CA1145802A - Lightened pivoting stator and rotor device - Google Patents
Lightened pivoting stator and rotor deviceInfo
- Publication number
- CA1145802A CA1145802A CA000357215A CA357215A CA1145802A CA 1145802 A CA1145802 A CA 1145802A CA 000357215 A CA000357215 A CA 000357215A CA 357215 A CA357215 A CA 357215A CA 1145802 A CA1145802 A CA 1145802A
- Authority
- CA
- Canada
- Prior art keywords
- rotor
- stator
- crowns
- magnetic
- lightened
- 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.)
- Expired
Links
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C39/00—Relieving load on bearings
- F16C39/06—Relieving load on bearings using magnetic means
- F16C39/063—Permanent magnets
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C2326/00—Articles relating to transporting
- F16C2326/47—Cosmonautic vehicles, i.e. bearings adapted for use in outer-space
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Magnetic Bearings And Hydrostatic Bearings (AREA)
- Reciprocating, Oscillating Or Vibrating Motors (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Photovoltaic Devices (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Grinding Of Cylindrical And Plane Surfaces (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE :
A stator and rotor lightened pivoting device for satellite.
It comprises two passive magnetic suspension means, each of which consists of a radially magnetized crown fastened to the rotor and of a radially magnetized crown fastened to the stator. These suspension means generate axial magnetic fields producing two contrary forces. A third means of the pivot-stop type is used so that the resulting force between said contrary forces is itself balanced by reaction of said pivot upon said stop. A pivoting means for the rotor comprises a motor responsive to the angular positioning of said rotor. The invention is particularly adapted to masts serving as connecting supports for orientable solar panels producing energy on board of a satellite.
A stator and rotor lightened pivoting device for satellite.
It comprises two passive magnetic suspension means, each of which consists of a radially magnetized crown fastened to the rotor and of a radially magnetized crown fastened to the stator. These suspension means generate axial magnetic fields producing two contrary forces. A third means of the pivot-stop type is used so that the resulting force between said contrary forces is itself balanced by reaction of said pivot upon said stop. A pivoting means for the rotor comprises a motor responsive to the angular positioning of said rotor. The invention is particularly adapted to masts serving as connecting supports for orientable solar panels producing energy on board of a satellite.
Description
~- ~14S802 1 The present invention is directed to pivoting devices for satellites, and more particularly, relates to masts serving as connecting supports for orientable solar panels producing electric energy on board.
The problem raised by the connection of such panels may receive a solution by readapting the technologies already developed and explained, in particular, in the Applicant's U.S. patent 3,955~858 of ~ay 11, 1976, entitled: "Satellite Momentum Wheel n .
; 10 As is known from this patent, a satellite momentum wheel with rotor and ætator may be provided with two passive radial centering magnetic means situated at opposite ends of the shaft of the rotor comprising as: deslred axially or radially magnetized crowns in the latter case, each means comprises, distributed between the rotor and the stator with opposite directions of ma.~net~zation, four magnetic crowns, arranged between pairs of concentric, toroidal rings of ferromagnetic material, fitted for generating two axial forces of equal values in opposite directions~ It results from this, for each means, a resultant axial force with a substantially nil value~
whereas axial magnetic fields in the gaps through said rings procure the required radial stiffness between said rotor and said statar~
~ ccording to such arrangement of said rad~al passive magnetic sus~e~sion means, in order to satisfy to EARNSHA~'s theorem there is provided a complementary third means of active suspension with electromagnetic axial center~ng means to be disposed between rot~r and stator, w~th the servo-control there~
of being effected from speed and position sensors for holdin~
the rotor in a constant given axial positiQn wit~ respect to the stator.
il~ i ~
` - ~145802 1 The necessity of reducing to the bare minimum the masses of the servo-equipments aboard satellites now being dev-eloped to the advantage of exploitation equipment, in particular electronic has brought the Applicant to face the suppression of some of said servo-equipments for which equivalent means could be substituted.
Thus, considering the occasional nature of the`operation of the auxiliary bearing device provided for protecting if need be movable parts in respect of stationary parts and since the available elements are driven into a slow rotation, the Applicant proposes according to the present invention to use permanently said bearing device which previously was provided às an auxiliary means, however with axial relief thereof by proper passive magnetic means in such a way that the above mentioned actiYe axial magnetic suspension means with its respective serYo-con-trol becomes totally useless so that it can be dispensed with.
To this end, in order to take into account technological requirements imposed by magnetic phenomena conditioning radial stiffness of the magnetic bearings used, there is preferably incorporated, in accordance with the present invention, the bearing means with pivot and stop disclosed in the above mentioned U.S. patent 3.955.858.
In this way and in view of the utilization of the pivot stop system previously suggested, it becomes possible to intro-duce a method o~ driving the rotor by means of a wheel-endless screw device of the magnetic type already described in the Applicant's French patents No 2.199.838 of April 12, 1974 and No 2.364.381 of April 6, 1978 entitled "Speed Reductor With Magnetic Gearing".
~ ' 1 The present invention will be better understood in the following detailed description of the means used for achieving the best realization of the invention, to be read with reference to the accompanying drawing showing in an axial cross-section an exemplifying form of embodiment of a supporting mast for solar panels.
It must first be noted that the above mentioned U.S.
Patent 3,955,858 concerns a supporting device for orientable solar panels comprising an axial suspension means having a servo-control by means of which the rotor is permanently held in a medium axial position with respect to the stator.
In other words, in said supporting device the rotor is constantly held axially to the zero position of the forces from the drawback electro-magnets, i.e. any axial deviation in either direction immediately produces a servo-control signal acting upon the respective electro-magnet so as to càncel the sensed devia-tion.
Such an arrangement has the advantage of totally elim-inating frictions, since moreover the radial suspension is per-manently ensured by passive magnetic centring crowns, i.e. of thetype which does not require a power supply. The drawback of such arrangement results from significant masses represented by magnets and electro-magnets on the one hand, and on the other hand, the servo-control speed sensor, so that the Applicant decided to have recourse to the auxiliary axial bearing device furnished i.n re-dundance to the above mentioned servo-control electro-magnetic system and therefore to suppress the latter.
In the attached drawing the passive radial centring crowns are disposed in a pair at the end of shaft 1 carrying solar panel 2, ~1~580Z
on the one hand, and on the other hand, at the end of body 3 secured to the body of the satellite 5 through an intermediary element 6.
Each pair of magnetized crowns consists of two tori 7,8 and 9,10 of a very high magnetic energy material such as for instance cobalt samarium and said tori which are radially magnetized in reverse directions are enclosed between properly machined rings 11,12;13,14 and 15,16;17,18 made of a ferro-magnetic material.
Thus, the magnetic fields close through both of the magnetic tori each consisting of both tori of magnetic material and the four ferro-magnetic rings, such that gaps el and e2 are substantially equal bet-ween the stationary and movable parts.
Such a system has an unstable balanced position correspon-ding to equal gaps for equivalent magnetic crowns.
An initial offsetting of the rotor from such balanced position produces a force in a well determined direction.
Said force is used for causing the rotor to bear against a stop.
As explained hereinabove, in accordance with the drawing the axial forces applied to the rotor lead to the expression: F1> F2 and the resulting force: F=F1-F2 is cancelled by reaction of part 1' of axis 1 against the pivoting stop 19 having a very small torque.
It will be understood that the magnetic means that can be used to produce F1~ F2 may be of any nature and include in particular on the F1 side either several pairs of crowns or larger magnetic dimen-sioning of F1 as compared to F2 possibly with incorporation of magneticadjustment therein.
11~S80Z
1 Thus, the forece F=Fl-F2 can be adjusted to any suitable value which may be as low as required.
Preferably but not exclusively, pivoting occurs from spatially qualified materials by means of a steel pivot against a doped polyimide stop such as suggested by the Applicant in his above mentioned U.$. Patent No. 3,955,858.
Normally, the magnetic crowns are dimensioned to ensure sufficient radial stiffness to hold the rotor in respect to the stator.
However, radial stiffness being limited by the utiliza-tion of magnetic means, the electric connection means from the solar panel to the body of the satellite and the rotational drive of the panel were provided in theprior solution in the form of a flexible coiled cable and a motor of the coaxial type so as to minimize extraneous stresses on the rotor.
In the solution proposed according to the present inven-tion, since a mechanical stop is used the resulting increased radial stiffness can be taken advantage of to drive into rotation the rotor by means of a wheel-endless screw system of the magnetic type such as suggested in the previously mentioned French patent No. 2,364,381 on the one hand, and on the other hand, to make current flow through sliding devices also described in the earlier Prench Patent No. 2,l99,838.
Therefore, the input current cables 20 and 21 are con-nected to said sliding contact devices ~denoted 22 and 23 but not shown on the drawing~, and motor 24 driving the magnetic endless screw 25 causes rotation of the wheel 26 secured to the shaft of rotor l. ~he electric connection means may also consist of a cable coil.
A suitably designed servo-control system moreover causes 114~ii80Z
1 the panel to take its correct angular position by varying input current 27 to the motor 24.
Furthermore, the temporary immobilization of the rotor in respect to the stator requires the incorporation of a locking device denoted 28 as a whole.
It can be noted generally that this invention proposes a lightened pivoting stator and rotor device for satellite which can be applied preferably to solar panels, but can also serve any other purpose such as, for instance, the orientation of antennas.
The relief of weight so obtained, which results from suppression of the servo-controlled ax~al suspension system cor-relatively causes increased reliability by eliminating potential failures in the servo-control.
Finally, the application force of the pivot on the stop can be set to any suitable value by adjusting the position of the stop, possibly servo-controlled to compensate for the wear thereof.
~ To this end, any known mechanical means permitting to ensure positive positioning of the stop can be applied thereto.
It will be understood that the present invention was only described with reference to a preferential e~emplifying form of embodiment and that various other changes and modifications may be made without departing from its spirit and scope as defined in the appended claims.
Thus, it is also possible to arrange the whole of the pair(s) of crowns or any magnetically equivalent device at the end of the shaft facing away from the pivot.
- _~_
The problem raised by the connection of such panels may receive a solution by readapting the technologies already developed and explained, in particular, in the Applicant's U.S. patent 3,955~858 of ~ay 11, 1976, entitled: "Satellite Momentum Wheel n .
; 10 As is known from this patent, a satellite momentum wheel with rotor and ætator may be provided with two passive radial centering magnetic means situated at opposite ends of the shaft of the rotor comprising as: deslred axially or radially magnetized crowns in the latter case, each means comprises, distributed between the rotor and the stator with opposite directions of ma.~net~zation, four magnetic crowns, arranged between pairs of concentric, toroidal rings of ferromagnetic material, fitted for generating two axial forces of equal values in opposite directions~ It results from this, for each means, a resultant axial force with a substantially nil value~
whereas axial magnetic fields in the gaps through said rings procure the required radial stiffness between said rotor and said statar~
~ ccording to such arrangement of said rad~al passive magnetic sus~e~sion means, in order to satisfy to EARNSHA~'s theorem there is provided a complementary third means of active suspension with electromagnetic axial center~ng means to be disposed between rot~r and stator, w~th the servo-control there~
of being effected from speed and position sensors for holdin~
the rotor in a constant given axial positiQn wit~ respect to the stator.
il~ i ~
` - ~145802 1 The necessity of reducing to the bare minimum the masses of the servo-equipments aboard satellites now being dev-eloped to the advantage of exploitation equipment, in particular electronic has brought the Applicant to face the suppression of some of said servo-equipments for which equivalent means could be substituted.
Thus, considering the occasional nature of the`operation of the auxiliary bearing device provided for protecting if need be movable parts in respect of stationary parts and since the available elements are driven into a slow rotation, the Applicant proposes according to the present invention to use permanently said bearing device which previously was provided às an auxiliary means, however with axial relief thereof by proper passive magnetic means in such a way that the above mentioned actiYe axial magnetic suspension means with its respective serYo-con-trol becomes totally useless so that it can be dispensed with.
To this end, in order to take into account technological requirements imposed by magnetic phenomena conditioning radial stiffness of the magnetic bearings used, there is preferably incorporated, in accordance with the present invention, the bearing means with pivot and stop disclosed in the above mentioned U.S. patent 3.955.858.
In this way and in view of the utilization of the pivot stop system previously suggested, it becomes possible to intro-duce a method o~ driving the rotor by means of a wheel-endless screw device of the magnetic type already described in the Applicant's French patents No 2.199.838 of April 12, 1974 and No 2.364.381 of April 6, 1978 entitled "Speed Reductor With Magnetic Gearing".
~ ' 1 The present invention will be better understood in the following detailed description of the means used for achieving the best realization of the invention, to be read with reference to the accompanying drawing showing in an axial cross-section an exemplifying form of embodiment of a supporting mast for solar panels.
It must first be noted that the above mentioned U.S.
Patent 3,955,858 concerns a supporting device for orientable solar panels comprising an axial suspension means having a servo-control by means of which the rotor is permanently held in a medium axial position with respect to the stator.
In other words, in said supporting device the rotor is constantly held axially to the zero position of the forces from the drawback electro-magnets, i.e. any axial deviation in either direction immediately produces a servo-control signal acting upon the respective electro-magnet so as to càncel the sensed devia-tion.
Such an arrangement has the advantage of totally elim-inating frictions, since moreover the radial suspension is per-manently ensured by passive magnetic centring crowns, i.e. of thetype which does not require a power supply. The drawback of such arrangement results from significant masses represented by magnets and electro-magnets on the one hand, and on the other hand, the servo-control speed sensor, so that the Applicant decided to have recourse to the auxiliary axial bearing device furnished i.n re-dundance to the above mentioned servo-control electro-magnetic system and therefore to suppress the latter.
In the attached drawing the passive radial centring crowns are disposed in a pair at the end of shaft 1 carrying solar panel 2, ~1~580Z
on the one hand, and on the other hand, at the end of body 3 secured to the body of the satellite 5 through an intermediary element 6.
Each pair of magnetized crowns consists of two tori 7,8 and 9,10 of a very high magnetic energy material such as for instance cobalt samarium and said tori which are radially magnetized in reverse directions are enclosed between properly machined rings 11,12;13,14 and 15,16;17,18 made of a ferro-magnetic material.
Thus, the magnetic fields close through both of the magnetic tori each consisting of both tori of magnetic material and the four ferro-magnetic rings, such that gaps el and e2 are substantially equal bet-ween the stationary and movable parts.
Such a system has an unstable balanced position correspon-ding to equal gaps for equivalent magnetic crowns.
An initial offsetting of the rotor from such balanced position produces a force in a well determined direction.
Said force is used for causing the rotor to bear against a stop.
As explained hereinabove, in accordance with the drawing the axial forces applied to the rotor lead to the expression: F1> F2 and the resulting force: F=F1-F2 is cancelled by reaction of part 1' of axis 1 against the pivoting stop 19 having a very small torque.
It will be understood that the magnetic means that can be used to produce F1~ F2 may be of any nature and include in particular on the F1 side either several pairs of crowns or larger magnetic dimen-sioning of F1 as compared to F2 possibly with incorporation of magneticadjustment therein.
11~S80Z
1 Thus, the forece F=Fl-F2 can be adjusted to any suitable value which may be as low as required.
Preferably but not exclusively, pivoting occurs from spatially qualified materials by means of a steel pivot against a doped polyimide stop such as suggested by the Applicant in his above mentioned U.$. Patent No. 3,955,858.
Normally, the magnetic crowns are dimensioned to ensure sufficient radial stiffness to hold the rotor in respect to the stator.
However, radial stiffness being limited by the utiliza-tion of magnetic means, the electric connection means from the solar panel to the body of the satellite and the rotational drive of the panel were provided in theprior solution in the form of a flexible coiled cable and a motor of the coaxial type so as to minimize extraneous stresses on the rotor.
In the solution proposed according to the present inven-tion, since a mechanical stop is used the resulting increased radial stiffness can be taken advantage of to drive into rotation the rotor by means of a wheel-endless screw system of the magnetic type such as suggested in the previously mentioned French patent No. 2,364,381 on the one hand, and on the other hand, to make current flow through sliding devices also described in the earlier Prench Patent No. 2,l99,838.
Therefore, the input current cables 20 and 21 are con-nected to said sliding contact devices ~denoted 22 and 23 but not shown on the drawing~, and motor 24 driving the magnetic endless screw 25 causes rotation of the wheel 26 secured to the shaft of rotor l. ~he electric connection means may also consist of a cable coil.
A suitably designed servo-control system moreover causes 114~ii80Z
1 the panel to take its correct angular position by varying input current 27 to the motor 24.
Furthermore, the temporary immobilization of the rotor in respect to the stator requires the incorporation of a locking device denoted 28 as a whole.
It can be noted generally that this invention proposes a lightened pivoting stator and rotor device for satellite which can be applied preferably to solar panels, but can also serve any other purpose such as, for instance, the orientation of antennas.
The relief of weight so obtained, which results from suppression of the servo-controlled ax~al suspension system cor-relatively causes increased reliability by eliminating potential failures in the servo-control.
Finally, the application force of the pivot on the stop can be set to any suitable value by adjusting the position of the stop, possibly servo-controlled to compensate for the wear thereof.
~ To this end, any known mechanical means permitting to ensure positive positioning of the stop can be applied thereto.
It will be understood that the present invention was only described with reference to a preferential e~emplifying form of embodiment and that various other changes and modifications may be made without departing from its spirit and scope as defined in the appended claims.
Thus, it is also possible to arrange the whole of the pair(s) of crowns or any magnetically equivalent device at the end of the shaft facing away from the pivot.
- _~_
Claims (4)
1. A stator and rotor lightened pivoting device for satellite, comprising:
-a first passive magnetic suspension means, -said first means comprising at least one pair of radially magnetized crowns surrounded by concentric ferro-magnetic rings, -one of said crowns being fastened to the rotor and the other crown being fastened to the stator, -said crowns generating an axial magnetic field through said ferro-magnetic rings, -said axial magnetic field producing a first axial force applied to the rotor on the one hand, and on the other hand, contribu-ting to the required radial stiffness between said rotor and said stator;
-a second passive magnetic suspension means, -said second means comprising at least one pair of radially magnetized crowns surrounded by concentric ferro-magnetic rings, -one of said crowns being fastened to the rotor and the other crown being fastened to the stator, -said crowns generating an axial magnetic field through said ferro-magnetic rings, -said axial magnetic field producing a second axial force applied to the rotor on the one hand, and on the other hand, contribu-ting to the required radial stiffness between said rotor and said stator;
-a third means of the pivot-stop type complementary to both said passive magnetic suspension means, -said third means being used so that the resulting force between said first force and said second force applied to the rotor is itself balanced by reaction of said pivot upon said stop;
-pivoting means for said rotor, -temporary locking device to temporarily secure said rotor to said stator, -and, connection means between said rotor and said stator to provide the electric connections.
-a first passive magnetic suspension means, -said first means comprising at least one pair of radially magnetized crowns surrounded by concentric ferro-magnetic rings, -one of said crowns being fastened to the rotor and the other crown being fastened to the stator, -said crowns generating an axial magnetic field through said ferro-magnetic rings, -said axial magnetic field producing a first axial force applied to the rotor on the one hand, and on the other hand, contribu-ting to the required radial stiffness between said rotor and said stator;
-a second passive magnetic suspension means, -said second means comprising at least one pair of radially magnetized crowns surrounded by concentric ferro-magnetic rings, -one of said crowns being fastened to the rotor and the other crown being fastened to the stator, -said crowns generating an axial magnetic field through said ferro-magnetic rings, -said axial magnetic field producing a second axial force applied to the rotor on the one hand, and on the other hand, contribu-ting to the required radial stiffness between said rotor and said stator;
-a third means of the pivot-stop type complementary to both said passive magnetic suspension means, -said third means being used so that the resulting force between said first force and said second force applied to the rotor is itself balanced by reaction of said pivot upon said stop;
-pivoting means for said rotor, -temporary locking device to temporarily secure said rotor to said stator, -and, connection means between said rotor and said stator to provide the electric connections.
2. A stator and rotor lightened pivoting device for satellite according to claim 1, wherein said pivoting means for the rotor consists of a wheel-endless magnetic screw system, the motor for driving the screw being servo-controlled responsive to the angular positioning of the rotor.
3. A stator and rotor lightened pivoting device for satellite according to claim 1, wherein the electric connection means between the rotor and stator consist of electric sliding contacts.
4. A stator and rotor lightened pivoting device for satellite according to claim 1, wherein the electric connection means between the rotor and the stator consist of a cable coil.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7920127A FR2463444A1 (en) | 1979-08-06 | 1979-08-06 | ALTERNATIVE STATOR PIVOTING DEVICE AND ROTOR FOR SATELLITE |
| FR7920.127 | 1979-08-06 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1145802A true CA1145802A (en) | 1983-05-03 |
Family
ID=9228660
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000357215A Expired CA1145802A (en) | 1979-08-06 | 1980-07-29 | Lightened pivoting stator and rotor device |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0023875B1 (en) |
| JP (1) | JPS5625100A (en) |
| AT (1) | ATE3736T1 (en) |
| CA (1) | CA1145802A (en) |
| DE (1) | DE3063680D1 (en) |
| FR (1) | FR2463444A1 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6398095U (en) * | 1986-12-16 | 1988-06-24 | ||
| KR101403195B1 (en) * | 2012-12-27 | 2014-06-02 | 주식회사 포스코 | Turbine apparatus and waste heat recovery generation system having the same |
| CN107958625B (en) * | 2018-01-26 | 2024-04-19 | 航天创客（北京）科技有限公司 | Teaching device for simulating satellite rotation |
| CN111152943B (en) * | 2020-01-13 | 2021-07-27 | 中国科学院空间应用工程与技术中心 | Fixing mechanism and spacecraft |
| CN113685444B (en) * | 2021-08-25 | 2022-06-17 | 中国航发沈阳黎明航空发动机有限责任公司 | Front bearing casing assembling method |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR467907A (en) * | 1913-04-08 | 1914-06-24 | Louis Gratzmueller | Device for returning a machine shaft, rotating at high speed |
| FR1237775A (en) * | 1959-06-18 | 1960-08-05 | Normacem Sa | Axial thrust balancing device in rotating machines |
| FR2187048A5 (en) * | 1972-05-29 | 1974-01-11 | Aerospatiale | |
| FR2294430A2 (en) * | 1974-12-10 | 1976-07-09 | Aerospatiale | Artificial moon inertia flywheel - has magnetic radial and axial centring mechanisms and damper also motor generator |
| FR2257077A1 (en) * | 1974-01-03 | 1975-08-01 | Aerospatiale | Artificial moon inertia flywheel - has magnetic radial and axial centring mechanisms and damper also motor generator |
-
1979
- 1979-08-06 FR FR7920127A patent/FR2463444A1/en active Granted
-
1980
- 1980-07-29 CA CA000357215A patent/CA1145802A/en not_active Expired
- 1980-08-04 AT AT80401152T patent/ATE3736T1/en not_active IP Right Cessation
- 1980-08-04 DE DE8080401152T patent/DE3063680D1/en not_active Expired
- 1980-08-04 EP EP80401152A patent/EP0023875B1/en not_active Expired
- 1980-08-05 JP JP10763580A patent/JPS5625100A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| FR2463444B1 (en) | 1983-02-11 |
| JPS5625100A (en) | 1981-03-10 |
| FR2463444A1 (en) | 1981-02-20 |
| EP0023875A1 (en) | 1981-02-11 |
| ATE3736T1 (en) | 1983-06-15 |
| DE3063680D1 (en) | 1983-07-14 |
| EP0023875B1 (en) | 1983-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA1127233A (en) | Inertia wheel | |
| US3976339A (en) | Magnetic suspension apparatus | |
| US3791704A (en) | Trimming apparatus for magnetic suspension systems | |
| US5291975A (en) | System and method for damping narrow band axial vibrations of a rotating device | |
| US4043614A (en) | Magnetic suspension apparatus | |
| US4090745A (en) | Magnetic suspension with magnetic stiffness augmentation | |
| JP3316257B2 (en) | Torsional moment measuring device | |
| US5625240A (en) | Magnetic bearing and mechanical thrust bearing device for positioning a body rotating relative to a stator body | |
| US4490635A (en) | Pure torque, limited displacement transducer | |
| GB1567785A (en) | Devices for damping the critical frequencies of a magneticcally suspended rotor | |
| Sabnis et al. | A magnetically suspended large momentum wheel | |
| WO1988005996A3 (en) | Triaxis stabilized platform | |
| JPS6329292A (en) | Magnetic isolation indicating gimbal device | |
| US4785212A (en) | Large angle magnetic suspension system | |
| US4983869A (en) | Magnetic bearing | |
| US4325586A (en) | Electromagnetic process for controlling orientation of a platform and platform for carrying out said process | |
| US4088018A (en) | Magnetic suspension and pointing system | |
| US5550413A (en) | Elongate torque motor and angular displacement control device incorporating it | |
| CA1145802A (en) | Lightened pivoting stator and rotor device | |
| US6834561B2 (en) | Radially actuated control moment gyroscope | |
| US5012170A (en) | Mechanical stabilization system with counter-rotating nested rotors | |
| US4268095A (en) | Magnetic bearing | |
| US3767139A (en) | Spacecraft spin stabilization system | |
| US5063336A (en) | Mechanical stabilization system using counter-rotation and a single motor | |
| US5820079A (en) | Mechanism for mounting and actuating a momentum wheel with high vibration isolation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |