CN202541847U - Control moment gyroscope substructure for minisatellite - Google Patents
Control moment gyroscope substructure for minisatellite Download PDFInfo
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- CN202541847U CN202541847U CN2012201178493U CN201220117849U CN202541847U CN 202541847 U CN202541847 U CN 202541847U CN 2012201178493 U CN2012201178493 U CN 2012201178493U CN 201220117849 U CN201220117849 U CN 201220117849U CN 202541847 U CN202541847 U CN 202541847U
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- control moment
- attachment face
- moment gyroscope
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- particle
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Abstract
The utility model relates to a control moment gyroscope substructure for a minisatellite. The control moment gyroscope substructure is formed by means of combination of integral casting and finish machining and mainly consists of seven characteristic faces, a first supporting face and a second supporting face are control moment gyroscope mounting faces provided by the substructure, namely a first mounting face and a first mounting face provides longitudinal support, a bottom mounting face is a substructure and satellite structure mounting face, a third mounting face is another control moment gyroscope mounting face provided by the substructure, and a connecting face is mainly used for connecting the first supporting face and the second supporting face to improve the integral structural rigidity. The control moment gyroscope substructure for the minisatellite is high in rigidity, small in size and light in weight, a real force transmission path of the substructure can be better met by means of combination of casting and fine machining, reliability and safety of the substructure in harsh mechanical environments such as rocket launching are improved, and control moment gyroscope ontrack function implementation is well guaranteed.
Description
Technical field
The utility model relates to small satellite control moment gyroscope aggregated(particle) structure, belongs to the satellite remote sensing technology field.
Background technology
The quick motor-driven small satellite of fine resolution has become one of important development direction of satellite remote sensing system.At present, most of in the world high-resolution imaging earth observation small satellites all are this type of satellites with quick attitude maneuver ability.The quick satellite imagery pattern of fine resolution has determined platform that the attitude dynamics characteristic of rapid posture maneuverability and fast and stable on a large scale must be able to be provided.Motor-driven in order to realize rapid posture, except selecting small-sized on-board equipment, adopt compact configuration topological design and whole star design optimization, to reduce outside the whole star rotor inertia as far as possible, also must consider to adopt the attitude control executive component of big moment output.At present, from the function unit product, momentum wheel maximum output torque 0.1Nm～0.5Nm commonly used; Can not satisfy the motor-driven requirement of rapid posture, therefore, the function unit that needs selection to have bigger output torque; Control moment gyroscope has big moment fan-out capability; In order to adapt to the motor-driven requirement of satellite rapid posture, the control moment gyroscope system adopts the pyramid configuration, type angle 36 degree.
According to the demand of satellite platform, need control moment gyroscope be installed on the satellite main structure through aggregated(particle) structure, this also is that this type of aggregated(particle) structure uses on small satellite for the first time.
The utility model content
The purpose of the utility model is to overcome the above-mentioned deficiency of prior art; Small satellite control moment gyroscope aggregated(particle) structure is provided; This small satellite control moment gyroscope aggregated(particle) structure rigidity is big, volume is little, in light weight; Improved reliability, the safety of aggregated(particle) structure under harsh mechanical environments such as rocket launching, for control moment gyroscope provides good guarantee in the realization of rail function.
The above-mentioned purpose of the utility model mainly is achieved through following technical scheme:
Small satellite control moment gyroscope aggregated(particle) structure; Obtain through integrated casting by first bearing surface, second bearing surface, first attachment face, second attachment face, the 3rd attachment face, joint face and installation bottom surface; Wherein first bearing surface and second bearing surface are symmetricly set on and install on the bottom surface; And be connected with second attachment face, first attachment face respectively, and be that second attachment face, first attachment face provide longitudinal ligament, the 3rd attachment face install on the bottom surface, between first bearing surface and second bearing surface; Joint face connects first bearing surface and second bearing surface; To improve integrally-built rigidity, first attachment face, second attachment face and the 3rd attachment face are used for the installation and control moment gyro, the bottom surface is installed is used for being connected with satellite.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, first attachment face, second attachment face and the 3rd attachment face are provided with the dowel hole that is used for the installation and control moment gyro and are connected screw; Around being installed, the bottom surface is provided with the connecting bore that is used to connect the satellite main structure.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, first attachment face, second attachment face and the angle of installing between the bottom surface are 10～50 °.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, the thickness that the bottom surface is installed is 5mm～8mm.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, the thickness of first attachment face, second attachment face is 10mm～20mm.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, the thickness of the 3rd attachment face is 5mm～20mm.
In above-mentioned small satellite control moment gyroscope aggregated(particle) structure, all have lightening hole on first bearing surface and second bearing surface to alleviate the aggregated(particle) structure quality.
The utility model advantage compared with prior art is:
(1) the utility model is according to the demand of satellite platform and the installation requirement of control moment gyroscope; Designed the novel aggregated(particle) structure of installation and control moment gyro; This aggregated(particle) structure comprises the installation bottom surface of three control moment gyroscope attachment faces and and satellite, and two bearing surfaces and a joint face, and above-mentioned six faces are through structure design cleverly; Realized reliable installation, and this aggregated(particle) structure has, and rigidity is big, volume is little, lightweight characteristics to control moment gyroscope and satellite;
(2) the utility model aggregated(particle) structure adopts inblock cast to combine the form of machine up; Meet the real Path of Force Transfer of aggregated(particle) structure more; Can the aggregated(particle) structure fundamental frequency be brought up to 229Hz; Improved reliability, the safety of aggregated(particle) structure under harsh mechanical environments such as rocket launching, for control moment gyroscope provides good guarantee in the realization of rail function;
(3) design of the utility model aggregated(particle) structure fully combines small satellite installing space and general assembly operability, and the space resource is less on the shared star, can adapt to the developing direction of small satellite compactness, practicality better;
(4) the utility model has carried out optimal design through a large amount of tests to the angle and the thickness of each attachment face of aggregated(particle) structure, and aluminium alloy ZL114A material has simultaneously further improved the reliability and stability of aggregated(particle) structure.
Description of drawings
Fig. 1 is the utility model small satellite control moment gyroscope aggregated(particle) structure profile scheme drawing 1;
Fig. 2 is the utility model small satellite control moment gyroscope aggregated(particle) structure profile scheme drawing 2;
Fig. 3 is the utility model small satellite control moment gyroscope and its aggregated(particle) structure scheme of installation;
Fig. 4 is the fit level random vibration test condition scheme drawing of identifying of the utility model small satellite control moment gyroscope and next structural group;
When being the utility model small satellite control moment gyroscope and its aggregated(particle) structure installation test, Fig. 5 is concerned about the measuring point scheme drawing.
The specific embodiment
Below in conjunction with accompanying drawing and specific embodiment the utility model is described in further detail:
The utility model small satellite control moment gyroscope aggregated(particle) structure has adopted the finite element topological optimization technology under the condition of design space that limits and load, to analyze and has obtained the main Path of Force Transfer in the aggregated(particle) structure design space.According to main Path of Force Transfer direction, consider that simultaneously the processing mode of support, quality carry out rational Design on Plane.
Like Fig. 1, the profile scheme drawing that is respectively the utility model small satellite control moment gyroscope aggregated(particle) structure different angles shown in Figure 2; Can know that by figure this novel small satellite control moment gyroscope aggregated(particle) structure adds fine limit work combination processing and manufacturing for aluminum alloy ZL114A casting; Mainly contain 7 characteristic faces and form, first bearing surface 1, second bearing surface 4, first attachment face 5, second attachment face 7, the 3rd attachment face 3, joint face 6 and bottom surface 2 is installed accomplishes through integral casting and fine limit work combination.In order to adapt to the installation requirement of control moment gyroscope; 3 attachment faces are provided, and 2 attachment faces of the control moment gyroscope that aggregated(particle) structure end face (first attachment face 5, second attachment face 7) provides for aggregated(particle) structure respectively provide the installation screw of 1 dowel hole and 4 M6; Another attachment face of control moment gyroscope that front (the 3rd attachment face 3) provides for aggregated(particle) structure; Installing on the bottom surface 2, between first bearing surface 1 and second bearing surface 4,1 dowel hole be provided, the installation screw of 6 M6; It is that aggregated(particle) structure and satellite structure are installed the bottom surface that bottom surface 2 is installed, and the 3rd attachment face 3 is 36 ° with the angle that bottom surface 2 is installed in the present embodiment
Aggregated(particle) structure left and right sides face (first bearing surface 1, second bearing surface 4) is symmetricly set on to be installed on the bottom surface 2; First bearing surface 1 connects second attachment face 7; Second bearing surface 4 connects first attachment face, 5, the first bearing surfaces 1 and second bearing surface 4 is respectively second attachment face 7 and first attachment face 5 provides longitudinal ligament.Respectively have 2 lightening holes to alleviate the aggregated(particle) structure quality on first bearing surface 1 and second bearing surface 4, as shown in Figure 2, first bearing surface 1 and second bearing surface 4 that the aggregated(particle) structure back side (joint face 6) is mainly aggregated(particle) structure provide interconnect function, improve integrally-built rigidity.
The control moment gyroscope attachment face that aggregated(particle) structure provides is provided with the dowel hole that is used for the installation and control moment gyro and is connected screw, is provided with the connecting bore that is used to be connected the satellite main structure around aggregated(particle) structure and the satellite structure attachment face.
Be illustrated in figure 3 as the utility model small satellite control moment gyroscope and its aggregated(particle) structure scheme of installation; Elder generation alignd 3 attachment faces of control moment gyroscope 12 when assembling connected with 3 attachment faces that aggregated(particle) structure provides; Be positioned at 8 M6 screws of end face (first attachment face 5, second attachment face 7) then earlier, and then 6 M6 screws of front (the 3rd attachment face 3) are installed.This mounting means, control moment gyroscope 12 base side muscle and lower flange upper surface have just been located fully.11 Φ 6.5mm mounting holes that at last control moment gyroscope 12 and aggregated(particle) structure 11 assemblies thereof provided through bottom (bottom surface 2 is installed) adopt 11 M6 screws and satellite structure firm and hard showing to be connected.
Convenient for the installation and control moment gyro, aggregated(particle) structure and satellite structure are installed the zone of the control moment gyroscope attachment face (the 3rd attachment face 3) that bottom surface (installation bottom surface 2) provides near aggregated(particle) structure and made the comformability structure design, the operational space of tension indicating wrench is provided.
The thickness of aggregated(particle) structure and satellite structure installation bottom surface (bottom surface 2 is installed) is 8mm in the present embodiment; The control moment gyroscope attachment face that aggregated(particle) structure provides (first attachment face 5, second attachment face 7) thickness is that 20mm inlays steel-wire screw-socket, and the control moment gyroscope attachment face that aggregated(particle) structure provides (the 3rd attachment face 3) thickness is that 14mm inlays steel-wire screw-socket.
The control moment gyroscope that this aggregated(particle) structure need carry is a cylinder mechanism, and quality is 17kg, and the aggregated(particle) structure quality is 2.7kg, and California bearing ratio is 5: 1.Height of center of mass after control moment gyroscope is installed is 278mm.The vibration that causes during rocket launching passes to aggregated(particle) structure through the connecting bore with the satellite structure plate, and passes to the control moment gyroscope body through the mounting hole with control moment gyroscope.
The utility model aggregated(particle) structure initial scheme design mock-up has been carried out the finite element topology optimization design; The main Path of Force Transfer that can obtain this time mechanism mainly concentrates on the attachment face of control moment gyroscope, and middle material improves contribution not quite to the fundamental frequency of whole mechanism.
Adopt finite element technique that newly-designed aggregated(particle) structure is analyzed; Control moment gyroscope and aggregated(particle) structure fabricate block integral body thereof are under the maximum quasi-static loads effect about about 40g; Maximum Von Mises stress is 103MPa; And the yield strength of aluminum alloy ZL114A is 407.1MPa, and margin of safety is about 3.
The control moment gyroscope body as quality point, when not considering that promptly control moment gyroscope body rigidity is considered, the support fundamental frequency is 229Hz, shows that aggregated(particle) structure itself has rigidity preferably.When considering control moment gyroscope body motion frequency characteristic, when soon control moment gyroscope body and aggregated(particle) structure were considered as fabricate block, the fabricate block fundamental frequency was 113Hz, can in each environment of satellite, not produce the dynam coupling.
Control moment gyroscope body and aggregated(particle) structure fabricate block have also carried out identifying the level sine vibration test and have identified the level random vibration test; Test frequency range from 10Hz to 2000Hz, each direction time length 120s, test condition is as shown in Figure 4; The concern measuring point is as shown in Figure 5; High speed rotor normal direction (directions X) in the vibration test is the principal modi of vibration direction, and the A01X formant appears at 112Hz, responds to be 20g
2/ Hz; The A01Y formant appears at 138Hz, responds to be 10g
2/ Hz; The A01Z formant appears at 148Hz, responds to be 8.7g
2/ Hz.The basically identical as a result of analyzing, testing, whole fabricate block dynamics is good, shows this reasonable in design.
The content of not doing to describe in detail in the utility model specification sheets belongs to those skilled in the art's known technology.
Claims (7)
1. small satellite control moment gyroscope aggregated(particle) structure; It is characterized in that: obtain through integrated casting by first bearing surface (1), second bearing surface (4), first attachment face (5), second attachment face (7), the 3rd attachment face (3), joint face (6) and installation bottom surface (2); Wherein first bearing surface (1) is symmetricly set on second bearing surface (4) and installs on the bottom surface (2); And be connected with second attachment face (7), first attachment face (5) respectively; And be that second attachment face (7), first attachment face (5) provide longitudinal ligament; The 3rd attachment face (3) be positioned at install on the bottom surface (2), between first bearing surface (1) and second bearing surface (4), joint face (6) connects first bearing surface (1) and second bearing surface (4), to improve integrally-built rigidity; First attachment face (5), second attachment face (7) are used for the installation and control moment gyro with the 3rd attachment face (3), bottom surface (2) is installed is used for being connected with satellite.
2. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: said first attachment face (5), second attachment face (7) and the 3rd attachment face (3) are provided with the dowel hole that is used for the installation and control moment gyro and are connected screw; Bottom surface (2) is installed is provided with the connecting bore that is used to connect the satellite main structure all around.
3. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: said first attachment face (5), second attachment face (7) and the angle of installing between the bottom surface (2) are 10～50 °.
4. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: the thickness of said installation bottom surface (2) is 5mm～8mm.
5. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: the thickness of said first attachment face (5), second attachment face (7) is 10mm～20mm.
6. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: the thickness of said the 3rd attachment face (3) is 5mm～20mm.
7. small satellite control moment gyroscope aggregated(particle) structure according to claim 1 is characterized in that: all have lightening hole to alleviate the aggregated(particle) structure quality on said first bearing surface (1) and second bearing surface (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012201178493U CN202541847U (en) | 2012-03-26 | 2012-03-26 | Control moment gyroscope substructure for minisatellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012201178493U CN202541847U (en) | 2012-03-26 | 2012-03-26 | Control moment gyroscope substructure for minisatellite |
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| Publication Number | Publication Date |
|---|---|
| CN202541847U true CN202541847U (en) | 2012-11-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012201178493U Expired - Lifetime CN202541847U (en) | 2012-03-26 | 2012-03-26 | Control moment gyroscope substructure for minisatellite |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
-
2012
- 2012-03-26 CN CN2012201178493U patent/CN202541847U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107380487A (en) * | 2017-06-06 | 2017-11-24 | 上海卫星工程研究所 | Integration side turns round satellite and the rocket connection ring |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121121 |
|
| CX01 | Expiry of patent term |