Satellite release mechanism and satellite release method

Abstract

To provide a satellite release mechanism capable of obliquely releasing a satellite to a rocket without complicating a structure.SOLUTION: By including the first pushing member that moves in the moving direction inclined at the first inclination angle with respect to the normal line of the connection surface with the rocket, the first satellite can be released in a direction inclined with respect to the connection surface with the rocket. Further, when the first satellite is released in the inclined direction, it is only necessary to adjust the moving direction of the first pushing member included in the first pushing mechanism, so that the mechanism for releasing the first satellite in the inclined direction can be prevented from being complicated.SELECTED DRAWING: Figure 9

Description

[Technical Field]

[0001] The present disclosure relates to a satellite deployment mechanism and a satellite deployment method for deploying a satellite from a rocket. [Background technology]

[0002] A satellite deployment mechanism has been proposed that is launched by a rocket and deploys a satellite. When a satellite is deployed from this satellite deployment mechanism, there is a risk of the satellite colliding with a structure on the rocket. To avoid this, it is possible to deploy the satellite at an angle so that the satellite moves away from the structure on the rocket. Patent Document 1 discloses a structure that changes the angle of the satellite relative to the rocket when deploying the satellite, thereby deploying the satellite at an angle. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Patent No. 3801640 Summary of the Invention [Problem to be solved by the invention]

[0004] By applying the technology described in Patent Document 1, it is possible to release a satellite at an angle relative to the rocket, but the structure described in Patent Document 1 has a complex mechanism for tilting the satellite at an angle, and there is a risk that the weight of the device will increase as the mechanism becomes more complex.

[0005] The present disclosure has been made to solve the above-mentioned problems, and its purpose is to provide a satellite deployment mechanism and a satellite deployment method that can deploy a satellite at an angle relative to a rocket without complicating the structure. [Means for solving the problem]

[0006] The satellite release mechanism of the first aspect is a satellite release mechanism that is launched by a rocket and releases a satellite, and includes a base including a first satellite mounting part to which a first satellite is fixed, a first fixing part that holds the first satellite on the first satellite mounting part, and a connection surface with the rocket, and a first pushing mechanism that is a mechanism for pushing the first satellite from the base, and includes a first pushing member that pushes the first satellite by moving in a predetermined moving direction that is inclined at a first inclination angle with respect to the normal to the connection surface with the rocket.

[0007] According to the first aspect, the first pushing mechanism that pushes out the first satellite from the base includes a first pushing member that moves in a moving direction that is inclined at a first tilt angle with respect to the normal of the connecting surface of the satellite release mechanism with the rocket, so the first satellite can be released in a direction inclined with respect to the connecting surface with the rocket. Furthermore, releasing the first satellite in an inclined direction requires only adjusting the moving direction of the first pushing member included in the first pushing mechanism, which prevents the mechanism that releases the first satellite in an inclined direction from becoming too complicated.

[0008] The satellite deployment mechanism of the second aspect preferably further comprises the following feature in addition to the satellite deployment mechanism of the first aspect: In the satellite deployment mechanism of the second aspect, the first tilt angle formed between a virtual movement direction line parallel to the movement direction of the first pusher member and a normal to the connection surface with the rocket is set to an angle greater than 0 degrees and less than 90 degrees.

[0009] According to the second aspect, the first inclination angle formed between the movement line parallel to the movement direction of the first extrusion member and the normal to the connection surface is adjusted to an angle greater than 0 degrees and less than 90 degrees, so that the first satellite can be released in an oblique direction relative to the connection surface with the rocket.

[0010] The satellite deployment mechanism of the third aspect is preferably the satellite deployment mechanism of the second aspect, further comprising the following feature: That is, in the satellite deployment mechanism of the third aspect, the base further includes a second satellite mount part to which a second satellite is fixed and a second fixing part that holds the second satellite on the second satellite mount part, and the satellite deployment mechanism further includes a second pushing mechanism that pushes the second satellite out of the base, the second pushing mechanism including a second pushing member that pushes the second satellite by moving in a predetermined moving direction that is inclined at a second tilt angle with respect to the normal to the connection surface with the rocket, and the second tilt angle is an angle different from the first tilt angle.

[0011] According to the third aspect, the first tilt angle and the second tilt angle are different from each other, so that the first satellite and the second satellite can be deployed in directions away from each other, thereby preventing the first satellite and the second satellite from coming into contact with each other during deployment.

[0012] The satellite deployment mechanism of the fourth aspect preferably further comprises the following feature in addition to the satellite deployment mechanism of the third aspect: In the satellite deployment mechanism of the fourth aspect, the first tilt angle is set to an angle greater than 0 degrees and less than 90 degrees, and the second tilt angle is set to an angle greater than 90 degrees and less than 180 degrees, or an angle greater than -90 degrees and less than 0 degrees.

[0013] According to the fourth aspect, by adjusting the first tilt angle and the second tilt angle to fall within the above-mentioned angle range, the first satellite and the second satellite can be released in directions away from each other.

[0014] The satellite deployment mechanism of the fifth aspect is preferably the satellite deployment mechanism of any one of the first to fourth aspects, further comprising the following feature: In the satellite deployment mechanism of the fifth aspect, the first pushing mechanism includes a pushing force adjustment mechanism that adjusts the pushing force with which the first pushing member pushes out the first satellite.

[0015] According to the fifth aspect, the first pushing member is provided with a pushing force adjustment mechanism that adjusts the pushing force with which the first satellite is pushed out, making it possible to finely adjust the pushing force with which the first satellite is pushed out.

[0016] The satellite deployment mechanism according to the sixth aspect is the satellite deployment mechanism according to the fifth aspect, and preferably further comprises the following feature: That is, the satellite deployment mechanism according to the sixth aspect includes a plurality of the first push-out mechanisms for one of the first satellite payload units.

[0017] According to the sixth aspect, since multiple first push-out mechanisms are provided for one first satellite payload, the push-out force applied to the first satellite can be adjusted more precisely. For example, the line of action of the resultant force of the push-out forces exerted by the multiple first push-out mechanisms on the first satellite can be adjusted to pass through the center of gravity of the first satellite. In this case, tilting of the first satellite after its deployment can be suppressed.

[0018] A seventh aspect of the satellite deployment method is a satellite deployment method using a satellite deployment mechanism that is launched by a rocket and deploys a satellite, in which the satellite is released from the fixing part that fixes it to the satellite mounting part, and the satellite is pushed in a predetermined moving direction that is inclined relative to the normal to a reference plane provided on the satellite deployment mechanism using a push-out mechanism that pushes out the satellite in a direction inclined relative to the normal.

[0019] According to the seventh aspect, by using the push-out mechanism to push out the satellite in a direction inclined with respect to a reference plane provided in the satellite release mechanism, the satellite can be easily released in a direction inclined with respect to the reference plane.

[0020] The satellite deployment method according to the eighth aspect preferably includes the following additional feature in addition to the satellite deployment method according to the seventh aspect: In the satellite deployment method according to the eighth aspect, when deploying the first and second satellites that are adjacent to each other, the first and second satellites are pushed in directions away from each other.

[0021] According to the eighth aspect, by pushing the first and second satellites arranged adjacent to each other in directions away from each other, it is possible to prevent the first and second satellites from coming into contact with each other when they are released.

[0022] The satellite deployment method according to the ninth aspect is preferably the same as the satellite deployment method according to the eighth aspect, further comprising the following feature: In other words, the satellite deployment method according to the ninth aspect pushes out the first satellite and the second satellite such that a first tilt angle formed between an imaginary movement direction line parallel to the direction in which the first satellite is pushed out and the normal to the reference plane is greater than 0 degrees and less than 90 degrees, and a second tilt angle formed between an imaginary movement direction line parallel to the direction in which the second satellite is pushed out and the normal to the reference plane is greater than -90 degrees and less than 0 degrees, or greater than 90 degrees and less than 180 degrees.

[0023] According to the ninth aspect, by pushing out the first satellite and the second satellite so that the first tilt angle and the second tilt angle are within the above-mentioned angle range, the first satellite and the second satellite can be released in directions away from each other. [Effects of the Invention]

[0024] According to the present disclosure, it is possible to provide a satellite deployment mechanism that can deploy a satellite in a direction inclined relative to the connection surface with the rocket without complicating the structure, and a satellite deployment method using the satellite deployment mechanism. [Brief explanation of the drawings]

[0025] [Figure 1] FIG. 1 is a perspective view schematically illustrating the internal structure of the tip of a rocket equipped with a satellite release mechanism according to a first embodiment of the present disclosure. [Figure 2] FIG. 2 is a perspective view of the rocket in FIG. 1 with the fairing protecting the nose removed. [Figure 3] FIG. 3 is a perspective view showing a state in which the satellite in FIG. 2 has been released. [Figure 4] FIG. 4 is an enlarged perspective view of the periphery of the plate shown in FIGS. 1 to 3. [Figure 5] 5A and 5B are a front view, a side view, and a top view of FIG. 4. [Figure 6] FIG. 2 is a diagram illustrating the shape of a plate. [Figure 7] FIG. 1 is a cross-sectional view of a satellite, a plate, and a pusher mechanism. [Figure 8] FIG. 2 is an enlarged cross-sectional view of the extrusion mechanism. [Figure 9] This is a side view of adjacent satellites in the direction of the rocket's movement. [Figure 10] 10 is a flowchart illustrating the steps performed by the satellite deployment mechanism when deploying a satellite. [Figure 11] FIG. 10 is a diagram schematically illustrating a satellite deployment mechanism according to a second embodiment of the present disclosure. [Figure 12] FIG. 10 is a diagram showing the state of the satellite after it has been released. DETAILED DESCRIPTION OF THE INVENTION

[0026] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, embodiments of a satellite deployment mechanism according to the present disclosure will be described in detail with reference to the drawings.

[0027] [First embodiment] Fig. 1 is a perspective view schematically showing the internal structure of the tip of a rocket 100 equipped with a satellite release mechanism 10 according to a first embodiment of the present disclosure. Fig. 2 is a perspective view of the rocket 100 in Fig. 1 with the fairing 12 protecting the tip removed.

[0028] As shown in FIG. 1, a fairing 12 is attached to the tip of the rocket 100. The fairing 12 is a protective member for protecting the tip of the rocket 100. The fairing 12 is a structure in which a pair of separation bodies 14 of the same shape are connected to each other while facing each other. Only one separation body 14 is shown in FIG. 1. When the pair of separation bodies 14 are connected to each other, the fairing 12 has a shape including a conical portion with a rounded top and a cylindrical portion. The fairing 12 is arranged around the center line Z of the rocket 100. The center line Z is a line parallel to the direction of travel of the rocket 100.

[0029] The fairing 12 contains the satellite deployment mechanism 10, which is launched by the rocket 100 and deploys the satellites, the six satellites 16A-16F to be deployed by the satellite deployment mechanism 10, and the nose 100a of the rocket 100. Note that FIG. 1 shows the structure of the satellite deployment mechanism 10 in a schematic manner, and each of the satellites 16A-16F is also shown as a schematic rectangular parallelepiped. Hereinafter, when there is no need to distinguish between the satellites 16A-16F, they will be referred to as satellites 16.

[0030] The rocket 100 has a tip 100a in the shape of a truncated cone. At the top of the truncated cone is a flat surface 102 that is perpendicular to the direction of travel of the rocket 100. The satellite release mechanism 10 is attached to the flat surface 102.

[0031] The satellite deployment mechanism 10 holds three satellites 16 around the center cylinder 24. The satellite deployment mechanism 10 also holds the satellites 16 in two stages in the direction of travel of the rocket 100. The satellite deployment mechanism 10 releases each satellite 16 in a direction approximately perpendicular to the direction of travel of the rocket 100, i.e., in the radial direction of the center cylinder 24.

[0032] The satellite release mechanism 10 includes a base 18 that holds each satellite 16 and a push-out mechanism 20 that pushes each satellite 16 out of the base 18 .

[0033] The base 18 includes a center cylinder 24 connected to the tip 100a of the rocket 100, plates 26A-26F to which the satellites 16A-16F are respectively fixed, and fixing portions 27A-27F that hold the satellites 16A-16F fixed to the plates 26A-26F. Hereinafter, when there is no need to distinguish between the plates 26A-26F, they will be referred to as the plates 26, and when there is no need to distinguish between the fixing portions 27A-27F, they will be referred to as the fixing portions 27.

[0034] The center cylinder 24 has a cylindrical shape. The lower surface 24a of the center cylinder 24 is, for example, a flat surface. The lower surface 24a is connected to the flat surface 102 of the tip 100a of the rocket 100. The lower surface 24a is part of the base 18 and serves as the connecting surface with the rocket 100 or a reference surface provided on the satellite release mechanism 10. Hereinafter, the lower surface 24a will be referred to as the connecting surface 24a with the rocket 100. The lower surface 24a may have an opening. The lower surface 24a may have, for example, a circular opening centered on the center line Z of the rocket 100. In other words, the lower surface 24a may be a flange protruding from the lower end of the center cylinder 24 toward the center line Z of the rocket 100.

[0035] Center cylinder 24 is disposed about center line Z of rocket 100. Six plates 26A-26F, to which satellites 16 are fixed, are attached to the outer periphery of center cylinder 24. Specifically, satellite 16A is fixed to plate 26A, satellite 16B is fixed to plate 26B, satellite 16C is fixed to plate 26C, satellite 16D is fixed to plate 26D, satellite 16E is fixed to plate 26E, and satellite 16F is fixed to plate 26F.

[0036] The plates 26 are arranged in two tiers in the direction of rocket 100's travel in the center cylinder 24. Specifically, plates 26A, 26C, and 26E are arranged at the front end of the center cylinder 24. Plates 26B, 26D, and 26F are arranged at the rear end of the center cylinder 24. If the direction toward the front end of the center cylinder 24, i.e., the direction of rocket 100's travel, is defined as the upward direction, and the direction toward the rear end of the center cylinder 24 is defined as the downward direction, plate 26B is arranged vertically below plate 26A, plate 26D is arranged vertically below plate 26C, and plate 26F is arranged vertically below plate 26E. Plates 26A and 26B are arranged parallel to each other, plates 26C and 26D are arranged parallel to each other, and plates 26E and 26F are arranged parallel to each other. Plates 26A, 26C, and 26E arranged at the tip end of center cylinder 24 are an example of the first satellite mounting section of the present disclosure, and plates 26B, 26D, and 26F arranged at the end end of center cylinder 24 are an example of the second satellite mounting section of the present disclosure.

[0037] When each satellite 16 is released from the satellite release mechanism 10, the satellite 16 moves in a direction away from each plate 26, as shown in FIG.

[0038] Fixing units 27A-27F are attached to the center of each of plates 26A-26F. Each fixing unit 27 is a mechanism for holding each satellite 16 to each plate 26. When each fixing unit 27 receives a satellite deployment command output from a controller built into rocket 100, it releases the connection between the corresponding plate 26 and the corresponding satellite 16. Since fixing units 27 are well-known technology, detailed description thereof will be omitted. Note that fixing units 27A, 27C, and 27E arranged on plates 26A, 26C, and 26E are examples of first fixing units of the present disclosure, and fixing units 27B, 27D, and 27F arranged on plates 26B, 26D, and 26F are examples of second fixing units of the present disclosure.

[0039] FIG. 4 is an enlarged perspective view of the periphery of plates 26A and 26C in FIGS. 1 to 3. FIG. 5 shows a front view, a side view, and a top view of FIG. 4. FIG. 6 is a diagram illustrating the shape of plate 26A. Note that plates 26A-26F are common to each other, and plates 26B-26F have the same shape as plate 26A. In the following description, plate 26A will be described as plate 26 that shares a shape with the other plates 26B-26F.

[0040] 4 to 6, the plate 26 is a rectangular flat plate having a predetermined thickness. The plate 26 is attached to the center cylinder 24 so that its longitudinal direction is aligned with the center line Z of the center cylinder 24. A fixing part 27A is attached to the center of the plate 26.

[0041] The surface of the plate 26 facing the center cylinder 24 has an arc-shaped recess 22 that follows the outer periphery of the center cylinder 24. The plate 26 is attached with the recess 22 in contact with the outer periphery of the center cylinder 24.

[0042] A satellite support member 28 is attached to one and the other of the longitudinal ends of the plate 26. The satellite support member 28 is a long member having a predetermined thickness, and is attached with its longitudinal direction perpendicular to the longitudinal direction of the plate 26. In other words, the satellite support member 28 is disposed with its longitudinal direction along the circumferential direction of the center cylinder 24. The satellite support member 28 is fixed to the plate 26 by welding or screws.

[0043] The satellite support member 28 has a recessed central portion in the longitudinal direction, which makes the central portion thinner than both ends in the longitudinal direction. The satellite support member 28 has abutment surfaces 28a on both longitudinal sides thereof, which are parallel to a surface 31 of the plate 26 that faces the satellite 16. When the satellite 16 is fixed to the plate 26, the abutment surfaces 28a of the satellite support member 28 abut against the satellite 16. The abutment surfaces 28a of the satellite support member 28 also have through-holes 30 that penetrate the satellite support member 28. Push rods 36 (described later) of the extrusion mechanism 20 are inserted into each through-hole 30. When the satellite 16 is separated from the satellite support member 28, the push rods 36 protrude from the through-holes 30, as shown in FIGS. 4 to 6.

[0044] The plate 26 has a through-hole 29 at each of its four corners, and the extrusion mechanisms 20 are fixed in a state in which the tips of the extrusion mechanisms 20 are inserted into the respective through-holes 29. In other words, four extrusion mechanisms 20 are provided for one plate 26. The extrusion mechanisms 20 have an elongated shape and are fixed in a state in which they pass through the center cylinder 24.

[0045] [Extrusion mechanism structure] The left diagram of Fig. 7 is a side view of the satellite 16 and the plate 26, i.e., a view of the satellite 16 and the plate 26 from the circumferential direction of the center cylinder 24, and the right diagram of Fig. 7 is an enlarged cross-sectional view of the area surrounded by the dashed line in the left diagram of Fig. 7. Fig. 8 is a further enlarged cross-sectional view of the extrusion mechanism 20 of Fig. 7.

[0046] The push-out mechanism 20 includes a casing 32, a push rod 36 housed in the casing 32 and movable relative to the casing 32, a spring 38 that applies a biasing force to the push rod 36 in the direction of protruding from the casing 32, and a push-out force adjustment mechanism 40 that adjusts the push-out force with which the push rod 36 pushes out the satellite 16. In Figures 7 and 8, the side of the push-out mechanism 20 facing the satellite 16 in the longitudinal direction is referred to as the front end side, and the opposite side is referred to as the rear end side.

[0047] The casing 32 is a cylindrical member that is open on one side in the longitudinal direction and has a bottom plate on the other side. The casing 32 is fixed to the center cylinder 24 while passing through the center cylinder 24. The bottom plate 32a, located on the tip side in the longitudinal direction of the casing 32, has an insertion hole 33 through which the push rod 36 is inserted. The diameter of the insertion hole 33 is larger than the diameter of the push rod 36.

[0048] The casing 32 further has a rod support portion 34 that slidably supports the push rod 36. The rod support portion 34 has a disk portion 34a fixed to the inner circumferential wall of the casing 32, and a cylindrical portion 34b that extends from the inner circumferential edge of the disk portion 34a in parallel to the central axis CL of the extrusion mechanism 20. The push rod 36 slides within the cylindrical portion 34b.

[0049] The push rod 36 is a member that is movable along the central axis CL of the push-out mechanism 20. The push rod 36 has a rod portion 36a and a spring holding portion 36b that is connected to the rear end of the rod portion 36a.

[0050] The rod portion 36a is disposed about the central axis CL and moves along the central axis CL. The tip of the rod portion 36a passes through an insertion hole 33 in the bottom plate 32a of the casing 32 and protrudes outside the casing 32. Meanwhile, the rear end of the rod portion 36a is connected to the spring holding portion 36b.

[0051] The spring retaining portion 36b has a cylindrical shape and a bottom plate 42. Specifically, the spring retaining portion 36b includes the bottom plate 42 and a cylindrical portion 44 that extends from the outer peripheral edge of the bottom plate 42 along the central axis CL.

[0052] The bottom plate 42 has a disk shape and is disposed in an orientation perpendicular to the central axis CL. The cylindrical portion 44 is movable along the central axis CL by sliding against the inner circumferential surface of the casing 32. The spring holding portion 36b holds one end of the spring 38, and the one end of the spring 38 abuts against the bottom plate 42.

[0053] The spring 38 is, for example, a coil spring. The spring 38 is arranged inside the casing 32 along the central axis CL. One end of the spring 38 abuts against the bottom plate 42 of the spring holding portion 36b. The other end of the spring 38 abuts against a spring receiving portion 46 (described later) that constitutes the pushing force adjustment mechanism 40.

[0054] The pushing force adjustment mechanism 40 is a mechanism that adjusts the pushing force with which the pushing mechanism 20 pushes out the satellite 16. The pushing force adjustment mechanism 40 is disposed on the rear end side in the longitudinal direction of the pushing mechanism 20. The pushing force adjustment mechanism 40 includes a spring receiving portion 46, a bolt holding portion 48, a load adjustment bolt 50, and a fixing nut 52.

[0055] The spring receiving portion 46 has a double cylindrical shape and a bottom plate 46a, and moves along the direction of the central axis CL within the casing 32. The spring receiving portion 46 has the bottom plate 46a, an inner cylindrical portion 46b, an outer cylindrical portion 46c, and a connecting plate portion 46d.

[0056] The bottom plate 46a is disc-shaped and disposed perpendicular to the central axis CL. The bottom plate 46a abuts against the load adjustment bolt 50. The inner tubular portion 46b is cylindrical and extends parallel to the central axis CL from the outer periphery of the bottom plate 46a. The inner circumferential surface of the inner tubular portion 46b is slidably fitted against the outer circumferential surface of an inner tubular portion 48b (described later) of the bolt holding portion 48. The outer tubular portion 46c is cylindrical, and its outer circumferential surface slides against the inner circumferential surface of the casing 32. The connecting plate portion 46d is ring-shaped and connects the inner tubular portion 46b and the outer tubular portion 46c. The other end of the spring 38 abuts against the connecting plate portion 46d.

[0057] The bolt holding portion 48 is a member that holds the load adjustment bolt 50 and is fixed to the casing 32. The bolt holding portion 48 includes an annular portion 48a having a threaded portion onto which the load adjustment bolt 50 is screwed, an inner cylindrical portion 48b extending from the outer peripheral edge of the annular portion 48a along the central axis CL, a connecting portion 48c extending radially outward from the rear end of the inner cylindrical portion 48b in the direction of the central axis CL, and an outer cylindrical portion 48d extending from the outer peripheral edge of the connecting portion 48c along the central axis CL.

[0058] The annular portion 48a is an annular member disposed inside the inner cylindrical portion 46b of the spring receiving portion 46 and centered on the central axis CL. The annular portion 48a has a threaded portion for screwing in the load adjustment bolt 50. The inner cylindrical portion 48b is cylindrical, and its outer peripheral surface slides against the inner peripheral surface of the inner cylindrical portion 46b. The connecting portion 48c is ring-shaped and connects the inner cylindrical portion 48b and the outer cylindrical portion 48d. The outer cylindrical portion 48d is cylindrical, and its outer peripheral surface is fixed to the inner peripheral surface of the casing 32 by welding or the like. In this way, the bolt holding portion 48 is fixed to the casing 32.

[0059] The load adjustment bolt 50 is screwed into the annular portion 48a of the bolt holder 48, and is arranged parallel to the central axis CL, centered on the central axis CL. The load adjustment bolt 50 has a threaded portion along its entire length. By adjusting the amount of threading of the load adjustment bolt 50, the relative position of the load adjustment bolt 50 in the direction of the central axis CL with respect to the annular portion 48a can be adjusted.

[0060] For example, the more the load adjustment bolt 50 is screwed into the threaded portion of the annular portion 48a, the more the load adjustment bolt 50 moves in the direction of the central axis CL toward the tip of the push-out mechanism 20. At this time, the spring receiving portion 46 that abuts against the load adjustment bolt 50 also moves in the direction of the central axis CL toward the tip of the push-out mechanism 20.

[0061] When the satellite 16 is fixed to the plate 26, the tip of the push rod 36 is pressed against the satellite 16 as shown in FIG. 7. That is, the satellite 16 prevents the push rod 36 from moving in the direction of the central axis CL. At this time, when the load adjustment bolt 50 moves toward the tip in the direction of the central axis CL, the spring receiving portion 46 that abuts against the push rod 36 also moves toward the tip in the direction of the central axis CL. As a result, the compression amount of the spring 38 interposed between the push rod 36 and the spring receiving portion 46 increases, and the pushing force with which the push rod 36 pushes out the satellite 16 increases. In this way, by adjusting the amount of threading of the load adjustment bolt 50, the pushing force generated by the push mechanism 20 can be adjusted. Note that the push rod 36 shown by the two-dot chain line in FIGS. 7 and 8 shows a state in which it is released from the pressure of the satellite 16. At this time, the spring 38 expands, causing the push rod 36 to move to the position shown by the two-dot chain line.

[0062] The fixing nut 52 is screwed onto the load adjustment bolt 50, and the fixing nut 52 abuts against the annular portion 48a. At this time, the fixing nut 52 and the annular portion 48a press against each other, increasing the fastening force between the load adjustment bolt 50 and the threaded portion of the annular portion 48a. As a result, the load adjustment bolt 50 is less likely to move relative to the threaded portion of the annular portion 48a.

[0063] With the above-described configuration, the push-out mechanism 20 generates a push-out force proportional to the compression amount of the spring 38. When this push-out force is transmitted to the satellite 16 and the connection between the satellite 16 and the plate 26 by the fixing part 27 is released, the push-out mechanism 20 pushes the satellite 16 in a direction away from the plate 26 in accordance with the push-out force. As a result, the satellite 16 is released from the satellite release mechanism 10. In addition, the push-out mechanism 20 is equipped with a push-out force adjustment mechanism 40, which allows fine adjustment of the push-out force with which the push rod 36 pushes out the satellite 16.

[0064] As shown in FIGS. 1 to 3, satellites 16A and 16B are arranged adjacent to each other along the center line Z. Similarly, satellites 16C and 16D, and satellites 16E and 16F are arranged adjacent to each other along the center line Z. Increasing the number of satellites carried on the rocket 100 is preferable, as it contributes to improving launch efficiency. To achieve this, it is preferable to narrow the gap S between adjacent satellites 16 along the center line Z on the satellite deployment mechanism 10. However, the narrower the gap S, the higher the possibility of adjacent satellites 16 colliding with each other during deployment.

[0065] In contrast, in this embodiment, the satellite release mechanism 10 is configured to release adjacent satellites 16 in directions away from each other. To achieve this, the push rod 36 of the push mechanism 20 that pushes out the satellite 16 is configured to move in a direction inclined with respect to the normal line Lv of the connection surface 24a. Specifically, as shown in FIG. 8 , an inclination angle θ greater than 0 degrees and less than 90 degrees is formed between a virtual movement direction line Lt parallel to the movement direction of the push rod 36 and the normal line Lv of the connection surface 24a with the rocket 100. The movement direction of the push rod 36 is parallel to the central axis line CL of the push mechanism 20. Therefore, the movement direction line Lt is the same line as the central axis line CL of the push mechanism 20. In this embodiment, the normal line Lv is a line extending perpendicularly from the planar connection surface 24a. The normal line Lv is also a line parallel to the center line Z. Furthermore, if the tip portion 100a is spherical crown-shaped, the center line Z of the rocket 100 may be treated as the normal line Lv.

[0066] As described above, the movement direction of the push rod 36 is inclined with respect to the normal line Lv of the connection surface 24a. Therefore, when a satellite 16 is released from the satellite release mechanism 10, the satellite 16 is pushed out in a diagonal direction with respect to the connection surface 24a, and the satellite 16 is released in a diagonal direction with respect to the connection surface 24a. This makes it possible to release adjacent satellites 16 in directions that separate them by adjusting the respective inclination angles θ of the adjacent satellites 16. Furthermore, because it is only necessary to adjust the movement direction of the push rod 36 when releasing a satellite 16 in a diagonal direction, the mechanism for releasing the satellite 16 in a diagonal direction does not become complicated.

[0067] FIG. 9 is a side view of satellites 16A and 16B, which are adjacent to each other in the direction of the center line Z of the center cylinder 24, i.e., the direction of travel of the rocket 100. The left view of FIG. 9 shows the state before the satellite 16 is released from the satellite release mechanism 10, and the right view of FIG. 9 shows the state after the satellite 16 is released from the satellite release mechanism 10. In FIG. 9, to distinguish between the pusher mechanism 20 located at the front end of the center cylinder 24 and pushing out the satellite 16A, and the pusher mechanism 20 located at the rear end of the center cylinder 24 and pushing out the satellite 16B, the pusher mechanism 20 that pushes out the satellite 16A will be referred to as the first pusher mechanism 20U, and the push rod 36 of the first pusher mechanism 20U will be referred to as the first push rod 36U. The pusher mechanism 20 that pushes out the satellite 16B will be referred to as the second pusher mechanism 20L, and the push rod 36 of the second pusher mechanism 20L will be referred to as the second push rod 36L. Satellite 16A is an example of a first satellite of the present disclosure, satellite 16B is an example of a second satellite of the present disclosure, first extrusion mechanism 20U and first push rod 36U are an example of a first extrusion mechanism and a first extrusion member of the present disclosure, and second extrusion mechanism 20L and second push rod 36L are an example of a second extrusion mechanism and a second extrusion member of the present disclosure.

[0068] As shown in FIG. 9, the movement direction of the first push rod 36U of each first push mechanism 20U that pushes out the satellite 16A is inclined by a first inclination angle θu with respect to the normal Lv of the connection surface 24a with the rocket 100. Specifically, the first inclination angle θu formed between the movement direction line Ltu of the first push rod 36U and the normal Lv of the connection surface 24a is set to an angle greater than 0 degrees and less than 90 degrees. In this embodiment, the first inclination angle θu is set to, for example, 85 degrees. Note that while FIG. 9 shows the satellite 16A being pushed out by two first push mechanisms 20U, in reality, the satellite 16A is pushed out by four first push mechanisms 20U arranged at the four corners of the plate 26A.

[0069] On the other hand, the second push rod 36L of the second extrusion mechanism 20L that extrudes the satellite 16B has a movement direction inclined by a second inclination angle θl with respect to the normal line Lv. Specifically, the second inclination angle θl formed between the movement direction line Ltl of the second push rod 36L and the normal line Lv of the connection surface 24a is set to an angle greater than 90 degrees and less than 180 degrees. In this embodiment, the inclination angle θl is set to, for example, 95 degrees. Note that although FIG. 9 shows the satellite 16B being extruded by two second extrusion mechanisms 20L, in reality, the satellite 16B is extruded by four second extrusion mechanisms 20L arranged at the four corners of the plate 26B.

[0070] In this way, by setting the first tilt angle θu to an angle greater than 0 degrees and less than 90 degrees, and the second tilt angle θl to an angle greater than 90 degrees and less than 180 degrees, the tilt angles θu and θl are different angles with the 90-degree boundary being the boundary. Here, the direction of the tilt angle of 90 degrees is an angle perpendicular to the direction of travel of the rocket 100, i.e., a direction perpendicular to the surfaces 31 of each plate 26A, 26B. Therefore, the satellites 16A and 16B are pushed in directions away from each other with respect to the normal to the surfaces 31 of each plate 26A, 26B. As a result, when the satellites 16A and 16B are deployed, the satellites 16A and 16B are deployed in directions away from each other, preventing contact between the satellites 16A and 16B.

[0071] Furthermore, satellites 16C and 16D, and satellites 16E and 16F, which are adjacent to each other in the direction of travel of rocket 100, are configured similarly to satellites 16A and 16B, and are therefore released in directions away from each other. Satellites 16C and 16E are examples of first satellites in the present disclosure, and satellites 16D and 16F are examples of second satellites in the present disclosure.

[0072] In addition, the position and pushing force of the push-out mechanism 20 that pushes out each satellite 16 are adjusted so that the line of action of the resultant force of the push-out forces acting on each satellite 16 passes through the center of gravity G of the respective satellite 16. In this embodiment, each satellite 16 is pushed out by four push-out mechanisms 20 that are disposed at the four corners of each plate 26. When adjusting the pushing force with which each push-out mechanism 20 pushes out a satellite 16, the center of gravity G is determined for each satellite 16, and the pushing force of each push-out mechanism 20 is adjusted so that the line of action of the resultant force of the push-out forces of the four push-out mechanisms 20 that push out each satellite 16 passes through the respective center of gravity G. This suppresses tilting of each satellite 16 when it is released, thereby preventing contact due to tilting of the satellite 16.

[0073] [Satellite release method] FIG. 10 is a flow chart illustrating the steps performed by the satellite deployment mechanism 10 when deploying the satellite 16.

[0074] First, in step S10, it is determined whether the satellite deployment mechanism 10 has received a satellite deployment command to deploy the satellite 16. If the satellite deployment command has not been received, i.e., if the determination in step S10 is negative, the process returns to step S10. If the satellite deployment command has been received, i.e., if the determination in step S10 is positive, in step S20, the fixation of the satellite 16 by the fixation units 27 that fix the satellite 16 to the plates 26 is released. Note that the fixation units 27 may release the fixation of the satellites 16 at the same time or at different times. Next, in step S30, the pusher mechanism 20 pushes the satellite 16 obliquely relative to the connection surface 24a with the rocket 100, thereby releasing the satellite 16 obliquely relative to the connection surface 24a.

[0075] At this time, satellites 16A, 16C, and 16E are pushed out at a first tilt angle θu greater than 0 degrees and less than 90 degrees, and satellites 16B, 16D, and 16F are pushed out at a second tilt angle θl greater than 90 degrees and less than 180 degrees. This causes satellites 16A, 16C, and 16E and satellites 16B, 16D, and 16F to be pushed in directions away from each other. As a result, contact between satellites 16A, 16C, and 16E and satellites 16B, 16D, and 16F is prevented.

[0076] [Second embodiment] FIG. 11 is a diagram schematically illustrating the structure of a satellite deployment mechanism 70 according to a second embodiment of the present disclosure. In the second embodiment, two satellites, a first satellite 72R and a second satellite 72L, are deployed by the satellite deployment mechanism 70. The direction of deployment of the first satellite 72R and the second satellite 72L is the same as the direction of travel of the rocket 100, i.e., the same as the normal Lv of the connection surface 76 with the rocket 100. The connection surface 76 is a reference surface provided on the satellite deployment mechanism 70. While FIG. 11 illustrates the first satellite 72R and the second satellite 72L arranged adjacent to each other, three or more satellites may be arranged adjacent to each other. In this embodiment, the first satellite 72R and the second satellite 72L are fixed to a common plate 74. In this manner, multiple satellites may be fixed to one plate 74. The plate 74 is an example of a first satellite mounting unit and a second satellite mounting unit according to the present disclosure.

[0077] The first satellite 72R and the second satellite 72L are arranged adjacent to each other in a direction perpendicular to the direction of travel of the rocket 100. To narrow the gap S between the adjacent first satellite 72R and second satellite 72L, the movement direction of the first push rod 36R of the first extrusion mechanism 20R is inclined with respect to the normal line Lv of the connection surface 76. Similarly, the movement direction of the second push rod 36L of the second extrusion mechanism 20L is inclined with respect to the normal line Lv of the connection surface 76. As shown in FIG. 11 , the first satellite 72R is extruded by three first extrusion mechanisms 20R, and the second satellite 72L is extruded by three second extrusion mechanisms 20L. The number of extrusion mechanisms 20R, 20L that extrude the first satellite 72R and the second satellite 72L is not limited to three.

[0078] As shown in FIG. 11 , a first inclination angle θr is formed between a virtual movement direction line Ltr parallel to the movement direction of the first push rod 36R constituting the first extrusion mechanism 20R and a normal line Lv to the connection surface 76. Here, when the clockwise direction with respect to the normal line Lv as the reference, i.e., 0 degrees, is defined as the positive direction, the first inclination angle θr has a positive value. Furthermore, a second inclination angle θl is formed between a virtual movement direction line Ltl parallel to the movement direction of the second push rod 36L constituting the second extrusion mechanism 20L and the normal line Lv to the connection surface 76. Here, when the clockwise direction with respect to the normal line Lv is defined as the positive direction, the second inclination angle θl has a negative value. Thus, since the first inclination angle θr and the second inclination angle θl have different positive and negative values ​​with respect to the normal line Lv, during satellite deployment, the first satellite 72R and the second satellite 72L are pushed in directions away from each other with respect to the normal line Lv. As a result, the first satellite 72R and the second satellite 72L are released in directions away from each other, preventing the first satellite 72R and the second satellite 72L from coming into contact with each other.

[0079] Furthermore, when the satellites are released, it is preferable that the first tilt angle θr is set to an angle greater than 0 degrees and less than 90 degrees, and the second tilt angle θl is set to an angle greater than -90 degrees and less than 0 degrees, so that the adjacent first satellite 72R and second satellite 72L are released in directions that move away from each other. In this embodiment, the first tilt angle θr is set to 5 degrees, and the second tilt angle θl is set to -5 degrees.

[0080] In addition, the line of action of the resultant force of the pushing forces generated when the three first push-out mechanisms 20R push out the first satellite 72R is adjusted to pass through the center of gravity G of the first satellite 72R. Similarly, the line of action of the resultant force of the pushing forces generated when the three second push-out mechanisms 20L push out the second satellite 72L is adjusted to pass through the center of gravity G of the second satellite 72L. As a result, tilting of the first satellite 72R and the second satellite 72L after release is suppressed.

[0081] As described above, the line of action of the resultant force of the pushing forces pushing out the first satellite 72R and the second satellite 72L passes through their respective centers of gravity G, thereby suppressing the tilt of the first satellite 72R and the second satellite 72L after release, but it is difficult to precisely adjust the resultant force of the pushing forces so that it passes through the center of gravity G, and it is possible that the first satellite 72R and the second satellite 72L may tilt due to a misalignment between the resultant force of the pushing forces and the center of gravity G. It is desirable to set the first tilt angle θr and the second tilt angle θl in consideration of this.

[0082] Figure 12(a) shows an example of when 1 second has passed since the release of the first satellite 72R and the second satellite 72L, and Figure 12(b) shows an example of when 10 seconds have passed since the release of the first satellite 72R and the second satellite 72L.

[0083] As shown in FIG. 12(a), one second after the satellites are released, the first satellite 72R is tilted one degree counterclockwise, and the second satellite 72L is tilted one degree clockwise. If the first satellite 72R tilts counterclockwise and the second satellite 72L tilts clockwise, the first satellite 72R and the second satellite 72L are more likely to collide. Furthermore, a tilt of one degree per second corresponds to the maximum imaginable tilt of the first satellite 72R and the second satellite 72L. Thus, even under conditions where the first satellite 72R and the second satellite 72L are most likely to collide, the first satellite 72R and the second satellite 72L are pushed away from each other, so the first satellite 72R and the second satellite 72L do not collide.

[0084] Furthermore, when 10 seconds have passed since the first satellite 72R and the second satellite 72L were released, the first satellite 72R and the second satellite 72L further tilted as shown in Figure 12(b). Specifically, the first satellite 72R tilts 10 degrees counterclockwise, and the second satellite 72L tilts 10 degrees clockwise. Even in this case, the first satellite 72R and the second satellite 72L move further apart, so the first satellite 72R and the second satellite 72L do not come into contact with each other.

[0085] In this way, the first tilt angle θr and the second tilt angle θl are set to angles that prevent the first satellite 72R and the second satellite 72L from touching each other, even if the first satellite 72R and the second satellite 72L are tilted after the satellites are released. Specifically, the first tilt angle θr and the second tilt angle θl are set within a range that prevents the first satellite 72R and the second satellite 72L from touching each other, relative to the maximum tilt that is expected when the first satellite 72R and the second satellite 72L are tilted after the satellites are released.

[0086] [Variations] In the above embodiment, the center cylinder 24 constituting the base 18 has a cylindrical shape, but the present disclosure is not limited to this. That is, when viewed from above, the center cylinder 24 may have a polygonal shape such as a triangle or a rectangle.

[0087] In the first embodiment, the satellite release mechanism 10 has three satellites 16 arranged in the circumferential direction of the base 18, and the satellites 16 arranged in two stages in the direction of travel of the rocket 100, but the number of satellites arranged in the circumferential direction and the number of stages of satellites arranged in the direction of travel of the rocket 100 are not limited to this. For example, two or four or more satellites 16 may be arranged in the circumferential direction of the base 18, or the satellites 16 may be arranged in three or more stages in the direction of travel of the rocket 100. In this regard, the number of satellites arranged on the base 18 may be changed as appropriate.

[0088] In the first embodiment, four push-out mechanisms 20 are provided for one plate 26, but the present disclosure is not limited to four push-out mechanisms 20. For example, two push-out mechanisms 20 may be provided for one plate 26, or three or five or more push-out mechanisms 20 may be provided for one plate 26. Furthermore, one push-out mechanism 20 may be provided for one plate 26. Note that even when the number of push-out mechanisms is changed, it is desirable to adjust the resultant force of the push-out forces generated by the respective push-out mechanisms so that it passes through the center of gravity G of the satellite.

[0089] In the first embodiment, satellite 16A is fixed to plate 26A, and satellite 16B is fixed to plate 26B, but satellites 16A and 16B may be fixed to a common plate. Similarly, satellites 16C and 16D may be fixed to a common plate, and satellites 16E and 16F may be fixed to a common plate. Furthermore, in the second embodiment, first satellite 72R and second satellite 72L are fixed to a common plate 74, but first satellite 72R and second satellite 72L may each be fixed to a separate plate. [Explanation of symbols]

[0090] 10:Satellite release mechanism 16A, 16C, 16E: 1st satellite (satellite) 16B, 16D, 16F: 2nd satellite (satellite) 18: Base 20: Extrusion mechanism 20R, 20U: First extrusion mechanism 20L: Second extrusion mechanism 24a: Connection surface with rocket (reference surface) 26A, 26C, 26E: Plates (first satellite mounting section) 26B, 26D, 26F: Plate (Second Satellite Mounting Section) 27A, 27C, 27E: 1st fixed part 27B, 27D, 27F: 2nd fixed part 36U: Push rod (first extrusion member) 36L: Push rod (second extrusion member) 40: Extrusion force adjustment mechanism 70:Satellite release mechanism 72R: 1st satellite (satellite) 72L: 2nd satellite (satellite) 74: Plate (first satellite mounting part, second satellite mounting part) 76: Connection surface with rocket (reference surface) 100: Rocket

Claims

1. A satellite deployment mechanism that is launched by a rocket and deploys a satellite, a base including a first satellite mounting part to which a first satellite is fixed, a first fixing part that holds the first satellite on the first satellite mounting part, and a connecting surface with the rocket; a first pushing mechanism for pushing the first satellite out of the base, the first pushing mechanism including a first pushing member that pushes the first satellite by moving in a predetermined moving direction that is inclined at a first inclination angle with respect to a normal to a connecting surface with the rocket.

2. 2. The satellite deployment mechanism according to claim 1, a first tilt angle formed between a virtual movement direction line parallel to the movement direction of the first pusher member and a normal to a connection surface with the rocket, the first tilt angle being set to an angle greater than 0 degrees and less than 90 degrees.

3. 2. The satellite deployment mechanism according to claim 1, the base further includes a second satellite mounting portion to which a second satellite is fixed, and a second fixing portion that holds the second satellite on the second satellite mounting portion; the satellite release mechanism further comprises a second pushing mechanism, which is a mechanism for pushing the second satellite out of the base, and includes a second pushing member that pushes out the second satellite by moving in a predetermined moving direction that is inclined at a second inclination angle with respect to a normal to a connecting surface with the rocket; the second tilt angle is different from the first tilt angle.

4. 4. The satellite deployment mechanism according to claim 3, the first tilt angle is set to an angle greater than 0 degrees and less than 90 degrees, The satellite release mechanism, wherein the second tilt angle is set to an angle greater than 90 degrees and less than 180 degrees, or an angle greater than −90 degrees and less than 0 degrees.

5. The satellite deployment mechanism according to any one of claims 1 to 4, The first pushing mechanism includes a pushing force adjustment mechanism that adjusts the pushing force with which the first pushing member pushes out the first satellite.

6. 6. The satellite deployment mechanism according to claim 5, A satellite deployment mechanism including a plurality of the first push-out mechanisms for one of the first satellite payloads.

7. A satellite deployment method using a satellite deployment mechanism that is launched by a rocket and deploys a satellite, comprising: Releasing the fixation by the fixing part that fixes the satellite to the satellite mount part; a satellite deployment method, wherein a push-out mechanism provided on the satellite deployment mechanism pushes out the satellite in a predetermined moving direction inclined with respect to a normal to a reference plane, the push-out mechanism pushing out the satellite in a direction inclined with respect to the normal;

8. 8. A satellite deployment method according to claim 7, comprising: A satellite deployment method, wherein when deploying a first satellite and a second satellite that are arranged adjacent to each other, the first satellite and the second satellite are pushed in directions away from each other.

9. 9. A satellite deployment method according to claim 8, comprising: a first tilt angle formed between a virtual movement direction line parallel to the direction in which the first satellite is pushed out and the normal to the reference plane is greater than 0 degrees and less than 90 degrees, and a second tilt angle formed between a virtual movement direction line parallel to the direction in which the second satellite is pushed out and the normal to the reference plane is greater than -90 degrees and less than 0 degrees, or greater than 90 degrees and less than 180 degrees.

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