG. 6 can be used as oxidant tanks, and the upper left and lower right large sections 34a and 34c can be used as fuel tanks. Thus, when the inside of the propellant tank 17 is equally divided into four, the center of gravity can be set to the center by alternately filling the fuel and the oxidant into the four sections.
However, the number of large sections is not limited to four, and may be three or less or five or more.

[Third Embodiment]
FIG. 7 is a cross-sectional view showing the configuration of the propellant tank integrated structure panel 10 according to the third embodiment of the present invention. Since the configuration other than the points described below is the same as that of the first or second embodiment, the description of the common points will be omitted as appropriate.
When the spacecraft has a cylindrical shape, the propellant tank 17 has a circular shape (disk shape) as shown in FIG. 7 instead of the octagonal shape and other polygonal shapes described in the first and second embodiments. ). In this case, the outer frame 12 is also circular (ring shape).
Also in this case, as shown in FIG. 7, as in the first embodiment, a configuration in which all the small sections communicate with each other in the outer peripheral portion of the propellant tank 17 can be adopted. Or it is good also as a structure which partitions off the inside of a propellant tank into the several large division (or four large division equally divided | segmented) spatially mutually independent like 2nd Embodiment.

[Fourth Embodiment]
FIG. 8 is a cross-sectional view showing the configuration of the propellant tank integrated structure panel 10 according to the fourth embodiment of the present invention. Since the configuration other than the points described below is the same as that of the first embodiment, the description of the common points will be omitted as appropriate.
This embodiment is a propellant tank integrated structure panel suitable for a spin attitude stabilization type spacecraft that rotates and stabilizes its attitude. The propellant tank 17 in the present embodiment is an octagon like the first embodiment, but may be another polygon.
In the case of a spin attitude stabilization type spacecraft that rotates and stabilizes its attitude, the propellant is subject to a centrifugal force much stronger than its surface tension, and the propellant is the inner wall of the propellant tank. It is necessary to consider sticking in a ring shape.

In this embodiment, a pressurization gas supply pipe (not shown) is connected to the central portion of the propellant tank 17 as a gas supply means for supplying the pressurization gas. A discharge mechanism 30 for discharging the propellant is connected.
Thus, by disposing the propellant from the center toward the outer periphery by disposing the gas supply means at the center and the discharge mechanism 30 at the outer periphery, the propellant can be efficiently discharged without countering the centrifugal force. Can do.

  In addition, since the propellant tank 17 is octagonal (polygonal), the propellant is concentrated at each apex at the final stage of discharge. Therefore, the propellant concentrated on each vertex of the polygon can be efficiently discharged by disposing the discharge mechanism 30 at each vertex of the outer peripheral portion of the propellant tank as in this embodiment.

  In the present embodiment, all the small sections communicate with each other in the outer peripheral portion of the propellant tank 17, but instead of such a configuration, the interior of the propellant tank is similar to the second embodiment. May be divided into a plurality of large sections (or four equally divided large sections) spatially independent of each other. In this case, a pressurization gas supply pipe (gas supply means) for supplying pressurization gas is connected to the center of the propellant tank for each large section, and at each apex of the outer periphery of the propellant tank, the large section Every time, it is necessary to connect a discharge mechanism for discharging the propellant.

[Fifth Embodiment]
FIG. 9 is a cross-sectional view showing a configuration of a propellant tank integrated structure panel according to a fifth embodiment of the present invention. Since the configuration other than the points described below is the same as that of the third embodiment, the description of the common points will be omitted as appropriate.
This embodiment is a propellant tank integrated structure panel suitable for a spin attitude stabilization type spacecraft as in the fourth embodiment described above. The propellant tank 17 is octagonal (polygonal) in the above-described fourth embodiment, but is circular in this embodiment.

In the present embodiment, a pressurization gas supply pipe (not shown) is connected to the center of the propellant tank 17 as a gas supply means for supplying the pressurization gas. A discharge mechanism 30 for discharging the propellant is connected to the location.
When the propellant tank is circular in a spin attitude stabilization type spacecraft, the propellant sticks to the inner wall of the propellant tank in a ring shape due to the rotation of the spacecraft, gradually reducing the width of the ring, and at the final stage of discharge, A thin film is formed on the inner wall of the outer periphery of the tank. Therefore, the propellant can be discharged by disposing the discharge mechanism 30 in at least one place on the outer peripheral portion of the propellant tank 17 as in the present embodiment. Of course, if necessary, the discharge mechanisms 30 may be arranged at a plurality of locations on the outer periphery of the propellant tank 17.

  In the present embodiment, all the small sections communicate with each other in the outer peripheral portion of the propellant tank 17, but instead of such a configuration, the interior of the propellant tank is similar to the second embodiment. May be divided into a plurality of large sections (or four equally divided large sections) spatially independent of each other. In this case, the pressurization gas supply pipe (gas supply means) for supplying the pressurization gas is connected to the central portion of the propellant tank for each large section, and to the outer periphery of the propellant tank, for each large section, It is necessary to connect a discharge mechanism that discharges the propellant.

  Although the embodiments of the present invention have been described above, the embodiments of the present invention disclosed above are merely examples, and the scope of the present invention is not limited to these embodiments. The scope of the present invention is indicated by the description of the scope of claims, and further includes meanings equivalent to the description of the scope of claims and all modifications within the scope.

It is a perspective view of the propellant tank integrated structure panel concerning a 1st embodiment of the present invention. FIG. 2 is a partial enlarged view of a section taken along line II in FIG. 1. It is the II-II sectional view taken on the line of FIG. It is sectional drawing of a frame member, and a perspective view of I type cross-section components. It is a figure explaining a deformation | transformation of a flat tank. It is sectional drawing of the propellant tank integrated structure panel concerning 2nd Embodiment of this invention. It is sectional drawing of the propellant tank integrated structure panel concerning 3rd Embodiment of this invention. It is sectional drawing of the propellant tank integrated structure panel concerning 4th Embodiment of this invention. It is sectional drawing of the propellant tank integrated structure panel concerning 5th Embodiment of this invention. It is a figure which shows schematic structure of the conventional propulsion system for spacecraft.

Explanation of symbols

DESCRIPTION OF SYMBOLS 10 Propellant tank integrated structure panel 12 Outer frame 13 Frame member 14 Beam member 17 Propellant tank 19 Honeycomb panel 20 Honeycomb core 21 Front plate 22 Back plate 24 Reinforcement member 28 Gas supply pipe for pressurization (gas supply means 30 discharge mechanism

Claims (7)

A propellant tank integrated structure panel in which a structural panel constituting a spacecraft structure and a propellant tank are integrated,
An outer frame to be a skeleton of the structural panel, and a propellant tank formed inside the outer frame,
The propellant tank has a flat shape, and the walls constituting both sides of the propellant tank are each constituted by a honeycomb panel,
Each honeycomb panel, Ri Do from the honeycomb core and the surface plates are bonded to both sides of the honeycomb core and back plates,
Wherein the propellant tank, the reinforcing member is provided for connecting the wall portions constituting the double-sided portion,
A plurality of the reinforcing members are arranged radially so as to partition the inside of the propellant tank into a plurality of small sections whose cross-sectional area decreases toward the center,
A propellant tank integrated structure panel, wherein a discharge mechanism for discharging the propellant is connected to a central portion or an outer peripheral portion of the propellant tank. All the small sections communicate with each other in the outer peripheral portion of the propellant tank, and a gas supply means for supplying a gas for pressurization is connected to the outer peripheral portion of the propellant tank. The propellant tank integrated structure panel according to claim 1 , wherein a discharge mechanism for discharging the propellant is connected to the propellant tank integrated structure panel. The inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other by a part of the plurality of reinforcing members, and the plurality of small compartments are formed in the large compartment, In each of the large sections, all the small sections in the same large section communicate with each other at the outer peripheral portion of the propellant tank.
A gas supply means for supplying a gas for pressurization is connected to the outer periphery of the propellant tank for each of the large compartments, and a propellant is supplied to the central portion of the propellant tank for each of the large compartments. The propellant tank integrated structure panel according to claim 2 , wherein a discharge mechanism for discharging is connected. All the small sections communicate with each other in the outer peripheral portion of the propellant tank, and a gas supply means for supplying a pressurizing gas is connected to the central portion of the propellant tank, and the outer peripheral portion of the propellant tank The propellant tank integrated structure panel according to claim 1 , wherein one or a plurality of discharge mechanisms for discharging the propellant is connected to the propellant tank integrated structure panel. The inside of the propellant tank is partitioned into a plurality of large compartments spatially independent from each other by a part of the plurality of reinforcing members, and the plurality of small compartments are formed in the large compartment, In each of the large sections, all the small sections in the same large section communicate with each other at the outer peripheral portion of the propellant tank.
A gas supply means for supplying a pressurizing gas is connected to the central portion of the propellant tank for each of the large compartments, and a propellant is supplied to the outer peripheral portion of the propellant tank for each of the large compartments. 5. The propellant tank integrated structure panel according to claim 4 , wherein a discharge mechanism for discharging is connected. 6. The propellant tank integrated structure panel according to claim 3 or 5 , wherein the large section is obtained by equally dividing the inside of the propellant tank into four parts. A propellant tank integrated structure panel according to claim 2 or 4 , wherein the propellant tank integrated structure panel is stacked in two stages.

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