CN107757950A - A kind of high rail Optical remote satellite structure - Google Patents
A kind of high rail Optical remote satellite structure Download PDFInfo
- Publication number
- CN107757950A CN107757950A CN201710829212.4A CN201710829212A CN107757950A CN 107757950 A CN107757950 A CN 107757950A CN 201710829212 A CN201710829212 A CN 201710829212A CN 107757950 A CN107757950 A CN 107757950A
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- fuel tank
- platform
- loaded cylinder
- satellite
- mounting seat
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- 230000003287 optical effect Effects 0.000 title claims abstract description 21
- 239000002828 fuel tank Substances 0.000 claims abstract description 83
- 239000000446 fuel Substances 0.000 claims abstract description 27
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 23
- 239000001301 oxygen Substances 0.000 claims abstract description 23
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 14
- 230000010354 integration Effects 0.000 claims description 38
- 239000000463 material Substances 0.000 claims description 10
- 210000000452 mid-foot Anatomy 0.000 claims description 9
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 8
- 238000010276 construction Methods 0.000 claims description 6
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 230000002787 reinforcement Effects 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims 2
- 230000007613 environmental effect Effects 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 description 1
- 240000002853 Nelumbo nucifera Species 0.000 description 1
- 235000006510 Nelumbo pentapetala Nutrition 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
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
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- 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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Photovoltaic Devices (AREA)
Abstract
A kind of high rail Optical remote satellite structure, including loaded cylinder (1), fuel tank (2), oxygen case (3), satellite platform (8), solar wing (11), load adapter structure (14), camera (15) etc.；Oxygen case (3) is arranged in loaded cylinder (1)；Each fuel tank (2) is arranged on loaded cylinder (1) both sides by arm-tie (5) at the top of the fuel box bracket (4) positioned at fuel tank (2) both ends and fuel tank respectively；Loaded cylinder (1), fuel tank (2), oxygen case (3), fuel box bracket (4), fuel tank top arm-tie (5) are arranged in satellite platform (8)；Camera (15) is arranged at the top of satellite platform (8) by load adapter structure (14)；Solar wing (11) is separately mounted to satellite platform (8) both sides.The present invention realizes the reduction of satellite entirety barycenter, load mounting surface environmental condition improves, while meets that fuel tank, oxygen case etc. control puopulsion equipment installation requirement.
Description
Technical field
The invention belongs to Design of spacecraft structure technical field, and the present invention relates to a kind of high rail Optical remote satellite structure.
Background technology
High rail Optical remote satellite can realize the uninterrupted observation to a certain target, complete with earth observation systems
Kind, high rail Optical remote satellite turns into an important directions of China's space remote sensor development.To adapt to high rail remote sensing fields hair
Exhibition demand, on existing telecommunication satellite platform base, for the big load, high stability, rapid posture machine of high rail remote sensing satellite
The distinguishing features such as kinetic force, the subsystems such as structure, propulsion, control are modified, form high rail remote sensing satellite platform, have height concurrently
Rail satellite and remote sensing satellite functional characteristics, and one of wherein mostly important design difficulty is exactly propulsion system (oxygen case, fuel
Case) mounting design, camera high stable mounting design, miscellaneous equipment mounting design etc..
China is the first country for carrying out high rail Optical remote satellite development, therefore its Platform Designing is also in the world at present
With stronger initiative.
Existing high rail satellite platform Main Load is antenna system, and satellite control and propulsion system (oxygen case, fuel tank) are main
Equipment is wanted to be mounted in satellite bearing cylinder, loaded cylinder oneself height.And the Main Load of high rail Optical remote satellite is optics
Load (camera), load weight accounting is relatively bigger, if directly borrowing existing high rail satellite platform, satellite entirety barycenter is higher,
Optics load mounting surface mechanical environment condition meeting very severe, therefore a kind of New Satellite structure platform need to be established, carried for load
Meet fuel tank, oxygen case, camera, other various kinds of equipment installation requirements simultaneously for good mounting characteristics.
The content of the invention
The technical problem to be solved in the present invention is：Overcome the deficiencies in the prior art, the invention provides a kind of high rail optics
Remote sensing satellite structure, by designing external hanging type fuel tank mounting means, realize the reduction of satellite entirety barycenter, load mounting surface environment
Improvement of terms, while meet that fuel tank, oxygen case etc. control puopulsion equipment installation requirement.
The technical solution adopted in the present invention is：A kind of high rail Optical remote satellite structure, including loaded cylinder, fuel tank,
Oxygen case, fuel box bracket, fuel tank top arm-tie, satellite platform, solar wing, load adapter structure, camera；Oxygen case is arranged on and held
In power cylinder；Each fuel tank is arranged on loaded cylinder by arm-tie at the top of the fuel box bracket and fuel tank positioned at fuel tank both ends respectively
Both sides；Loaded cylinder, fuel tank, oxygen case, fuel box bracket, fuel tank top arm-tie are arranged in satellite platform；Camera passes through load
Lotus adapter structure is arranged at the top of satellite platform；Solar wing is separately mounted to satellite platform both sides.
The fuel box bracket is metal reinforced flat plate structure, material 2A14T6, respectively symmetrically installed in loaded cylinder two
Side；Fuel box bracket side is arc interface, is connected with loaded cylinder side wall；Fuel tank mid-stent is provided with fuel tank mounting hole,
Fuel tank one end is arranged in fuel tank mounting hole.
Arm-tie is slab construction at the top of the fuel tank, and there is fuel tank connecting interface at middle part, and side is arc interface, with holding
Power cylinder side wall is connected；Arm-tie is respectively symmetrically arranged on loaded cylinder both sides and close to loaded cylinder one end port at the top of each fuel tank；Respectively
Fuel tank one end is connected by fuel tank connecting interface with arm-tie at the top of fuel tank.
The satellite platform includes dividing plate, outer panel, platform top, platform floor, midfoot support plate；Dividing plate has four,
It is connected respectively with arm-tie, loaded cylinder at the top of fuel box bracket, fuel tank, is symmetrically mounted on loaded cylinder both sides and on crossing loaded cylinder
Symmetry axis, the plane of fuel tank symmetry axis are symmetrical；Platform top, platform floor are separately mounted to loaded cylinder both ends；Outer panel two
End is connected with platform top, platform floor respectively, with platform top, platform floor composition octahedral structure；Midfoot support plate is
Cross hang structure, between dividing plate and outer panel, solar wing is fixed on midfoot support plate, on outer panel.
The load adapter structure is arranged in the middle part of platform top, is toroidal shell structure, and camera is adapted to installed in load
In structure.
The load adapter structure includes box-type local support structure, integration mounting seat outside barrel shell, inside barrel shell
Integration mounting seat, barrel shell outside integration mounting seat is arranged on the upper surface of load adapter structure upper, annular platform, along ring
Shape platform is circumferentially uniformly distributed；Integration mounting seat and barrel shell outside integration are pacified inside box-type local support structure, barrel shell
It is corresponding to fill seat installation site, installed in the lower surface of load adapter structure upper, annular platform.
The camera uses supported at three point form, respectively with integration mounting seat, box-type local support outside each barrel shell
Integration mounting seat is fixedly connected by screw inside structure, barrel shell.
Integration mounting seat is slab construction outside the barrel shell, 9 camera connecting holes is distributed with, material is titanium alloy.
The box-type local support structure is angle box structure, respectively with the following table of load adapter structure upper, annular platform
Face, load adapter structure side inner walls are connected.
Integration mounting seat has the block structure of reinforcement for inside inside the barrel shell, and camera connecting hole, cylinder is distributed with
Integration mounting seat is located at outside barrel shell in integration mounting seat inside shell, and material is titanium alloy.
The present invention compared with prior art the advantages of be：
(1) present invention is designed, fuel tank support knot relative to existing high rail satellite platform by the plug-in configuration of fuel tank
Structure design, loaded cylinder connection design etc., significantly reduce loaded cylinder oneself height, and then realize the reduction of satellite entirety barycenter, load
Mechanical environment improves lifting.
(2) octahedra formula configuration is used by whole star, is meeting that fuel tank, oxygen case, solar wing, number pass antenna and other each
Satellite structure size is effectively controlled while kind equipment installation requirements, to meet delivery envelope requirement；It is octahedra by whole star
Body structure form, meet that the installation of fuel tank external hanging type, delivery envelope requirement and solar wing, number pass antenna and miscellaneous equipment installation
Demand.By designing Three-points supporting type high stable load adapter structure, the high stable installation of camera is realized.
(3) by Three-points supporting type high stable load adapter structure, bikini optical camera load adaptation can fully be adapted to
Support demand, while meet rigidity, intensity, stability support requirement, realize the installation of camera high stable.
Brief description of the drawings
Fig. 1 is the whole star structure type outline of the present invention；
Fig. 2 is the whole star structure type internal structure of the present invention；
Fig. 3 is the loaded cylinder external hanging fuel mounting means of the present invention；
Fig. 4 is arm-tie at the top of the fuel tank of the present invention；
Fig. 5 is the fuel box bracket of the present invention；
Fig. 6 is the high stable load adapter structure outline of the present invention；
Fig. 7 is the high stable load adapter structure barrel shell internal structure of the present invention；
Fig. 8 is the box-type local support structure of the present invention；
Fig. 9 is integration titanium alloy mounting seat outside the barrel shell of the present invention；
Figure 10 is integration titanium alloy mounting seat inside the barrel shell of the present invention.
Embodiment
The present invention is further described below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of high rail Optical remote satellite structure, including loaded cylinder 1, fuel tank 2, oxygen case 3,
Arm-tie 5, satellite platform 8, solar wing 11, load adapter structure 14, camera 15 at the top of fuel box bracket 4, fuel tank；Oxygen case 3 is pacified
In loaded cylinder 1；Each fuel tank 2 passes through arm-tie 5 at the top of the fuel box bracket 4 positioned at the both ends of fuel tank 2 and fuel tank respectively
Installed in the both sides of loaded cylinder 1；Loaded cylinder 1, fuel tank 2, oxygen case 3, fuel box bracket 4, fuel tank top arm-tie 5 are arranged on satellite
In platform 8；Camera 15 is arranged on the top of satellite platform 8 by load adapter structure 14；Solar wing 11 is separately mounted to satellite and put down
The both sides of platform 8.
As shown in figure 5, fuel box bracket 4 is metal reinforced flat plate structure, material 2A14T6, respectively symmetrically it is arranged on and holds
The both sides of power cylinder 1；The side of fuel box bracket 4 is arc interface, is connected with the side wall of loaded cylinder 1；The middle part of fuel box bracket 4 is provided with fuel
Case mounting hole, the one end of fuel tank 2 are arranged in fuel tank mounting hole.
As shown in figure 4, arm-tie 5 is slab construction at the top of fuel tank, there is fuel tank connecting interface 9 at middle part, and side is arc
Interface, it is connected with the side wall of loaded cylinder 1；Arm-tie 5 is respectively symmetrically arranged on the both sides of loaded cylinder 1 and close to loaded cylinder at the top of each fuel tank
1 one end port；Each one end of fuel tank 2 is connected by fuel tank connecting interface 9 with arm-tie 5 at the top of fuel tank.
Satellite platform 8 includes dividing plate 7, outer panel 12, platform top 13, platform floor 10, midfoot support plate 20；Dividing plate 7
Have four, with fuel box bracket 4, at the top of fuel tank, arm-tie 5, loaded cylinder 1 are connected respectively, be symmetrically mounted on the both sides of loaded cylinder 1 and
Plane on the symmetry axis of loaded cylinder 1 excessively, the symmetry axis of fuel tank 2 is symmetrical；Platform top 13, platform floor 10 are separately mounted to hold
The both ends of power cylinder 1；The both ends of outer panel 12 are connected with platform top 13, platform floor 10 respectively, with platform top 13, platform floor 10
Form octahedral structure；Midfoot support plate 20 is cross hang structure, between dividing plate 7 and outer panel 12, solar wing 11
It is fixed on midfoot support plate 20, on outer panel 12.
As shown in Figure 6, Figure 7, load adapter structure 14 is arranged on the middle part of platform top 13, is toroidal shell structure, camera
15 are arranged on load adapter structure 14.Load adapter structure 14 includes box-type local support structure 16, barrel shell outside entirety
Change mounting seat 17, barrel shell inside integration mounting seat 18, integration mounting seat 17 is arranged on load adapter structure 14 outside barrel shell
The upper surface of upper, annular platform, circumferentially it is uniformly distributed along ring-shaped platform；It is overall inside box-type local support structure 16, barrel shell
It is corresponding with integration 17 installation sites of mounting seat outside barrel shell to change mounting seat 18, is put down installed in the upper, annular of load adapter structure 14
The lower surface of platform.Camera 15 uses supported at three point form, with integration mounting seat 17, box-type local support knot outside each barrel shell
Integration mounting seat 18 is fixedly connected by screw inside structure 16, barrel shell.
As Figure 8-Figure 10, integration mounting seat 17 is slab construction outside barrel shell, and 9 camera connecting holes are distributed with.
Box-type local support structure 16 is angle box structure, respectively the lower surface with the upper, annular platform of load adapter structure 14, load
The side inner walls of adapter structure 14 are connected, for supporting.Integration mounting seat 18 has the block knot of reinforcement for inside inside barrel shell
Structure, camera connecting hole is distributed with, integration mounting seat 18 is in barrel shell outside integration mounting seat 17 inside barrel shell.
Concrete composition is as follows：
1) whole star height of center of mass
The height 1979mm of satellite bearing cylinder 1, reduce more than 1000mm relative to conventional high rail satellite platform, thus can realize
Whole star filling state height of center of mass control is in 1200mm.
2) fuel tank and oxygen case mounting means
Satellite propulsion system is mainly made up of fuel tank 2 and oxygen case 3, and oxygen case 3 is installed in loaded cylinder 1, with the high rail of tradition
Satellite platform oxygen case installation form (oxygen case 3, fuel tank 2 are mounted in loaded cylinder 1) is basically identical.
Fuel tank 2 is divided into two, is individually positioned in outside loaded cylinder 1, celestial body east and west sides, and fuel tank 2 passes through fuel tank branch
Arm-tie 5 is arranged on the both sides of loaded cylinder 1 at the top of frame 4 and fuel tank.
Fuel box bracket 4 is designed as metal reinforced structure, and support bending rigidity is highly provided by reinforcement, while relative to
Entity structure overall weight reduces by 70%, material selection 2A14T6, is made using integrated machine add mode.Fuel box bracket 4 provides
With the connecting interface 6 of fuel tank, and respectively with loaded cylinder 1, dividing plate 7, form rectangular two panels outer panel 12 with dividing plate 7 and be spirally connected
Connection.
Arm-tie 5 constrains fuel tank lateral displacement, release length travel at the top of fuel tank, with lifted cross-brace rigidity and
Superfluous constraint is not introduced, avoids being deformed mismatching under severe mechanical environment, and then causes satellite structure or fuel tank to be sent out
It is raw to destroy.Arm-tie 5 provides fuel tank connecting interface 9 at the top of fuel tank, and the loaded cylinder 1, dividing plate 7 and the composition of dividing plate 7 with center are grown
Square two panels outer panel 12 is spirally connected connection.
3) octahedra platform structure form
Satellite platform 8 uses octahedra formula structure, on the one hand adapts to loaded cylinder external hanging fuel installation requirement, on the other hand
Include space using delivery as far as possible, sufficient installing space is provided for solar wing 11 and miscellaneous equipment.
4) camera high stable mounting means
Camera 15 is installed by load adapter structure 14 and satellite platform 8.The top and bottom of load adapter structure 14 provide respectively
With camera 15, the connecting interface of satellite platform 8.Load adapter structure 14 is cylinder shell type structure.Camera 15 for reduce platform deformation and
Vibration influences on it, using supported at three point form.Therefore, the upper surface of load adapter structure 14 of corresponding three camera support points is set
In respect of integration mounting seat 17, barrel shell inside integration mounting seat 18 outside box-type local support structure 16, barrel shell, to meet
High rigidity, high intensity, high stable support require.Integration mounting seat 17, the material of barrel shell inside integration mounting seat 18 outside barrel shell
Expect for titanium alloy.
Box-type local support structure 16 is real by partial closure's formula using the composite material moulded material structures of 3mm-5mm
Current situation portion stiffness and strength is obviously improved, while avoids the weight cost strengthened using globality.
Corresponding to 9 tie points of each camera mounting seat, there is cylinder in the upper surface of load adapter structure 14, lower surface design
Integration bearing 17, barrel shell inside integration mounting seat 18, give full play to titanium alloy low bulk, high intensity, high rigidity outside shell
Characteristic.And being glued by way of being spirally connected and being combined, camera tie point, load adapter structure body, box-type are locally propped up
Support structure forms entirety, realizes the support stiffness of camera 15, intensity, stability integrated design.
Unspecified part of the present invention belongs to technology as well known to those skilled in the art.
Claims (10)
1. a kind of high rail Optical remote satellite structure, it is characterised in that including loaded cylinder (1), fuel tank (2), oxygen case (3), combustion
Arm-tie (5), satellite platform (8), solar wing (11), load adapter structure (14), camera at the top of hopper support (4), fuel tank
(15)；Oxygen case (3) is arranged in loaded cylinder (1)；Each fuel tank (2) passes through the fuel tank branch positioned at fuel tank (2) both ends respectively
Arm-tie (5) is arranged on loaded cylinder (1) both sides at the top of frame (4) and fuel tank；Loaded cylinder (1), fuel tank (2), oxygen case (3), fuel
Arm-tie (5) is arranged in satellite platform (8) at the top of box bracket (4), fuel tank；Camera (15) is pacified by load adapter structure (14)
At the top of satellite platform (8)；Solar wing (11) is separately mounted to satellite platform (8) both sides.
A kind of 2. high rail Optical remote satellite structure according to claim 1, it is characterised in that：The fuel box bracket
(4) it is metal reinforced flat plate structure, material 2A14T6, respectively symmetrically installed in loaded cylinder (1) both sides；Fuel box bracket (4)
Side is arc interface, is connected with loaded cylinder (1) side wall；Fuel tank mounting hole, fuel tank are provided with the middle part of fuel box bracket (4)
(2) one end is arranged in fuel tank mounting hole.
A kind of 3. high rail Optical remote satellite structure according to claim 1 or 2, it is characterised in that：The fuel tank top
Portion's arm-tie (5) is slab construction, and there is fuel tank connecting interface (9) at middle part, and side is arc interface, with loaded cylinder (1) side wall phase
Even；Arm-tie (5) is respectively symmetrically arranged on loaded cylinder (1) both sides and close to loaded cylinder (1) one end port at the top of each fuel tank；Each combustion
Hopper (2) one end is connected by fuel tank connecting interface (9) with arm-tie (5) at the top of fuel tank.
A kind of 4. high rail Optical remote satellite structure according to claim 3, it is characterised in that：The satellite platform (8)
Including dividing plate (7), outer panel (12), platform top (13), platform floor (10), midfoot support plate (20)；Dividing plate (7) has four
Piece, it is connected respectively with arm-tie (5), loaded cylinder (1) at the top of fuel box bracket (4), fuel tank, is symmetrically mounted on loaded cylinder (1) two
Side and on cross loaded cylinder (1) symmetry axis, fuel tank (2) symmetry axis plane it is symmetrical；Platform top (13), platform floor (10)
It is separately mounted to loaded cylinder (1) both ends；Outer panel (12) both ends are connected with platform top (13), platform floor (10) respectively, with
Platform top (13), platform floor (10) composition octahedral structure；Midfoot support plate (20) is cross hang structure, installed in every
Between plate (7) and outer panel (12), solar wing (11) is fixed on midfoot support plate (20), on outer panel (12).
A kind of 5. high rail Optical remote satellite structure according to claim 4, it is characterised in that：The load adapter structure
(14) it is arranged in the middle part of platform top (13), is toroidal shell structure, camera (15) is arranged on load adapter structure (14).
A kind of 6. high rail Optical remote satellite structure according to claim 5, it is characterised in that：The load adapter structure
(14) box-type local support structure (16), barrel shell outside integration mounting seat (17), barrel shell inside integration mounting seat are included
(18), integration mounting seat (17) is arranged on the upper surface of load adapter structure (14) upper, annular platform outside barrel shell, along ring
Shape platform is circumferentially uniformly distributed；Outside box-type local support structure (16), barrel shell inside integration mounting seat (18) and barrel shell
Integration mounting seat (17) installation site is corresponding, installed in the lower surface of load adapter structure (14) upper, annular platform.
A kind of 7. high rail Optical remote satellite structure according to claim 5 or 6, it is characterised in that：The camera (15)
Using supported at three point form, respectively with integration mounting seat (17), box-type local support structure (16), barrel shell outside each barrel shell
Internal integration mounting seat (18) is fixedly connected by screw.
A kind of 8. high rail Optical remote satellite structure according to claim 7, it is characterised in that：It is overall outside the barrel shell
It is slab construction to change mounting seat (17), 9 camera connecting holes is distributed with, material is titanium alloy.
A kind of 9. high rail Optical remote satellite structure according to claim 8, it is characterised in that：The box-type locally props up
Support structure (16) is angle box structure, respectively the lower surface with load adapter structure (14) upper, annular platform, load adapter structure
(14) side inner walls are connected.
A kind of 10. high rail Optical remote satellite structure according to claim 8 or claim 9, it is characterised in that：Inside the barrel shell
Integration mounting seat (18) has the block structure of reinforcement for inside, and camera connecting hole, the integration installation of barrel shell inside is distributed with
Seat (18) is located at outside barrel shell in integration mounting seat (17), and material is titanium alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710829212.4A CN107757950B (en) | 2017-09-14 | 2017-09-14 | High-orbit optical remote sensing satellite structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710829212.4A CN107757950B (en) | 2017-09-14 | 2017-09-14 | High-orbit optical remote sensing satellite structure |
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| CN107757950A true CN107757950A (en) | 2018-03-06 |
| CN107757950B CN107757950B (en) | 2020-06-09 |
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| CN201710829212.4A Active CN107757950B (en) | 2017-09-14 | 2017-09-14 | High-orbit optical remote sensing satellite structure |
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| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
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| CN109484673A (en) * | 2018-12-24 | 2019-03-19 | 深圳航天东方红海特卫星有限公司 | A kind of payload platform separate type remote sensing micro satellite configuration and its assembly method |
| CN109823576A (en) * | 2019-02-20 | 2019-05-31 | 上海卫星工程研究所 | Bearer connection structure for planetary landing device |
| CN110450981A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | Deployable separate type satellite platform and its assembly application method |
| CN111059206A (en) * | 2019-12-28 | 2020-04-24 | 中国科学院沈阳自动化研究所 | Piezoelectric active vibration damper of flexible solar wing supporting structure |
| CN111891386A (en) * | 2020-06-30 | 2020-11-06 | 北京空间飞行器总体设计部 | Three-dimensional modular structure for supporting multiple loads |
| CN111891386B (en) * | 2020-06-30 | 2022-04-08 | 北京空间飞行器总体设计部 | Three-dimensional modular structure for supporting multiple loads |
| CN112373727A (en) * | 2020-11-24 | 2021-02-19 | 中国空间技术研究院 | Separable satellite propulsion system configuration |
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| CN107757950B (en) | 2020-06-09 |
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