CN113371228A - Truss type satellite structure suitable for point type satellite-rocket separation mode - Google Patents
Truss type satellite structure suitable for point type satellite-rocket separation mode Download PDFInfo
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- CN113371228A CN113371228A CN202110662522.8A CN202110662522A CN113371228A CN 113371228 A CN113371228 A CN 113371228A CN 202110662522 A CN202110662522 A CN 202110662522A CN 113371228 A CN113371228 A CN 113371228A
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- 210000001503 joint Anatomy 0.000 claims abstract description 57
- 239000002131 composite material Substances 0.000 claims abstract description 25
- 238000005192 partition Methods 0.000 claims description 8
- 239000000853 adhesive Substances 0.000 claims description 7
- 230000001070 adhesive effect Effects 0.000 claims description 7
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000003292 glue Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 238000004804 winding Methods 0.000 claims description 2
- 239000011159 matrix material Substances 0.000 claims 1
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- 238000010923 batch production Methods 0.000 abstract description 3
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- 108010066057 cabin-1 Proteins 0.000 description 11
- 108010066114 cabin-2 Proteins 0.000 description 8
- 230000005540 biological transmission Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 239000000805 composite resin Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
- B64G1/643—Interstage or payload connectors for arranging multiple satellites in a single launcher
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Abstract
The invention discloses a truss type satellite structure suitable for a point type satellite-rocket separation mode, which comprises a composite material truss and a honeycomb sandwich structure plate, and is provided with a platform cabin and a load cabin; the composite material truss comprises a platform cabin truss upright rod, a load cabin truss upright rod, a truss cross rod, a hoisting joint, a satellite-rocket separation joint and an inter-cabin butt joint; the load cabin truss upright rods correspond to the platform cabin truss upright rods one by one; the bottom end of the platform cabin truss upright rod is fixedly connected with a satellite-rocket separation joint, and the top end of the platform cabin truss upright rod is fixedly connected with the bottom end of the load cabin truss upright rod through an inter-cabin butt joint; the top end of the load cabin truss upright rod is fixedly connected with a hoisting joint. The satellite structure can meet the requirements of the satellite on strength, rigidity, precision and various interfaces, is easy to process and assemble, and can meet the requirements of product batch production and modularized subdivision operation.
Description
Technical Field
The invention relates to the technical field of satellite structure design, in particular to a truss type satellite structure suitable for a point type satellite-rocket separation mode.
Background
At present, the structure of the domestic non-return satellite mostly adopts a central bearing cylinder and structural plate type (plate cylinder type) configuration or a structural plate type (plate frame type) configuration, and the structure and a carrying interface mostly adopt a belted type connection and separation mode. With the requirement of a satellite networking on a one-arrow-and-multi-satellite launching structure, the traditional plate-cylinder type and plate-frame type satellite structures are difficult to adapt to the requirement that the one-arrow-and-multi-satellite launching adopts point type explosion bolt satellite-and-arrow connection and separation.
Disclosure of Invention
In view of the above, the invention provides a truss type satellite structure suitable for a point type satellite-rocket separation mode, which can meet the requirements of the satellite on strength, rigidity, precision and various interfaces, is easy to process and assemble, and can meet the requirements of mass production and modularized subdivision operation of products.
The invention adopts the following specific technical scheme:
a truss type satellite structure suitable for a point-type satellite-rocket separation mode comprises a composite material truss for bearing force and a honeycomb sandwich structure plate fixedly connected to the composite material truss, wherein a platform cabin and a load cabin positioned at the top of the platform cabin are enclosed by the honeycomb sandwich structure plate;
the composite material truss comprises platform cabin truss upright rods extending in the vertical direction, load cabin truss upright rods extending in the vertical direction, truss cross rods extending in the horizontal direction, hoisting joints, satellite-rocket separation joints and inter-cabin butt joints;
the platform cabin truss upright rods are distributed along the circumferential direction of the platform cabin;
the load cabin truss upright rods are distributed along the circumferential direction of the load cabin and correspond to the platform cabin truss upright rods one by one;
the bottom end of the platform cabin truss upright rod is fixedly connected with the satellite-rocket separation joint, and the top end of the platform cabin truss upright rod is fixedly connected with the bottom end of the load cabin truss upright rod through the inter-cabin butt joint;
the top end of the load cabin truss upright rod is fixedly connected with the hoisting joint;
and one truss cross rod is fixedly connected between the circumferentially adjacent hoisting joints, between the adjacent satellite-rocket separation joints and between the adjacent cabin butt joints.
Furthermore, the platform cabin truss upright rods, the load cabin truss upright rods and the truss cross rods are formed by winding high-modulus carbon fiber M55J resin-based composite materials.
Furthermore, the satellite-rocket separation joint, the hoisting joint and the inter-cabin butt joint are all formed by machining aluminum alloy.
Furthermore, the satellite-rocket separation joint is provided with a rod piece connecting interface for connecting the platform cabin truss upright rods and the truss cross rods, a tool interface for connecting a ground tool, a satellite-rocket connecting interface for connecting the satellite-rocket connecting and separating device and a plate interface for connecting the honeycomb sandwich structure plate.
Furthermore, the inter-cabin butt joint comprises an upper joint and a lower joint which are detachably connected;
the upper joint is provided with a vertical rod interface for connecting a vertical rod of the load cabin truss;
the lower joint is provided with a rod piece connecting interface used for connecting the platform cabin truss upright rod and the truss cross rod and a plate interface used for connecting the honeycomb sandwich structure plate.
Furthermore, the hoisting joint is provided with a hoisting hole for connecting a hoisting tool, a plate interface for connecting the honeycomb sandwich structure plate and a rod connecting interface for connecting the truss cross rod and the load cabin truss upright rod.
Furthermore, the load cabin truss vertical rod, the platform cabin truss vertical rod and the truss cross rod are all bonded by normal-temperature curing glue to form a plurality of structural slab connecting pieces, and the structural slab connecting pieces are used for connecting the honeycomb sandwich structural slab.
Still further, the honeycomb sandwich structure panel comprises a platform honeycomb sandwich structure panel and a load compartment honeycomb sandwich structure panel;
the platform honeycomb sandwich structure plate comprises a platform bottom plate, a platform side plate, a platform partition plate and a middle plate;
the load cabin honeycomb sandwich structure plate comprises a load cabin side plate, a load cabin top plate and a load cabin partition plate.
Further, the platform cabin truss upright rods are connected to the satellite-rocket separation joints and the inter-cabin butt joints through rod pieces in an adhesive mode;
the load cabin truss upright rods are connected with the inter-cabin butt joints and the hoisting joints through rod pieces in an adhesive manner;
the truss cross rod is connected with the hoisting joint, the inter-cabin butt joint and the satellite-rocket separation joint through rod pieces in an adhesive mode.
Furthermore, the composite material truss is of a cuboid structure;
four platform cabin truss upright rods are distributed along the circumferential direction of the platform cabin.
Has the advantages that:
the truss type satellite structure adopts the composite truss as a main bearing structure, the honeycomb sandwich structure plate is fixedly installed on the composite truss, the assembling structure of the truss and the honeycomb sandwich structure plate is simple, the satellite and arrow butt joint is a truss joint, the force transmission path is shortest, the satellite and arrow butt joint is simple and direct, the concentrated load can be effectively borne and transmitted, meanwhile, the satellite and arrow butt joint can also provide an interface with a carrying tool and a ground tool, the requirements of the satellite on strength, rigidity, precision and various interfaces can be met by adopting the structure, the processing and the assembling are easy, and the requirements of product batch production and modularized cabin division operation can be met.
Drawings
FIG. 1 is a schematic perspective view of a trussed satellite structure according to the present invention;
FIG. 2 is a schematic view of a split structure of the trussed satellite construction of FIG. 1;
FIG. 3 is an exploded view of the trussed satellite configuration of FIG. 1;
FIG. 4 is a schematic perspective view of a composite truss of the trussed satellite construction of FIG. 1;
FIG. 5 is a schematic perspective view of a satellite-rocket separation joint of the composite truss of FIG. 4;
FIG. 6 is a perspective view of the alternate view of the satellite-rocket separation joint of FIG. 5;
FIG. 7 is a schematic perspective view of a lifting sub of the composite truss of FIG. 4;
fig. 8 is a schematic view of the assembly structure of the platform bottom plate and the platform side plates with the truss cross bars.
Wherein, 1-platform cabin, 2-load cabin, 3-platform cabin truss upright rod, 4-load cabin truss upright rod, 5-truss cross rod, 6-hoisting joint, 7-star-arrow separation joint, 8-inter-cabin butt joint, 9-platform bottom plate, 10-platform middle plate, 11-platform side plate, 12-platform clapboard, 13-load cabin top plate, 14-load cabin side plate, 15-load cabin clapboard, 16-structural plate connecting piece, 17-rod piece connecting interface, 18-tool interface, 19-star-arrow connecting interface, 20-plate interface, 21-hoisting hole interface
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a truss type satellite structure suitable for a point-type satellite-rocket separation mode, which comprises a composite material truss for bearing force and a honeycomb sandwich structure plate fixedly connected to the composite material truss, wherein the truss type satellite structure comprises a platform cabin 1 and a load cabin 2 positioned at the top of the platform cabin 1, wherein the honeycomb sandwich structure plate is enclosed into the platform cabin 1; as shown in the structure of fig. 2, the bottom of the truss-like satellite structure constitutes a platform cabin 1 and the top constitutes a load cabin 2; the honeycomb sandwich structure plate can adopt an aluminum alloy skin or a carbon fiber skin aluminum honeycomb sandwich structure;
the composite material truss comprises platform cabin truss upright rods 3 extending in the vertical direction, load cabin truss upright rods 4 extending in the vertical direction, truss cross rods 5 extending in the horizontal direction, hoisting joints 6, satellite-rocket separation joints 7 and inter-cabin butt joints 8; as shown in the structure of fig. 4, the composite truss may be a rectangular parallelepiped structure, or may be in other shapes; when the composite material truss is in a cuboid structure, four platform cabin truss upright rods 3 are distributed along the circumferential direction of the platform cabin 1;
the platform cabin truss upright rods 3 are distributed along the circumferential direction of the platform cabin 1;
the load cabin truss upright posts 4 are distributed along the circumferential direction of the load cabin 2 and correspond to the platform cabin truss upright posts 3 one by one; as shown in the structure of fig. 4, when the composite truss is of a rectangular structure and is provided with four platform cabin truss upright rods 3, the top of each platform cabin truss upright rod 3 is respectively provided with one load cabin truss upright rod 4 in one-to-one correspondence, that is, four load cabin truss upright rods 4 are distributed around the load cabin 2;
as shown in the structure of fig. 4, the bottom end of the platform cabin truss upright rod 3 is fixedly connected with a satellite-rocket separation joint 7, and the top end is fixedly connected with the bottom end of the load cabin truss upright rod 4 through an inter-cabin butt joint 8; as shown in the structures of fig. 5 and 6, the satellite-rocket separation joint 7 may be provided with a rod connection interface 17 for connecting the truss upright rods 3 and the truss cross rods 5 of the platform cabin, a tooling interface 18 for connecting a ground tooling, a satellite-rocket connection interface 19 for connecting a satellite-rocket connection separation device, and a plate interface 20 for connecting a honeycomb sandwich structure plate; the rod connecting interface 17 can be a blind hole for splicing the truss upright stanchion 3 and the truss cross rod 5 of the platform cabin; the tool interface 18, the satellite-rocket connecting interface 19 and the plate interface 20 can be through holes;
as shown in the structure of fig. 4, the top end of the load cabin truss upright rod 4 is fixedly connected with a hoisting joint 6; the hoisting joint 6 is convenient for hoisting and carrying the truss type satellite structure; as shown in the structure of fig. 7, the hoisting connector 6 is provided with a hoisting hole 21 for connecting a hoisting tool, a plate connector 20 for connecting a honeycomb sandwich structure plate, and a rod connecting connector 17 for connecting the truss cross rod 5 and the truss upright rod 4 of the load cabin;
as shown in the structure of fig. 4, a truss cross bar 5 is fixedly connected between circumferentially adjacent hoisting joints 6, between adjacent satellite-rocket separation joints 7, and between adjacent interbay butt joints 8.
The truss type satellite structure adopts the composite truss as a main bearing structure, the honeycomb sandwich structure plate is fixedly installed on the composite truss, the assembling structure of the truss and the honeycomb sandwich structure plate is simple, the satellite and arrow butt joint is a truss joint, the force transmission path is shortest, the satellite and arrow butt joint is simple and direct, the concentrated load can be effectively borne and transmitted, meanwhile, the satellite and arrow butt joint can also provide an interface with a carrying tool and a ground tool, the requirements of the satellite on strength, rigidity, precision and various interfaces can be met by adopting the structure, the processing and the assembling are easy, and the requirements of product batch production and modularized cabin division operation can be met.
In a specific embodiment, the platform cabin truss upright rods 3, the load cabin truss upright rods 4 and the truss cross rods 5 are wound and formed by high-modulus carbon fiber M55J resin-based composite materials. The satellite-rocket separation joint 7, the hoisting joint 6 and the inter-cabin butt joint 8 are all formed by machining aluminum alloy.
As shown in the structure of fig. 2 and 4, the inter-bay butt joint 8 includes an upper joint (not shown) and a lower joint (not shown) which are detachably connected; the upper joint is provided with a vertical rod interface for connecting a vertical rod 4 of the load cabin truss; the lower joint is provided with a rod connecting interface 17 for connecting the platform cabin truss upright rods 3 and the truss cross rods 5, and a plate interface 20 for connecting the honeycomb sandwich structure plates. In order to facilitate the connection of the upper joint and the lower joint, a positioning matching interface can be arranged between the upper joint and the lower joint.
The interbay butt joint 8 is composed of an upper joint and a lower joint which are detachably connected, so that the platform cabin 1 and the load cabin 2 can be independently assembled, the platform cabin 1 and the load cabin 2 are assembled through the fixed connection between the upper joint and the lower joint after the assembly is completed, and the flexible assembly of the truss type satellite structure is convenient to realize.
As shown in the structures of fig. 4 and 8, the load compartment truss upright rods 4, the platform compartment truss upright rods 3 and the truss cross rods 5 are all bonded with a plurality of structural plate connecting pieces 16 through normal temperature curing glue, and the structural plate connecting pieces 16 are used for connecting the honeycomb sandwich structural plates. In the structure of fig. 8, a platform bottom plate 9 and a platform side plate 11 are taken as examples to show a connection structure between a structural plate connecting piece 16 and a honeycomb sandwich structural plate, the structural plate connecting piece 16 is bonded on the truss cross rod 5 through normal temperature curing glue, and both the platform bottom plate 9 and the platform side plate 11 are fixedly connected to the structural plate connecting piece 16 through fasteners such as screws, bolts and the like, so that the platform bottom plate 9 and the platform side plate 11 are fixedly installed on the truss cross rod 5, and similarly, the honeycomb sandwich structural plates are installed on the load compartment truss vertical rod 4, the platform compartment truss vertical rod 3 and the truss cross rod 5 one by one, and finally, the assembly of the composite truss is realized.
As shown in the structure of fig. 3, the honeycomb sandwich structure plate includes a platform honeycomb sandwich structure plate and a load compartment 2 honeycomb sandwich structure plate; wherein:
the platform honeycomb sandwich structure plate comprises a platform bottom plate 9, a platform side plate 11, a platform partition plate 12 and a middle plate; as shown in the structure of fig. 3, the middle plate is arranged between the platform cabin 1 and the load cabin 2, the platform cabin 1 is enclosed by the platform side plates 11 arranged on the platform cabin truss upright rods 3, the platform bottom plate 9 arranged on the truss cross rods 5 and the middle plate, and the platform partition plate 12 can partition the platform cabin 1;
the honeycomb sandwich structure plate of the load cabin 2 comprises a load cabin side plate 14, a load cabin top plate 13 and a load cabin clapboard 15; as shown in the structure of fig. 3, the load compartment 2 is positioned on the top of the platform compartment 1, the load compartment 2 is formed by surrounding load compartment side plates 14 mounted on the load compartment truss upright rods 4 and the truss cross rods 5 and a load compartment top plate 13 mounted on the truss cross rods 5, and the load compartment 2 can be divided by the load compartment partition plate 15.
On the basis of the above embodiments, the platform cabin truss upright rods 3 are connected with the satellite-rocket separation joints 7 and the inter-cabin butt joints 8 through rod pieces in an adhesive manner; the load cabin truss upright stanchions 4 are connected with the inter-cabin butt joints 8 and the lifting joints 6 through rod pieces in an adhesive manner; the truss beam 5 is connected by rod gluing to a hoisting joint 6, an interbay butt joint 8 and a starboard separation joint 7.
When the truss type satellite structure is assembled, the truss structure is assembled firstly, the truss is assembled from bottom to top by taking a satellite-rocket butt joint as a reference, and the assembly precision of the truss and the precision of the interfaces of the truss, a carrier rocket, a ground tool and a structural plate can be ensured by the tool; and then, gluing the truss and the structural plate connecting piece 16 by taking the mounting surface adjusting tool of each structural plate as a reference, and finally mounting the structural plates. During the installation process, the platform cabin structure and the load cabin structure can be decomposed according to the requirements of final assembly operation.
By aiming at different structural schemes and applicable satellite-rocket interface forms thereof, and through the contrastive analysis in the aspects of modal analysis, structural characteristic comparison, structural manufacturability, layout adaptability and the like, the truss type structure has greater advantages on the one-rocket and multi-satellite launching point type satellite-rocket interface, mainly reflects that the truss is more direct in force transmission path, high in structural rigidity, large in structural bearing ratio, good in general assembly operation openness and simple in production and assembly process, and provides reference for the structural design of the one-rocket and multi-satellite launching direct-in-orbit satellite in China.
The truss type satellite structure is verified through whole satellite mechanical analysis, identification static force test and vibration test verification and satellite-rocket butt joint separation test, and shows that structural rigidity, strength and precision all meet design requirements, the general assembly hoisting, transportation, separation and combination of cabins and the like are convenient to operate and good in openness, and sixteen pieces of on-orbit flight verification are performed. In addition, the truss type satellite structure can also be popularized and applied to other satellites connected by one-arrow multi-satellite launching point type stars.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A truss type satellite structure suitable for a point-type satellite-rocket separation mode is characterized by comprising a composite material truss for bearing force and a honeycomb sandwich structure plate fixedly connected to the composite material truss, wherein a platform cabin and a load cabin positioned at the top of the platform cabin are enclosed by the honeycomb sandwich structure plate;
the composite material truss comprises platform cabin truss upright rods extending in the vertical direction, load cabin truss upright rods extending in the vertical direction, truss cross rods extending in the horizontal direction, hoisting joints, satellite-rocket separation joints and inter-cabin butt joints;
the platform cabin truss upright rods are distributed along the circumferential direction of the platform cabin;
the load cabin truss upright rods are distributed along the circumferential direction of the load cabin and correspond to the platform cabin truss upright rods one by one;
the bottom end of the platform cabin truss upright rod is fixedly connected with the satellite-rocket separation joint, and the top end of the platform cabin truss upright rod is fixedly connected with the bottom end of the load cabin truss upright rod through the inter-cabin butt joint;
the top end of the load cabin truss upright rod is fixedly connected with the hoisting joint;
and one truss cross rod is fixedly connected between the circumferentially adjacent hoisting joints, between the adjacent satellite-rocket separation joints and between the adjacent cabin butt joints.
2. A trussed satellite structure according to claim 1 wherein the platform truss legs, the load compartment truss legs and the truss beams are formed by winding high modulus carbon fiber M55J resin matrix composite material.
3. A trussed satellite structure according to claim 2 wherein the satellite-rocket separation joints, the lifting joints and the inter-bay butt joints are machined from aluminum alloy.
4. The truss-like satellite structure of claim 1 wherein the satellite-rocket separation joint is provided with a rod connection interface for connecting the platform cabin truss upright rods and the truss cross rods, a tooling interface for connecting a ground tooling, a satellite-rocket connection interface for connecting a satellite-rocket connection separation device, and a plate interface for connecting the honeycomb sandwich structure plates.
5. A trussed satellite structure according to claim 1, wherein the inter-bay butt joints comprise upper and lower joints that are removably connected;
the upper joint is provided with a vertical rod interface for connecting a vertical rod of the load cabin truss;
the lower joint is provided with a rod piece connecting interface used for connecting the platform cabin truss upright rod and the truss cross rod and a plate interface used for connecting the honeycomb sandwich structure plate.
6. A trussed satellite structure according to claim 1 wherein the lifting joints are provided with lifting holes for connection of a spreader, panel interfaces for connection of honeycomb sandwich panels, and rod connection interfaces for connection of the truss crossbars to the truss uprights of the load compartment truss.
7. A trussed satellite structure according to claim 1 wherein the load cell truss uprights, the platform cell truss uprights and the truss cross-bars are all bonded by room temperature curing glue with a plurality of structural panel connectors for connecting the honeycomb sandwich structural panels.
8. A trussed satellite structure according to claim 7, wherein the honeycomb sandwich structure panel comprises a platform honeycomb sandwich structure panel and a load compartment honeycomb sandwich structure panel;
the platform honeycomb sandwich structure plate comprises a platform bottom plate, a platform side plate, a platform partition plate and a middle plate;
the load cabin honeycomb sandwich structure plate comprises a load cabin side plate, a load cabin top plate and a load cabin partition plate.
9. A trussed satellite structure according to claim 1, wherein the platform pod truss legs are adhesively attached by rods to the satellite-rocket breakaway joint and the inter-pod butt joint;
the load cabin truss upright rods are connected with the inter-cabin butt joints and the hoisting joints through rod pieces in an adhesive manner;
the truss cross rod is connected with the hoisting joint, the inter-cabin butt joint and the satellite-rocket separation joint through rod pieces in an adhesive mode.
10. A trussed satellite structure according to any one of claims 1 to 9, wherein the composite truss is a cuboid structure;
four platform cabin truss upright rods are distributed along the circumferential direction of the platform cabin.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110662522.8A CN113371228A (en) | 2021-06-15 | 2021-06-15 | Truss type satellite structure suitable for point type satellite-rocket separation mode |
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| CN202110662522.8A CN113371228A (en) | 2021-06-15 | 2021-06-15 | Truss type satellite structure suitable for point type satellite-rocket separation mode |
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| CN116750217A (en) * | 2023-08-23 | 2023-09-15 | 北京星河动力装备科技有限公司 | Double-layer satellite separation structure and satellite separation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116750217A (en) * | 2023-08-23 | 2023-09-15 | 北京星河动力装备科技有限公司 | Double-layer satellite separation structure and satellite separation method thereof |
| CN116750217B (en) * | 2023-08-23 | 2023-11-14 | 北京星河动力装备科技有限公司 | Double-layer satellite separation structure and satellite separation method thereof |
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Application publication date: 20210910 |