CN111216924A - Satellite distributor and carrier rocket system - Google Patents
Satellite distributor and carrier rocket system Download PDFInfo
- Publication number
- CN111216924A CN111216924A CN202010179570.7A CN202010179570A CN111216924A CN 111216924 A CN111216924 A CN 111216924A CN 202010179570 A CN202010179570 A CN 202010179570A CN 111216924 A CN111216924 A CN 111216924A
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- satellite
- support
- longitudinal
- support plate
- cross beam
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Abstract
The invention provides a satellite distributor and a carrier rocket system, wherein the satellite distributor comprises: a support plate structure comprising a plurality of layers of support plates; the longitudinal supporting structure is connected between two adjacent layers of the supporting plates; the beam structure comprises a first beam and a second beam which are arranged on opposite surfaces of two layers of support plates which are adjacent from top to bottom, the first beam and the second beam are arranged oppositely and are distributed radially, and the first beam and the second beam form an installation position suitable for fixedly installing the catapult of the cube star. The satellite distributor can be suitable for installation of the cubic stars, and during installation, the cubic stars can be connected to two sides of the same cross beam, so that the satellite distributor can be used for installing a plurality of cubic stars simultaneously, the satellites can be separated one by one and can also be separated in the same time period, and risks of collision or interference cannot exist between the satellites.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a satellite distributor and a carrier rocket system.
Background
In recent years, launching of microsatellites has become a main demand for commercial launching, and the demand for launching of microsatellites is increasing, but since a rocket is too expensive for a microsatellite and a microsatellite can be purchased for commercial launching, in recent years, the microsatellites are often in a mode of carrying and launching.
When the microsatellite is used for carrying and launching, the launching period of the main satellite influences the launching period of the main satellite, the time cost is high, and most microsatellites are separated after the main satellite is separated, so that the orbit of the microsatellite only can be transferred to the orbit of the main satellite, and the launching of the microsatellites is negatively influenced.
The method provides a launching platform for the microsatellite, which is particularly important for commercial aerospace, and has great commercial value. The cuboids are low-cost micro-nano satellites adopting international universal standards, and the volume of 1U is 10 centimeters multiplied by 10 centimeters by taking U as a unit. Because the cube star component adopts the universalization, modularization and standardization design concept, the cube star has the characteristics of low development cost, large function density, high technical maturity and short development period, under the normal condition, the cube star is installed in an ejector which is a cuboid box, and after the cube star reaches a designated position along with a carrier rocket, a door of the ejector is opened to eject the cube star. The cuboids become the main satellites for commercial use, and the current satellite distributors are all provided for specific satellites, and no satellite distributor suitable for the cuboids is provided.
Disclosure of Invention
Therefore, an object of the present invention is to provide a satellite dispenser and a launch vehicle system that are suitable for cube installation.
The invention provides a satellite distributor, comprising:
a support plate structure comprising a plurality of layers of support plates;
the longitudinal supporting structure is connected between two adjacent layers of the supporting plates;
the beam structure comprises a first beam and a second beam which are arranged on opposite surfaces of two layers of support plates which are adjacent from top to bottom, the first beam and the second beam are arranged oppositely and are distributed radially, and the first beam and the second beam form an installation position suitable for fixedly installing the ejector.
The longitudinal supporting structure comprises a central supporting piece connected to the central position of the supporting plates on two adjacent layers, and the first cross beams and the second cross beams are radially arranged on the central supporting piece.
The central supporting piece comprises an upper circular chassis, a lower circular chassis and a plurality of longitudinal connecting plates, the upper circular chassis and the lower circular chassis are suitable for being fixedly connected with the supporting plate, the longitudinal connecting plates are connected between the two circular chassis and are distributed radially, and slots suitable for the insertion of the beam structures are formed in the circular chassis.
The longitudinal support structure further comprises at least one longitudinal beam connecting the first cross beam and the second cross beam, and the longitudinal beam is perpendicular to the first cross beam and the second cross beam.
The longitudinal beam is connected between each first cross beam and each second cross beam, and the longitudinal beams, the first cross beams, the second cross beams and the central support piece form a square frame in an enclosing mode.
The supporting plate is of a triangle-like structure, the number of the first cross beams and the number of the second cross beams are three, and the length extending directions of the first cross beams and the second cross beams are coincided with the central line of the triangle-like structure.
The supporting plate comprises three end parts and three arc-shaped edges for connecting any two end parts, and straight lines for connecting the two end parts are positioned outside the supporting plate.
The supporting plate on the uppermost layer is connected with a plurality of transverse mounting plates, and the transverse mounting plates are suitable for mounting the ejector.
The transverse mounting plates are provided with a plurality of transverse mounting plates, and the size of each transverse mounting plate is adapted to the ejector.
The supporting plate is provided with three layers.
The backup pad includes upper skin, lower floor's skin and connects upper skin with the net rib between the skin of lower floor.
The invention also provides a carrier rocket system which comprises a satellite support and the satellite distributor connected to the satellite support.
The technical scheme of the invention has the following advantages:
1. the satellite distributor provided by the invention is provided with the multiple layers of supporting plates, the first cross beam and the second cross beam are respectively arranged on the opposite surfaces of the two layers of supporting plates which are adjacent up and down, the ejector for installing the cube star is provided with the standard screw hole, the ejector is fixed on the cross beam through the screw, and the cube star is a universal standard satellite, so that the satellite distributor can be suitable for installing the cube star.
2. The satellite distributor provided by the invention has the advantages that the longitudinal supporting structure comprises a central supporting piece connected to the central positions of two adjacent layers of supporting plates, the first cross beams and the second cross beams are radially arranged on the central supporting piece, the central supporting piece plays a main force bearing role in the middle, the structure is simple, and the first cross beams and the second cross beams are radially arranged on the central supporting piece, so that the structure is stable.
3. According to the satellite distributor provided by the invention, the central supporting piece comprises an upper circular chassis and a lower circular chassis which are suitable for being fixedly connected with the supporting plate, and a plurality of longitudinal connecting plates which are connected between the two circular chassis and radially distributed, the circular chassis is provided with the slots suitable for the insertion of the beam structure, and the structure of the central supporting piece greatly lightens the mass and can meet the requirement of required bearing load.
4. According to the satellite distributor provided by the invention, the longitudinal support structure further comprises at least one longitudinal beam for connecting the first cross beam and the second cross beam, the longitudinal beam is perpendicular to the first cross beam and the second cross beam, and the arrangement of the longitudinal beam can increase the connection rigidity of two adjacent layers of support plates up and down, so that the connection stability of a satellite on the distributor is ensured.
5. According to the satellite distributor provided by the invention, one longitudinal beam is connected between each first cross beam and each second cross beam, the longitudinal beams, the first cross beams, the second cross beams and the central support part form a square frame in a surrounding manner, the square frame can be used for positioning the installation position of the ejector, and the transmission of the satellite flight load to the cabin body is realized through the longitudinal beams from top to bottom, so that the force transmission path is simple, no bending path exists, and the occupation of the space in the fairing can be reduced.
6. According to the satellite distributor provided by the invention, the supporting plate is of a triangle-like structure, the number of the first cross beams and the number of the second cross beams are respectively three, the length extending directions of the first cross beams and the second cross beams are superposed with the center line of the triangle-like structure, the triangular structure is adopted, the stress strength can be greatly improved, and the weight is light.
7. According to the satellite distributor provided by the invention, the support plate comprises three end parts and three arc-shaped edges for connecting any two end parts, the straight line for connecting the two end parts is positioned outside the support plate, the weight of the support plate is light, and the stress strength can be ensured.
8. According to the satellite distributor provided by the invention, the supporting plate positioned on the uppermost layer is connected with the plurality of transverse mounting plates, and the transverse mounting plates are suitable for mounting the ejectors, so that the satellite distributor can be ensured to mount satellites.
9. According to the satellite distributor provided by the invention, the plurality of transverse mounting plates are arranged, and the size of each transverse mounting plate is matched with that of the ejector, so that the satellite can be conveniently positioned and mounted.
10. According to the satellite distributor provided by the invention, the supporting plates are provided with three layers, and a large number of satellites can be installed in the satellite distributor under the condition that the load of a carrier rocket is met.
11. According to the satellite distributor provided by the invention, the supporting plate comprises the upper skin, the lower skin and the grid ribs connected between the upper skin and the lower skin, and the supporting plate is high in strength and light in weight.
12. The carrier rocket system provided by the invention comprises a satellite support and the satellite distributor connected to the satellite support, and can separate a plurality of satellites simultaneously when the carrier rocket system launches the rocket, so that the launching cost of a single satellite is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural view of a satellite dispenser provided in embodiment 1 of the present invention;
FIG. 2 is a schematic view of the satellite dispenser of FIG. 1 without the transverse mounting plate;
FIG. 3 is a schematic structural view of a support plate of the satellite dispenser shown in FIG. 1;
FIG. 4 is a schematic view of the satellite dispenser of FIG. 1 mounted on a satellite support;
description of reference numerals:
1-a support plate; 11-end portion; 12-an arc-shaped edge; 2-a first beam; 3-a central support; 4-longitudinal beams; 5-transverse mounting plate; 6-a second beam; 7-a catapult; 8-satellite support.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Example 1
The present embodiment provides a specific implementation of a satellite dispenser, which is applied to a launch vehicle, as shown in fig. 1 and 2, and includes: a supporting plate structure, a longitudinal supporting structure and a beam structure.
The supporting plate structure includes a plurality of layers of supporting plates 1, and in this embodiment, the supporting plate structure includes three layers of supporting plates 1, which are a first layer, a second layer, and a third layer from bottom to top. Each supporting plate 1 is of a triangle-like structure, the number of the first cross beams 2 and the number of the second cross beams 6 are three on the supporting plate 1, and the length extending directions of the first cross beams 2 and the second cross beams 6 are coincided with the central line of the triangle-like structure.
Specifically, as shown in fig. 3, the support plate 1 includes three end portions 11 and three arc-shaped sides 12 connecting any two end portions 11, and a straight line connecting the two end portions 11 is located outside the support plate 1.
The supporting plate 1 comprises an upper skin, a lower skin and a grid rib connected between the upper skin and the lower skin. The support plate 1 is high in strength and light in weight. When the processing is carried out, the supporting plate 1 is formed by an aluminum alloy machine, and the processing cost is lower.
The longitudinal supporting structure is connected between the two adjacent layers of supporting plates 1, is used for connecting the two adjacent layers of supporting plates 1 up and down, and plays a supporting role.
The beam structure comprises a first beam 2 and a second beam 6 which are respectively arranged on opposite surfaces of upper and lower adjacent two layers of supporting plates 1, the first beam 2 and the second beam 6 are oppositely arranged and are radially distributed, and the first beam 2 and the second beam 6 form installation positions suitable for fixedly installing ejectors 7. In the present embodiment, three cross beams are disposed on the upper end surface or the lower end surface of each supporting plate 1, and the included angle between any two cross beams is 120 °. When the device is installed, one ejector 7 is installed on the same side of the first cross beam 2 and the second cross beam 6 which are opposite up and down, so that two ejectors 7 can be installed on the left side and the right side of each group of the first cross beam 2 and the second cross beam 6 which are opposite, 6 ejectors 7 can be installed between every two layers of support plates 1 which are adjacent up and down, and the support plates 1 of the embodiment have three layers, so that 12 ejectors 7 can be installed between the layers of the support plates 1.
More specifically, the distance between two adjacent layers of the supporting plates 1 is slightly larger than the side length of the ejector 7 for mounting the 6U cube star, and the satellite distributor of the embodiment is particularly used for mounting the 6U cube star. The catapult 7 is preset with screw holes, and when the catapult 7 is installed, the catapult 7 is fixed on the first cross beam 2 and the second cross beam 6 through screws.
The longitudinal supporting structure comprises a central supporting piece 3 connected to the central position of two adjacent layers of supporting plates 1, and first cross beams 2 and second cross beams 6 are radially arranged on the central supporting piece 3.
The central supporting piece 3 comprises an upper circular chassis, a lower circular chassis and a plurality of longitudinal connecting plates, wherein the upper circular chassis and the lower circular chassis are suitable for being fixedly connected with the supporting plate 1, the longitudinal connecting plates are connected between the two circular chassis and are distributed radially, and the circular chassis is provided with a slot suitable for being inserted into a beam structure. This construction of the central support 3 reduces the mass to a great extent and at the same time meets the requirements for the required load-bearing capacity. The upper circular chassis and the lower circular chassis are connected with the supporting plate 1 through screws, and when the cross beam is installed on the central supporting piece 3, the cross beam is inserted into the inserting groove of the circular chassis and is connected with the longitudinal connecting plate through screws.
The longitudinal support structure further comprises at least one longitudinal beam 4 connecting the first cross beam 2 and the second cross beam 6, the longitudinal beam 4 being perpendicular to the first cross beam 2 and the second cross beam 6. The longitudinal beam 4 can increase the connection rigidity of the two layers of support plates 1 which are adjacent up and down, thereby ensuring the connection stability of the satellite on the distributor.
A longitudinal beam 4 is connected between each first cross beam 2 and each second cross beam 6, and the longitudinal beam 4, the first cross beams 2, the second cross beams 6 and the central support 3 form a square frame in an enclosing mode. The upper side and the lower side of one side surface of the ejector 7 are fixed on the first cross beam 2 and the second cross beam 6, and the left side and the right side are abutted against the longitudinal beam 4 and the central support member 3. The square frame can be used for positioning the mounting position of the ejector 7, the satellite flight load is transferred to the cabin body from top to bottom through the longitudinal beam 4, the force transfer path is simple, no bending path exists, and the space in the fairing can be occupied. And the cover body of the ejector 7 is arranged at one side of the satellite distributor facing to the outer side, so that the ejector 7 can automatically open the cover body to eject the satellite. The longitudinal beam 4 and the cross beam are connected through screws.
The supporting plate 1 positioned on the uppermost layer is connected with a plurality of transverse mounting plates 5, the transverse mounting plates 5 are suitable for mounting the ejector 7, and the transverse mounting plates 5 are connected with the supporting plate 1 through screws. The cross beam, the longitudinal beam 4 and the transverse mounting plate 5 are all formed by aluminum alloy machining.
The transverse mounting plates 5 are provided in plurality, and the size of each transverse mounting plate 5 is adapted to the ejector 7. Specifically, three transverse mounting plates 5 are provided, so that three cuboids can be mounted on the uppermost supporting plate 1, a total of 15 standard interface 6U satellites can be mounted on the satellite distributor, and correspondingly, a carrier rocket can carry at most 15 standard interface 6U satellites.
The maximum outer diameter of the satellite distributor, namely the distance from the center of the support plate 1 to the end part 11 is 1100mm, the maximum outer diameter of the central support part 3, namely the diameter of the circular chassis is 150mm, and the cross beam and the longitudinal beam 4 are both in a C-shaped structure, so that the rigidity of the satellite distributor can be ensured to a large extent.
This satellite distributor can be applicable to the installation of cube star to the accessible is adjusted the distance between the adjacent two-layer backup pad 1 from top to bottom, thereby satisfies the installation of the cube star of different specifications, and during the installation, the cube star all can be connected to the both sides of same crossbeam, consequently, this satellite distributor can install many cube stars simultaneously, and many satellites can separate one by one, also can separate by same time quantum, can not have the risk of collision or interference each other. The satellite distributor is large in bearing capacity, light in weight, simple in structure, convenient to assemble, high in generalization degree, small in space occupied in a cabin due to the structural form, and capable of effectively reducing the mass of a last-stage rocket, so that the carrying capacity of the rocket is improved.
Example 2
The embodiment provides a launch vehicle system, as shown in fig. 4, which comprises a satellite support 8 and a satellite distributor connected to the satellite support 8, wherein the launch vehicle system can separate a plurality of satellites simultaneously when launching the rocket, and the cost of launching a single satellite is reduced. Specifically, the bottom support plate 1 of the satellite distributor is connected to the last secondary satellite support 8 through screws.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (12)
1. A satellite dispenser, comprising:
a support plate structure comprising a plurality of layers of support plates (1);
the longitudinal supporting structure is connected between two adjacent layers of the supporting plates (1);
crossbeam structure, including dividing first crossbeam (2), second crossbeam (6) on the opposite face of being set up adjacent two-layer backup pad (1) from top to bottom, first crossbeam (2), second crossbeam (6) set up relatively, and all are radial distribution, first crossbeam (2) second crossbeam (6) form the installation position that is suitable for catapult (7) fixed mounting.
2. Satellite dispenser according to claim 1, wherein said longitudinal support structure comprises a central support (3) connected at a central position of two adjacent layers of said support plate (1), said first cross-members (2), said second cross-members (6) being radially mounted on said central support (3).
3. Satellite distributor according to claim 2, wherein said central support (3) comprises two upper and lower circular chassis suitable for being fixedly connected to said support plate (1), and a plurality of longitudinal connecting plates connected between said two circular chassis and radially distributed, said circular chassis being provided with slots suitable for the insertion of said cross-beam structure.
4. Satellite dispenser according to claim 2, wherein the longitudinal support structure further comprises at least one longitudinal beam (4) connecting the first cross beam (2) and the second cross beam (6), the longitudinal beam (4) being perpendicular to the first cross beam (2) and the second cross beam (6).
5. The satellite dispenser according to claim 4, wherein one longitudinal beam (4) is connected between each first cross beam (2) and the second cross beam (6), and the longitudinal beam (4), the first cross beam (2), the second cross beam (6) and the central support (3) enclose a square frame.
6. The satellite dispenser according to any one of claims 1-5, wherein the support plate (1) is a triangle-like structure, three beams (2, 6) are respectively arranged on the support plate (1), and the length extension directions of the beams (2, 6) coincide with the middle line of the triangle-like structure.
7. Satellite dispenser according to claim 6, wherein the support plate (1) comprises three ends (11) and three curved sides (12) connecting any two of the ends (11), the straight line connecting the two ends (11) being located outside the support plate (1).
8. Satellite distributor according to claim 1, wherein a number of transverse mounting plates (5) are connected to the uppermost support plate (1), said transverse mounting plates (5) being adapted to mount the ejector (7).
9. Satellite dispenser according to claim 8, wherein said transversal mounting plate (5) is provided in plurality, and each of said transversal mounting plates (5) is sized to fit said ejector (7).
10. Satellite dispenser according to any one of claims 1-9, wherein the support plate (1) is provided with three layers.
11. Satellite dispenser according to claim 1, wherein the support plate (1) comprises an upper skin, a lower skin, and a grid rib connected between the upper and lower skins.
12. A launch vehicle system, characterized in that it comprises a satellite support (8) and a satellite dispenser according to any one of claims 1-11 connected to said satellite support (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010179570.7A CN111216924A (en) | 2020-03-13 | 2020-03-13 | Satellite distributor and carrier rocket system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010179570.7A CN111216924A (en) | 2020-03-13 | 2020-03-13 | Satellite distributor and carrier rocket system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111216924A true CN111216924A (en) | 2020-06-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010179570.7A Withdrawn CN111216924A (en) | 2020-03-13 | 2020-03-13 | Satellite distributor and carrier rocket system |
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| Country | Link |
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| CN (1) | CN111216924A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061421A (en) * | 2020-09-24 | 2020-12-11 | 上海宇航系统工程研究所 | Multi-satellite parallel transmitting device based on auxiliary support |
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
-
2020
- 2020-03-13 CN CN202010179570.7A patent/CN111216924A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112061421A (en) * | 2020-09-24 | 2020-12-11 | 上海宇航系统工程研究所 | Multi-satellite parallel transmitting device based on auxiliary support |
| CN113581493A (en) * | 2021-07-30 | 2021-11-02 | 北京微焓科技有限公司 | Plate-shaped satellite main frame and plate-shaped satellite |
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| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Applicant after: Beijing Star glory Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. Applicant before: Beijing Star glory Technology Co.,Ltd. |
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Application publication date: 20200602 |
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