JP2009241805A - Artificial satellite - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To reduce a risk of intrusion control of contamination into a propellant tank concerning propellant filling at a launching site to an artificial satellite, and a cost required for propellant filling work. <P>SOLUTION: The artificial satellite comprises a satellite structure, the propellant tank equipped with a connecting adaptor and a valve mechanism with an ammunition, a pipe detachably connecting the connecting adaptor of the propellant tank and a thruster, and an ammunition control device driving the valve mechanism with the ammunition. The propellant tank is installed in the artificial satellite at the launching site of the artificial satellite. <P>COPYRIGHT: (C)2010,JPO&INPIT

Description

  The present invention relates to an artificial satellite to which a propellant tank filled with propellant is attached.

  A propellant tank of an artificial satellite (hereinafter referred to as satellite) is attached to the satellite body and supplies propellant to the combustion chamber of the thruster through a pipe. 2. Description of the Related Art Conventionally, a propellant tank mounting structure is known in which a propellant tank is housed in a hollow cylinder of a thrust tube that is a main structure of a satellite (see, for example, Patent Document 1).

JP-A-5-310197

  In a conventional satellite, a propellant tank is attached to the satellite structure in advance, and the propellant tank is filled with propellant during launch site preparation work before the satellite is mounted on the launch vehicle. The propellant for filling is carried to the launch site together with the propellant filling device by the transport tank, and is filled into the propellant tank using the propellant filling device.

  In general, hydrazine is used as a propellant. However, since hydrazine is highly toxic and highly volatile, strict contamination management and filling amount management are required in filling propellants. The installation of the propellant filling device is accompanied by strict cleanliness management, complicated piping assembly work and piping leak checking work at the launch site, and when removing the filling device during filling and after filling, In preparation for leakage of propellant, a special scape suit will be worn for a long time.

  In addition, a number of filters are installed in the piping filled from the propellant tank for transportation into the propellant tank inside the satellite so as to maintain the quality of the propellant filled. The transport tank is filled with high-pressure nitrogen gas in order to pass through the filter during propellant filling. Therefore, since nitrogen gas and vaporized propellant are mixed in the tank and piping, the accurate amount of propellant filling in the propellant tank inside the satellite and the internal pressure are measured, and the peripheral equipment and atmospheric temperature, The filling operation is performed while monitoring the pressure and weight.

  After propellant filling, waste propellant dumped to remove contamination during pipe assembly, vaporized propellant evaporated during filling and discharged out of the filling device, invalid propellant remaining in the filling pipe after filling, and Hazardous substances, etc. generated by washing the filling equipment after filling are transported to the propellant shipper. Therefore, tremendous cost and safety risk management is required for propellant filling.

  In the past, propellant was filled from the propellant tank for transportation to the propellant tank inside the satellite at the launch site of the satellite, so there are many risks related to work safety, propellant quality, work schedule, etc. The filling operation was costly. For this reason, reduction of the launch site work cost included in the satellite manufacturing cost and risk reduction have been desired.

  This invention is made in order to solve the subject which concerns, and it aims at reducing the risk and cost regarding a propellant filling in the launch range to an artificial satellite.

An artificial satellite according to the present invention includes a propellant tank including a satellite structure, a connection adapter, a tank, a valve mechanism with a connection adapter pyrotechnic provided between the connection adapter and the tank, and the propellant tank. A holding unit attached to the satellite structure, a connection interface connected to the connection adapter of the propellant tank, a pipe connected to the thruster, and a drive signal to the valve mechanism with pyrotechnics A crater control device for outputting,
The valve mechanism with pyrotechnics closes the flow path between the connection adapter and the tank before receiving the drive signal from the crater control device, and after receiving the drive signal from the crater control device, The flow passage with the tank is opened.

  According to the present invention, it is possible to reduce the risk and cost associated with the propellant filling at the launch site to the artificial satellite.

Embodiment 1 FIG.
Hereinafter, an artificial satellite (hereinafter referred to as a satellite) according to Embodiment 1 of the present invention will be described with reference to the drawings. FIG. 1 is a diagram illustrating a configuration of a satellite according to the first embodiment.

In the figure, a satellite 1 includes a satellite structure 2 that constitutes a satellite body, a satellite-equipped mission device 3, a solar cell paddle 4, a thruster 5, and a cassette type propellant tank 6. The satellite structure 2 forms a hexahedral structure by combining a plurality of structure panels in a box shape. On one surface of the structure panel in the satellite structure 2, a satellite-equipped mission device 3 is installed. The satellite-equipped mission equipment 3 constitutes an antenna device that communicates with the ground and an observation device that observes the earth and space. The solar cell paddle 4 is attached to two opposing surfaces different from the attachment surface of the satellite-equipped mission equipment 3 in the satellite structure 2. The solar cell paddle 4 generates power by sunlight and supplies power to the satellite structure 2. The propellant tank 6 is accommodated inside the satellite structure 2. The thruster 5 is attached to the satellite structure 2 and is used as a propulsion device that applies a propulsive force to the satellite 1 to move its position and attitude.
For the sake of explanation, illustration of the other satellite-equipped devices such as a power source and an attitude control device will be omitted.

  FIG. 2 is a diagram showing the internal configuration of an artificial satellite loaded with a propellant tank, the installation structure of the propellant tank inside the satellite structure, and the configuration of the propellant tank. In the figure, a central cylinder 7, a crater product control device 20, and a pipe 9 are provided inside the satellite structure 2. Further, the above-described cassette type propellant tank 6 is mounted inside the satellite structure 2.

  The central cylinder 7 is a structural member arranged in the center of the satellite structure 2 and having a hollow cylindrical shape. The cylindrical end portion of the central cylinder 7 is open, and this opening portion faces the opening hole 15 of the thruster mounting surface in the satellite structure 2. The opening hole 15 of the satellite structure 2 is closed by a removable access panel. Around the central cylinder 7, an attitude control device, a power source, a computer, data, and various satellite-equipped devices such as a power bus and electrical components are arranged. A plurality of thrusters 5 are arranged around the central cylinder 7 on the outer surface of the satellite structure 2. One or two or more propellant tanks 6 are mounted inside the central cylinder 7 and are detachably held and fixed by a holding portion 21. The example of the figure shows a state before one propellant tank 6 is attached and another propellant tank 6 is attached. The propellant tank 6 is inserted into the central cylinder 7 through the opening hole 15 with the access panel of the satellite structure 2 opened, or is drawn out of the central cylinder 7.

  The piping 9 is attached to the central cylinder 7 and connects the inside of the central cylinder 7 and the thruster 5 to constitute a propulsion system piping interface. A connection adapter 12 constituting a connection interface with the connection adapter 11 is provided at the end of the pipe 9. In the pipe 9, the number of branch branches is determined according to the number of propellant tanks 6 to be connected, and the number of connection adapters 12 connected to the ends of the branch branches is determined. The branch branch pipe of the pipe 9 is connected to one or a plurality of main pipes. A main pipe of the pipe 9 is connected to a combustion chamber 8 provided in each thruster 5. The propellant tank 6 includes a pipe 10 directly connected to the propellant supply hole of the tank 28, a connection adapter 11 provided at an end of the pipe 10, and a pyrotechnic valve mechanism 13 provided in the pipe 10. Is provided.

  The propellant tank 6 is previously filled with, for example, hydrazine as a propellant. When the propellant tank 6 is attached to the central cylinder 7, the connection adapter 11 of the pipe 10 on the propellant tank side is detachably connected to the connection adapter 12 of the pipe 9 on the satellite structure side. As a result, the pipe 10 is connected to the pipe 9. Moreover, the wiring of the crater control device 20 is detachably connected to the valve mechanism 13 with pyrotechnics. Upon receiving a control command from the ground, the crater control device 20 outputs a drive signal to the pyrotechnic valve mechanism 13. As a result, the crater control device 20 controls the explosion of the pyrotechnic valve mechanism 13 to drive the internal plug and open the valve. The valve mechanism 13 with pyrotechnics is configured so that the propellant filled in the propellant tank 6 does not leak to the outside unless the valve is opened by pyrotechnics on the track. After the propellant tank 6 is provided with the connection adapter 12 and the pyrotechnic valve mechanism 13 in this way, the propellant tank 6 filled with the propellant is transported to an arbitrary place (for example, a launch site of a satellite). The propellant tank 6 can be incorporated in the satellite structure at the destination of the transfer destination. Further, providing the connection adapter 12 facilitates the work of connecting the propellant tank 6 to the propulsion system piping interface.

  FIGS. 3A and 3B are diagrams showing a configuration example of the valve mechanism 13 with a pyrotechnic, wherein FIG. 3A shows a state where the valve is closed by the plug 30, and FIG. 3B shows a state where the valve is opened by the valve 31. In the figure, the pyrotechnic valve mechanism 13 includes a connecting portion 29 for attaching to the piping 10 of the propellant tank 6, a plug 30, a valve 31, a booster 32 connected to the valve 31, and a booster 32 slidingly. The cylinder 33 which moves, the initiator 34 for detonating the booster 32, and the receiving part 35 are provided. The plug 30 is made of a solid plate and has no through hole. The valve 31 has a through hole in the center. The valve 31 contacts the stopper 30 and is connected between the stopper 30 and the booster 32. The booster 32 has an end abutting against the stopper 30 and slides in the cylinder 33 to move the valve 31 together with the stopper 30.

Next, the operation of the pyrotechnic-equipped valve mechanism 13 will be described.
In FIG. 3A, before the control of the crater control device 20, the plug 30 is in a state of blocking the flow of the pipe 10, so that the propellant existing in the pipe 10 does not flow out of the propellant tank 6. The flow path is obstructed and the valve is closed.

  In FIG. 3 (b), when the crater product control device 20 receives a control command for opening the valve, the crater product control device 20 sends a drive signal (drive voltage) to the initiator 34, so that the initiator 34 is ignited. . As the initiator 34 ignites, the internal gunpowder ignites and the booster 32 is detonated. The booster 32 is moved to the connection portion 29 side by the explosion of the booster 32 and is pushed by the booster 32 to move the plug 30 and the valve 31 to the receiving portion 35 side. The receiving part 35 captures the plug 30 so that the plug 30 does not fall out. Thus, the valve is opened when the valve 31 circulates the pipe 10.

  A manual valve (not shown) may be provided between the tank 28 of the propellant tank 6 and the pyrotechnic valve mechanism 13. At this time, when filling the propellant, the manual valve is opened and the pyrotechnic valve mechanism 13 is removed. After filling the propellant, the manual valve can be opened after the manual valve is closed and then the pyrotechnic valve mechanism 13 is attached.

  4A and 4B are diagrams showing the configuration of a connection adapter for piping. FIG. 4A is a configuration diagram, and FIG. 4B is a diagram showing a connected state. In the figure, the connection adapter 11 includes a convex conical seal portion 40 and a male screw portion 41. Further, the connection adapter 12 includes a concave conical seal portion 42 and a female screw portion 43. The convex conical seal portion 40 of the connection adapter 11 and the concave conical seal portion 42 of the connection adapter 12 are in close contact with each other, and the male screw portion 41 and the female screw portion 43 are fastened to each other. Are connected with airtightness, and the pipe 9 and the pipe 10 are connected. Note that the configuration of the connection adapters 11 and 12 is not limited to this, and the combination of the conical seal portion and the screw portion may be a combination opposite to each other.

Next, a procedure for attaching the propellant-filled cassette type propellant tank 6 to the satellite structure 2 will be described. The propellant tank 6 is assembled to the satellite 1 in the following order 1) to 5).
1) The propellant is filled in the propellant tank 6 in advance by the propellant manufacturer.
2) Transport the propellant tank 6 to the launch site of the satellite 1. At this time, the satellite 1 is transported to the launch site in a state where the propellant tank 6 is not mounted inside the central cylinder 7.
3) At the launch site of the satellite 1, the access panel is removed from the structure panel 2 of the satellite 1, and the propellant tank 6 is inserted into the central cylinder 7 through the opening hole 15.
4) The pipes 9 and 10 are connected by connecting the connection adapters 11 and 12 together.
5) The mounting operation of the propellant tank 6 is completed by connecting the wiring of the crater control device 20 to the valve mechanism 13 with pyrotechnics.
In this installation work, when air mixed into the pipe becomes a problem when the pipe 9 and the pipe 10 are connected, an air vent valve is provided in the pipe, and after connecting the connection adapters 11 and 12, the air in the pipe is removed. By evacuating, the residual air can be reduced to a negligible level.
In addition, after the satellite 1 is launched into the space from the ground, a control command is sent from the ground station to the crater control device 20 on the satellite orbit.
Thereafter, the crater control device 20 sends a drive voltage to the valve mechanism 13 with pyrotechnics to drive the valve mechanism 13 with pyrotechnics. Thereby, the valve | bulb of the valve mechanism 13 with a pyrotechnics will be in an open state, and the flow path of the propellant tank 6 and the piping 9 inside a satellite will be ensured.
Thus, the propellant supplied from the propellant tank 6 is supplied to the combustion chamber 8 of the thruster 5, and the thruster 5 obtains propulsive force by combustion of the propellant in the combustion chamber 8.

As described above, the satellite 1 according to the first embodiment can be loaded with the propellant-filled cassette type propellant tank 6 at the launch site. Therefore, instead of filling the transport tank by the propellant manufacturer, the propellant tank 6 of the satellite 1 may be filled directly with the propellant. Moreover, it is not necessary to perform the propellant filling operation with many risks at the launch site.
As a result, it is possible to reduce risks such as contamination intrusion when filling the propellant at the launch site, work with a heavy work load, schedule impact at the time of an accident, and costs associated therewith.

The propellant tank 6 is preinstalled with a connection adapter 11 for connecting to the satellite propulsion system piping, and the propellant filled between the connection adapter 11 and the tank 28 is completely blocked. A valve mechanism 13 with pyrotechnics is provided. For this reason, the propellant does not flow out to the atmosphere when the propellant tank 6 is attached at the launch site.
Therefore, the propellant tank 6 can be assembled by attaching the propellant tank 6 to the satellite 1 and connecting the connection adapter 11 to the connection adapter 12 without performing high-risk work at the launch site.
As a result, it is possible to replace the long-term field work from propellant filling preparation work at the launch site to post-fill post-treatment with assembly work that can be performed in a short time. The level of contamination management and filling amount management can be improved.

Furthermore, the piping work is completed only by directly connecting the connection adapter of the propellant tank 6 to the artificial satellite propulsion system piping. For this reason, it is not necessary to connect a filling device or transport tank to the satellite propellant tank at the launch site, and to perform complicated piping assembly to fill the propellant, and the number of connection adapters that increases the risk of contamination Less.
As a result, the possibility of contamination sources entering the satellite propulsion system becomes extremely high. However, in the case of the cassette type propellant tank according to the present invention, the risk can be reduced.

  Moreover, by using the propellant tank 6, all the propellant filling operations to the propellant tank 6 can be performed by the propellant manufacturer with dedicated equipment. For this reason, the risks associated with strict contamination management and strict filling procedure management can be greatly reduced, and the propellant that has become invalid during filling of the propellant at the launch site, and the return of the filling device to the shipper, In addition, harmful cleaning work before returning is unnecessary.

It is a figure which shows the structure of the artificial satellite by Embodiment 1 of this invention. It is a figure which shows the structure of the propellant tank by Embodiment 1 of this invention, and the internal structure of the artificial satellite which loaded the propellant tank. It is a figure which shows the structure of the valve mechanism 13 with a pyrotechnics by Embodiment 1 of this invention. It is a figure which shows the structure of the connection adapter by Embodiment 1 of this invention.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 1 Artificial satellite (satellite), 2 satellite structure, 5 thruster, 6 propellant tank, 7 central cylinder, 9 piping, 10 piping, 11 connection adapter, 12 connection adapter, 13 valve mechanism with pyrotechnics, 20 crater control device .

Claims (1)

The satellite structure,
A propellant tank comprising a connection adapter, a tank, and a valve mechanism with a connection adapter pyrotechnics provided between the connection adapter and the tank;
A holding part for mounting the propellant tank on the satellite structure;
A connection interface connected to the propellant tank connection adapter, and a pipe connected to the thruster;
A crater control device that outputs a drive signal to the valve mechanism with pyrotechnics,
With
The valve mechanism with pyrotechnics closes the flow path between the connection adapter and the tank before receiving the drive signal from the crater control device, and after receiving the drive signal from the crater control device, An artificial satellite characterized by opening the flow path to the tank.

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