Assembly method for an orbital insertion vehicle carrying multiple artificial satellites

Abstract

To provide an efficient and safe assembly method for a track input machine loaded with multiple satellites.SOLUTION: An assembly method for a track input machine (11) loaded with multiple satellites (10) includes: preparing a plurality of satellite bodies (200); preparing a satellite support body (12), and a plurality of propulsion system modules (100) equipped with a propellant tank (102) or the like; charging a green propellant into each propellant tank of the plurality of propulsion system modules and attaching a plurality of charged propulsion system modules respectively to a plurality of satellite fitting parts (13) of the satellite support body; and assembling the track input machine loaded with a plurality of satellites by joining the plurality of satellite bodies respectively to the plurality of charged propulsion system modules attached to the satellite support body.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to a method for assembling an orbital injection machine equipped with a plurality of artificial satellites.

Background Art

[0002] In recent years, the construction of satellite constellations that launch a plurality of artificial satellites into low or medium orbits and operate them in cooperation has been accelerating towards realization. With satellite constellations, it is possible to realize services such as earth observation covering the entire earth, satellite phones, and GPS. Hereinafter, in this specification, "artificial satellite" will be simply referred to as "satellite".

[0003] To construct such satellite constellations, it is necessary to launch a large number of satellites into orbit, and spacecraft equipped with mechanisms for this purpose have been proposed. For example, Patent Document 1 discloses a satellite-mounted release mechanism that can carry a plurality of satellites and prevent and release collisions between satellites.

[0004] In addition, in conventional satellites, a highly toxic chemical propellant called hydrazine has been used. In recent years, however, thrusters using a less toxic propellant (hereinafter referred to as a green propellant) have been proposed and are being put into practical use (see Patent Document 2 and Non-Patent Document 1). Examples of green propellants include HAN (Hydroxyl Ammonium Nitrate)-based HAN systems, ADN (Ammonium DiNitramide) systems, HNF (Hydrazinium NitroFormate) systems, or hydrogen peroxide.

Prior Art Documents

Patent Documents

[0005]

Patent Document 1

Patent Document 2

Non-Patent Documents

[0006] [Non-Patent Document 1] "Towards Green Satellite Propulsion Systems - Development of Thrusters and Propulsion Systems Using Low-Toxicity Propellant -" (Mitsubishi Heavy Industries Technical Journal Vol. 56 No. 1 (2019) New Products and New Technologies Special Feature) [Overview of the project] [Problems that the invention aims to solve]

[0007] However, previous satellite assembly flows assumed the use of hydrazine, a highly toxic chemical propellant. Therefore, hydrazine was filled into the satellite after its assembly was complete, and the finished satellite was then mounted on the rocket. More specifically, the following assembly flow was employed.

[0008] First, a vendor specializing in propulsion system outfitting completes the propulsion system module by outfitting the base panel with propellant storage tanks, thrusters, and various piping. The satellite manufacturer then assembles the satellite body using the completed propulsion system module. Finally, the propulsion system vendor fills the assembled satellite with propellant (hydrazine), and the completed satellite is then mounted on the rocket. In this conventional flow, a product transportation process is required between the satellite manufacturer and the propulsion system vendor, making it difficult to improve work efficiency.

[0009] In particular, some satellite constellations utilize dozens of satellites, requiring a single orbital insertion vehicle to carry and launch a large number of satellites. To accommodate such a large number of satellites, the conventional assembly flow described above is extremely inefficient. Furthermore, the use of hydrazine necessitates strict safety management of toxic substances, resulting in a significant workload. While the use of less toxic green propellants as an alternative to hydrazine has been considered in recent years, the inefficient assembly flow remains in place.

[0010] Therefore, the objective of the present invention is to provide an efficient and safe assembly method for an orbital insertion machine that carries multiple satellites. [Means for solving the problem]

[0011] According to one aspect of the present invention, a method for assembling an orbital insertion vehicle carrying multiple satellites is provided, comprising: preparing multiple satellite bodies; preparing a satellite support and multiple propulsion system modules fitted with propellant tanks, thrusters, and piping; filling each of the propellant tanks of the multiple propulsion system modules with green propellant; attaching the multiple filled propulsion system modules to the multiple satellite mounting portions of the satellite support; joining the multiple satellite bodies to the multiple filled propulsion system modules attached to the satellite support to constitute the multiple satellites; and assembling the orbital insertion vehicle carrying the multiple satellites. [Effects of the Invention]

[0012] According to the present invention, an orbital insertion vehicle carrying multiple satellites can be assembled efficiently and safely. [Brief explanation of the drawing]

[0013] [Figure 1] Figure 1 is a schematic assembly flow diagram showing the assembly method of an orbital launching machine according to one embodiment of the present invention. [Figure 2] Figure 2 is a front view of the track launching machine assembled according to this embodiment. [Figure 3] Figure 3 is a plan view of the track insertion machine illustrated in Figure 2. [Figure 4] Figure 4 is a schematic diagram of the satellite to be mounted on the orbital insertion vehicle assembled according to this embodiment. [Figure 5] Figure 5 is an outfitting diagram showing a schematic side view of the propulsion system module in the satellite exemplified in Figure 4. [Figure 6] Figure 6 is a schematic side view of the pipe support fitting used in the propulsion system module illustrated in Figure 5. [Figure 7] Figure 7 is a schematic side view showing the propulsion system module exemplified in Figure 5 attached to the orbital launching machine. [Figure 8] FIG. 8 is a schematic side configuration diagram of a completed satellite in which a satellite main body is attached to the propulsion system module illustrated in FIG. 7. [Figure 9] FIG. 9 is a schematic cross-sectional configuration diagram of an orbit injection machine according to another embodiment of the present invention.

BRIEF DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0014] <SUMMARY OF THE EMBODIMENT> According to an embodiment of the present invention, each of a plurality of satellites includes a satellite main body and a propulsion system module, and the satellite main body and the propulsion system module are assembled separately. Each of the assembled plurality of propulsion system modules is filled with a green propellant and detachably attached to a satellite support. A plurality of satellite main bodies are respectively joined to the plurality of propulsion system modules attached to the satellite support to assemble an orbit injection machine to which a plurality of satellites are attached.

[0015] Thus, each satellite is configured to be separable into a satellite main body and a propulsion system module. The propulsion system module filled with the green propellant (hereinafter referred to as a filled propulsion system module) is attached to the satellite support, and the satellite main body is joined to each filled propulsion system module. Therefore, the production of the filled propulsion system module using the green propellant and the production of the satellite main body can be carried out in parallel as independent processes, and it is possible to efficiently and safely assemble an orbit injection machine equipped with a plurality of satellites. In particular, although various functions may be mounted on each satellite main body, the propulsion system module can be made common regardless of the type of satellite, so that the production efficiency can be further improved. In addition, the application of the green propellant enables the filling of the propellant in any process of assembling each satellite, increasing the degree of freedom of the production procedure and enabling efficient production.

[0016] Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. However, the components, their shapes, dimensions and dimensional ratios, and arrangements described in the following embodiments are merely examples for explaining the embodiments, and are not intended to limit the technical scope of the present invention only to them.

[0017] 1. Embodiment 1.1) Assembly process As illustrated in FIG. 1, the assembly method of the orbital injection machine according to an embodiment of the present invention is divided into a propulsion system manufacturing operation 1 and a satellite manufacturing operation 2, and the orbital injection machine 11 on which a plurality of satellites 10 are mounted can be manufactured efficiently and safely.

[0018] The propulsion system manufacturing operation 1 is executed by a propulsion system vendor specializing in propulsion system outfitting work. The propulsion system vendor assembles the propulsion system module 100 described later, fills it with a green propellant, and detachably joins the filled propulsion system module 100 to the satellite support 12. The filled propulsion system module 100 is outfitted with a tank 102 filled with a propellant on a base plate 101 and other members (not shown in the figure) (such as thrusters, pipes, etc.) (details will be described later).

[0019] A plurality of satellite attachment parts 13 are provided around the satellite support 12. The plurality of filled propulsion system modules 100 filled with the green propellant are respectively detachably attached to the plurality of satellite attachment parts 13 of the satellite support 12. By filling the green propellant at the stage of assembling the plurality of propulsion system modules 100 in this way and detachably attaching the filled propulsion system module 100 to the satellite support 12, a series of operations can be completed at the base of one vendor.

[0020] The satellite manufacturing operation 2 is an operation executed by a satellite manufacturer. First, the satellite body 200 is assembled in advance, and then the satellite body 200 is joined to the filled propulsion system module 100 of the satellite support 12 assembled by the propulsion system manufacturing operation 1. Thereby, the satellite support 12 to which a plurality of satellites 10 are attached can be completed as the orbital injection machine 11.

[0021] As an example, if 12 satellites 10 are to be loaded onto the orbital insertion vehicle 11, the satellite manufacturer has already completed the assembly of 12 satellite bodies S1 to S12 through satellite manufacturing work 2. After the satellite support 12, to which 12 pre-filled propulsion system modules 100 have been attached, is delivered from the propulsion system vendor, the satellite support 12 carrying the 12 satellites 10 can be constructed by sequentially joining the satellite bodies S1 to S12 to the 12 pre-filled propulsion system modules 100. This satellite support 12 is then loaded onto the orbital insertion vehicle 11. Furthermore, by connecting an electrical performance verification device to the satellite support 12, it becomes possible to perform electrical performance testing on all 12 satellites 10 at once.

[0022] The detailed structure and function of the satellite 10 and orbital insertion machine 11 in this embodiment will be described below with reference to Figures 2 to 8. Here, an example is shown in which 12 satellites 10 are mounted on the orbital insertion machine 11, but this is not the only option, and any desired number of satellites can be mounted depending on the orbital insertion machine.

[0023] 1.2) Orbital insertion vehicle As illustrated in Figures 2 and 3, the orbital insertion machine 11 includes a satellite support 12 and satellites S10 attached to satellite mounting portions 12 of the satellite support 12. In this embodiment, the satellite support 12 has a configuration of three cylindrical supports stacked on top of each other. As shown in Figure 3, each support has four satellite mounting portions 13 provided at equal intervals around the cylindrical side surface. The satellite mounting portions 13 can be any mechanism that detachably holds the satellite 10, and the holding and releasing method is not limited.

[0024] By stacking and fixing three cylindrical supports, each having four satellite attachment points 13, a satellite support 12 is constructed with a total of 12 satellite attachment points 13. By joining satellite bodies S1 to S12 to these 12 satellite attachment points 13, an orbital launcher 11 is assembled with 12 satellites 10 detachably attached. By changing the number of satellite supports 12 in each support stage and the number of stages of the support, it is possible to mount any desired number of satellites.

[0025] 1.3) Satellite As illustrated in Figure 4, the satellite 10 consists of a propulsion module 100 and a satellite body 200, each manufactured separately and finally joined together to form a single satellite. The satellite body 200 is the main part of the satellite 10 excluding the propulsion module 100, and includes panels 201, including solar panels, and equipment 202, such as electronic devices that constitute the control system. The propulsion module 100 and the satellite body 200 are joined together by connecting members 203, such as screws.

[0026] <Propulsion System Module> As illustrated in Figure 5, the propulsion module 100 is the basic structure of the satellite 10, and the equipment necessary for the propulsion system is fitted onto the base plate 101. The base plate 101 supports the entire load of the satellite 10 and transmits the load during launch. The tank 102 filled with green propellant is fixed to the base plate 101 by a tank support bracket 103. A diaphragm 104 is provided inside the propellant tank 102 and is filled with pressurized gas. The pressurized gas is introduced through a pressurized gas pipe 105. The pressurized gas pipe 105 is fixed to the base plate 101 by a pipe support bracket 106 and is connected to a pressurized gas valve 107.

[0027] Furthermore, the green propellant filled in the propellant tank 102 is supplied to the thruster 109 through the propellant piping 108. The propellant piping 108 is fixed to the base plate 101 by pipe support brackets 106 and 110 and connected to the propellant valve 111. The thruster 109 has a predetermined thrust level and is used for attitude control, altitude and orbit maintenance of the separated satellite 10. In Figure 5, one thruster 109 is provided in the propulsion system module 100, but it is not limited to this, and two or four thrusters may be provided.

[0028] As shown in Figure 6, the pipe support brackets 106 and 110 are constructed by fixing the support bracket 301 to the base plate 101 with bolts 302, and fixing the pipe clamp 303, which holds the pipe 105 or 109, to the support bracket 301 with bolts 304.

[0029] As illustrated in Figure 7, the propulsion module 100 is detachably attached to the satellite mounting portion 13 of the satellite support 12. Any holding and releasing mechanism can be used to connect the satellite mounting portion 13 and the base plate 101 of the propulsion module 100. The satellite body 200 is mounted and fixed on top of the propulsion module 100, which is held by the satellite mounting portion 13.

[0030] As described above, the propulsion module 100 is held by the satellite mounting portion 13 of the satellite support 12, and the satellite body 200 is joined on top of it by fastening members 203 such as screws, thereby completing the satellite 10 as shown in Figure 8.

[0031] Returning to Figure 1, the propulsion system vendor attaches 12 pre-filled propulsion system modules 100 to the satellite support 12 in a separable manner, and the satellite manufacturer sequentially attaches the satellite bodies S1 to S12 to the 12 pre-filled propulsion system modules 100. In this way, the satellite support 12 with the 12 satellites 10 attached is assembled as an orbital insertion vehicle 11. This process makes it possible to safely and efficiently assemble an orbital insertion vehicle 11 carrying multiple satellites 10. Furthermore, the application of green propellants allows for the filling of propellant at any stage of the assembly of individual satellites.

[0032] 2. Other Embodiments Although the above embodiment illustrates the assembly process of a multi-launch orbital insertion vehicle 11 carrying a large number (12) satellites, the present invention is similarly applicable to a dual-launch orbital insertion vehicle carrying two satellites.

[0033] As illustrated in Figure 9, the dual-launch small rocket 400 can be equipped with the aforementioned upper and lower satellite support units 12, the pre-filled propulsion system modules 100 can be attached to each satellite mounting section 13, and the respective satellite bodies 200 (S1 and S2) can be mounted on top of them to configure the satellite support unit 12, which carries two satellites, as an orbital insertion vehicle.

[0034] In conventional assembly processes, filling the propellant (hydrazine) after the assembly of each satellite and then mounting the two satellites one above the other is not done due to the hazardous nature of the work. The inability to fill the propellant until the final stage, when the mounting of the two satellites is complete, was a challenge and a factor contributing to the length of the work process.

[0035] In contrast, the present invention allows for the filling of propellant at any stage of the assembly of individual satellites by applying green propellant, and ensures safety even when the satellites are mounted vertically after filling. Furthermore, it enables parallel work, contributing to process shortening. [Industrial applicability]

[0036] This invention is applicable to the assembly process of an orbital insertion vehicle equipped with a satellite that can be separated into a satellite body and a propulsion system module. [Explanation of Symbols]

[0037] 1 Propulsion system manufacturing work 2 Satellite manufacturing work 10 satellites 11 Orbital Insertion Vehicle 12 Satellite support 13 Satellite mounting section 100 Propulsion System Module 101 Base Plate 102 tanks 109 Thruster 200 Satellite Body 201 Panel 202 Equipment

Claims

1. A method for assembling an orbital insertion vehicle carrying multiple satellites, Prepare multiple satellite bodies, A satellite support structure and multiple propulsion system modules equipped with propellant tanks, thrusters, and piping are prepared. Green propellant is filled into each of the propellant tanks of the aforementioned multiple propulsion system modules. The multiple pre-filled propulsion system modules are attached to the multiple satellite mounting portions of the satellite support, The plurality of satellite bodies are joined to the plurality of pre-filled propulsion system modules attached to the satellite support to constitute the plurality of satellites, and the orbital insertion vehicle on which the plurality of satellites are mounted is assembled. A method for assembling an orbital insertion machine, characterized by the features described above.

2. The method for assembling an orbital insertion vehicle according to claim 1, characterized in that the work of assembling the plurality of propulsion system modules and filling them with the green propellant and the work of assembling the plurality of satellite bodies are performed independently.

3. The method for assembling an orbital insertion vehicle according to claim 1 or 2, characterized in that the multiple propulsion system modules are common to the multiple satellites.

4. The method for assembling an orbital insertion machine according to any one of claims 1 to 3, characterized in that the satellite support has a cylindrical shape, and the plurality of satellite mounting parts are provided around the side surface of the cylindrical shape at equal intervals in the circumferential direction and the height direction, respectively.

5. The method for assembling an orbital insertion machine according to any one of claims 1 to 4, characterized in that the satellite support has a multi-stage structure in which a plurality of cylindrical supports are connected, and a plurality of satellite mounting parts are provided at equal intervals in the circumferential direction around the side surface of the cylindrical support of each stage.

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