CN102012490B - Installation arrangement of satellite-borne magnetometer - Google Patents
Installation arrangement of satellite-borne magnetometer Download PDFInfo
- Publication number
- CN102012490B CN102012490B CN 200910195289 CN200910195289A CN102012490B CN 102012490 B CN102012490 B CN 102012490B CN 200910195289 CN200910195289 CN 200910195289 CN 200910195289 A CN200910195289 A CN 200910195289A CN 102012490 B CN102012490 B CN 102012490B
- Authority
- CN
- China
- Prior art keywords
- magnetometer
- satellite
- probe
- sun wing
- design
- 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
Landscapes
- Measuring Magnetic Variables (AREA)
Abstract
The invention discloses installation arrangement of a satellite-borne magnetometer, comprising solar wings connected with a satellite body and a solar wing sailboard, wherein a bracket for installing the magnetometer is arranged at the outer side of the solar wing. The satellite body is connected with the solar wing sailboard through a hinge; the solar wing sailboard is connected with the bracket of the magnetometer through a hinge; and probes of the magnetometer are respectively fixed on the bracket of the magnetometer through bolts. The invention has simple theory and engineering feasibility, meets the technical requirements of specially using an extension mechanism to ensure that a residual magnetic index at installation position of the two probes of the magnetometer is less than 0.5 nT, optimizes the whole satellite arrangement design, saves weight for the whole satellite design, and avoids the design of complex extension mechanism. The invention has the advantages of shortening development cycle, saving development cost and the like.
Description
Technical field
The present invention relates to star with the general technical field of magnetometer, be specifically related to a kind of method for arranging of the magnetometer position for Martian satellite.
Background technology
The application of magnetometer class load in satellite is more, it is a kind of instrument of detection of magnetic field more widely, this class load is used has certain specific (special) requirements, need to avoid the satellite self-field to its impact, therefore, when the satellite overall structural arrangement, generally need special arrangement/mechanism that the position of magnetometer is installed, be used for satisfying the service range requirement of magnetometer.
At present, the magnetometer that uses on satellite, most extension means that adopt 2 foldings or 3 foldings when the satellite overall structural arrangement are installed magnetometer in the extension means end, and the required distance of magnetometer and celestial body is guaranteed in the satellite rear expansion of entering the orbit.This extension means own vol is huge, complex structure, not only star of every development must design a complete special magnetometer extension means of cover, and increased certain weight for satellite platform design, expend simultaneously a large amount of research funds, caused whole star fiduciary level reduction, satellite to launch the shortcomings such as risk increase at rail.
Summary of the invention
Problem to be solved by this invention is to overcome spaceborne magnetometer class load in prior art, method with extension means end installation magnetometer, the present invention proposes a kind of method for arranging of spaceborne magnetometer, the method utilizes sun wing outside increase support mode that magnetometer is installed, utilize the expansion function of the sun wing, guarantee the required distance of magnetometer and celestial body.
The principle of the invention is simple, engineering feasibility is strong, utilize the method can make two magnetometers pop one's head in installation place remanent magnetism index less than 0.5nT, solved and utilized specially extension means to realize the scheme of this index request, optimized whole star topological design, be whole star design save weight, also avoided the design of complicated extension means simultaneously.
Description of drawings
Fig. 1 is the present invention at satellite during on ground, celestial body and magnetometer probe positions schematic diagram
Fig. 2 is the present invention at satellite in orbit the time, celestial body and magnetometer probe positions schematic diagram
Embodiment
The present invention is further detailed explanation below in conjunction with drawings and Examples
Schematic diagram outside the sun wing as shown in Figure 1, comprise that the sun wing, the sun wing windsurfing that are connected with celestial body form, be provided with the support that magnetometer is installed outside the sun wing, this support comprises that magnetometer support 3, first magnetometer probe the 4, second magnetometer probe 5 form.Above-mentioned celestial body 1 is connected with sun wing windsurfing 2 by hinge, and sun wing windsurfing 2 is connected with magnetometer support 3 by hinge; First above-mentioned magnetometer probe the 4 and second magnetometer probe 5 is fixed by screws in respectively on magnetometer support 3.Be magnetometer probe installation location structural representation as shown in Figure 2, the second magnetometer probe 5 is positioned at satellite sun wing windsurfing end, the first magnetometer probe 4 outermost 450mm apart from sun wing windsurfing 2, two probe spacing 450mm.After solar wing spreading, magnetometer just is extensible to the position far away apart from satellite body, thereby satisfies the installation place remanent magnetism index of magnetometer less than the requirement of 0.5n.
Satellite is before emission, sun wing windsurfing 2 and magnetometer support 3 are in rounding state, after the satellite and the rocket separate, to launch according to mission program sun wing windsurfing 2 and magnetometer support 3, after launching, magnetometer just is extensible to the position far away apart from satellite body, thereby satisfies the installation place remanent magnetism index of magnetometer less than the requirement of 0.5n.
Claims (1)
1. the supporting structure of a spaceborne magnetometer, comprise the sun wing, the sun wing windsurfing that are connected with celestial body, it is characterized in that, be provided with the support that magnetometer is installed outside the sun wing, this support comprises magnetometer support [3], the first magnetometer probe [4], the second magnetometer probe [5]; Described celestial body [1] is connected with sun wing windsurfing [2] by hinge, and described sun wing windsurfing [2] is connected with magnetometer support [3] by hinge; Described the first magnetometer probe [4] and magnetometer probe [5] are fixed by screws in respectively on magnetometer support [3]; The second magnetometer probe [5] is positioned at satellite sun wing windsurfing [2] end, and the first magnetometer probe [4] is apart from the outermost 450mm of sun wing windsurfing [2], two probe spacing 450mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910195289 CN102012490B (en) | 2009-09-08 | 2009-09-08 | Installation arrangement of satellite-borne magnetometer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200910195289 CN102012490B (en) | 2009-09-08 | 2009-09-08 | Installation arrangement of satellite-borne magnetometer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102012490A CN102012490A (en) | 2011-04-13 |
| CN102012490B true CN102012490B (en) | 2013-05-22 |
Family
ID=43842721
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200910195289 Active CN102012490B (en) | 2009-09-08 | 2009-09-08 | Installation arrangement of satellite-borne magnetometer |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102012490B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107682017B (en) * | 2017-09-29 | 2020-04-14 | 中国科学院地质与地球物理研究所 | Satellite-borne magnetometer magnetic field data compression processing method and device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6076773A (en) * | 1998-04-10 | 2000-06-20 | Hughes Electronics Corporation | Spin-stabilized spacecraft and methods |
| US6298289B1 (en) * | 1999-04-24 | 2001-10-02 | The Boeing Company | Integrated spacecraft control system and method |
| DE60301117T2 (en) * | 2002-12-13 | 2006-06-08 | The Boeing Co., Chicago | Method and device for dynamic compensation with reaction wheels during a longer deployment of a large reflector |
| DE60304808T2 (en) * | 2002-12-13 | 2006-12-21 | The Boeing Co., Chicago | Method and device for position control with solar pressure moments during a longer deployment of a large reflector |
| CN101226561A (en) * | 2007-12-28 | 2008-07-23 | 南京航空航天大学 | Minitype simulation support system and operating method for minitype spacecraft attitude orbital control system |
| CN101344788A (en) * | 2008-09-02 | 2009-01-14 | 南京航空航天大学 | Simulation test equipment and method for moonlet attitude control reliability validation |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6588708B2 (en) * | 2001-01-29 | 2003-07-08 | The Boeing Company | Spacecraft methods and structures for acquiring and determining power-safe attitudes |
| US6762716B2 (en) * | 2002-12-13 | 2004-07-13 | The Boeing Company | Digital beacon asymmetry and quantization compensation |
-
2009
- 2009-09-08 CN CN 200910195289 patent/CN102012490B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6076773A (en) * | 1998-04-10 | 2000-06-20 | Hughes Electronics Corporation | Spin-stabilized spacecraft and methods |
| US6298289B1 (en) * | 1999-04-24 | 2001-10-02 | The Boeing Company | Integrated spacecraft control system and method |
| DE60301117T2 (en) * | 2002-12-13 | 2006-06-08 | The Boeing Co., Chicago | Method and device for dynamic compensation with reaction wheels during a longer deployment of a large reflector |
| DE60304808T2 (en) * | 2002-12-13 | 2006-12-21 | The Boeing Co., Chicago | Method and device for position control with solar pressure moments during a longer deployment of a large reflector |
| CN101226561A (en) * | 2007-12-28 | 2008-07-23 | 南京航空航天大学 | Minitype simulation support system and operating method for minitype spacecraft attitude orbital control system |
| CN101344788A (en) * | 2008-09-02 | 2009-01-14 | 南京航空航天大学 | Simulation test equipment and method for moonlet attitude control reliability validation |
Non-Patent Citations (6)
| Title |
|---|
| 倪亦斌.某种新型磁强计在星载部件测试中的应用研究.《中国空间科学技术》.2000,(第3期),66-70. |
| 卫星收拢太阳翼频率响应分析;方宝东;《机械设计与研究》;20050630;第21卷(第3期);95-97 * |
| 地磁场中卫星磁测试环境与设备;李荣福;《航天器环境工程》;20080229(第1期);72-79 * |
| 方宝东.卫星收拢太阳翼频率响应分析.《机械设计与研究》.2005,第21卷(第3期),95-97. |
| 李荣福.地磁场中卫星磁测试环境与设备.《航天器环境工程》.2008,(第1期),72-79. |
| 某种新型磁强计在星载部件测试中的应用研究;倪亦斌;《中国空间科学技术》;20000630(第3期);66-70 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102012490A (en) | 2011-04-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EA025867B1 (en) | Multiple space vehicle launch system | |
| CN101850851B (en) | Distribution structure of SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite | |
| CN103482084B (en) | A kind of novel Stretching of solar wings based on banded spring and supporting mechanism | |
| CN109927936B (en) | Static orbit satellite with load isolated from platform thermal deformation | |
| CN102437404B (en) | Integrated structure of rigidized inflatable deployable truss type planar antenna and solar array | |
| CN104260901A (en) | Modular two-component propulsion system | |
| CN106374995A (en) | Space application communication platform based on rail retaining last stage of carrier rocket | |
| CN101850852B (en) | SPORT (Solar Polar Orbit Radio Telescope) clock scanning satellite | |
| CN102358437A (en) | Layout method for 10 N thrusters of high orbit satellite platform | |
| CN108860659A (en) | A kind of integrated satellite based on deployable plate phased array antenna | |
| CN204056318U (en) | A kind of satellite structure being applicable to GNSS LEO occultation | |
| CN106628252B (en) | It is a kind of that orbit aerocraft structure is stayed based on parallel configuration's payload adapter | |
| CN106486730A (en) | Spaceborne deployable plate aerial sub-truss and its assembly method | |
| CN102012490B (en) | Installation arrangement of satellite-borne magnetometer | |
| EP3359448B1 (en) | Solar array deployment | |
| CN112977884A (en) | Sailboard sunshade type double-super satellite platform system for morning and evening tracks | |
| CN103253381B (en) | Grounding design method of multi-cabin combined type spacecraft | |
| CN106777638B (en) | Zero-trim layout design method for propulsion cabin of eccentric spacecraft | |
| CN102683796A (en) | Satellite-borne folding mobile antenna and locking method thereof | |
| JP2018531177A6 (en) | Deployment of solar array | |
| CN104290918B (en) | Miniaturization track towboat satellite configuration and layout design method | |
| CN109878761A (en) | Wedge shape space physics field measurement satellite configuration and its assembly method | |
| CN111559519B (en) | Ultra-long wave astronomical observation satellite and array configuration thereof | |
| Schwanbeck | Advanced Solar Arrays on the ISS | |
| Sugawara et al. | A satellite for demonstration of Panel Extension Satellite (PETSAT) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20180112 Address after: 100089 floor 16, floor No. 2, No. 2, No. 5, West Sanhuan North Road, Beijing Patentee after: The eight hospital (Beijing) Space Technology Research Institute Co. Ltd. Address before: 200240 Shanghai city Minhang District Huaning Road No. 251 Patentee before: Shanghai Satellite Engineering Research Institute |
|
| TR01 | Transfer of patent right |