CN203010161U - Three-body frame for magnetically suspended control moment gyro - Google Patents
Three-body frame for magnetically suspended control moment gyro Download PDFInfo
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- CN203010161U CN203010161U CN 201220749870 CN201220749870U CN203010161U CN 203010161 U CN203010161 U CN 203010161U CN 201220749870 CN201220749870 CN 201220749870 CN 201220749870 U CN201220749870 U CN 201220749870U CN 203010161 U CN203010161 U CN 203010161U
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Abstract
The utility model discloses a three-body frame for magnetically suspended control moment gyro. The three-body frame comprises an annular frame, a right dustproof cover and a left dustproof cover, wherein the annular frame carries rotating shafts at two ends of a high-speed rotor system; the assembly difficulty of the component is greatly reduced; the rotating precision of the high-speed rotor system is improved; the annular frame avoids the problem of large deformation of a thin-wall structure by utilizing the structures of a weight-loss groove and a reinforcing rib in an assembly manner of mounting the left dustproof cover and the right dustproof cover at the radial end faces; the structure rigidity is greatly improved on the premise of low quality of the three-body frame; an entire ring is formed by an inclined straight surface and an arc transitional surface; a box mounting plane for establishing the frame control system is provided; and integration of the frame control system and the frame structure is achieved. The three-body frame for the magnetically suspended control moment gyro has the advantages of being high in assembly accuracy, strong in structure rigidity, high in product integration, simple in structure, easy to manufacture and the like.
Description
Technical field
The utility model relates to a kind of magnetic suspension control torque gyroscope trisome framework.
Background technique
Magnetic suspension control torque gyroscope is to be applied to the inertia actuator that Large Spacecraft such as Spacelab and space station hold position and control, and changes the high-speed rotor system moment of momentum by frame system, thereby realizes and reach the too purpose of device attitude adjustment of navigating.
Framework is to build frame system, and at present, the magnetic suspension control torque gyroscope of use all adopts two body frameworks to build frame system both at home and abroad.Abroad, from 1986, the Soviet Union took the lead in using the large magnetic suspension control-moment gyro of two body frameworks, maximum output torque 200Nm, and then realize that the space station attitude of 94 tons of weights controls.At home, since 2007, take BJ University of Aeronautics ﹠ Astronautics as representative, the 1000Nms of the two body frameworks of continuity development always and the magnetic suspension control torque gyroscope of 200Nms moment of momentum.
As the term suggests two body frameworks are namely by two hemisphere type system frameworks, each hemisphere type framework is thin walled structures, leave the cylindrical mounting hole of cooperation of running shaft at the ball-type top, two running shafts of high-speed rotor system are arranged on respectively in the mounting hole of two body frameworks, and two hemisphere type frameworks fasten the change that realizes the high-speed rotor system moment of momentum after symmetry is installed.This two body frameworks exist some not enough on assembling and configuration aspects, and at first, framework adopts the symmetrical assembling of double-body bike, can't realize that high-speed rotor system two ends running shaft highi degree of accuracy is coaxial, thereby restrict the frame system running accuracy; Secondly, its ball shape structure can't arrange the mountion plate of framework control circuit box, cause the framework control system to separate with machine product, can't the implementation framework control system and machine product integrated, and the thin walled structures of framework itself can reduce complete machine structure rigidity greatly, large deformation easily occurs under the impact of the factors such as environmental mechanics and temperature variation, thereby assembly precision is lost, cause a non-removable difficult problem between parts.
The model utility content
The technical problem that the utility model solves is: overcome the deficiencies in the prior art, a kind of magnetic suspension control torque gyroscope trisome framework is provided, well guaranteed frame system rotating coaxial degree, for framework control circuit and connector assembly provide mounting plane, the output circuit of drive end input and test end all is integrated on structural body, the non-dismountable problem of having avoided large deformation to bring.
The technical solution of the utility model is: a kind of magnetic suspension control torque gyroscope trisome framework comprises ring-like framework, right dust cover and left dust cover; Ring-like framework radially two ends, left and right symmetrical position respectively has the mandrel mounting hole of a circle; Each circular mandrel mounting hole each side have one to be used for the mountion plate be connected with astrovehicle; The both sides of ring-like framework up and down semi-ring are plane structure, all are connected by arc-shaped structure between two planes, consist of the domain; The lightening grooves that is used for weight reduction is adopted on ring-like framework radial ring type surface, and right dust cover and left dust cover all adopt hemisphere type metal thin-wall structure, is fixedly mounted on the axial both ends of the surface of annular frame surperficial.
Described two mandrel mounting hole coaxalitys are not more than 0.012mm.
The utility model advantage compared with prior art is:
The utility model adopts this structure of annular frame to carry high-speed rotor system two ends running shaft, thoroughly change the separation assembling of two body frameworks, and then realized that high-speed rotor system two ends rotating shaft rotates on a structure, its rotating coaxial degree is increased to 0.012mm by the 0.1mm of present technology; Adopt square lightening grooves and leave stiffening rib at ring-like framework radial end face, significantly having alleviated weight, having avoided two body framework thin-walled large deformation problems and the non-removable potential risk of assembling; Left and right dust cover adopts the thin-walled ball shape structure, avoided direct stressed position, thereby the decrease thin walled structures is to the integral product stiffness effect; Framework control system and framework integrated makes product structure simple, is easy to make.
Description of drawings
Fig. 1 is the utility model magnetic suspension control torque gyroscope trisome framework schematic diagram;
Fig. 2 is the ring-like framework sketch of the utility model;
Fig. 3 is the utility model magnetic suspension control torque gyroscope trisome framework integrative assembly schematic diagram.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing:
Magnetic suspension control torque gyroscope of the present utility model comprises ring-like framework 1, right dust cover 2 and left dust cover 3 with trisome framework such as Fig. 1.
As shown in Figure 1 and Figure 2, ring-like framework 1 footpath to the left and right the two ends symmetrical position mandrel mounting hole 12 of a circle is respectively arranged; Be easy to guarantee the coaxality of symmetrical circular hole by mechanical boring processing technology, for high-speed rotor system provides the high-precision rotary benchmark, each circular mandrel mounting hole 12 each side have one to be used for the mountion plate 11 be connected with astrovehicle, design and installation face is parallel with ring-like framework axis, and final assembly is more prone to; The specific design structure need of mountion plate 11 are decided according to the structure of connection astrovehicle.The both sides of ring-like framework semi-ring Shang Xia 1 are ramp structure, all are connected by arc-shaped structure between two inclined-planes, consist of the domain, and this tiltedly facing directly with the arc shaped surface ring type structure reduced structural volume greatly; Ring-like framework 1 radial ring profile adopts the lightening grooves 9 and the stiffening rib 10 that are used for weight reduction to realize increasing substantially structural rigidity under the low-quality prerequisite of trisome framework; Right dust cover 2 and left dust cover 3 adopt hemisphere type metal thin-wall structure, be fixedly mounted on the axial both ends of the surface of annular frame 1 surperficial, implementation structure is inner dustproof, and it is directly stressed that axial mounting point is avoided thin walled structures, thereby the decrease thin walled structures is to the integral product stiffness effect.
Fig. 3 is magnetic suspension control torque gyroscope of the present utility model trisome framework integrative assembly schematic diagram.Utilize ring-like framework 1 by the highly coaxial mounting hole 12 of two ends symmetry, carry high-speed rotor system 6 drive end rotation mandrels 7 and test end rotation mandrel 8, realize high-speed rotor system 6 high-precision rotaries.Framework control circuit box 5 and circuit connector fitting seat 4 are arranged on tiltedly facing directly on mountion plate that ring-like framework 1 provides, make framework control system and framework integrated, pass through control system, driving high-speed rotor system rotates around mandrel by a fixed angular speed, thereby can continuously change the moment of momentum of high-speed rotor system, thereby externally produce the moment that varies in size, regulate and pose stabilization control in order to the spatial attitude that changes the astrovehicles such as Spacelab and space station.
Through metering and test, the trisome framework can realize that high-speed rotor system rotating coaxial degree is better than 0.012mm, and its angle of rotation measuring accuracy is better than 0.6 '.
The content that is not described in detail in the utility model specification belongs to related domain professional and technical personnel's known technology.
Claims (2)
1. a magnetic suspension control torque gyroscope trisome framework, is characterized in that: comprise ring-like framework (1), right dust cover (2) and left dust cover (3); Respectively there is the mandrel mounting hole (12) of a circle in ring-like framework (1) footpath two ends symmetrical position to the left and right; Each circular mandrel mounting hole (12) each side have one to be used for the mountion plate (11) be connected with astrovehicle; The both sides of ring-like framework (1) up and down semi-ring are plane structure, all are connected by arc-shaped structure between two planes, consist of the domain; The lightening grooves (9) that is used for weight reduction is adopted on the radially ring-like surface of ring-like framework (1), right dust cover (2) and left dust cover (3) all adopt hemisphere type metal thin-wall structure, and axially both ends of the surface are surperficial to be fixedly mounted on annular frame (1).
2. magnetic suspension control torque gyroscope according to claim 1 trisome framework, it is characterized in that: described two mandrel mounting holes (12) coaxality is not more than 0.012mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220749870 CN203010161U (en) | 2012-12-26 | 2012-12-26 | Three-body frame for magnetically suspended control moment gyro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220749870 CN203010161U (en) | 2012-12-26 | 2012-12-26 | Three-body frame for magnetically suspended control moment gyro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203010161U true CN203010161U (en) | 2013-06-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220749870 Expired - Lifetime CN203010161U (en) | 2012-12-26 | 2012-12-26 | Three-body frame for magnetically suspended control moment gyro |
Country Status (1)
| Country | Link |
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| CN (1) | CN203010161U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103471576A (en) * | 2013-09-24 | 2013-12-25 | 北京控制工程研究所 | Frame drive power supply integrated component |
| CN106123882A (en) * | 2016-06-22 | 2016-11-16 | 陕西宝成航空仪表有限责任公司 | Monoblock type gyro thin walled framed structure for torpedo |
| CN107131880A (en) * | 2017-05-10 | 2017-09-05 | 北京航天控制仪器研究所 | A kind of inertially stabilized platform Combined spherical framework |
| CN110542432A (en) * | 2019-08-13 | 2019-12-06 | 中国航空工业集团公司西安飞行自动控制研究所 | Single-shaft frame for split design and assembly and manufacturing method thereof |
-
2012
- 2012-12-26 CN CN 201220749870 patent/CN203010161U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103471576A (en) * | 2013-09-24 | 2013-12-25 | 北京控制工程研究所 | Frame drive power supply integrated component |
| CN103471576B (en) * | 2013-09-24 | 2015-10-21 | 北京控制工程研究所 | A kind of framework drives power supply integral component |
| CN106123882A (en) * | 2016-06-22 | 2016-11-16 | 陕西宝成航空仪表有限责任公司 | Monoblock type gyro thin walled framed structure for torpedo |
| CN106123882B (en) * | 2016-06-22 | 2019-01-22 | 陕西宝成航空仪表有限责任公司 | Monoblock type gyro thin walled framed structure for torpedo |
| CN107131880A (en) * | 2017-05-10 | 2017-09-05 | 北京航天控制仪器研究所 | A kind of inertially stabilized platform Combined spherical framework |
| CN107131880B (en) * | 2017-05-10 | 2020-04-10 | 北京航天控制仪器研究所 | Combined spherical frame of inertially stabilized platform |
| CN110542432A (en) * | 2019-08-13 | 2019-12-06 | 中国航空工业集团公司西安飞行自动控制研究所 | Single-shaft frame for split design and assembly and manufacturing method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20161118 Address after: 100000, No. 3, North Road, Yongfeng industrial base, Beijing, Haidian District Patentee after: Aerospace Times Electronic Technology Co.,Ltd. Address before: 100854 Yongding Road, Beijing, No. 50, No. Patentee before: BEIJING XING HUA MACHINERY FACTORY |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20190307 Address after: Room 205, 2nd floor, 6th building, 8th courtyard, Haixin Road, Daxing District, Beijing 102600 Patentee after: Beijing Aerospace Xinghua Technology Co.,Ltd. Address before: No. 3 Yongjie North Road, Yongfeng Industrial Base, Haidian District, Beijing 100000 Patentee before: Aerospace Times Electronic Technology Co.,Ltd. |
|
| TR01 | Transfer of patent right | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130619 |
|
| CX01 | Expiry of patent term |