CN106542080B - Antenna mounting truss structure - Google Patents
Antenna mounting truss structure Download PDFInfo
- Publication number
- CN106542080B CN106542080B CN201610920480.2A CN201610920480A CN106542080B CN 106542080 B CN106542080 B CN 106542080B CN 201610920480 A CN201610920480 A CN 201610920480A CN 106542080 B CN106542080 B CN 106542080B
- Authority
- CN
- China
- Prior art keywords
- stringer
- support
- antenna mounting
- truss structure
- mounting truss
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/064—Stringers; Longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/065—Spars
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Joining Of Building Structures In Genera (AREA)
Abstract
A kind of antenna mounting truss structure provided by the invention, comprising: antenna mounting truss, antenna mounting truss include rod piece and the support joint being arranged on rod piece and erection joint；First stringer component, the first stringer component include more first stringers, and one end of the first stringer is connect with support joint, are equipped with stringer connector in the other end of the first stringer；One end of support rod, support rod is connect with erection joint, is equipped with mounting base in the other end of support rod；Support plate, support plate are fixed by stringer connector and mounting base；Second stringer component, the second stringer component include more second stringers, and one end of the second stringer is connect with stringer connector, are equipped with support base in the other end of the second stringer；Bottom plate, bottom plate are arranged on support base.The present invention has following innovative design: carbon fiber antenna mounting truss and aluminum honeycomb panel being carried out integrated design, introduce aluminum honeycomb panel structure, the torsion stiffness for improving truss honeycomb plate structure form of high degree.
Description
Technical field
The present invention relates to aerospace craft structure, specially a kind of antenna mounting truss that can carry big magnitude payload
Structure.
Background technique
Currently, the carbon fiber truss structure in spacecraft structure is only formed by connector, rod piece simple composite, connector and rod piece
Between be connected by screw bolts or be glued.Such pure truss structure form has the disadvantage that
1) truss structure is more single, and the whole Space Oblique idler arms that rely on of truss reverse more to resist, truss torsion stiffness
It is relatively low；
2) truss inner space utilization rate is insufficient, and only truss outer surface level can provide installation carrying, benefit for payload
It is lower with efficiency；
3) truss splicing assembly method is simple, and assembly precision is limited, has been unable to satisfy the use of high-precision discriminating rate satellite
It is required that.
Above-mentioned deficiency greatly limits application of the truss structure on spacecraft structure.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide the antennas that one kind can carry big magnitude payload
Supporting girder structure.
In order to solve the above technical problems, a kind of antenna supporting girder structure provided by the invention, comprising: antenna mounting
Truss, the antenna mounting truss include rod piece and the support joint being arranged on the rod piece and erection joint；First stringer
Component, the first stringer component include more first stringers, and one end of first stringer is connect with the support joint,
The other end of first stringer is equipped with stringer connector；Support rod, one end of the support rod are connect with the erection joint,
The other end of the support rod is equipped with mounting base；Support plate, the support plate are solid by the stringer connector and the mounting base
It is fixed；Second stringer component, the second stringer component include more second stringers, one end of second stringer and the stringer
Connector connection is equipped with support base in the other end of second stringer；Bottom plate, the bottom plate are arranged on the support base.
Preferably, the support plate is aluminum honeycomb panel.
Preferably, partition is equipped in the support plate.
Preferably, angle box is equipped in the outside of the first stringer component.
Preferably, the antenna mounting truss structure includes jointing, the jointing by connecting rod respectively with
The erection joint, the support base, the mounting base and support joint connection.
Preferably, the first reinforcing rib is equipped between first stringer.
Preferably, the second reinforcing rib is equipped between support plate and the partition.
Preferably, the rod piece is square beam structure.
Preferably, the cross section of first stringer and second stringer is L shape.
Compared with prior art, the present invention has following innovative design:
1) innovative that carbon fiber antenna mounting truss and aluminum honeycomb panel are subjected to integrated design, for single truss-like
The insufficient defect of formula torsional property introduces aluminum honeycomb panel structure, is innovated using the different advantages of two kinds of typical structures, greatly
The torsion stiffness for improving truss honeycomb plate structure form of degree；
2) aluminum honeycomb panel apply for big magnitude Satellite Payloads provide installation and bearing while, and for other electricity
Sub- single machine provides certain installation space, improves truss structure utilization efficiency；
It 3) is the fiber continuity for guaranteeing carbon fiber structural on antenna mounting truss, design avoids doing excessively in rod piece as far as possible
Aperture, therefore introduce the connection that stringer component realizes carbon fibre member bar and cellular board；
4) research breakthrough is carried out to the assembly technology of truss honeycomb mixing integral structure, for the first time using inverted upwards from pushing up
Assembly method.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention
Objects and advantages will become more apparent upon.
Fig. 1 is inventive antenna supporting girder structure structural schematic diagram；
Fig. 2 is inventive antenna supporting girder structure assembly process figure one；
Fig. 3 is inventive antenna supporting girder structure assembly process figure two；
Fig. 4 is inventive antenna supporting girder structure assembly process figure three；
Fig. 5 is inventive antenna supporting girder structure assembly process figure four；
Fig. 6 is inventive antenna supporting girder structure assembly process figure five.
In figure:
1- rod piece 2- support joint 3- erection joint
4- the first stringer 5- stringer connector 6- support rod
7- mounting base 8- support plate the second stringer of 9-
10- support base 11- bottom plate 12- partition
The angle 13- box 14- jointing 15- connecting rod
16- the first reinforcing rib the second reinforcing rib of 17-
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
As shown in Figure 1, the invention mainly comprises: antenna mounting truss (is connect by rod piece 1 and the support being arranged on rod piece 1
First 2 and erection joint 3 form), support plate 8 (the present embodiment use aluminum honeycomb panel), stringer component (4 component of the first stringer and the
Two stringers, 9 component), bottom plate 11 and angle box 13.The installation interface of payload is mainly by the support joint on antenna mounting truss
2, erection joint 3 or rod piece 1 (the present embodiment uses square beam), other electronics standalone components are mounted on internal aluminum honeycomb panel.It is logical
It crosses optimization technique, interts support plate 8 in the Bonding Process based on antenna mounting truss (the present embodiment uses aluminum honeycomb panel)
And the assembly of stringer component (9 component of 4 component of the first stringer and the second stringer), it is ultimately formed into truss cellular board integral type knot
Structure can provide enough installation spaces while carrying big magnitude payload for electronic building brick single machine.
As shown in Fig. 2~Fig. 6, embodiment includes: antenna mounting truss mainly by a certain number of support joints 2, installation
Connector 3 and rod piece 1 (the present embodiment uses square beam) composition, when splicing, take inverted assemble sequence, use assembly tooling first
Support joint 2, erection joint 3 and rod piece 1 (the present embodiment uses square beam) are subjected to splicing fixation and form antenna mounting truss, so
One end that cross section is L-shaped first stringer 4 is inserted into support joint 2 afterwards, is connect in the other end installation stringer of the first stringer 4
First 5.Meanwhile one end of support rod 6 being inserted into erection joint 3, mounting base 7 is installed in the other end of support rod 6, completes bottom
The component in portion.
Then, then be supported plate 8 (the present embodiment use cellular board) assembly trim, with stringer connector 5 and mounting base 7
It is fixed.Meanwhile partition 12 is equipped in support plate 8, isolate different installation spaces.It is installed on stringer connector 5 again transversal
Face is L-shaped second stringer 9, and support base 10 is arranged again at the top of the second stringer 9.Bottom plate 11 is finally mounted on support base
On 10 be glued positioning, after certain time solidification after from rigid tooling stripping forming.
Directly connect with other extraneous devices for convenience, be also provided with by connecting rod 15 respectively with erection joint 3,
The jointing 14 that support base 10, mounting base 7 and support joint 2 connect；Moreover, being equipped with angle in the outside of 4 component of the first stringer
Box 13 facilitates the transmitting of power.
In addition, being respectively set between support plate 8 and partition 12 between the first stringer 4 equipped with the first reinforcing rib 16 and
Two reinforcing ribs 17 are to improve whole intensity.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (9)
1. a kind of antenna mounting truss structure characterized by comprising
Antenna mounting truss, the antenna mounting truss include that rod piece and the support joint and installation that are arranged on the rod piece connect
Head；
First stringer component, the first stringer component include more first stringers, one end of first stringer and the branch
Connector connection is supportted, is equipped with stringer connector in the other end of first stringer；
Support rod, one end of the support rod are connect with the erection joint, are equipped with mounting base in the other end of the support rod；
Support plate, the support plate are fixed by the stringer connector and the mounting base；
Second stringer component, the second stringer component include more second stringers, one end and the purlin of second stringer
The connection of connector is equipped with support base in the other end of second stringer；
Bottom plate, the bottom plate are arranged on the support base.
2. antenna mounting truss structure according to claim 1, which is characterized in that the support plate is aluminum honeycomb panel.
3. antenna mounting truss structure according to claim 1, which is characterized in that be equipped with partition in the support plate.
4. antenna mounting truss structure according to claim 1, which is characterized in that in the outside of the first stringer component
Equipped with angle box.
5. antenna mounting truss structure according to claim 1, which is characterized in that the antenna mounting truss structure includes
Jointing, the jointing by connecting rod respectively with the erection joint, the support base, the mounting base and described
Support joint connection.
6. antenna mounting truss structure according to claim 1, which is characterized in that be equipped with the between first stringer
One reinforcing rib.
7. antenna mounting truss structure according to claim 3, which is characterized in that set between support plate and the partition
There is the second reinforcing rib.
8. antenna mounting truss structure according to claim 1, which is characterized in that the rod piece is square beam structure.
9. antenna mounting truss structure according to claim 1, which is characterized in that first stringer and second purlin
The cross section of item is L shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610920480.2A CN106542080B (en) | 2016-10-21 | 2016-10-21 | Antenna mounting truss structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610920480.2A CN106542080B (en) | 2016-10-21 | 2016-10-21 | Antenna mounting truss structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106542080A CN106542080A (en) | 2017-03-29 |
| CN106542080B true CN106542080B (en) | 2019-01-08 |
Family
ID=58393282
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610920480.2A Active CN106542080B (en) | 2016-10-21 | 2016-10-21 | Antenna mounting truss structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106542080B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107331940B (en) * | 2017-05-27 | 2019-08-02 | 上海卫星工程研究所 | Adapt to the antisymmetry high rigidity mixed structure of spaceborne big front antenna H-type installation |
| CN108820252B (en) * | 2018-06-20 | 2020-04-21 | 上海卫星工程研究所 | Cabin inner and outer truss and honeycomb panel combined satellite cabin section structure |
| CN109263057B (en) * | 2018-09-26 | 2019-09-13 | 中国科学院长春光学精密机械与物理研究所 | A kind of bonding and assembly method of precision carbon fiber truss |
| CN110061343B (en) * | 2019-04-11 | 2020-12-08 | 上海卫星工程研究所 | Combined supporting structure for large antenna of deep space probe |
| CN111098507B (en) * | 2019-12-31 | 2021-11-26 | 上海复合材料科技有限公司 | Method for in-situ gluing assembly of satellite composite material truss |
| CN111942565A (en) * | 2020-08-05 | 2020-11-17 | 中国航空工业集团公司沈阳飞机设计研究所 | Beam type lattice structure and micro-truss structure with same |
| CN112963479B (en) * | 2021-04-07 | 2021-10-01 | 清华大学 | Bistable cell and multistable mechanical structure with multi-level structure |
| CN113799965B (en) * | 2021-10-28 | 2023-07-21 | 陕西飞机工业有限责任公司 | Plane knapsack inclined type double-area-array dome structure |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201086828Y (en) * | 2007-04-28 | 2008-07-16 | 上海卫星工程研究所 | Non-deformation full-carbon frame used for man-made satellite |
| CN103075629B (en) * | 2011-10-26 | 2016-07-20 | 上海卫星工程研究所 | A kind of large-scale pre-buried complicated small deformation framework cellular board |
| CN202454720U (en) * | 2012-02-29 | 2012-09-26 | 西安空间无线电技术研究所 | Thermal-stabilizing framework of thin film antenna |
| CN102748563A (en) * | 2012-06-21 | 2012-10-24 | 上海卫星工程研究所 | All-composite-material and all-glued frame structure device |
| CN103963360A (en) * | 2014-05-06 | 2014-08-06 | 上海卫星工程研究所 | Honeycomb sandwich plate and frame bottom surface integrated structure |
-
2016
- 2016-10-21 CN CN201610920480.2A patent/CN106542080B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106542080A (en) | 2017-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106542080B (en) | Antenna mounting truss structure | |
| CN100534861C (en) | Device and method for non-symmetrical mixed carbon-metal assembly | |
| CN103935529B (en) | A kind of quick response satellite structure | |
| CN108820252A (en) | Truss and honeycomb board combined type satellite cargo tank structure inside and outside a kind of cabin | |
| CN109850186A (en) | A kind of flat-rack satellite structure and assembly method for several satellite in a rocket parallel connection transmitting | |
| CN102230489B (en) | T-shaped connection structure of composite material laminboard | |
| CN106486730A (en) | Spaceborne deployable plate aerial sub-truss and its assembly method | |
| CN201086828Y (en) | Non-deformation full-carbon frame used for man-made satellite | |
| CN108045597A (en) | Modularization, sectional satellite structure | |
| CN202454720U (en) | Thermal-stabilizing framework of thin film antenna | |
| CN103963360A (en) | Honeycomb sandwich plate and frame bottom surface integrated structure | |
| CN107336847B (en) | Satellite control moment gyro group mounting structure | |
| CN113306699A (en) | Connecting structure and method for horizontal tail and vertical tail of T-tail layout aircraft | |
| CN105035360A (en) | Cabin-segmentation type separable platform configuration based on four-point connection | |
| CN205329996U (en) | Square steel post for building combined | |
| CN107317088B (en) | Multistory masonry structure assembly method for spaceborne big front antenna H-type installation | |
| CN220414673U (en) | Assembled steel truss structure | |
| CN207919385U (en) | Reinforced composite material foam sandwich cylinder/column mixed connection structure | |
| CN111411696A (en) | Connecting structure for space pipe truss node and construction method thereof | |
| CN114476125B (en) | Satellite platform structure | |
| CN204720854U (en) | Spliced prefabricated cabin and prefabricated cabin formula transformer station | |
| CN103774804A (en) | Solar heat collecting unit module for energy-saving house with glass curtain wall | |
| CN203998728U (en) | Chip jacking stock | |
| CN107231122A (en) | Solar cell module framework | |
| CN203755565U (en) | Solar heat collection unit module used for building |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |