MOTOR HAVING INTEGRAL DETENT

Abstract: An actuating system for a primary flight control surface including unique electric drive motors having an integral detent mode. The motors include a unique laminated stator core and means for changing the continuity of the magnetic circuit. The stator core structure is split into two part-cylindrical elements which define air gaps between their opposing ends. Flux gates fill the air gaps and provide magnetic circuit continuity. The flux gates are connected to solenoids which can displace the flux gates in and out of the air gaps, thereby changing the continuity of the magnetic circuit of the motor. The motor rotor aligns its magnetic axis with the air gaps, and will resist substantial imposed torque loads.

Description: MOTOR HAVING INTEGRAL DETENT This application is a continuation-in-part of two U.S. patent applications: Serial No. 383,395, a Continuation-in- part of Serial No. 107,150 now patent number 4,852,245 a division of Patent No. 4,709,180; and Serial No. 345,312 filed April 26, 1989. BACKGROUND OF THE INVENTION The present invention relates generally to the construction, configuration, and use of an electrical machine comprising a motor having an integral detent or magnetic. The motor is particularly adapted for use within an actuation system for driving a leading edge flap of an aircraft airfoil which requires periodic holding against substantial backdriving forces on the flap. Electrically driven primary flight control surfaces such as leading edge flaps require a detent or brake to hold motor position against aerodynamic loads during flight which tend to back-drive the actuation system. Previous designs have used motor stall current to provide the brake function. However, this requires continuous energization of one motor winding resulting in unacceptable thermal stress. The thermal stresses and the continuous energization of a winding combine to substantially reduce the reliability of the motor. In addition, for dual electric motor driven actuation systems, an additional friction type brake is required to provide a reaction point for single motor operation. Present state of the art systems utilize solenoid operated friction type brakes that are physically large and subject to wear, requiring periodic maintenance and replacement. Because primary flight control surfaces such as leading edge flap drives, are required to be highly reliable, designers have generally used hydraulic motor drive systems instead of electric motor drive systems. However, hydraulic systems in aircraft have their own set of limitations and reliability problems. Accordingly, it is desirable to have a highly reliable electric motor drive system as an alternative to hydraulic systems. In U.S. Patent No. 4,852,245, a parent application to the present invention. Applicant details a high reliability, high power density toothless stator motor which is relatively inexpensive to produce and which eliminates the usual "T" shaped ferromagnetic stator core teeth. The copper windings are installed in slot areas between adjacent radially outwardly extending support fins of a plastic cylindrical winding support structure. The support fins and the winding support structure do not carry magnetic flux and are relatively thin, thereby the slot area in which the stator windings are installed is maximized. The stator windings may be pre-wound on a form and easily dropped into the slots between the support fins. A laminated cylindrical flux core surrounds the stator windings and support structure to provide magnetic flux linkage for the rotor. High energy product permanent magnets having significant energy increases over previously known permanent magnets allow the construction of a high strength permanent magnet rotor for use with the above described toothless stator motor. For example, samarium cobalt permanent magnets having an energy product of thirty (3000 tesla) or neodymium-iron-boron magnets which have an energy product of thirty-five MGO (3500 tesla) . A rotor making the maximum use of high energy product permanent magnets is disclosed in Applicant's United States Patent No. 4,667,123 issued May 19, 1987. The use of such high energy product permanent magnets permits reliable electric machines to be built which are capable of supplying high power outputs. While the above references detail an electric motor which has the requisite power and reliability for use in a primary flight surface drive actuation system, the brake problem remained a limiting factor. Accordingly, a high power density electric motor which includes a highly reliable brake is highly desirable. SUMMARY OF THE INVENTION The preferred embodiment of the present invention contemplates using a two pole permanent magnet rotor and a toothless stator motor as detailed in the parent applications and summarized above. In addition, the motor includes a unique laminated stator core and a means for changing the continuity of the magnetic circuit defined primarily by the laminated stator core and two pole permanent magnet. The laminated stator core structure is split into two part-cylindrical elements, with each lamination now being generally a part-circular plate. When assembled about the stator windings, the part- cylindrical elements are designed to have air gaps between the opposing ends. A pair of flux gates are configured to fill the air gaps between the part-cylindrical elements, and to provide magnetic circuit continuity therebetween. Accordingly, the air gaps and matching flux gates can have a number of different configurations. The flux gates are preferably connected to solenoid devices which can displace the flux gates in and out of the air gaps, thereby changing the continuity of the magnetic circuit of the motor. During motor operation, the solenoids insert the flux gates into the air gaps. When the motor is not in use and the detent mode is required, the solenoids are turned off and springs pull the flux gates out of the air gaps. The permanent magnet rotor will then rotate to align its magnetic axis with the air gaps. Once in alignment, the magnetic circuit surrounding the rotor is in a preferred orientation and will resist substantial imposed torque loads. A pair of motors according to this design are incorporated in an actuation system for a primary flight control surface as drive motors. The resulting system replaces the existing hydraulic or electric motor and potentially eliminates the need for an additional friction brake. The motors drive a plurality of geared actuators via interconnecting shafts. The actuators in turn drive the flight control surface. DESCRIPTION OF THE DRAWINGS Figure 1 shows a schematic representation of an aircraft including a leading edge flap drive system; Figure 2 is a schematic view of the power drive assembly of Fig l; Figure 3 is a partial cross-sectional view of one of the motors of Fig. 2; Figure 4 is a partial cross-sectional view taken along line 4-4 of Figure 3 and depicting the solenoid and flux gates in an open position; Figure 5 is a partial cross-sectional view similar to Figure 4 depicting the flux gate in the closed position; Figure 6 is a first alterative embodiment for the flux gate and solenoid actuation depicting the flux gate in the open position; Figure 7 is a partial cross-sectional view similar to Figure 6 depicting the alterative flux gate arrangement in the closed position; Figure 8 is a second alterative embodiment shown in partial cross-sectional view with the flux gate in the open position; Figure 9 is a view similar to Figure 8 depicting the second alterative embodiment of the flux gate in the closed position; Figure 10 - Figure 12 are simplified views showing only the stator core elements and the permanent magnet rotor and associated magnetic flux field and magnetic circuit of the motor of Figures 1-9. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT Fig. 1 shows a schematic representation of an aircraft 10 including an actuation system 12 to drive a pair of leading edge flaps 14, 16. The actuation system 12 includes a power drive unit 18 which drives first, second, third and fourth actuators 20, 22, 24, and 26, each individually attached to the leading edge flap 14. A pair of inboard torque shafts 28 extend from the power drive unit 18 to angle gearboxes 30 at their outboard end. The angle gear boxes 30 are in turn connected to fusible shafts 32 which extend out to the first actuators 20. First, second, and third shafts 34, 36, and 38 interconnect the first actuators 20 with the second actuators 22, the second actuators 22 with the third actuators 24, and the third actuators 24 with the fourth actuators 26, respectively. The actuation system 12 also includes an electronic controller 40, which is connected to the power drive unit 18, a pair of rotational position transducers 42 on each side of the power drive unit 18, as well as rotational position transducers 44 and 46 located at the outboard end of fourth actuators 26. In operation, a command from the aircraft pilot is sent to the electronic controller 40 which directs the power drive unit 18 to rotationally drives the torque shafts at a relatively high rotational speed. The actuators 20, 22, 24 and 26 include torque multiplying, speed reducing features which substantially reduce the rotational output to the flaps 14, 16, on the order of between from 300 : 1, to 3000 : 1. Thus, in order to move the flaps 14, 16 through an angle of ten degrees the shafts would rotate approximately seventy times for an actuator reduction ratio of 2500 : 1. In order to prevent severe damage to the aircraft 10, the electronic controller 40 receives position signals from transducers 42 on the power drive unit 18 and from the transducers 44 and 46 on the fourth actuators 26. The electronic controller 40 compares these signals to determine whether the actuators are being properly driven by the power drive unit 18. In the event that the signals do not match, the electronic controller 40 activates a brake within the fourth actuators 26, locking the position of the actuators 26. The electronic controller 40 also simultaneously shuts off power to the power drive unit 18, thus effectively shutting down the actuation system 12. During period of the flight when the flaps 14, 16 are not being rotationally driven, the motors 50 go into a detent holding mode, essentially acting as a brake to resist back- driving forces exerted on the flaps 14, 16. This detent mode is described more thoroughly below with respect to the detail design of the motors 50. The power drive unit 18 of Fig. 1 comprising the pair of electric motors 50 illustrated schematically in Fig.2 and in detailed cross section in Fig. 3. Each electric motor 50 has a housing 52, which is essentially cylindrical, and has two end bells 54, 56, each of which includes smaller concentric cylindrical bearing support areas 58, 60, respectively, located in their centers. The assembly consisting of the housing 52 and the end bells 54, 56 is sealed. A permanent magnet rotor 62, preferably comprising a solid cylinder permanent magnet 63 contained in a retaining sleeve 65 of high strength, non-magnetic material, is attached to a shaft 68 supported within the housing 52 on bearings 64, 66, mounted in the cylindrical bearing support areas 58, 60. The output via shafts 68 is coupled through a differential 69 (Fig. 2) to drive the inboard torque shafts 28 of the actuation system 12. The motors 50 include a toothless stator 51 having a winding support structure 70 which is essentially cylindrical with a plurality of longitudinally extending support fins 72 extending radially outwardly from the cylindrical portion, with slot areas located between adjacent support fins 72. The number of slot areas may vary as in conventional stators. The winding support structure 70 is made of non-magnetizable material, for example a high temperature engineering plastic such as polyamide-imide with the support fins 72 and the* cylindrical portion of the winding support structure manufactured integrally. It may be noted from Figure 3 that the support fins 72 are longitudinally mounted on the cylindrical portion of the winding support structure 70 intermediate the two ends, with portions at both ends of the cylindrical portion of the winding support structure 70 not carrying the support fins 72. Hence, the cylindrical portion of the winding support structure 70 is somewhat longer than the support fins 72, and extends from the support fins at both ends of the winding support structure 70. The ends of the winding support structure 70 not carrying the support fins 72 are where the interconnections between the portions of the stator windings 76 lying in the slot areas between the support fins 72 are made and where the lead wires are carried. The stator windings 76 may be prefabricated on forms of insulated magnet wire, and then laid into the slot areas between the support fins 72 on the winding support structure 70. The stator windings 76 will typically include two conductors installed into each slot area separated by insulating strips 78, each of which conductors may have multiple turns. Figure 4 depicts the stator windings 76 wound and mounted in the slot areas around the winding support structure 70, and a pair of stator core elements 80 made of magnetizable material such as electrical steel installed at the periphery of the winding support structure 70 containing the stator windings 76. Since the stator core elements 80 are made of magnetizable material which is typically conductive, an insulating liner 84 is installed between the inner diameter of the stator core elements 80 and the outer diameter of the winding support structure 70 carrying the stator windings 76. It is important to note that the only insulators necessary in the toothless stator 71 are insulating strips 78 and the insulating liner 84. The stator windings 76 need not be impregnated with varnish, and therefore may easily be cooled by flowing coolant through the stator 51. The stator core elements 80 are preferably a pair of generally part-cylindrical members made up of a plurality of laminations 82. Each lamination may include raised portions 86 arranged around its outer periphery. The raised portions 86 function to support the stator core elements 80 inside the housing 52 while allowing cooling flow between the stator core elements 80 and the housing 52. Note that in smaller machines, ferrite elements may be substituted for the laminated construction of the stator core elements 80. As shown in Fig. 4, the stator core elements 80 are designed to have air gaps 88 between the opposing ends. A pair of flux gates 90 are oppositely disposed on the motor 50 (Fig. 3) and configured to be inserted into the air gaps 88 between the part-cylindrical stator core elements 80, and thereby provide magnetic circuit continuity between the stator core elements 80. The flux gates 90 of Figs. 3-5 are depicted as elongated generally "V" shaped bars made from a plurality of laminated sheets of electrical steel bonded together. The flux gates 90 are preferably connected to means for displacing the flux gates such as solenoids 92, which can displace the flux gates 90 in and out of the air gaps 88, thereby changing the continuity of the magnetic circuit of the motor 50. During motor operation, coils 94 of the solenoids 92 are energized to drive a plunger 95 attached to the flux gate 90 inserting the flux gates 90 into the air gaps 88. Once inserted and during motor operation, the magnetic circuit surrounding the permanent magnet rotor 62 will tend to retain the flux gates 90 between the stator core elements 80 to preserve magnetic circuit continuity. When the motor 50 is not in use to provide a driving output, the detent or brake mode is engaged when springs 98, associated with the solenoids 92, pull up on the plunger 95 and withdraw the flux gates 90 from the air gaps 88. The permanent magnet rotor 62 will then align its magnetic axis 102 with the air gaps 88. Once aligned, the magnetic circuit surrounding the permanent magnet rotor 62 is in a preferred orientation and will resist imposed torque loads. The assembled stator core elements 80, flux gates 90 and solenoids 92 are installed over the winding support structure 70 carrying the stator windings 76 with the insulating liner 84 therebetween, and the resulting assembly is mounted inside the housing 52. The inner diameter of the ends of the cylindrical portion of the winding support structure 70 are mounted in interference fit fashion around the outer diameter of the cylindrical bearing support areas 58, 60 at the ends of the housing 52. A chamber is formed between the interior of the housing 52 and the outer surfaces of the winding support structure 70 through which coolant may be circulated. The housing 52 may also include an inlet channel 105 at one end of the housing 52, and an outlet channel 106 at the other tend of the housing 52. It may therefore be appreciated that a cooling fluid may be circulated through the housing 52 through the inlet channel 105, through the stator windings 76 and around the stator core elements 80, and out of the housing 52 through the outlet channel 106 to cool the stator assembly of the electric motors 50. An additional aperture 107 in the housing 52 is used to bring the winding leads 108 from the stator windings 76 through the housing 52, which aperture 107 is otherwise sealed. While generally not required for flap drive motors, active cooling may benefit other uses for the motor 50 of the present invention. Within the motor 50, the stator core elements 80 extend a majority of the arcuate distance between opposite magnetic poles of the permanent magnet rotor 62. The spaces between the facing edges of the stator core elements 80 define the magnetic air gaps 88. The width of the air gaps 88 is one of the factors which determines the maximum torque resisting force in the detent mode for the motor 50, and may be designed to be in the range of from slightly greater than zero degrees up to thirty degrees in arcuate length. Preferably the width of the air gaps 88 is approximately equal to the radial air gap distance between the outer diameter of the permanent magnet rotor 62 and the inner diameter of the stator core elements 80, to maximize the pull out torque for the brake or detent position. The exact cross sectional shape of the air gaps 88 will depend upon the shape of the flux gate 90 which is designed to fit into the air gaps 88 as tightly as possible, and to complete a perfect hollow cylinder with the stator core elements 80. In the detent mode, the motor 50 develops torque between the stator core elements 80 and permanent magnet rotor 62 due to the substantial change in reluctance of the magnetic circuit when the magnetic axis of the permanent magnet rotor 62 is angularly displaced from the centerline of the air gaps 88. The torque increases to a maximum value when the permanent magnet rotor 62 is rotated approximately forty-five degrees from the centerline of air gap 88 of the stator 51. The torque then decreases, reaching an unstable zero level at ninety degrees of relative rotation. The magnetic detent provides a new method to produce holding torque without wearing parts and requires no power input in the static operating modes. Normal motor design and operation is not significantly affected by the installation of the movable flux gates 90 and the activating solenoids 92. Figures 6 & 7 depict an alternative embodiment incorporating sliding flux gates 91 and solenoids 92 for use in the invention. In this configuration, the sliding flux gates 91 move tangentially with respect to the stator 51. The sliding flux gates 91 have a shape approximating an elongated bar having right triangle cross sections with the long side being curvalinear and preferably having a radius of curvature equal to the radius of curvature of the outer diameter of the stator core elements 80. Figure 6 depicts the sliding flux gate 91 as being in the open position thereby producing a magnetic air gap 88 between the opposite ends of the stator core elements 80. As in Figures 4 and 5, the solenoid 92 includes a plunger 95 attached to the sliding flux gate 91, is used to withdraw the sliding flux gate 91 to define the air gap 88, while a spring 98 returns the sliding flux gate 91 to the closed position for motor operation, as shown in Figure 7. It may be appreciated that while one solenoid 92 and sliding flux gate 91 may be sufficient to open and close the magnetic air gaps 88, it may be preferable to have opposing solenoids 92 and two opposing sliding flux gates 91 as depicted in Figure 6A to thereby provide continuity within the magnetic circuit during motor operation, and also to optimize the air gap geometry during the break or detent mode of operation. Figures 8 and 9 depict a second alterative arrangement for the motor 50. In this alterative arrangement, a flux gate actuation device 120 includes a rotational driver 122 and a rotational flux gate 124. The rotational flux gate 124 is essentially a cylinder which includes a ferromagnetic flux permeable element 126. The rotational flux gate 124 is designed to rotate about an axis and the ferromagnetic flux permeable element 126 has the shape of an elongated segment of a hollow cylinder, and is contained on the rotational flux gate 124 within one hemisphere. Thus, when the rotational flux gate 124 is rotated one hundred eighty degrees into the open position as depicted in Figure 8, the flux permeable element 126 is spaced apart from the stator core elements 80. During motor operation, the rotational flux gate 124 is rotated back to the zero position such that ferromagnetic flux permeable element 126 forms a continuous magnetic circuit with the stator core elements 80. It will be appreciated that this alternative design will have an air gap cross section matching the cross sectional shape of the flux permeable element 126. Within any of the embodiments of Figures 4 through 9, the solenoid coils 94 or the actuation device 122 may be energized by current delivered to a commutation device 130 (Fig. 3) for the motor. Thereby, when the motor is commanded to rotate, current which is to be commutated into one of the sets of stator windings initially flows through the solenoid coils 94 (for example) so as to energize the coil 94 and cause the solenoid 92 to insert the flux gate 90 (or 91) into the air gap 88, thereby completing the magnetic circuit for the motor 50. Conversely, when the motor is not energized, power to the solenoid 92 is shut off, and the spring 98 pulls the flux gates 90 out of the air gaps 88. The operation of the brake or detent feature of the invention is most readily understood with reference to Figs. 10-12, wherein only the permanent magnet rotor 62, and the two stator core elements 80, are depicted. The magnetic flux surrounding the permanent magnet rotor 62 is depicted by magnetic field lines 110. The stator core elements 80 act as a magnetically easy flow path for the magnetic flux, compressing the magnetic field surrounding the permanent magnet rotor 62. In Fig. 10 the magnetic axis is aligned with the air gap 88 and the permanent magnet rotor 62 is thus in a preferred zero torque location with no flux leakage between the ends of stator core elements 80. However, if the permanent magnet rotor 62 is rotated with respect to the stator core elements 80, there will be a distortion of the magnetic field, leakage across the ends of stator core elements 80, and a resistance to the rotation. Figure 11 shows the effect on the magnetic field which results from rotating permanent magnet rotor 62 approximately forty-five degrees with respect to the air gaps 88. In this orientation, a significant amount of the magnetic flux is forced to leak across the air gaps 88 between the ends of stator core elements 80. Additionally, the flux passing through the permanent magnet rotor 62 has been decreased due to the change in the magnetic circuit reluctance. This change in flux is resisted by the permanent magnet rotor 62, and requires work input into the motor 50. Figure 12 shows the unstable zero torque position where the permanent magnet rotor 62 has been rotated exactly ninety degrees from the air gap 88. In this orientation, all of the decreased magnetic flux is forced to leak across the air gaps 88, and the relative attraction to realignment of the magnetic axis with the air gaps 88 is equalized in the clockwise and counter clockwise directions. Thus, at the ninety degree position, zero torque is exerted upon the permanent magnet rotor 62 and stator core elements 80, and the permanent magnet rotor 62 is at an unstable position. When the orientation of the magnetic axis deviates from the 90 degree position, the permanent magnet rotor 62 will prefer to continue rotation in the same direction in order to realign with the air gaps 88. For stator core elements 80 formed of a ferro¬ magnetic material with any given properties, maximum torque will be realized from a magnet of any given diameter and length when the maximum radial thickness (Rm) of the stator core elements 80 is determined by the equation: Rm = Rmag * (Bmag/Bpole) and the radial thickness (R) of the stator core elements 80 varies according to the equation: Rm » Rm * cos θ where: Rmag is the radius of the permanent magnet rotor 62; Bmag is the flux density in the magnet at the minimum reluctance position; Bpole is the optimum maximum density in flux pole iron at the minimum reluctance position, (about 90 K L/sq. in. for silicon steel) ; and θ is the angular deviation from Rm. Thus it may be appreciated that the optimum cross sectional design for the stator core elements 80 is generally a crescent shape. However, since this is impractical for motor operation, the preferred shape is at best approximated by the design of the flux gates 90 in Figures 4-7 above. Furthermore, the torque developed in a reluctance coupling is given by the equation: T = dE / dθ * K wherein E is the magnetic co-energy of the system; 0 is the angular displacement of the permanent magnet rotor 62; and K is a constant. The maximum change in the magnetic co-energy (E) for an ideal coupling is a function of the change in magnetic flux density for a 90 degree displacement and zero pole leakage. In practice, the ideal is not realizable due to the flux leakage existing between the two stator core elements 80. Although leakage can be reduced by reducing flux pole dimension Rm, the higher saturation which occurs at the minimum reluctance position is counter productive. It may be appreciated that at the minimum reluctance position and with negligible iron saturation, flux density in the magnet is uniform regardless of the ratio between the width of air gap 88 to the diameter of the permanent magnet rotor 62 (Rmag) , and that the density in the air gap varies sinusoidally, being maximum in the direction of magnetization of the permanent magnet rotor 62. The teachings of the present invention are obviously useful for machines of different sizes, power capability, and structure as will be appreciated by those skilled in the art. In particular, while the two pole permanent magnet rotor and toothless stator motor construction is preferred, it will be appreciated that conventional motors could be adapted by the teachings herein. Accordingly, it is expected that the scope of the invention will be defined only by the appended claims.

Claims: CLAIMS : 1. An electric motor (50) including an integral magnetic detent (62, 80) said electric motor including a rotor member (62) drivingly connecting with an output shaft (68), said rotor member having a magnetic portion (63) providing a diametrical magnetic field, an annular stator winding (76) circumscribing said rotor member receiving electrical power and drivingly rotating said rotor member and drive shaft, and a circumferentially extending magnetically-permeable stator core (80) circumscribing said stator winding and defining a magnetic flux path for said magnetic field, characterized in that said stator core (80) defines at least one circumferentially extending air gap (88) whereat said stator core magnetic flux path is circumferentially discontinuous, and a selectively movable magnetic flux gate member (90) in a first position closing said air gap (88) to render said flux path circumferentially continuous for motor operation and in a second position said flux gate being displaced from said air gap, whereby a magnetic pole of said magnetic portion aligns with said air gap absent said flux gate member and detents said drive rotor member and drive shaft to resist rotation thereof. 2. The invention of claim 1 wherein said magnetic portion (63) provides a pair of diametrically opposite magnetic poles, and said stator core (80) includes a pair of diametrically opposite air gaps (88) , said air gaps each being closable by a respective flux gate member (90) . 3. The invention of claim 2 wherein each magnetic flux gate member is movable radially between said first position and said second position, and said second position, a solenoid selectively moving said flux gate member to one of said positions, and a resilient member yieldably biasing said flux gate member to the other of said positions. 4. the invention of claim 2 wherein each magnetic flux gate member is rotational about a respected axis generally parallel with said rotor member. 5. An actuation system for alternately moving and holding position of a flight control surface of an aircraft, and actuator system including an electric motor and shaft power transmission means coupling said motor with said flight control service to move the latter in response to operation of said motor, and braking means selectively operable during nonoperation of said motor for holding position of said flight control surface, characterized in that said motor is a permanent magnet machine including a magnetic flux circuit which is circumferentially continuous for motor operation, said flux circuit defines an air gap circumferential discontinuity receiving a magnet flux gate member, and said braking means includes means for removing said flux gate from said magnetic circuit defining said discontinuity and magnetically detenting said motor to hold position of said flight control surface. 6. The actuation system of claim 5 wherein said motor includes a rotor portion having a permanent magnet with diametrically opposite magnetic poles, and magnetic circuit including a magnetically permeable stator core member circumscribing said rotor member and defining said air gap into which said flux gate member is receivable. 7. The invention of claim 6 wherein said air gap and said flux gate member are each generally V-shaped, said flux gate member being receivable into said air gap to close the circumferential magnetic discontinuity thereat. 8. The invention of claim 6 wherein said flux gate is movable generally tangentially of said stator core member, said air gap being generally of triangular configuration in axial view, and said flux gate member being complementary in shape with said air gap. 9. The invention of claim 6 wherein said air gap is generally arcuate in shape and opens radially outwardly upon said stator core member, and flux gate member being of complementary arcuate shape and being rotational about a respective axis generally with said rotor portion to dispose said flux gate member either within or spaced out of said air gap. 10. The invention of claim 5 wherein said motor includes a pair of diametrically opposite air gaps each receiving a respective flux gate member.

Inventors: DENK JOSEPH, DENK, JOSEPH
Applicants: ALLIED SIGNAL INC, ALLIED-SIGNAL INC.
Application year: 1991
Main classification: H02K26
IPC codes: B64C13, H02K1, H02K3, H02K7, H02K21, H02K26