CN111792056B - Bearing and satellite-rocket connection integrated satellite structural slab - Google Patents

Bearing and satellite-rocket connection integrated satellite structural slab Download PDF

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Publication number
CN111792056B
CN111792056B CN202010681868.8A CN202010681868A CN111792056B CN 111792056 B CN111792056 B CN 111792056B CN 202010681868 A CN202010681868 A CN 202010681868A CN 111792056 B CN111792056 B CN 111792056B
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satellite
rocket
embedded
panel
embedded part
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CN111792056A (en
Inventor
曾惠忠
刘芃
刘志全
闫峰林
韩飞
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Shenzhen Aerospace Dongfanghong Satellite Co ltd
Beijing Institute of Spacecraft System Engineering
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Aerospace Dongfanghong Development Ltd
Beijing Institute of Spacecraft System Engineering
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/10Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64GCOSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00Cosmonautic vehicles
    • B64G1/22Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

The invention provides a satellite structure plate integrating bearing and satellite-rocket connection, which comprises a honeycomb sandwich structure plate, wherein the width direction of the honeycomb sandwich structure plate is the X direction, the length direction of the honeycomb sandwich structure plate is the Y direction, and the thickness direction of the honeycomb sandwich structure plate is the Z direction. The invention has the beneficial effects that: the satellite-rocket connection rigidity is improved, the structure weight is reduced, and the satellite-rocket connection is facilitated.

Description

Bearing and satellite-rocket connection integrated satellite structural slab
Technical Field
The invention relates to a satellite structural slab, in particular to a satellite structural slab integrating bearing and satellite-rocket connection.
Background
Satellite structures are typically attached to the launch vehicle in both point and rim configurations.
The connection and separation mechanism corresponding to the point type connection mode is an explosive bolt; the arrangement is flexible, the occupied space is small, but the structure stress at the connection position of the satellite and the arrow is concentrated, the stress is higher, and the satellite launching device is generally suitable for small satellites, particularly satellites launched in parallel by one rocket and multiple stars.
The connection and separation mechanism corresponding to the ring frame type connection mode is a belt and an explosion bolt; the stress at the connection position of the satellite and the arrow is uniform, the stress is lower, but the occupied space is large, and the satellite and the arrow are generally suitable for large satellites, single-satellite launching or small satellites launched in series by one arrow and multiple satellites.
The point-type connected plate-type satellite structure is adopted, the satellite structure is not directly connected with a butt-joint frame structure of a carrier rocket, but is transited by a connecting and separating mechanism, two ends of the separating mechanism are respectively connected with a satellite structure plate and the butt-joint frame structure of the carrier rocket, one end of the separating mechanism is separated from the carrier rocket along with the satellite after the satellite and the rocket are separated, and the separating mechanism is provided with a satellite-rocket point-type connecting and separating module and a device thereof (patent name: the satellite-rocket point-type connecting and separating module and the device thereof: patent number: CN 201610538456.2) and an integrally designed satellite-rocket separating mechanism (patent name: the integrally designed satellite-rocket separating mechanism: patent number: CN 201410528677.2). The satellite structure adopts the separation mechanism, the self occupied space of the connection and separation mechanism can be reduced, the interface of the satellite structure is simple, and the flexibility of satellite and rocket connection design is improved. But at the same time brings some disadvantages: 1) the connection rigidity of the satellite and the rocket is influenced by the self rigidity of the separating mechanism parts (the upper transfer cylinder and the satellite end separating seat in the patent) besides the explosive bolt, and the rigidity of the separating mechanism parts needs to be properly improved, so that the weight is increased; 2) the installation and operation space is occupied along the rocket launching direction, and the utilization rate of the inner space of the fairing of the carrier rocket is reduced.
The satellite structure reported in the literature "a rigid frame and box plate combined small satellite main structure design" is directly connected with a butt-joint frame structure of a launch vehicle (Zeng Hui Zhong, etc. a rigid frame and box plate combined small satellite main structure design [ C ]. 2015 minisatellite technical exchange discourse corpus, Beijing, 2015.06.30). The satellite-rocket connection design of the document ensures that no installation and operation space is occupied along the rocket launching direction. However, the satellite and rocket connectors are embedded in the four corners of the satellite bottom plate and are within the square outline of the satellite, so that the opening of the main force transmission structure at the root part of the satellite side plate is caused, a reinforcing embedded part needs to be designed at the opening of the side plate, after the explosive bolt is installed, an external corner box needs to be installed at the opening of the side plate for reinforcement, and the reinforcing measures and the corresponding connecting screws additionally increase the weight; and the metal angle box can be installed only after the satellite and the arrow are connected, so that the installation and the operation are inconvenient, the working flow of the satellite and the carrying is poor, and the working interface is unclear.
Therefore, how to improve the connection rigidity of the satellite and the arrow, reduce the structural weight and facilitate the connection of the satellite and the arrow is a technical problem to be solved urgently by technical personnel in the field.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a satellite structural slab integrating bearing and satellite-rocket connection.
The invention provides a satellite structure plate integrating bearing and satellite-rocket connection, which comprises a honeycomb sandwich structure plate, wherein the width direction of the honeycomb sandwich structure plate is the X direction, the length direction of the honeycomb sandwich structure plate is the Y direction, and the thickness direction of the honeycomb sandwich structure plate is the Z direction.
As a further improvement of the invention, the negative Z panel, the positive Z panel, the honeycomb core, the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the front thread embedded part are bonded into the honeycomb sandwich structure plate through heating, curing and bonding.
As a further improvement of the invention, the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the front thread embedded part are bonded with the honeycomb core through J47D foaming glue by heating and curing, and the honeycomb core, the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the front thread embedded part are bonded with the negative Z panel and the positive Z panel through J47B + C plate core glue by heating and curing.
As a further improvement of the invention, the number of the satellite-rocket joint embedded beams is two, the length direction of the satellite-rocket joint embedded beams is the X direction, and the distance between the two satellite-rocket joint embedded beams is half of the Y direction length of the honeycomb sandwich structure plate.
As a further improvement of the invention, two end parts of each satellite-rocket joint embedded beam respectively extend out of the honeycomb sandwich structure plate, and a satellite-rocket joint is respectively arranged on the two end parts.
As a further improvement of the invention, the rocket joint at each end part is provided with an explosion bolt mounting unthreaded hole and an explosion bolt mounting threaded hole, and the rocket joint at each end part is also provided with a triangular reinforcing rib along the X direction and a rectangular reinforcing rib along the Y direction.
As a further improvement of the invention, the explosive bolt mounting unthreaded hole is composed of an explosive bolt mounting round hole and an explosive bolt mounting taper hole.
As a further improvement of the invention, the explosive bolt mounting unthreaded hole and the explosive bolt mounting threaded hole are both positioned on one side outside the cabin enveloped by the rectangular reinforcing rib.
As a further improvement of the invention, each satellite-rocket joint embedded beam and a honeycomb core around the satellite-rocket joint embedded beam are bonded into a whole through foaming glue, a large bearing interface embedded part is arranged on the honeycomb sandwich structure plate, and the honeycomb core around the large bearing interface embedded part is filled with the foaming glue.
As a further improvement of the invention, the negative Z panel and the positive Z panel are made of 2A12 aluminum alloy plates, the honeycomb core is made of LF2 aluminum alloy with the side length of 5mm and the wall thickness of 0.03mm, and the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the front thread embedded part are all made of 2A12 aluminum alloy bars.
The invention has the beneficial effects that: through the scheme, the connection rigidity of the satellite and the arrow is improved, the structural weight is reduced, and the satellite and the arrow are conveniently connected.
Drawings
Fig. 1 is an overall schematic diagram of a satellite structural slab integrating bearing and satellite-rocket connection.
FIG. 2 is a negative Z view of a hidden negative Z panel of a load bearing and satellite-rocket connected integrated satellite structure panel of the present invention.
FIG. 3 is a schematic view of a satellite-rocket joint for bearing and connecting a satellite and a rocket into an integrated satellite structural plate.
Fig. 4 is a sectional view taken along line a-a of fig. 2.
Detailed Description
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1, a satellite structural slab integrating bearing and satellite-rocket connection is a honeycomb sandwich structural slab, the center of the slab is provided with a circular large opening 9, the rest parts are provided with small openings, and the whole component part comprises: the structure comprises a negative Z panel 1, a positive Z panel 2, a honeycomb core 3, a satellite-rocket joint embedded beam 4, a lateral thread embedded part 5, a plate edge through hole embedded part 6 and a front thread embedded part 7, wherein all parts are bonded into an integral structural plate through one-time heating curing. The negative Z panel 1 and the positive Z panel 2 are made of 2A12 aluminum alloy plates, the honeycomb core 3 is made of LF2 aluminum alloy with the side length of 5mm and the wall thickness of 0.03mm, and the satellite-rocket joint embedded beam 4, the lateral thread embedded part 5, the plate edge through hole embedded part 6 and the front thread embedded part 7 are made of 2A12 aluminum alloy bars. The star-arrow joint embedded beam 4, the lateral thread embedded part 5, the plate edge through hole embedded part 6 and the front thread embedded part 7 are bonded with the honeycomb core 3 through J47D foaming adhesive in a heating curing manner. The honeycomb core 3, the satellite-rocket joint embedded beam 4, the lateral thread embedded part 5, the plate edge through hole embedded part 6 and the front thread embedded part 7 are bonded with the negative Z panel 1 and the positive Z panel 2 through J47B + C plate core glue by heating, curing and bonding. All parts are bonded into an integral structural plate through one-time heating curing.
As shown in fig. 2, the distance between the star and arrow joint embedded beams 4 is approximately half of the length of the structural plate in the Y direction. The honeycomb core around the embedded part of the large bearing interface is filled with foaming glue 8 for reinforcement. 2 ends of the satellite-rocket joint embedded beam 4 extend out of the honeycomb sandwich structure plate, and 1 satellite-rocket joint is provided respectively. And the lateral thread embedded part 5 and the plate edge through hole embedded part 6 are used for connecting the structural plate with other structural plates. The front-side threaded embedded part 7 is used for providing an equipment mounting interface and is divided into a front-side threaded embedded part 72 with a threaded hole facing to the positive Z direction and a front-side threaded embedded part 71 with a threaded hole facing to the negative Z direction according to equipment mounting requirements. And (4) trimming and filing the embedded parts at interference positions.
As shown in fig. 3, the star-arrow joint at each end provides a blast bolt mounting unthreaded hole 41 and a blast bolt mounting threaded hole 42, and is further designed with a triangular reinforcing rib 43 and a rectangular reinforcing rib 44 to ensure that the load is transferred from the integral structural plate to the blast bolt mounting interface.
As shown in fig. 4, the explosive bolt mounting unthreaded hole 41 is composed of an explosive bolt mounting round hole 411 and an explosive bolt mounting tapered hole 412, and both are located on the outboard side of the side plate envelope, so that the explosive bolt mounting does not need to occupy an intra-satellite space. And further, after the satellite is connected with the carrier rocket, additional operation for connecting the satellite and the carrier rocket is not needed.
The front threaded embedded part 7 provides an equipment installation interface, the satellite and rocket joint embedded beam 4 provides a satellite and rocket interface to be directly connected with the carrier rocket, and the load of the bottom plate installation equipment in the satellite launching process is transmitted to the negative Z panel 1, the positive Z panel 2 and the honeycomb core 3 through the front threaded embedded part 7, then transmitted to the satellite and rocket joint embedded beam 4 and finally transmitted to the carrier rocket through the satellite and rocket interface on the satellite and rocket joint embedded beam 4. And finally obtaining the structural plate integrating bearing and satellite-rocket connection.
The invention provides a satellite structure plate integrating bearing and satellite-rocket connection, which is positioned at the bottom of a whole satellite, provides a large number of equipment installation interfaces, and simultaneously directly provides a satellite-rocket interface to be directly connected with a carrier rocket. In the process of satellite launching, the load of the equipment mounted on the satellite is transmitted to the structural plate through the equipment mounting interface, then transmitted to the satellite-rocket interface on the structural plate, and finally transmitted to the carrier rocket through the satellite-rocket interface, and finally the structural plate integrating bearing and satellite-rocket connection is obtained.
According to the satellite structural slab integrating bearing and satellite-rocket connection, provided by the invention, 4 satellite-rocket connectors are solidified in the structural slab in an embedded mode. The satellite and rocket joint extends out of the satellite side plate and is positioned outside the satellite profile, the local part of the satellite and rocket joint is provided with the reinforcing rib, and a reinforcing external corner box which can be installed after the satellite and rocket butt joint is completed does not need to be designed. In order to ensure the satellite-rocket connection rigidity and the structural slab strength, every 2 satellite-rocket joints are designed into a whole, namely 2 satellite-rocket joints are designed at two ends of a satellite-rocket joint embedded beam 4, and the satellite-rocket joint embedded beam 4 and the surrounding honeycomb cores 3 are bonded into a whole through foaming glue. The distance between the two satellite-rocket joint embedded beams 4 is selected to be half of the length of the bottom plate, so that the bending moment normal stress in the middle of the structural plate is approximately zero, and the stress of the panel at the large opening in the middle of the bottom plate is reduced. In addition, the honeycomb core around the embedded part of the large bearing interface is filled with foaming glue for reinforcement.
The invention provides a satellite structure plate integrating bearing and satellite-rocket connection, which has the following advantages:
(1) the satellite structural plate is directly connected with the carrier rocket structure, and the connection rigidity is good;
(2) 4 satellite-rocket joints are positioned at 2 ends of the 2 embedded beams, and the strength and the rigidity of the structural slab are improved by reasonably designing the span of the 2 embedded beams;
(3) reinforcing ribs are locally designed on the satellite and rocket interface, so that the connection rigidity and the local structural strength of the satellite and rocket are improved;
(4) the satellite structural plate is directly connected with the carrier rocket structure, and the structure weight can be reduced without a separation mechanism for transition;
(5) the satellite-rocket joint is positioned outside the side plate, local strength and rigidity of the satellite-rocket connection interface are improved through the reinforcing rib, a reinforcing corner box does not need to be installed on the side part, and the weight of the structure can be reduced;
(6) the bearing and satellite-rocket connection integrated structure of the pre-embedded satellite-rocket interface stiffening beam of the honeycomb sandwich structure plate can modify the total thickness, the panel material and the thickness of the honeycomb sandwich structure plate and the size of the satellite-rocket interface stiffening beam according to the bearing and satellite-rocket connection requirements of specific satellites, and can be suitable for different small satellite structures which are connected and separated with a carrier rocket in a point mode or plate type satellite structures which are launched in parallel by one rocket and a plurality of stars.
The invention provides a bearing and satellite-rocket connection integrated satellite structure plate which is suitable for a small satellite structure separated from a carrier rocket by point connection or a plate-type satellite structure launched in parallel by one rocket and multiple stars.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.

Claims (5)

1. The utility model provides a bear and connect integration satellite structure board with satellite and rocket which characterized in that: the honeycomb sandwich structure plate comprises a honeycomb sandwich structure plate, wherein the width direction of the honeycomb sandwich structure plate is X direction, the length direction of the honeycomb sandwich structure plate is Y direction, and the thickness direction of the honeycomb sandwich structure plate is Z direction, the honeycomb sandwich structure plate comprises a negative Z panel, a positive Z panel and a honeycomb core, the honeycomb core is positioned between the negative Z panel and the positive Z panel, a satellite-rocket joint embedded beam, a lateral thread embedded part, a plate edge through hole embedded part and a positive thread embedded part for providing an equipment installation interface are further arranged between the negative Z panel and the positive Z panel, the satellite-rocket joint embedded beam is provided with two satellite-rocket joint embedded beams, the length direction of the satellite-rocket joint embedded beam is X direction, the distance between the two satellite-rocket joint embedded beams is half of the Y direction length of the honeycomb sandwich structure plate, two end parts of each satellite-rocket joint embedded beam respectively extend out of the honeycomb sandwich structure plate, and are respectively provided with a satellite-rocket joint, the negative Z panel, The honeycomb sandwich structure plate is formed by bonding a positive Z panel, a honeycomb core, a satellite-rocket joint embedded beam, a lateral thread embedded part, a plate edge through hole embedded part and a positive thread embedded part through heating and curing, wherein the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the positive thread embedded part are bonded with the honeycomb core through J47D foaming glue through heating and curing, the honeycomb core, the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the positive thread embedded part are bonded with the negative Z panel and the positive Z panel through J47B + C panel core glue through heating and curing, an explosion bolt mounting unthreaded hole and an explosion bolt mounting threaded hole are arranged on the satellite-rocket joint at each end part, and the satellite-rocket joint at each end part is also provided with a triangular reinforcing rib along the X direction and a rectangular reinforcing rib along the Y direction.
2. The integrated satellite structure board for bearing and connecting satellite and rocket according to claim 1, wherein: the explosive bolt mounting unthreaded hole is composed of an explosive bolt mounting round hole and an explosive bolt mounting taper hole.
3. The load-bearing and satellite-rocket connecting integrated satellite structure plate according to claim 2, wherein: the explosive bolt mounting unthreaded hole and the explosive bolt mounting threaded hole are both positioned on one side outside the cabin enveloped by the rectangular reinforcing rib.
4. The integrated satellite structure board for bearing and connecting satellite and rocket according to claim 1, wherein: each satellite-rocket joint embedded beam is bonded with the honeycomb cores around the satellite-rocket joint embedded beam into a whole through foaming glue, a large bearing interface embedded piece is arranged on the honeycomb sandwich structure plate, and the honeycomb cores around the large bearing interface embedded piece are filled with the foaming glue.
5. The integrated satellite structure board for bearing and connecting satellite and rocket according to claim 1, wherein: the negative Z panel and the positive Z panel are made of 2A12 aluminum alloy plates, the honeycomb core is made of LF2 aluminum alloy with the side length of 5mm and the wall thickness of 0.03mm, and the satellite-rocket joint embedded beam, the lateral thread embedded part, the plate edge through hole embedded part and the front thread embedded part are all made of 2A12 aluminum alloy bars.
CN202010681868.8A 2020-07-15 2020-07-15 Bearing and satellite-rocket connection integrated satellite structural slab Active CN111792056B (en)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201077532Y (en) * 2007-09-25 2008-06-25 北京空间飞行器总体设计部 Lifting joint of plate-type communication satellite
CN101673880A (en) * 2009-10-21 2010-03-17 中国电子科技集团公司第五十四研究所 Method for manufacturing antenna reflecting surface with aluminum skin honeycomb sandwich structure
CN104729503A (en) * 2015-03-17 2015-06-24 中国空间技术研究院 Rod-type supporting structure earth sensor support

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2000085697A (en) * 1998-09-18 2000-03-28 Mitsubishi Electric Corp Sandwich panel for satellite structure
JP4462715B2 (en) * 2000-05-11 2010-05-12 富士重工業株式会社 Manufacturing method of honeycomb sandwich structure using composite material and forming jig used for manufacturing of honeycomb sandwich structure
CN208508907U (en) * 2018-02-11 2019-02-15 浙江杉盛模塑科技有限公司 A kind of honeycomb composite plate satellite signal receiver

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201077532Y (en) * 2007-09-25 2008-06-25 北京空间飞行器总体设计部 Lifting joint of plate-type communication satellite
CN101673880A (en) * 2009-10-21 2010-03-17 中国电子科技集团公司第五十四研究所 Method for manufacturing antenna reflecting surface with aluminum skin honeycomb sandwich structure
CN104729503A (en) * 2015-03-17 2015-06-24 中国空间技术研究院 Rod-type supporting structure earth sensor support

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Address after: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province

Patentee after: Shenzhen Aerospace Dongfanghong Satellite Co.,Ltd.

Patentee after: Beijing Institute of Spacecraft System Engineering

Address before: 518000 whole building of satellite building, 61 Gaoxin South Jiudao, Yuehai street, Nanshan District, Shenzhen City, Guangdong Province

Patentee before: AEROSPACE DONGFANGHONG DEVELOPMENT Ltd.

Patentee before: Beijing Institute of Spacecraft System Engineering

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