CN107181339A - A kind of ball motor for aircraft master end lever system - Google Patents
A kind of ball motor for aircraft master end lever system Download PDFInfo
- Publication number
- CN107181339A CN107181339A CN201710422683.3A CN201710422683A CN107181339A CN 107181339 A CN107181339 A CN 107181339A CN 201710422683 A CN201710422683 A CN 201710422683A CN 107181339 A CN107181339 A CN 107181339A
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- Prior art keywords
- permanent magnets
- holes
- rotor
- conical
- hemisphere
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K1/00—Details of the magnetic circuit
- H02K1/06—Details of the magnetic circuit characterised by the shape, form or construction
- H02K1/22—Rotating parts of the magnetic circuit
- H02K1/27—Rotor cores with permanent magnets
- H02K1/2706—Inner rotors
- H02K1/272—Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis
- H02K1/274—Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of two or more circumferentially positioned magnets
- H02K1/2753—Inner rotors the magnetisation axis of the magnets being perpendicular to the rotor axis the rotor consisting of two or more circumferentially positioned magnets the rotor consisting of magnets or groups of magnets arranged with alternating polarity
- H02K1/276—Magnets embedded in the magnetic core, e.g. interior permanent magnets [IPM]
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/04—Windings characterised by the conductor shape, form or construction, e.g. with bar conductors
- H02K3/28—Layout of windings or of connections between windings
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K3/00—Details of windings
- H02K3/46—Fastening of windings on the stator or rotor structure
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Permanent Magnet Type Synchronous Machine (AREA)
Abstract
The invention discloses a kind of ball motor for aircraft master end lever system, the ball motor is connected to the left and right sides of existing aircraft handling panel (10A) and forms double ball motor steerable systems.Ball motor includes A hemisphere stator (1), B hemisphere stator (2), rotor (3), take-off lever (4), base (5), armature winding component (6), magnetic force block assembly (7) and buphthalmos bearing assembly (8).Wherein, A hemisphere stator (1) then forms a hollow ball after being docked with B hemisphere stator (2), rotor (3) is placed in hollow ball, take-off lever (4) is arranged on rotor (3) top, A hemisphere stator (1) is arranged on base (5) with B hemisphere stator (2), armature winding component (6) and buphthalmos bearing assembly (8) are arranged on A hemisphere stator (1) and on B hemisphere stator (2), magnetic force block assembly (7) is arranged in the gap of rotor (3).Double ball motor steerable systems realize the force feedback of rudder face load and the synchronization of lose-lose rod, reduce a wherein side due to the maloperation to aircraft that is lacking in experience.
Description
Technical field
The present invention relates to a kind of ball motor, more particularly, refer to a kind of ball motor for aircraft master end lever system.
Background technology
Flight By Wire (Fly-By-Wire, FBW) is a kind of handle input by airborne vehicle driver in aviation field, is led to
Cross converter and be changed into electric signal, handled through computer or electronic controller, then grasped by cable transmission to executing agency's one kind
Vertical system.It eliminates mechanical driving device and fluid pressure line in traditional steerable system.Active control technology (ACT) and fax
Flight control (FBW) system, the development of the appearance of this two new technologies to aircraft generates tremendous influence.And active side lever is
Fax side lever steerable system with active control technology.It can make the flight control, thrust control and firepower control of aircraft
Major control function is integrated and is possibly realized, so as to significantly improve the performance of aircraft.Such as use the fax of active control technology
After steerable system, relaxed static stability (RSS) control technology makes B-52 bomber horizontal tails area reduce 45%, and structure gross weight subtracts
Few 6.4%, voyage adds 4.3%；Fighter plane lift-drag ratio is set to improve 8%~15%.Maneuver load controls (NILC) technology
C-5A transporter wing roots bending moment is set to reduce 30%~50%；The F4E fighter planes angular speed that spirals is set to add 33%.Active whirlpool
Flow control (AVC) technology coordinates the yaw speed increase by 50% in use, making X29 in the big angles-of-attack of low speed with rudder.
Using task compatibility wing (MAW) than that using conventional airfoil aircraft range can be made to increase by 30%, wing bearing capacity is improved
50%.
Traditional aircraft mechanical manoeuvring system is typically all using central control stick, and fly-by-wire can then use small side
Lever operation, so can both mitigate the work load of pilot, and the sight that pilot observes instrument can again no longer driven by center
The influence of bar, while also eliminating influence of the acceleration of gravity to pilot and control stick input quantity.
The content of the invention
In order to solve in traditional fly-by-wire control stick on the one hand without rudder face feedback loading, another aspect control rod double
Between the defect that can not be synchronized with the movement, the present invention devise it is a kind of can be applied to the ball motor of aircraft master end lever system, should
Ball motor is connected to the existing aircraft handling panel 10A left and right sides and forms double ball motor steerable systems.
The present invention devises a kind of ball motor for aircraft master end lever system, it is characterised in that：The ball motor bag
A hemisphere stator (1), B hemisphere stator (2), rotor (3), take-off lever (4), base (5), armature winding component (6), magnetic force are included
Block assembly (7) and buphthalmos bearing assembly (8).Wherein, A hemisphere stator (1) is identical with the structure of B hemisphere stator (2), and A hemisphere
Stator (1) then forms a hollow ball after being docked with B hemisphere stator (2)；
Armature winding component (6) includes structure identical A armature winding (6A), B armature winding (6B), C armature winding
(6C), D armature winding (6D), E armature winding (6E), F armature winding (6F), G armature winding (6G), H armature winding (6H), I
Armature winding (6I), J armature winding (6J), K armature winding (6K) and L armature winding (6L).Every three armature winding composition one
Row.
Magnetic force block assembly (7) includes structure identical A group Halbach permanent magnet arrays (7A), B groups Halbach forever
Magnet array (7B), C group Halbach permanent magnet arrays (7C) and D group Halbach permanent magnet arrays (7D).
The A groups Halbach permanent magnet array (7A) is arc.It includes AA permanent magnets (7A1), AB permanent magnets
(7A2), AC permanent magnets (7A3), AD permanent magnets (7A4) and AE permanent magnets (7A5).A group Halbach permanent magnet arrays (7A) are pacified
Mounted in A gaps (3E) place of rotor (3).The magnetizing direction of A group Halbach permanent magnet arrays (7A) is respectively：AA permanent magnets
The magnetizing direction of (7A1) and AE permanent magnets (7A5) is the radial magnetizing for the central point O for pointing to rotor (3)；AC permanent magnets (7A3)
Magnetizing direction point to export-oriented radial magnetizing for the central point O of rotor (3)；AB permanent magnets (7A2) and AD permanent magnets (7A4)
Magnetizing direction is the cutting orientation magnetizing of vertical rotor (3) diameter, and the magnetizing direction of AB permanent magnets (7A2) and AD permanent magnets (7A4)
Conversely.
The B groups Halbach permanent magnet array (7B) is arc.It includes BA permanent magnets (7B1), BB permanent magnets
(7B2), BC permanent magnets (7B3), BD permanent magnets (7B4) and BE permanent magnets (7B5).B group Halbach permanent magnet arrays (7B) are pacified
Mounted in B gaps (3F) place of rotor (3).The magnetizing direction of B group Halbach permanent magnet arrays (7B) is respectively：BA permanent magnets
The magnetizing direction of (7B1) and BE permanent magnets (7B5) is the radial magnetizing for the central point O for pointing to rotor (3)；BC permanent magnets (7B3)
Magnetizing direction point to export-oriented radial magnetizing for the central point O of rotor (3)；BB permanent magnets (7B2) and BD permanent magnets (7B4)
Magnetizing direction is the cutting orientation magnetizing of vertical rotor (3) diameter, and the magnetizing direction of BB permanent magnets (7B2) and BD permanent magnets (7B4)
Conversely.
The C groups Halbach permanent magnet array (7C) is arc.It includes CA permanent magnets (7C1), CB permanent magnets
(7C2), CC permanent magnets (7C3), CD permanent magnets (7C4) and CE permanent magnets (7C5).C group Halbach permanent magnet arrays (7C) are pacified
Mounted in C gaps (3G) place of rotor (3).The magnetizing direction of C group Halbach permanent magnet arrays (7C) is respectively：CA permanent magnets
The magnetizing direction of (7C1) and CE permanent magnets (7C5) is the radial magnetizing for the central point O for pointing to rotor (3)；CC permanent magnets (7C3)
Magnetizing direction point to export-oriented radial magnetizing for the central point O of rotor (3)；CB permanent magnets (7C2) and CD permanent magnets (7C4)
Magnetizing direction is the cutting orientation magnetizing of vertical rotor (3) diameter, and the magnetizing direction of CB permanent magnets (7C2) and CD permanent magnets (7C4)
Conversely.
The D groups Halbach permanent magnet array (7D) is arc.It includes DA permanent magnets (7D1), DB permanent magnets
(7D2), DC permanent magnets (7D3), DD permanent magnets (7D4) and DE permanent magnets (7D5).D group Halbach permanent magnet arrays (7D) are pacified
Mounted in D gaps (3H) place of rotor (3).The magnetizing direction of D group Halbach permanent magnet arrays (7D) is respectively：DA permanent magnets
The magnetizing direction of (7D1) and DE permanent magnets (7D5) is the radial magnetizing for the central point O for pointing to rotor (3)；DC permanent magnets (7D3)
Magnetizing direction point to export-oriented radial magnetizing for the central point O of rotor (3)；DB permanent magnets (7D2) and DD permanent magnets (7D4)
Magnetizing direction is the cutting orientation magnetizing of vertical rotor (3) diameter, and the magnetizing direction of DB permanent magnets (7D2) and DD permanent magnets (7D4)
Conversely.
Buphthalmos bearing assembly (8) includes structure identical A buphthalmos bearing (8A), B buphthalmos bearing (8B), C buphthalmos bearings
(8C), D buphthalmos bearing (8D), E buphthalmos bearing (8E), F buphthalmos bearing (8F), G buphthalmos bearing (8G) and H buphthalmos bearing (8H).
The middle part of A hemisphere stator (1) is provided with AA conical through-holes (1A), AB conical through-holes (1B), AC conical through-holes (1C)；A
One end of hemisphere stator (1) is provided with AA opening conical through-holes (1D), AB opening conical through-holes (1E), AC opening conical through-holes
(1F)；The other end of A hemisphere stator (1) is provided with (AD) opening conical through-hole (1G), AE opening conical through-holes (1H), AF opening cones
Shape through hole (1I)；A hemisphere stator (1) is provided with AA through holes (1-1) and AB through holes (1-2).The bottom of A hemisphere stator (1) is provided with
The AA screwed hole (1-3) fixed for the convex round platform (5A) with base (5), EA screws (5A3) pass through the interior dome of base (5)
EA through holes (5A1) rear thread on platform (5A) is connected in the AA screwed holes (1-3) of the bottom of A hemisphere stator (1).A hemisphere is determined
The Internal Spherical Surface of sub (1), which is provided with, to be used to install the AC bearing holes (1L) of A buphthalmos bearing (8A), for installing B buphthalmos bearing (8B)
AD bearing holes (1M), the AA bearing holes (1J) for installing C buphthalmos bearing (8C), the AB for installing D buphthalmos bearing (8D)
Bearing hole (1K).
AA conical through-holes (1A) place is used to A armature winding (6A) is fixedly mounted.
AB conical through-holes (1B) place is used to B armature winding (6B) is fixedly mounted.
AC conical through-holes (1C) place is used to C armature winding (6C) is fixedly mounted.
The middle part of B hemisphere stator (2) is provided with BA conical through-holes (2A), BB conical through-holes (2B), BC conical through-holes (2C)；B
One end of hemisphere stator (2) is provided with BA opening conical through-holes (2D), BB opening conical through-holes (2E), BC opening conical through-holes
(2F)；The other end of B hemisphere stator (2) is provided with BD opening conical through-holes (2G), BE opening conical through-holes (2H), BF opening tapers
Through hole (2I)；B hemisphere stator (2) is provided with BA through holes (2-1) and BB through holes (2-2).The bottom of B hemisphere stator (2) is provided with use
In the BA screwed hole (2-3) fixed with the convex round platform (5A) of base (5), EB screws (5A4) pass through the convex round platform of base (5)
EB through holes (5A2) rear thread on (5A) is connected in the BA screwed holes (2-3) of the bottom of B hemisphere stator (2).B hemisphere stators
(2) Internal Spherical Surface, which is provided with, to be used to install the BA bearing holes (2J) of E buphthalmos bearing (8E), for installing F buphthalmos bearing (8F)
BB bearing holes (2K), the BC bearing holes (2L) for installing G buphthalmos bearing (8G), the BD axles for installing H buphthalmos bearing (8H)
Bearing bore (2M).
BA conical through-holes (2A) place is used to G armature winding (6G) is fixedly mounted.
BB conical through-holes (2B) place is used to H armature winding (6H) is fixedly mounted.
BC conical through-holes (2C) place is used to I armature winding (6I) is fixedly mounted.
AA opening conical through-holes (1D) form A conical through-holes (1-4A), the A after being docked with BA opening conical through-holes (2D)
Conical through-hole (1-4A) place is used to D armature winding (6D) is fixedly mounted.
AB opening conical through-holes (1E) form B conical through-holes (1-4B), the B after being docked with BB opening conical through-holes (2E)
Conical through-hole (1-4B) place is used to E armature winding (6E) is fixedly mounted.
AC opening conical through-holes (1F) form C conical through-holes (1-4C), the C after being docked with BC opening conical through-holes (2F)
Conical through-hole (1-4C) place is used to F armature winding (6F) is fixedly mounted.
AD opening conical through-holes (1G) form D conical through-holes (2-4A), the D after being docked with BD opening conical through-holes (2G)
Conical through-hole (2-4A) place is used to J armature winding (6J) is fixedly mounted.
AE opening conical through-holes (1H) form E conical through-holes (2-4B), the E after being docked with BE opening conical through-holes (2H)
Conical through-hole (2-4B) place is used to K armature winding (6K) is fixedly mounted.
AF opening conical through-holes (1I) form F conical through-holes (2-4C), the F after being docked with BF opening conical through-holes (2I)
Conical through-hole (2-4B) place is used to L armature winding (6L) is fixedly mounted.
The top of rotor (3) is top panel (3I), and the top panel (3I), which is provided with, to be used to fix take-off lever (4)
The CA screwed holes (3I1) of clutch disk (4B)；The bottom of rotor (3) is bottom panel (3J)；The spheroid of rotor (3) is provided with A
Flap (3A), B flaps (3B), C flaps (3C) and D flaps (3D), are A gaps (3E), B between A flaps (3A) and B flaps (3B)
It is B gaps (3F) between flap (3B) and C flaps (3C), is C gaps (3G), D flaps between C flaps (3C) and D flaps (3D)
It is D gaps (3H) between (3D) and A flaps (3A)；The centerbody (3-1) of rotor (3) is provided with A end faces (3-1A), B end faces (3-
1B), C-terminal face (3-1C), D end faces (3-1D), E end faces (3-1E), F end faces (3-1F), G end faces (3-1G), H end faces (3-1H), I
End face (3-1I), J end faces, K end faces, L end faces；Wherein, A end faces (3-1A), B end faces (3-1B) and C-terminal face (3-1C) are located between A
Gap (3E)；D end faces (3-1D), E end faces (3-1E) and F end faces (3-1F) are located at B gaps (3F)；G end faces (3-1G), H end faces (3-
1H) it is located at C gaps (3G) with I end faces (3-1I)；J end faces, K end faces and L end faces are located at D gaps (3H).
The A gaps (3E) are used to place A group Halbach permanent magnet arrays (7A), and AA permanent magnets (7A1) are arranged on
On the A end faces (3-1A) of the centerbody (3-1) of rotor (3), AC permanent magnets (7A3) are arranged on the centerbody (3-1) of rotor (3)
On B end faces (3-1B), AE permanent magnets (7A5) are arranged on the C-terminal face (3-1C) of the centerbody (3-1) of rotor (3), AB permanent magnets
(7A2) is arranged between AA permanent magnets (7A1) and AC permanent magnets (7A3), and AD permanent magnets (7A4) are arranged on AC permanent magnets (7A3)
Between AE permanent magnets (7A5).
The B gaps (3F) are used to place B group Halbach permanent magnet arrays (7B), and BA permanent magnets (7B1) are arranged on
On the D end faces (3-1D) of the centerbody (3-1) of rotor (3), BC permanent magnets (7B3) are arranged on the centerbody (3-1) of rotor (3)
On E end faces (3-1E), BE permanent magnets (7B5) are arranged on the F end faces (3-1F) of the centerbody (3-1) of rotor (3), BB permanent magnets
(7B2) is arranged between BA permanent magnets (7B1) and BC permanent magnets (7B3), and BD permanent magnets (7B4) are arranged on BC permanent magnets (7B3)
Between BE permanent magnets (7B5).
The C gaps (3G) are used to place C group Halbach permanent magnet arrays (7C), and CA permanent magnets (7C1) are arranged on
On the G end faces (3-1G) of the centerbody (3-1) of rotor (3), CC permanent magnets (7C3) are arranged on the centerbody (3-1) of rotor (3)
On H end faces (3-1H), CE permanent magnets (7C5) are arranged on the I end faces (3-1I) of the centerbody (3-1) of rotor (3), CB permanent magnets
(7C2) is arranged between CA permanent magnets (7C1) and CC permanent magnets (7C3), and CD permanent magnets (7C4) are arranged on CC permanent magnets (7C3)
Between CE permanent magnets (7C5).
The D gaps (3H) are used to place D group Halbach permanent magnet arrays (7D), and DA permanent magnets (7D1) are arranged on
On the J end faces of the centerbody (3-1) of rotor (3), DC permanent magnets (7D3) are arranged on the K end faces of the centerbody (3-1) of rotor (3)
On, DE permanent magnets (7D5) are arranged on the L end faces of the centerbody (3-1) of rotor (3), and DB permanent magnets (7D2) are arranged on DA permanent magnetism
Between body (7D1) and DC permanent magnets (7D3), DD permanent magnets (7D4) be arranged on DC permanent magnets (7D3) and DE permanent magnets (7D5) it
Between.
One end of take-off lever (4) is control stick (4A), and the other end of take-off lever (4) is clutch disk (4B)；Control stick
The hand that (4A) is used for pilot is grasped；Clutch disk (4B), which is provided with, is used for the DA through holes (4B1) that DA screws (4B2) are passed through, and wears
The DA screws (4B2) for crossing DA through holes (4B1) are fixed in the CA screwed holes (3I1) of the top panel of rotor (3) (3I).
Base (5) is provided with outer round platform (5B) and convex round platform (5A)；Convex round platform (5A) provided with EA through holes (5A1),
EB through holes (5A2), EA through holes (5A1) are passed through for EA screws (5A3), and EA screws (5A3) screw thread through EA through holes (5A1) is solid
It is scheduled in the AA screwed holes (1-3) of the bottom of A hemisphere stator (1)；EB through holes (5A2) are passed through for EB screws (5A4), through EB
The EB screws (5A4) of through hole (5A2) are threadedly secured in the BA screwed holes (2-3) of the bottom of B hemisphere stator (2)；Outer round platform
(5B) is provided with EC through holes (5B1), and the screw thread through EC through holes (5B1) is fixed on spiral shell on aircraft handling panel (10A)
In pit.
The advantage for double ball motors applied to aircraft master end lever system that the present invention is designed is：
1. rotor design makes magnetic force block and rotor sphere conformal into four interstitial structures using gap, armature around
Under group is powered, the alternating fields that magnetic force block is provided so that rotor can form the motion of two degrees of freedom.
2. the cooperation of rotor and stator is conducive to assemble, while utilizing taper into ball design after the splicing of the valve of divided stator two
The sphere that through hole installs armature winding is conformal, and the inside and outside of ball motor is concentric sphere volume structure, reaches the symmetrical of permanent magnetism and coil
Install.
3. the ball motor that 2 present invention are designed is installed using aircraft handling panel, on the one hand can realizes to aircraft lifting and landing
The force feedback of rudder face and aileron rudder face.On the other hand it can realize that the manipulation between pilot is synchronous, reduce wherein side's experience
Lack the maloperation caused.Existing fly-by-wire, without the synchronization system between control stick.
4. by manipulating the take-off lever (or claiming control stick) of side, operating aircraft lifts rudder face to realize the pitching of aircraft
Motion, manipulates the deflection of aileron rudder face to realize the rolling movement of aircraft.
Brief description of the drawings
Fig. 1 is the relative position schematic diagram of double ball motors in the lever system of aircraft master end.
Fig. 2A is the external structure of ball motor of the present invention.
Fig. 2 B are another visual angle external structures of ball motor of the present invention.
Fig. 2 C are the exploded views of ball motor of the present invention.
Fig. 2 D are another exploded views of ball motor of the present invention.
Fig. 3 A are the structure charts of rotor of the present invention.
Fig. 3 B are the cut-away views of rotor of the present invention.
Fig. 3 C are the top views of rotor of the present invention.
Fig. 3 D are the upward views of rotor of the present invention.
Fig. 3 E are rotor of the present invention and take-off lever, the installation diagram of magnetic force block assembly.
Fig. 3 F are the assembling sections of rotor of the present invention and magnetic force block assembly.
Fig. 4 is the structure chart of magnetic force block assembly of the present invention.
Fig. 5 A are the structure charts of two hemisphere stators of the invention.
Fig. 5 B are another viewing angle constructions figures of two hemisphere stators of the invention.
Fig. 5 C are the forward sight structure charts after two hemisphere stator docking of the present invention.
Fig. 5 D are the relief angle structure charts after two hemisphere stator docking of the present invention.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail.
Shown in Figure 1, a kind of double ball motors for aircraft master end lever system that the present invention is designed, are existing
The aircraft handling panel 10A left and right sides is respectively mounted two structure identical ball motors, i.e., left ball motor 10B and right ball motor
10C。
Referring to shown in Fig. 1, Fig. 2A, Fig. 2 B, Fig. 2 C, the ball motor that the present invention is designed, it includes A hemisphere stator 1, B half
Ball stator 2, rotor 3, take-off lever 4, base 5, armature winding component 6, magnetic force block assembly 7 and buphthalmos bearing assembly 8.Wherein, A half
Ball stator 1 is identical with the structure of B hemisphere stator 2；A hemisphere stator 1 then forms a hollow ball after being docked with B hemisphere stator 2,
It is described hollow interior for placing rotor 3.Take-off lever 4 is arranged on the top of rotor 3, and A hemisphere stator 1 is arranged on bottom with B hemisphere stator 2
On seat 5, armature winding component 6 and buphthalmos bearing assembly 8 are arranged on A hemisphere stator 1 and B hemisphere stator 2, magnetic force block assembly 7
In the gap of rotor 3.Base 5 and take-off lever 4 are processed for aluminum alloy materials.A hemisphere stator 1, B hemisphere stator 2 and turn
Son 3 is No. 45 Steel material processing.
Armature winding component 6
Referring to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, armature winding component 6 include structure identical A armature winding 6A,
B armature winding 6B, C armature winding 6C, D armature winding 6D, E armature winding 6E, F armature winding 6F, G armature winding 6G, H armatures
Winding 6H, I armature winding 6I, J armature winding 6J, K armature winding 6K and L armature winding 6L.Every three armature winding composition one
Row.Described armature winding component 6 is respectively and fixedly installed on A hemisphere stator 1 and B hemisphere stator 2.
In the present invention, each armature winding is 0.7mm by cross-sectional area28 layers of square coil of copper wire winding obtain, often
Layer line circle is 25 circles.
In the present invention, the rated power of each armature winding of design is 25 watts.
Magnetic force block assembly 7
Referring to shown in Fig. 2 D, Fig. 3 E, Fig. 3 F, Fig. 4, magnetic force block assembly 7 includes structure identical A group Halbach permanent magnetism
Volume array 7A, B group Halbach permanent magnet array 7B, C group Halbach permanent magnet array 7C and D group Halbach permanent magnet battle array
Arrange 7D.
As shown in figure 4, the A groups Halbach permanent magnet array 7A includes AA permanent magnet 7A1, AB permanent magnets 7A2, AC
Permanent magnet 7A3, AD permanent magnet 7A4 and AE permanent magnet 7A5.The conformal obtained A group Halbach permanent magnet arrays of five permanent magnets
7A is arc.A group Halbach permanent magnet arrays 7A is arranged at the A gaps 3E of rotor 3.As illustrated in Figure 3 F, A groups Halbach
Permanent magnet array 7A magnetizing direction is respectively：AA permanent magnet 7A1 and AE permanent magnets 7A5 magnetizing direction is sensing rotor 3
Central point O radial magnetizing；AC permanent magnets 7A3 magnetizing direction points to export-oriented radial magnetizing (i.e. for the central point O of rotor 3
AC permanent magnets 7A3 magnetizing direction is opposite with AA permanent magnet 7A1 and AE permanent magnets 7A5 magnetizing direction)；AB permanent magnets 7A2 and
AD permanent magnets 7A4 magnetizing direction is the cutting orientation magnetizing of vertical rotor 3 diameter, and AB permanent magnets 7A2 and AD permanent magnets 7A4 fills
Magnetic direction is opposite.
As shown in figure 4, the B groups Halbach permanent magnet array 7B includes BA permanent magnet 7B1, BB permanent magnets 7B2, BC
Permanent magnet 7B3, BD permanent magnet 7B4 and BE permanent magnet 7B5.The conformal obtained B group Halbach permanent magnet arrays of five permanent magnets
7B is arc.B group Halbach permanent magnet arrays 7B is arranged at the B gaps 3F of rotor 3.It can similarly be obtained according to shown in Fig. 3 F, B
Group Halbach permanent magnet array 7B magnetizing direction is respectively：BA permanent magnet 7B1 and BE permanent magnets 7B5 magnetizing direction is finger
To the central point O of rotor 3 radial magnetizing；BC permanent magnets 7B3 magnetizing direction points to export-oriented footpath for the central point O of rotor 3
To magnetize (i.e. BC permanent magnets 7B3 magnetizing direction is opposite with BA permanent magnet 7B1 and BE permanent magnets 7B5 magnetizing direction)；BB is forever
Magnet 7B2 and BD permanent magnet 7B4 magnetizing direction is the cutting orientation magnetizing of the diameter of vertical rotor 3, and BB permanent magnets 7B2 and BD permanent magnetism
Body 7B4 magnetizing direction is opposite.
As shown in figure 4, the C groups Halbach permanent magnet array 7C includes CA permanent magnet 7C1, CB permanent magnets 7C2, CC
Permanent magnet 7C3, CD permanent magnet 7C4 and CE permanent magnet 7C5.The conformal obtained C group Halbach permanent magnet arrays of five permanent magnets
7C is arc.C group Halbach permanent magnet arrays 7C is arranged at the C gaps 3G of rotor 3.As illustrated in Figure 3 F, C groups Halbach
Permanent magnet array 7C magnetizing direction is respectively：CA permanent magnet 7C1 and CE permanent magnets 7C5 magnetizing direction is sensing rotor 3
Central point O radial magnetizing；CC permanent magnets 7C3 magnetizing direction points to export-oriented radial magnetizing (i.e. for the central point O of rotor 3
CC permanent magnets 7C3 magnetizing direction is opposite with CA permanent magnet 7C1 and CE permanent magnets 7C5 magnetizing direction)；CB permanent magnets 7C2 and
CD permanent magnets 7C4 magnetizing direction is the cutting orientation magnetizing of vertical rotor 3 diameter, and CB permanent magnets 7C2 and CD permanent magnets 7C4 fills
Magnetic direction is opposite.
As shown in figure 4, the D groups Halbach permanent magnet array 7D includes DA permanent magnet 7D1, DB permanent magnets 7D2, DC
Permanent magnet 7D3, DD permanent magnet 7D4 and DE permanent magnet 7D5.The conformal obtained D group Halbach permanent magnet arrays of five permanent magnets
7D is arc.D group Halbach permanent magnet arrays 7D is arranged at the D gaps 3H of rotor 3.It can similarly be obtained according to shown in Fig. 3 F, D
Group Halbach permanent magnet array 7D magnetizing direction is respectively：DA permanent magnet 7D1 and DE permanent magnets 7D5 magnetizing direction is finger
To the central point O of rotor 3 radial magnetizing；DC permanent magnets 7D3 magnetizing direction points to export-oriented footpath for the central point O of rotor 3
To magnetize (i.e. DC permanent magnets 7D3 magnetizing direction is opposite with DA permanent magnet 7D1 and DE permanent magnets 7A5 magnetizing direction)；DB is forever
Magnet 7D2 and DD permanent magnet 7D4 magnetizing direction is the cutting orientation magnetizing of the diameter of vertical rotor 3, and DB permanent magnets 7D2 and DD permanent magnetism
Body 7D4 magnetizing direction is opposite.
In the present invention, Halbach permanent magnet array 7 is to provide alternating fields.When armature winding component 6 is powered
Generate Ampere force so that rotor 3 forms the output torque around X-axis or Y-axis rotation, as illustrated in Figure 3 F.
Buphthalmos bearing assembly 8
Referring to shown in Fig. 2 C, Fig. 2 D, buphthalmos bearing assembly 8 includes structure identical A buphthalmos bearing 8A, B buphthalmos bearings
8B, C buphthalmos bearing 8C, D buphthalmos bearing 8D, E buphthalmos bearing 8E, F buphthalmos bearing 8F, G buphthalmos bearing 8G and H buphthalmos bearing 8H.
Buphthalmos bearing assembly 8 is separately mounted in the bearing hole of the Internal Spherical Surface of A hemisphere stator 1 and B hemisphere stator 2.Pass through 8 buphthalmos axles
Hold and support rotor 3 so that rotor 3 can be moved in A hemisphere stator 1 and the hollow ball of the formation of B hemisphere stator 2.
In the present invention, buphthalmos bearing is processed for non-magnet material, will not produce interference to the output torque of rotor 3.Its
The ceramic buphthalmos bearing that can be produced from Taizhou City Gaogang District Fei Erte drive apparatus factory.
A hemisphere stator 1
Referring to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, Fig. 5 A, Fig. 5 B, the middle part of A hemisphere stator 1 is provided with AA conical through-holes
1A, AB conical through-hole 1B, AC conical through-hole 1C；One end of A hemisphere stator 1 is provided with AA opening conical through-hole 1D, AB opening tapers
Through hole 1E, AC opening conical through-hole 1F；The other end of A hemisphere stator 1 is provided with AD opening conical through-hole 1G, AE opening conical through-holes
1H, AF opening conical through-hole 1I；A hemisphere stator 1 is provided with AA through hole 1-1 and AB through holes 1-2.The bottom of A hemisphere stator 1 is provided with
The EA on the convex round platform 5A of base 5 is passed through for AA screwed holes 1-3, the EA screw 5A3 with the convex round platform 5A of base 5 fixations
Through hole 5A1 rear threads are connected in the AA screwed holes 1-3 of the bottom of A hemisphere stator 1.The Internal Spherical Surface of A hemisphere stator 1 is provided with use
In installation A buphthalmos bearings 8A AC bearing holes 1L, the AD bearing holes 1M for installing B buphthalmos bearings 8B, for installing C buphthalmos axles
Hold 8C AA bearing holes 1J, the AB bearing holes 1K for installing D buphthalmos bearings 8D.
It is used to A armature winding 6A is fixedly mounted at AA conical through-holes 1A.
It is used to B armature winding 6B is fixedly mounted at AB conical through-holes 1B.
It is used to C armature winding 6C is fixedly mounted at AC conical through-holes 1C.
B hemisphere stator 2
Referring to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, Fig. 5 A, Fig. 5 B, the middle part of B hemisphere stator 2 is provided with BA conical through-holes
2A, BB conical through-hole 2B, BC conical through-hole 2C；One end of B hemisphere stator 2 is provided with BA opening conical through-hole 2D, BB opening tapers
Through hole 2E, BC opening conical through-hole 2F；The other end of B hemisphere stator 2 is provided with BD opening conical through-hole 2G, BE opening conical through-holes
2H, BF opening conical through-hole 2I；B hemisphere stator 2 is provided with BA through hole 2-1 and BB through holes 2-2.The bottom of B hemisphere stator 2 is provided with
The EB on the convex round platform 5A of base 5 is passed through for BA screwed holes 2-3, the EB screw 5A4 with the convex round platform 5A of base 5 fixations
Through hole 5A2 rear threads are connected in the BA screwed holes 2-3 of the bottom of B hemisphere stator 2.The Internal Spherical Surface of B hemisphere stator 2 is provided with use
In installation E buphthalmos bearings 8E BA bearing holes 2J, the BB bearing holes 2K for installing F buphthalmos bearings 8F, for installing G buphthalmos axles
Hold 8G BC bearing holes 2L, the BD bearing holes 2M for installing H buphthalmos bearings 8H.
It is used to G armature winding 6G is fixedly mounted at BA conical through-holes 2A.
It is used to H armature winding 6H is fixedly mounted at BB conical through-holes 2B.
It is used to I armature winding 6I is fixedly mounted at BC conical through-holes 2C.
In the present invention, referring to shown in Fig. 5 C, Fig. 5 D, one is then formed after A hemisphere stator 1 is docked with B hemisphere stator 2
Hollow ball.It is described hollow interior for placing rotor 3.I.e.：
AA is open after conical through-hole 1D is docked with BA openings conical through-hole 2D and forms A conical through-holes 1-4A, and the A tapers are led to
It is used to D armature winding 6D is fixedly mounted at the 1-4A of hole.
AB is open after conical through-hole 1E is docked with BB openings conical through-hole 2E and forms B conical through-holes 1-4B, and the B tapers are led to
It is used to E armature winding 6E is fixedly mounted at the 1-4B of hole.
AC is open after conical through-hole 1F is docked with BC openings conical through-hole 2F and forms C conical through-holes 1-4C, and the C tapers are led to
It is used to F armature winding 6F is fixedly mounted at the 1-4C of hole.
AD is open after conical through-hole 1G is docked with BD openings conical through-hole 2G and forms D conical through-holes 2-4A, and the D tapers are led to
It is used to J armature winding 6J is fixedly mounted at the 2-4A of hole.
AE is open after conical through-hole 1H is docked with BE openings conical through-hole 2H and forms E conical through-holes 2-4B, and the E tapers are led to
It is used to K armature winding 6K is fixedly mounted at the 2-4B of hole.
AF is open after conical through-hole 1I is docked with BF openings conical through-hole 2I and forms F conical through-holes 2-4C, and the F tapers are led to
It is used to L armature winding 6L is fixedly mounted at the 2-4B of hole.
Rotor 3
Referring to shown in Fig. 2A, Fig. 2 C, Fig. 2 D, Fig. 3 A~Fig. 3 F, rotor 3 is formed in one structure.The top of rotor 3 is
Top panel 3I, the top panel 3I are provided with the CA screwed holes 3I1 for the clutch disk 4B for being used to fix take-off lever 4；Rotor 3
Bottom be bottom panel 3J；The spheroid of rotor 3 is provided with A flap 3A, B flap 3B, C flap 3C and D flap 3D, A flaps 3A
Between B flaps 3B be between 3E, B flap 3B and C the flap 3C of A gaps between 3F, C flap 3C and D the flap 3D of B gaps be C
It is D gaps 3H between gap 3G, D flap 3D and A flap 3A；Wherein, A gaps 3E and C gap 3G are to be oppositely arranged, B gaps 3F
It is to be oppositely arranged with D gaps 3H；The centerbody 3-1 of rotor 3 is provided with 12 end faces, i.e. A end faces 3-1A, B end faces 3-1B, C
End face 3-1C, D end face 3-1D, E end face 3-1E, F end face 3-1F, G end face 3-1G, H end face 3-1H, I end face 3-1I, J end face, K
End face, L end faces；Wherein, A end faces 3-1A, B end faces 3-1B and C-terminal face 3-1C is located at A gaps 3E；D end face 3-1D, E end faces 3-1E
It is located at B gaps 3F with F end faces 3-1F；G end face 3-1G, H end face 3-1H and I end faces 3-1I is located at C gaps 3G；J end faces, K end faces
It is located at D gaps 3H with L end faces.
Referring to shown in Fig. 3 E, Fig. 3 F, Fig. 4, the A gaps 3E is used to place A group Halbach permanent magnet array 7A, and AA
Permanent magnet 7A1 is arranged on the centerbody 3-1 of rotor 3 A end faces 3-1A, and AC permanent magnets 7A3 is arranged on the centerbody 3- of rotor 3
On 1 B end faces 3-1B, AE permanent magnets 7A5 is arranged on the centerbody 3-1 of rotor 3 C-terminal face 3-1C, and AB permanent magnets 7A2 is installed
Between AA permanent magnet 7A1 and AC permanent magnets 7A3, AD permanent magnets 7A4 is arranged between AC permanent magnet 7A3 and AE permanent magnets 7A5.
Referring to shown in Fig. 3 E, Fig. 3 F, Fig. 4, the B gaps 3F is used to place B group Halbach permanent magnet array 7B, and BA
Permanent magnet 7B1 is arranged on the centerbody 3-1 of rotor 3 D end faces 3-1D, and BC permanent magnets 7B3 is arranged on the centerbody 3- of rotor 3
On 1 E end faces 3-1E, BE permanent magnets 7B5 is arranged on the centerbody 3-1 of rotor 3 F end faces 3-1F, and BB permanent magnets 7B2 is installed
Between BA permanent magnet 7B1 and BC permanent magnets 7B3, BD permanent magnets 7B4 is arranged between BC permanent magnet 7B3 and BE permanent magnets 7B5.
Referring to shown in Fig. 3 E, Fig. 3 F, Fig. 4, the C gaps 3G is used to place C group Halbach permanent magnet array 7C, and CA
Permanent magnet 7C1 is arranged on the centerbody 3-1 of rotor 3 G end faces 3-1G, and CC permanent magnets 7C3 is arranged on the centerbody 3- of rotor 3
On 1 H end faces 3-1H, CE permanent magnets 7C5 is arranged on the centerbody 3-1 of rotor 3 I end faces 3-1I, and CB permanent magnets 7C2 is installed
Between CA permanent magnet 7C1 and CC permanent magnets 7C3, CD permanent magnets 7C4 is arranged between CC permanent magnet 7C3 and CE permanent magnets 7C5.
Referring to shown in Fig. 3 E, Fig. 3 F, Fig. 4, the D gaps 3H is used to place D group Halbach permanent magnet array 7D, and DA
Permanent magnet 7D1 is arranged on the centerbody 3-1 of rotor 3 J end faces, and DC permanent magnets 7D3 is arranged on the centerbody 3-1 of rotor 3 K
On end face, DE permanent magnets 7D5 is arranged on the centerbody 3-1 of rotor 3 L end faces, and DB permanent magnets 7D2 is arranged on DA permanent magnets
Between 7D1 and DC permanent magnets 7D3, DD permanent magnets 7D4 is arranged between DC permanent magnet 7D3 and DE permanent magnets 7D5.
Take-off lever 4
Referring to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, one end of take-off lever 4 is control stick 4A, and the other end of take-off lever 4 is connection
Disk 4B；The hand that control stick 4A is used for pilot is grasped；Clutch disk 4B, which is provided with, is used for the DA through holes that DA screws 4B2 is passed through
4B1, the DA screws 4B2 through DA through holes 4B1 is fixed in the top panel 3I of rotor 3 CA screwed holes 3I1.
Base 5
Referring to shown in Fig. 2A, Fig. 2 B, Fig. 2 C, Fig. 2 D, base 5 is provided with outer round platform 5B and convex round platform 5A；Convex round platform
5A is passed through provided with EA through hole 5A1, EB through hole 5A2, EA through holes 5A1 for EA screws 5A3, through EA through holes 5A1 EA screws
5A3 is threadedly secured in the AA screwed holes 1-3 of the bottom of A hemisphere stator 1；EB through holes 5A2 is passed through for EB screws 5A4, is passed through
EB through holes 5A2 EB screws 5A4 is threadedly secured in the BA screwed holes 2-3 of the bottom of B hemisphere stator 2；Outer round platform 5B is provided with
EC through hole 5B1, the screw thread through EC through holes 5B1 is fixed in the screwed hole on aircraft handling panel 10A.
The ball motor that the present invention is designed is applied in the lever system of aircraft master end, in A hemisphere stator 1 and B hemisphere stator 2
Middle 12 armature winding of insertion, embedded 4 groups of Halbach permanent magnet arrays on rotor 3, when being powered to armature winding, according to
Ampere's law, electrified wire can produce Ampere force in magnetic field, and ampere force direction and magnetic direction, the sense of current, which follow left hand, to be determined
Then.Therefore, the take-off lever 4 of ball motor can rotate around X-axis or Y-axis, realize the rotary motion of two degrees of freedom.
(A) rudder face force feedback
Because fly-by-wire and aircraft rudder surface are not mechanically connected, it is impossible to as traditional mechanical manoeuvring system,
The load of rudder face is directly fed back by mechanical legacy system, to cause pilot to understand, grasp the flight progress of aircraft.Therefore,
Ball motor steerable system in the aircraft master end lever system that the present invention is designed, can be realized pair by the banking motion of motor
The brief introduction feedback of rudder face load so that pilot will be seen that, grasp the flight progress of aircraft.Wherein, take-off lever 4 revolves around X-axis
The output torque turned, can feed back the load condition of aileron rudder face, and the output torque rotated around Y-axis can feed back lifting rudder face
Load condition.
(B) primary control surface
Pilot promotes X-axis rotary motion of the take-off lever 4 along rotor 3, can with the deflection of the aileron rudder face of operating aircraft,
And then realize the rolling of aircraft；Promote Y-axis rotary motion of the take-off lever 4 along rotor 3 can with the elevator of operating aircraft, and then
Realize the elevating movement of aircraft.
(C) synchronization of control rod double
Ball motor steerable system in the aircraft master end lever system that the present invention is designed can realize that control rod double (is exported
Bar 4) synchronization.Generally, aircraft has two pilots.When one of pilot is in operating aircraft, another pilot
The control stick at place can realize the former control action.Therefore, two pilots can understand the control action of other side mutually, from
And a wherein side is reduced due to the maloperation to aircraft that is lacking in experience.
Claims (10)
1. a kind of ball motor for aircraft master end lever system, it is characterised in that：The ball motor includes A hemisphere stators
(1), B hemisphere stator (2), rotor (3), take-off lever (4), base (5), armature winding component (6), magnetic force block assembly (7) and ox
Axis oculi bearing assembly (8)；Wherein, A hemisphere stator (1) is identical with the structure of B hemisphere stator (2), and A hemisphere stator (1) and B hemisphere
A hollow ball is then formed after stator (2) docking；
Armature winding component (6) include structure identical A armature winding (6A), B armature winding (6B), C armature winding (6C),
D armature winding (6D), E armature winding (6E), F armature winding (6F), G armature winding (6G), H armature winding (6H), I armatures around
Group (6I), J armature winding (6J), K armature winding (6K) and L armature winding (6L)；Every three armature winding composition one is arranged；
Magnetic force block assembly (7) includes structure identical A group Halbach permanent magnet arrays (7A), B group Halbach permanent magnets
Array (7B), C group Halbach permanent magnet arrays (7C) and D group Halbach permanent magnet arrays (7D)；
The A groups Halbach permanent magnet array (7A) is arc；Its include AA permanent magnets (7A1), AB permanent magnets (7A2),
AC permanent magnets (7A3), AD permanent magnets (7A4) and AE permanent magnets (7A5)；A group Halbach permanent magnet arrays (7A), which are arranged on, to be turned
A gaps (3E) place of sub (3)；The magnetizing direction of A group Halbach permanent magnet arrays (7A) is respectively：AA permanent magnets (7A1) and
The magnetizing direction of AE permanent magnets (7A5) is the radial magnetizing for the central point O for pointing to rotor (3)；The side of magnetizing of AC permanent magnets (7A3)
Export-oriented radial magnetizing is pointed to for the central point O of rotor (3)；The magnetizing direction of AB permanent magnets (7A2) and AD permanent magnets (7A4)
For the cutting orientation magnetizing of vertical rotor (3) diameter, and AB permanent magnets (7A2) are opposite with the magnetizing direction of AD permanent magnets (7A4)；
The B groups Halbach permanent magnet array (7B) is arc；Its include BA permanent magnets (7B1), BB permanent magnets (7B2),
BC permanent magnets (7B3), BD permanent magnets (7B4) and BE permanent magnets (7B5)；B group Halbach permanent magnet arrays (7B), which are arranged on, to be turned
B gaps (3F) place of sub (3)；The magnetizing direction of B group Halbach permanent magnet arrays (7B) is respectively：BA permanent magnets (7B1) and
The magnetizing direction of BE permanent magnets (7B5) is the radial magnetizing for the central point O for pointing to rotor (3)；The side of magnetizing of BC permanent magnets (7B3)
Export-oriented radial magnetizing is pointed to for the central point O of rotor (3)；The magnetizing direction of BB permanent magnets (7B2) and BD permanent magnets (7B4)
For the cutting orientation magnetizing of vertical rotor (3) diameter, and BB permanent magnets (7B2) are opposite with the magnetizing direction of BD permanent magnets (7B4)；
The C groups Halbach permanent magnet array (7C) is arc；Its include CA permanent magnets (7C1), CB permanent magnets (7C2),
CC permanent magnets (7C3), CD permanent magnets (7C4) and CE permanent magnets (7C5)；C group Halbach permanent magnet arrays (7C), which are arranged on, to be turned
C gaps (3G) place of sub (3)；The magnetizing direction of C group Halbach permanent magnet arrays (7C) is respectively：CA permanent magnets (7C1) and
The magnetizing direction of CE permanent magnets (7C5) is the radial magnetizing for the central point O for pointing to rotor (3)；The side of magnetizing of CC permanent magnets (7C3)
Export-oriented radial magnetizing is pointed to for the central point O of rotor (3)；The magnetizing direction of CB permanent magnets (7C2) and CD permanent magnets (7C4)
For the cutting orientation magnetizing of vertical rotor (3) diameter, and CB permanent magnets (7C2) are opposite with the magnetizing direction of CD permanent magnets (7C4)；
The D groups Halbach permanent magnet array (7D) is arc；Its include DA permanent magnets (7D1), DB permanent magnets (7D2),
DC permanent magnets (7D3), DD permanent magnets (7D4) and DE permanent magnets (7D5)；D group Halbach permanent magnet arrays (7D), which are arranged on, to be turned
D gaps (3H) place of sub (3)；The magnetizing direction of D group Halbach permanent magnet arrays (7D) is respectively：DA permanent magnets (7D1) and
The magnetizing direction of DE permanent magnets (7D5) is the radial magnetizing for the central point O for pointing to rotor (3)；The side of magnetizing of DC permanent magnets (7D3)
Export-oriented radial magnetizing is pointed to for the central point O of rotor (3)；The magnetizing direction of DB permanent magnets (7D2) and DD permanent magnets (7D4)
For the cutting orientation magnetizing of vertical rotor (3) diameter, and DB permanent magnets (7D2) are opposite with the magnetizing direction of DD permanent magnets (7D4)；
Buphthalmos bearing assembly (8) include structure identical A buphthalmos bearing (8A), B buphthalmos bearing (8B), C buphthalmos bearing (8C),
D buphthalmos bearing (8D), E buphthalmos bearing (8E), F buphthalmos bearing (8F), G buphthalmos bearing (8G) and H buphthalmos bearing (8H)；
The middle part of A hemisphere stator (1) is provided with AA conical through-holes (1A), AB conical through-holes (1B), AC conical through-holes (1C)；A hemisphere
One end of stator (1) is provided with AA opening conical through-holes (1D), AB opening conical through-holes (1E), AC opening conical through-holes (1F)；A half
The other end of ball stator (1) is provided with (AD) opening conical through-hole (1G), AE opening conical through-holes (1H), AF opening conical through-holes
(1I)；A hemisphere stator (1) is provided with AA through holes (1-1) and AB through holes (1-2)；The bottom of A hemisphere stator (1) be provided be used for
The fixed AA screwed holes (1-3) of the convex round platform (5A) of base (5), EA screws (5A3) pass through the convex round platform (5A) of base (5)
On EA through holes (5A1) rear thread be connected in the AA screwed holes (1-3) of the bottom of A hemisphere stator (1)；A hemisphere stator (1)
Internal Spherical Surface, which is provided with, to be used to install the AC bearing holes (1L) of A buphthalmos bearing (8A), the AD bearings for installing B buphthalmos bearing (8B)
Hole (1M), the AA bearing holes (1J) for installing C buphthalmos bearing (8C), the AB bearing holes for installing D buphthalmos bearing (8D)
(1K)；
AA conical through-holes (1A) place is used to A armature winding (6A) is fixedly mounted；
AB conical through-holes (1B) place is used to B armature winding (6B) is fixedly mounted；
AC conical through-holes (1C) place is used to C armature winding (6C) is fixedly mounted；
The middle part of B hemisphere stator (2) is provided with BA conical through-holes (2A), BB conical through-holes (2B), BC conical through-holes (2C)；B hemisphere
One end of stator (2) is provided with BA opening conical through-holes (2D), BB opening conical through-holes (2E), BC opening conical through-holes (2F)；B half
The other end of ball stator (2) is provided with BD opening conical through-holes (2G), BE opening conical through-holes (2H), BF opening conical through-holes
(2I)；B hemisphere stator (2) is provided with BA through holes (2-1) and BB through holes (2-2)；The bottom of B hemisphere stator (2) be provided be used for
The fixed BA screwed holes (2-3) of the convex round platform (5A) of base (5), EB screws (5A4) pass through the convex round platform (5A) of base (5)
On EB through holes (5A2) rear thread be connected in the BA screwed holes (2-3) of the bottom of B hemisphere stator (2)；B hemisphere stator (2)
Internal Spherical Surface, which is provided with, to be used to install the BA bearing holes (2J) of E buphthalmos bearing (8E), the BB bearings for installing F buphthalmos bearing (8F)
Hole (2K), the BC bearing holes (2L) for installing G buphthalmos bearing (8G), the BD bearing holes for installing H buphthalmos bearing (8H)
(2M)；
BA conical through-holes (2A) place is used to G armature winding (6G) is fixedly mounted；
BB conical through-holes (2B) place is used to H armature winding (6H) is fixedly mounted；
BC conical through-holes (2C) place is used to I armature winding (6I) is fixedly mounted；
AA opening conical through-holes (1D) form A conical through-holes (1-4A), the A tapers after being docked with BA opening conical through-holes (2D)
Through hole (1-4A) place is used to D armature winding (6D) is fixedly mounted；
AB opening conical through-holes (1E) form B conical through-holes (1-4B), the B tapers after being docked with BB opening conical through-holes (2E)
Through hole (1-4B) place is used to E armature winding (6E) is fixedly mounted；
AC opening conical through-holes (1F) form C conical through-holes (1-4C), the C tapers after being docked with BC opening conical through-holes (2F)
Through hole (1-4C) place is used to F armature winding (6F) is fixedly mounted；
AD opening conical through-holes (1G) form D conical through-holes (2-4A), the D tapers after being docked with BD opening conical through-holes (2G)
Through hole (2-4A) place is used to J armature winding (6J) is fixedly mounted；
AE opening conical through-holes (1H) form E conical through-holes (2-4B), the E tapers after being docked with BE opening conical through-holes (2H)
Through hole (2-4B) place is used to K armature winding (6K) is fixedly mounted；
AF opening conical through-holes (1I) form F conical through-holes (2-4C), the F tapers after being docked with BF opening conical through-holes (2I)
Through hole (2-4B) place is used to L armature winding (6L) is fixedly mounted；
The top of rotor (3) is top panel (3I), and the top panel (3I) is provided with the connection for being used for fixing take-off lever (4)
The CA screwed holes (3I1) of disk (4B)；The bottom of rotor (3) is bottom panel (3J)；The spheroid of rotor (3) is provided with A flaps
(3A), B flaps (3B), C flaps (3C) and D flaps (3D), are A gaps (3E), B flaps between A flaps (3A) and B flaps (3B)
It is B gaps (3F) between (3B) and C flaps (3C), is C gaps (3G), D flaps (3D) between C flaps (3C) and D flaps (3D)
It is D gaps (3H) between A flaps (3A)；The centerbody (3-1) of rotor (3) provided with A end faces (3-1A), B end faces (3-1B),
C-terminal face (3-1C), D end faces (3-1D), E end faces (3-1E), F end faces (3-1F), G end faces (3-1G), H end faces (3-1H), I end faces
(3-1I), J end faces, K end faces, L end faces；Wherein, A end faces (3-1A), B end faces (3-1B) and C-terminal face (3-1C) are located at A gaps
(3E)；D end faces (3-1D), E end faces (3-1E) and F end faces (3-1F) are located at B gaps (3F)；G end faces (3-1G), H end faces (3-
1H) it is located at C gaps (3G) with I end faces (3-1I)；J end faces, K end faces and L end faces are located at D gaps (3H)；
The A gaps (3E) are used to place A group Halbach permanent magnet arrays (7A), and AA permanent magnets (7A1) are arranged on rotor
(3) on the A end faces (3-1A) of centerbody (3-1), AC permanent magnets (7A3) are arranged on the B ends of the centerbody (3-1) of rotor (3)
On face (3-1B), AE permanent magnets (7A5) are arranged on the C-terminal face (3-1C) of the centerbody (3-1) of rotor (3), AB permanent magnets
(7A2) is arranged between AA permanent magnets (7A1) and AC permanent magnets (7A3), and AD permanent magnets (7A4) are arranged on AC permanent magnets (7A3)
Between AE permanent magnets (7A5)；
The B gaps (3F) are used to place B group Halbach permanent magnet arrays (7B), and BA permanent magnets (7B1) are arranged on rotor
(3) on the D end faces (3-1D) of centerbody (3-1), BC permanent magnets (7B3) are arranged on the E ends of the centerbody (3-1) of rotor (3)
On face (3-1E), BE permanent magnets (7B5) are arranged on the F end faces (3-1F) of the centerbody (3-1) of rotor (3), BB permanent magnets
(7B2) is arranged between BA permanent magnets (7B1) and BC permanent magnets (7B3), and BD permanent magnets (7B4) are arranged on BC permanent magnets (7B3)
Between BE permanent magnets (7B5)；
The C gaps (3G) are used to place C group Halbach permanent magnet arrays (7C), and CA permanent magnets (7C1) are arranged on rotor
(3) on the G end faces (3-1G) of centerbody (3-1), CC permanent magnets (7C3) are arranged on the H ends of the centerbody (3-1) of rotor (3)
On face (3-1H), CE permanent magnets (7C5) are arranged on the I end faces (3-1I) of the centerbody (3-1) of rotor (3), CB permanent magnets
(7C2) is arranged between CA permanent magnets (7C1) and CC permanent magnets (7C3), and CD permanent magnets (7C4) are arranged on CC permanent magnets (7C3)
Between CE permanent magnets (7C5)；
The D gaps (3H) are used to place D group Halbach permanent magnet arrays (7D), and DA permanent magnets (7D1) are arranged on rotor
(3) on the J end faces of centerbody (3-1), DC permanent magnets (7D3) are arranged on the K end faces of the centerbody (3-1) of rotor (3), DE
Permanent magnet (7D5) is arranged on the L end faces of the centerbody (3-1) of rotor (3), and DB permanent magnets (7D2) are arranged on DA permanent magnets
Between (7D1) and DC permanent magnets (7D3), DD permanent magnets (7D4) are arranged between DC permanent magnets (7D3) and DE permanent magnets (7D5)；
One end of take-off lever (4) is control stick (4A), and the other end of take-off lever (4) is clutch disk (4B)；Control stick (4A) is used
Grasped in the hand of pilot；Clutch disk (4B), which is provided with, is used for the DA through holes (4B1) that DA screws (4B2) are passed through, logical through DA
The DA screws (4B2) in hole (4B1) are fixed in the CA screwed holes (3I1) of the top panel of rotor (3) (3I)；
Base (5) is provided with outer round platform (5B) and convex round platform (5A)；Convex round platform (5A) leads to provided with EA through holes (5A1), EB
Hole (5A2), EA through holes (5A1) are passed through for EA screws (5A3), and the EA screws (5A3) through EA through holes (5A1) are threadedly secured in
In the AA screwed holes (1-3) of the bottom of A hemisphere stator (1)；EB through holes (5A2) are passed through for EB screws (5A4), through EB through holes
The EB screws (5A4) of (5A2) are threadedly secured in the BA screwed holes (2-3) of the bottom of B hemisphere stator (2)；On outer round platform (5B)
Provided with EC through holes (5B1), the screw thread through EC through holes (5B1) is fixed in the screwed hole on aircraft handling panel (10A).
2. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：The ball motor
It is connected to the left and right sides of existing aircraft handling panel (10A) and forms double ball motor steerable systems.
3. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Halbach
Permanent magnet array is alternating fields.
4. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Each armature
The rated power of winding is 25 watts.
5. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Each armature
Winding is 0.7mm by cross-sectional area28 layers of square coil of copper wire winding obtain, be 25 circles per layer line circle.
6. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Buphthalmos bearing
Processed for non-magnet material.
7. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Base (5)
Processed with take-off lever (4) for aluminum alloy materials.
8. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：A hemisphere is determined
Sub (1), B hemisphere stator (2) and rotor (3) are No. 45 Steel material processing.
9. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Utilize aircraft
Control panel installs 2 ball motors, on the one hand can realize the force feedback to aircraft lifting and landing rudder face and aileron rudder face；On the other hand
It can realize that the manipulation between pilot is synchronous, reduce wherein side's experience and lack the maloperation caused；Existing Flight By Wire system
System, without the synchronization system between control stick.
10. a kind of ball motor for aircraft master end lever system according to claim 1, it is characterised in that：Pass through behaviour
The control stick of vertical side, operating aircraft lifts rudder face to realize the elevating movement of aircraft, manipulates the deflection of aileron rudder face to realize
The rolling movement of aircraft.
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| CN201710422683.3A CN107181339B (en) | 2017-06-07 | 2017-06-07 | A kind of ball motor for aircraft master end lever system |
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| CN201710422683.3A CN107181339B (en) | 2017-06-07 | 2017-06-07 | A kind of ball motor for aircraft master end lever system |
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| CN107181339B CN107181339B (en) | 2019-03-19 |
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| CN109746417A (en) * | 2018-03-01 | 2019-05-14 | 北京航大新材科技有限公司 | A kind of hydraulic wedge mechanism of counter-pressure casting machine |
| US11009892B2 (en) | 2019-03-19 | 2021-05-18 | Honeywell International Inc. | Active human-machine user interface feedback system with spherical motor |
| CN112994524A (en) * | 2021-03-29 | 2021-06-18 | 北京航空航天大学 | Multi-degree-of-freedom spherical driver applied to control load system of aviation aircraft |
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|---|---|
| CN107181339B (en) | 2019-03-19 |
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