Motion simulator

Abstract: A flight motion simulator (10) includes a unit under test (16) supported on a stationary frame (12) for angular and translational movement along pitch (28), roll (26), and yaw axes (30). A rotor element (25) is secured to the unit under test and has a spherical configuration. Magnetic bearings (24) supported by the stationary frame (12) support the rotor element (25) in three degrees of freedom of movement. A drag-cup induction motor (86) is mounted on the frame (12) and connected to the unit under test to generate three degrees of freedom of movement by generating a rotating magnetic flux in a stator assembly (76) to induce a corresponding flow of currents in the rotor element (72) to produce torque and motion in the unit under test (16) in the same direction as the flux movement in the stator assembly (76).

Description: This invention relates to a flight motion simulator. Such a simulator can for example, be suitable for testing an inertial guidance control system that simultaneously simulates rotational and translational movement of a unit under test in three orthogonal axes. Motion simulators are utilised to produce fore and aft, lateral, elevational, rill, pitch and yaw movements or any combination of such movements to test guidance control systems used in missiles, satellites and the like. A known six degree of freedom simulator, as disclosed in Patent Specification US-A-3 295 224, comprises three mutually perpendicular axes of linear movement and three axes of rotational movement, one of the axes being normal to the other two. A platform is supported above a base by six powered and linearly controlled actuators. Each actuator extends between the platform and the base to provide vertical linear translation and pitch and roll motions of the platform. Patent Specification US-A-3 449 843 discloses a lightweight six degree of freedom simulator for zero gravity study. The simulator includes a base levitated by air bearing pad on a smooth floor. The bearing pads provide two degrees of translational freedom in a horizontal plane and one degree of rotational freedom about a vertical axis. Extending upwardly from the three-legged base is a column on which is mounted a pair of bearings and an elongate parallelogram. A seat assembly is mounted on the parallelogram to translate vertically therewith. This arrangement provides three degrees of transitional freedom and three degrees of rotational freedom of the motion simulator. It is also known in inertial instrumentation to support gyroscopes and accelerometers by means of electrical fields. For example, an inertial member in the form of a perfect sphere is maintained centred precisely at the centre of an electrode support structure. Electric fields are established by a set of electrodes forming a spherical envelope about the inertial member. Three pairs of electrodes are utilised to generate electrical support fields along one of three orthogonal axes. Patent Specification US-A-3 954 024 discloses an inertial support in which three pairs of electrodes are utilised and in the event the inertial member is not perfectly centred, a closed loop servo control restores a conductive sphere to a centred position between support electrodes. Patent Specification US-A-3 697 143 discloses an electrostatically supported gyroscope in which a conductive ball is supported between pairs of electrodes. A suspension utilises a plurality of amplifiers for sensing the voltage difference between electrodes of a pair. A control system detects displacement of the ball with respect to the electrode pair. A displacement signal is generated to apply a charge to the electrodes in a direction and with a force for restoring the ball to a centred position between the electrodes. It is also known, as disclosed in Patent Specification US-A-4 511 190 to utilise magnetic bearings for controlling the attitude of artificial satellites. While it is known to utilise electrostatic and hydraulic means for supporting a unit under test in a motion simulator, the known motion actuators are limited in the response time of the actuator to generate the required motion upon actuation. Conventionally, with a unit under test supported in a gimballed system, the natural resonant frequency of the gimballed system limits the bandwidth and is achievable to about 75 Hz. Therefore, there is a need for a motion simulator that efficiently simulates vibration characteristics at frequencies greater than the frequencies achievable by conventional torque actuators. In the Journal of Guidance Control and Dynamics Vol. 10 No 1 Jan/Feb 1987 pages 104-114 there is set out a design study for a high-accuracy three-axis test table wherein a base mounts three gimbals on which a test package is supported. An inner gimbal is configured as a sphere with a square hole for mounting the test package, a middle gimbal is configured as an oval with a hollow spherical inside surface and an outer gimbal is configured as a sphere with a hollow discus-shaped inside surface. The gimbals are supported one within another by bearings, angular position transducers indicate angles and torque actuators are provided in the form of induction motors. According to one aspect of the invention there is provided a flight motion simulator comprising: a unit under test; a stationary frame to support the unit under test for angular and translational movement; and a rotor element secured to the unit under test, the rotor element having the configuration of a segment of a sphere; characterised by: magnetic bearing means supported by the stationary frame to support the rotor element for unlimited rotation in a roll axis and limited rotation in a pitch axis and a yaw axis and limited translational movement in three orthogonal axes; drive means mounted on the stationary frame and connected to the unit under test to generate torque in three rotational degrees of freedom of angular movement and translational movement along the three orthogonal axes; and means to sense the position of the unit under test relative to the stationary frame to control the drive means to generate torque and translational movement to move the unit under test in a selected one of the three degrees of freedom of angular movement and along a selected one of the three orthogonal axes. According to another aspect of the invention there is provided apparatus for generating three degrees of movement in a motion simulator comprising, a movable member, a stationary member, a rotor element having a surface in the configuration of a segment of a sphere, the rotor element being fixed to the movable member, and a stator assembly secured to the stationary member and positioned in close proximity to one surface of the rotor element, the stator assembly having a configuration conforming to the configuration of the rotor element, characterised by magnetic bearing means to support the movable member on the stationary member for unlimited rotation in a roll axis and limited rotation in a pitch axis and a yaw axis and limited translational movement in three orthogonal axes, a magnetic flux carrying member secured to the stationary member and positioned in close proximity to the surface of the rotor element, the stator assembly including a plurality of polyphase electrical windings, the electrical windings being positioned orthogonal to one another on the stator assembly, and means for supplying polyphase current to the windings to generate a rotating magnetic flux in the stator assembly to induce a corresponding flow of currents in the rotor element to produce torque and motion in the movable member in the same direction as the flux movement in the stator assembly. According to a further aspect of the invention there is provided a method for simulating flight motion in a test unit comprising positioning a test unit on a stationary frame, and mounting a spherical segment of a rotor element on the test unit, characterised by supporting the test unit by magnetic bearings for unlimited rotation along one axis and limited rotation along two axes and limited translational movement along three orthogonal axes on the stationary frame, sensing the position of the test unit relative to the stationary frame, securing a spherical segment of a stator assembly to the stationary frame in close proximity to the rotor element spherical segment, supporting first and second electrical windings on the stator assembly spherical segment to extend in an orthogonal relationship to one another, injecting polyphase current through the first and second electrical windings to generate a rotating magnetic flux in the stator assembly, and inducing flow of currents in response to the rotating magnetic flux in the rotor element to produce torque and limited rotational motion in the test unit in the same direction as the flux movement in the stator assembly. Embodiments of a motion simulator incorporating the invention can: have unlimited travel in the roll axis and limited travel in the pitch and yaw axis; provide a spherical motion simulator operable to generate rotational and translational movement of a unit under test in three orthogonal axes; provide a six degree of freedom motion simulator with unlimited travel in the roll axis, limited travel in the pitch and yaw axes, and limited translational motion in the X, Y and Z axes; utilise magnetic bearings to support a unit under test for movement in six degrees freedom in a flight motion simulator; and utilise a drag-cup induction motor to generate torque in pitch, yaw, and roll axes of a unit under test in a flight motion simulator. The invention is further illustrated by way of non-limiting example with reference to the accompanying drawings in which: Figure 1 is a fragmentary perspective view partially in section of a flight motion simulator according to the invention; Figure 2 is an enlarged orthographic illustration of a spherical stator segment of a drag-cup type induction motion used in a motion simulator according to the invention; Figure 3 is an enlarged fragmentary orthographic view of a segment of the stator of Figure 2, illustrating the stator slotted in two directions with overlying electrical windings positioned in the slots; Figure 4 is an enlarged fragmentary schematic illustration of one embodiment of a drag-cup induction type motor that includes a pair of stators positioned on opposite sides of a spherical rotor; Figure 5 is a view similar to Figure 4, illustrating a drag-cup type induction motor having a pair of single slotted stators on opposite sides of a spherical rotor; Figure 6 is an enlarged fragmentary orthographic view of a stator segment in which the windings are bonded to the surface of the stator magnetic structure; and Figure 7 is a schematic illustration of a control system for operation of the drag-type induction motors in a motion simulator according to the invention. Referring to the drawings and particularly to Figure 1, there is illustrated a flight motion simulator generally designated by the numeral 10 that includes a stationary frame 12 for supporting a unit 14 under test, illustrated in phantom, fixed within a movable member 16 that is supported by a gimballed system for movement in six degrees of freedom. The stationary frame 12 includes a support housing 20 having an arcuate configuration for receiving and supporting a drag-cup induction motor generally designated by the numeral 22. A magnetic bearing suspension system generally designated by the numeral 23 includes a plurality of spherical magnetic bearings 23 positioned adjacent a rotor element 25 to support the movable member 16 for rotational and translational motion. Air gap sensor devices 27 and associated electronic control means (not shown) measure the width of an air gap 29 as shown in Figures 4 and 5 between the magnetic bearings 24 and the rotor elements 25. The devices 27 are located at fixed positions around the periphery of the spherical surface of the rotor element 25 to deduce translational movement of the rotor element 25. The unit 14 under test, together with the movable member 16, is completely rotatable within the stationary frame 12 about a roll axis 26. Partial rotational movement of the combined unit 14 under test and the member 16 within a selected field of view is also produced along a pitch axis 28 and a yaw axis 30. As will be explained later in greater detail, the unit 14 under test is also movable translationally in a limited range along the three axes 26, 28 and 30 thereby to provide six degrees of freedom of motion for the unit 14. The gimballed system for movably supporting the unit 14 and the member 16 on the frame 12 includes a first linkage arm 31 that is supported for pivotal movement about the yaw axis 30 by bearings 32 which are supported on journals 34, only one of which is shown in Figure 1. A second linkage arm 36 is supported on the frame 12 for pivotal movement about the pitch axis 28 by bearings 38 also supported on journals 40 that extend outwardly from the frame 12. Only one of the journals 40 is shown in Figure 1. Each of the linkage arms 31 and 36 includes elongate slots 42 and 44 respectively. An engagement member, such as a pin 46, is connected and extends outwardly from an end portion 48 of the member 16 and extends through the slot 44 in the linkage arm 36. An end portion 50 of the pin 46 is received within a journal 49 supported by bearings 51 retained in a readout assembly generally designated by the numeral 52. The readout assembly 52 is retained by anti-rotation pins 54 within the slot 42 of the linkage arm 31. The readout assembly 52 includes a conventional resolver or angular position encoder to sense rotational movement of the member 16 about the roll axis 26. Similar to the readout assembly 52 on the end 50 of the pin 46, a readout assembly 56 is positioned on the journal 34 that extends from the support housing 20 coaxial with the yaw axis 30. Another readout assembly 60 is mounted on the journal 40 that extends from the stationary support housing 20 coaxially aligned with the pitch axis 28. Each of the readout assemblies associated with the axes 26, 28 and 30 includes a resolver mechanism 66 and a tachometer 68 as known in the art. The operation of the resolver 66 and tachometer 68 is well known and therefore will not be discussed in detail. It is the function of the resolver 66 associated with each of the readout assemblies 52, 56 and 60 on the three axes 26, 28 and 30 to sense the angular displacement of the unit 14 about the respective axis. The angular displacement sensed is converted by the resolvers 66 for the roll, pitch and yaw axes into electrical input signals which are transmitted to a motor control circuit generally designated by the numeral 70 in Figure 7. The input signals to the circuit 70 from each of the readout assemblies provide a frame of reference of the relative positions of the pitch, yaw and roll axes. As will be explained later in greater detail, the control circuit 70 is operable to compare the relative positions represented by the input signals to the desired position of the axes. As a result of this comparison, an output signal is transmitted to the respective drag-cup motors 22 to establish the appropriate amplitude, frequency and phase sequence of voltage to apply to the motors for the corresponding motion of the unit 14 under test. The induction motors 22 control the movement of the unit 14. Upon pivotal movement of the member 16 about the respective axes 26, 28 and 30, the pin 46 is movable in the slot 44. When the member 16 pivots about the yaw axis 30, the linkage arm 31 moves with the member 16, resulting in movement of the resolver 66 for the readout assembly 56. Pivotal movement of the member 16 about the pitch axis 28 results in corresponding movement of the linkage arm 36 and rotation of the readout assembly 60. Preferably, the pin 46 and the linkage arms 31 and 36 have low inertia and friction to minimise the input of error into the sensing of the movement of the unit 14 under test. As illustrated in Figure 1, the drag-cup induction motors 22 have a spherical shell geometry that permit the generation of torque in three degrees of freedom of movement. In one embodiment, four induction motors 22 are positioned in spherical segments around the test unit 14. Each induction motor 22 includes a rotor element 72, preferably fabricated of copper or aluminium, and formed integral with the movable member 16. A rotor element 72, as shown in Figure 1, is positioned between a stationary magnetic flux carrying element 74 and a stator element 76 which is stationarily positioned on the support housing 20. Figure 2 illustrates the spherical configuration of a representative stator element 76 and includes a set of slots 78 that extend in one direction which is orthogonal to another set of slots 80. As shown in Figure 2, the stator slots 78 and 80 receive polyphase windings 82 and 84 respectively. The windings 82 and 84 are positioned orthogonal to each other. Positioning the windings 82 and 84 diametrically opposite each other, when energised from the same AC source, produces a rotating flux field. As shown in Figure 3, the stator element 76 can be planar rather than spherical. By supplying three phase currents in both of the windings 82 and 84, roll motion and pivotal motion is generated in the movable member 16. For example, by supplying current to the windings 82 and 84 with the stator elements 76 positioned at the top and bottom of the simulator 10, both roll and pitch torques are induced in the rotor element 72. The pitch torque produces a motion about the pitch axis 28. Similarly, supplying polyphase AC current in a selected one of the windings of the stator elements 76 positioned on the sides of the motion simulator 10 results in motion about the yaw axis 30. Flux produced by the currents in the stator elements 76 pass through the rotor element 72, which is, as indicated above, fabricated of a highly conductive material such as aluminium or copper. As the flux wave propagates along the stator elements 76 eddy currents are induced in the rotor element 72 producing a reaction torque. Thus, where the surfaces of the stator elements 76, as shown in Figure 1, are spherical in shape and are positioned at 90 degrees relative to one another, mutually perpendicular torques are applied to the rotor element 72. Now referring to Figure 4, there is illustrated an embodiment of an alternate form of a drag-cup induction motor generally designated by the numeral 86 that includes a pair of laminated stator elements 90 and 92, each having a segmented spherical configuration. Each stator element 90 and 92 is slotted in two orthogonal directions and polyphase windings 94 and 96 are positioned in the slots. The wound stator elements 90 and 92 are positioned on both sides of a spherically-shaped rotor element 72 with an air gap provided between the opposite surfaces of the rotor 72 and the respective stator elements 90 and 92. With this arrangement, the torque developed per unit of area is approximately twice the torque developed by a single-sided stator arrangement as illustrated in Figure 1. As with the drag-cup induction motor shown in Figure 1, the induction motor 86 shown in Figure 4 produces roll motion in the moving member 16 when multiphase AC current is supplied to the windings 94. Supplying polyphase AC current in the windings 96 of the stator elements 90 and 92 located at the top and bottom of the motion simulator 10 produces motion about the pitch axis 28. Also, when polyphase current is supplied to the windings 96 of the stator elements 90 and 92 positioned on the sides of the motion simulator 10, movement of the member 16 is generated about the yaw axis 30. Also stops 97 and 99 are provided to limit movement of the member 16 and rotor element 72. Now referring to Figure 5, there is illustrated a further embodiment of a drag-cup induction motor, generally designated by the numeral 100 that includes a laminated stator element 102 slotted into only one direction for receiving polyphase windings 104. However, a second spherical segmented stator element 106 is positioned oppositely of the first stator element 102 with a rotor element 72 positioned therebetween, as discussed above with regard to the embodiment shown in Figure 4. The stator element 106 also includes a plurality of slots. The slots in the stator element 106 are orthogonal to the corresponding slots in the stator element 102. Windings 110 are positioned in the slots of the stator element 106 and are thus orthogonal to the windings 104. The stator elements described above in regard to the various embodiments of the drag-cup induction motors 22, 86 and 100 shown in Figures 1, 4 and 5 all include a slotted configuration. Another embodiment of the stator element 76 of drag-cup induction motor shown in Figure 1 is illustrated in Figure 6. As shown in Figure 6 winding elements 114 and 116 are bonded to the surface of a flux carrying element 118 which is part of the stator. Further, the windings 114 and 116 occupy a portion of the air gap between the flux carrying members 118 and the element 74. The windings 114 and 116 are each in the form of layers where the layers are bonded together. This arrangement facilitates the generation of uniform ripple-free torque produced at any angle of motion. With each of the drag-cup induction motors discussed above, the rotor element is shaped in a spherical shell geometry so that three dimensions of torque can be simultaneously induced in the rotor element. The stationary wound stator elements are located interior to and/or exterior to the rotor element. Preferably, the stator elements in each of the embodiments as shown in Figures 1, 4, 5 and 6 are segregated into quadrants of individual elements having an arcuate configuration that corresponds to a segment of a sphere. Each of the segments comprising the stator elements contain two sets of the three-phase windings which are, as above described, orthogonal to one another. The windings are positioned opposite one another and are energised from the same three phase source thus producing a rotating flux field. By supplying three phase currents in both of the two sets of stator element windings the magnetic flux in the stator element can be made to rotate not only in a single degree of freedom but in two degrees of freedom. The moving flux in the stator element induces currents in the rotor element which in turn generates torque and motion in the same direction as the flux movement in the stator element. Consequently, two degrees of freedom of rotor motion results from energising a pair of stator elements. Accordingly, by inducing currents in stator elements positioned at the top and bottom of the simulator 10, both roll and pitch torques are produced in the rotor element. Similarly, the stator elements on both sides of the simulator 10 are utilised to produce both roll and yaw torques. Preferably, the windings of the drag-cup induction motors are driven by three transistorized three phase, variable voltage, variable frequency, sine wave inverters. Inverters suitable for use with the drag-cup induction motors described above are known in the art and therefore will not be described herein in detail. Now referring to Figure 7, there is schematically illustrated a control system 122 for operating the drag-cup induction motors. The control system 122 receives feedback signals from the readout assemblies 52, 56 and 60 illustrated in Figure 1. The input signals serve as a frame of reference for the simulator roll, pitch and yaw positions, as well as a simulation of vehicle velocities. The input signals are converted into a coordinate system by a command translator that includes in one embodiment a conventional microprocessor. Output from the command translator is transmitted to a servo control computer which compares the measured roll, pitch and yaw positions and velocities with selected values thereof. Then the servo control computer calculates the appropriate current reference signals I ref to be transmitted to the roll, pitch and yaw inverters. In addition, the computer transmits to the respective inverts the actual velocity signals W R for the roll inverter, W P for the pitch converter, and W Y for the yaw inverter. In addition, a signal representing the desired velocities, W R , W P and W Y are transmitted to the roll, pitch and yaw inverters. The respective input signals to the inverters are utilised by the inverters to provide a resultant output signal transmitted to each of the windings of the respective stator elements to generate the selected amplitudes, frequencies, and phase sequence of voltage to apply to the windings. Also, as seen in Figure 7, a current feedback signal is also transmitted from the output of each inverter for adjustments in the output signal. As discussed above, the magnetic bearings 24, illustrated in Figure 1, are operable to suspend the movable member 16 of the motion simulator 10. With this arrangement, it is possible to simulate vibration characteristics in the form of high frequency components of translational motion. By utilising spherical shaped magnetic bearings there is no contact between the rotor element and the stator element, and as a result there is no friction in the usual sense. The only resistance to motion is incurred by a very small amount of hysteresis loss in the rotor iron as the flux reverses in each element of the rotor iron as it passes from pole to pole. This loss is very uniform and therefore the associated rag has virtually no impact on angular positioning accuracy. By use of spherical-shaped magnetic bearings, three dimensional rotation can be achieved with a high degree of precision without requiring a high degree of machining precision. This is possible because the air gap in a magnetic bearing is large, similar to the air gap in an electric motor. As a result, minor amounts of runout, surface irregularity, or lack of concentricity have little impact on the rotor element as it rotates. Further by utilising the magnetic bearings, the component of pointing error associated with the intersection of the axes is substantially reduced or eliminated. This is possible because the position of the rotor within the spherical magnetic bearing can be adjusted with three reference position potentiometers corresponding to the X, Y and Z axes in the magnetic bearing position control loops. A magnetic bearing suitable for use in the invention includes a pair of rows of electromagnets where the pairs are equally spaced around a rotor member, such as the movable member 16 illustrated in Figure 1, that has a ferrous outer ring in close proximity to the electromagnets. Forces are exerted on the rotor member by supplying current to the coils of the electromagnets. By adjusting the currents in each electromagnet, the forces are brought into balance to permit the rotor member to be positioned at rest in a levitated state under a condition of equalised forces. As a rule, a balanced condition represents an unstable equilibrium point because the attractive force of each electromagnet varies inversely with the distance between the rotor member and the poles of the electromagnet. Consequently, if the rotor member moves an infinitesimal distance from the point of equilibrium, the forces become unbalanced so as to cause the rotor member to move even farther from the equilibrium point. Consequently, as is well known in the art, in order to achieve a stable suspension of the rotor within the magnetic field, it is necessary to close a position loop around the unstable force producing system and to provide compensation for the unstabilising force nonlinearity. The air gap sensors 27, shown in Figure 1, are of the inductive or eddy-current type. In combination with a high frequency source of excitation and amplitude demodulator, the air gap sensors 27 are used to sense the rotor element position within the air gap. Preferably eight air gap sensors 27 are spread around the periphery of the rotor element 25 and positioned adjacent and between the magnetic bearings 24. The bearings 24 have a spherical configuration which facilitates unrestrained angular motion of the unit under test 16 in three angular degrees of freedom. In operation the air gap sensors 27 being in close proximity with the magnetic bearings 24 constantly monitor the width of the air gap 29 between the bearings 24 and the spherical surface of the rotor member 25. Feedback signals are transmitted from the sensors 27 to a control means which in response to the measured gap signal control the currents to each of the magnetic bearings to maintain the desired air gap for a desired distance between the rotor element 72 and the stator element 76. In this manner, the desired centre of rotation of the simulator 10 is maintained. A plurality of position sensors are used to sense the air gaps between the rotor and stator members of the magnetic bearings. Because these sensors are not on the axes of each of the control loops it is necessary algebraically to combine the signals to obtain the rotor displacement signals along each of the control lop axes. In operation of the flight motion simulator 10, angular position sensing means are utilised to measure the rotation of the spherical rotor element about the three orthogonal axes. This is accomplished in one method by utilising a known optical in-plane surface motion sensor. This kind of sensing device utilises a non-contact technique permitting a stand-off distance between the sphere surface and the sensor. Preferably to cover the three degrees of freedom (roll, pitch and yaw) with one level of redundancy, a total of six sensors in four packages are utilised. The sensors are located at four positions in the pitch-yaw plane, separated by 90 degrees in which two sensors are positioned in each of diametrically opposed locations and single sensors in the other two locations.

Claims: A flight motion simulator comprising: a unit (14) under test; a stationary frame to support the unit (14) under test for angular and translational movement; and a rotor element (25, 72) secured to the unit (14) under test, the rotor element (25, 72) having the configuration of a segment of a sphere; characterised by: magnetic bearing means (24) supported by the stationary frame (12) to support the rotor element (25, 72) for unlimited rotation in a roll axis (26) and limited rotation in a pitch axis (28) and a yaw axis (30) and limited translational movement in three orthogonal axes; drive means (22, 86, 100) mounted on the stationary frame (12) and connected to the unit (14) under test to generate torque in three rotational degrees of freedom of angular movement and translational movement along the three orthogonal axes; and means to sense the position of the unit (14) under test relative to the stationary frame (12) to control the drive means (22, 86, 100) to generate torque and translational movement to move the unit (14) under test in a selected one of the three degrees of freedom of angular movement and along a selected one of the three orthogonal axes. A flight motion simulator according to claim 1, in which: the unit (14) under test has the roll, pitch and yaw axes (26, 28, 30); the magnetic bearing means (24) supports the unit under test for movement about a selected one of the axes; and the drive means (22, 86, 100) includes a plurality of assemblies selectively positioned on the periphery of the rotor element (72) to generate torque of the rotor element about the axes. A flight motion simulator according to claim 1, in which: the drive means includes a plurality of drag-cup induction motors (22, 86, 100) positioned in arcuately shaped segments around the unit (14) under test. A flight motion simulator according to claim 3, in which each of the drag-cup induction motors (22, 86, 100) has shell configuration conforming to the spherical configuration of the rotor element (72) to generate torque of the rotor element (72) in three degrees of freedom of movement. A flight motion simulator according to claim 1, in which: the drive means includes a plurality of stator segments (76) positioned on the stationary frame (12) in close proximity to and around the rotor element (25); each of the stator segments (76) has a configuration conforming to the spherical configuration of the rotor element (25); a pair of three phase electrical windings (82, 84) supported in orthogonal relation to each other are provided on each of the stator segments (76); and means are provided to supply alternating current power to the electrical windings (82, 84) to produce a magnetic flux in the stator segments to induce current in the rotor element and produce corresponding torque and motion in the rotor element (72). A flight motion simulator according to claim 1, in which the drive means (22, 86, 100) includes a stator element (76, 90, 92, 102, 106) supported by the stationary frame (12) in spaced relation closely adjacent to one surface of the rotor element (72), and the stator element includes electrical means (82, 84, 94, 96, 104, 110) to induce electrical current in the rotor element (72) to generate motion of the rotor element (72) in a selected one of three orthogonal axes. A flight motion simulator according to claim 6, in which a magnetic flux carrying element (74, 118) is supported by the stationary frame in spaced relation closely adjacent to the opposite surface of the rotor element (72). A flight motion simulator according to claim 6, in which a second station element (92, 106) is supported by the stationary frame in spaced relation closely adjacent to an opposite surface of the rotor element (72), the second stator element (92, 106) and the first stator element (90, 102) are aligned with one another on opposite sides of the rotor element (72), and the first and second stator elements (90, 92, 102, 106) include polyphase electrical windings (94, 96, 104, 110) with the windings (94, 96, 104, 110) positioned orthogonal to each other. A flight motion simulator according to claim 1, in which the drive means (22, 86, 100) includes four stator elements (76, 90, 92, 102, 106) located in quadrant relationship to one another around the periphery of the unit (12) under test, and each of the stator elements has an arcuate configuration. A flight motion simulator according to claim 1, in which the magnetic bearing means (24) includes means (49, 50) for translationally displacing the rotor element (72). Apparatus for generating three degrees of movement in a motion simulator comprising, a movable member (16), a stationary member (12), a rotor element (72) having a surface in the configuration of a segment of a sphere, the rotor element being fixed to the movable member (16), and a stator assembly (76, 90, 92, 102, 106) secured to the stationary member (12) and positioned in close proximity to one surface of the rotor element, the stator assembly having a configuration conforming to the configuration of the rotor element, characterised by magnetic bearing means (24) to support the movable member (16) on the stationary member (12) for unlimited rotation in a roll axis (26) and limited rotation in a pitch axis (28) and a yaw axis (30) and limited translational movement in three orthogonal axes, a magnetic flux carrying member (74, 118) secured to the stationary member (12) and positioned in close proximity to the surface of the rotor element (72), the stator assembly (76, 90, 92, 102, 106) including a plurality of polyphase electrical windings (82, 84, 94, 96, 104, 110), the electrical windings being positioned orthogonal to one another on the stator assembly, and means for supplying polyphase current to the windings to generate a rotating magnetic flux in the stator assembly to induce a corresponding flow of currents in the rotor element to produce torque and motion in the movable member (16) in the same direction as the flux movement in the stator assembly. Apparatus according to claim 11, in which the stator assembly includes four stator elements (76, 90, 92, 102, 106) located in quadrant relationship to one another around the periphery of a unit under test, and the stator assembly has an arcuate configuration. Apparatus according to claim 11, in which the stator assembly includes a first set of slots (78) positioned in side-by-side relationship on the stator assembly, and a second set of slots (80) are positioned orthogonally relative to the first set of slots (78), and each of the sets of slots (78, 80) receives the electrical windings. Apparatus according to claim 11, in which a pair of the stator assemblies (76, 90, 92, 102, 106) are positioned at top and bottom quadrants of the rotor element (72), and the windings (82, 84, 94, 96, 104, 110) upon energization of polyphase current generate roll and pitch torques in the rotor element (72). Apparatus according to claim 11, in which a pair of the stator assemblies (76, 90, 92, 102, 106) are position at side quadrants of the rotor element (72), and the windings (82, 84, 94, 96, 104, 110) upon energization by polyphase current generate roll and yaw torques in the rotor element (72). Apparatus according to claim 11, in which two sets (94, 96, 104, 110) of the windings are positioned in overlying orthogonal relationship to each other, and the windings are bonded to each other and to the stator assembly to maintain the orthogonal relationship of the windings on the stator assembly. Apparatus according to claim 11, in which the magnetic flux carrying member includes a second stator assembly positioned oppositely to the first stator assembly with the rotor element (72) positioned therebetween, and each of the stator assemblies includes a plurality of slots (78, 80) positioned in side-by-side relation to receive the windings where the slots in the first stator assembly (78) are positioned orthogonally relative to the slots (80) in the second stator assembly to position the windings in orthogonal relationship. A method for simulating flight motion in a test unit comprising positioning a test unit on a stationary frame (12), and mounting a spherical segment of a rotor element (72) on the test unit, characterised by supporting the test unit by magnetic bearings for unlimited rotation along one axis (26) and limited rotation along two axes (82, 30) and limited translational movement along three orthogonal axes on the stationary frame (12), sensing the position of the test unit relative to the stationary frame, securing a spherical segment of a stator assembly (76, 90, 92, 102, 106) to the stationary frame in close proximity to the rotor element (72) spherical segment, supporting first and second electrical windings (82, 84, 94, 96, 104, 110) on the stator assembly spherical segment to extend in an orthogonal relationship to one another, injecting polyphase current through the first and second electrical windings to generate a rotating magnetic flux in the stator assembly, and inducing flow of currents in response to the rotating magnetic flux in the rotor element to produce torque and limited rotational motion in the test unit in the same direction as the flux movement in the stator assembly. A method according to claim 18, which includes, maintaining the first and second electrical windings in first and second sets of orthogonally positioned slots (78, 80) in the stator assembly. A method according to claim 18, which includes, positioning a pair of the stator assemblies each wound with orthogonally positioned windings on opposite sides of the stator element. A method according to claim 18, which includes, positioning a stator assembly on opposite sides of the rotor element, and positioning a pair of electrical windings on each stator assembly in an orthogonal relationship to one another. A method according to claim 18, which includes, bonding the first and second electrical windings (114, 116) in orthogonal relationship to the surface of the stator assembly (118). A method according to claim 18, which includes, positioning a stator assembly (76, 90, 92, 102, 106) on opposite sides of the rotor element (72), positioning one set of electrical windings (82, 94, 104) on one stator assembly, and positioning another set of electrical windings (84, 96, 110) on the other stator assembly with the electrical windings being positioned in orthogonal relationship. A method according to claim 18, which includes, positioning one of the stator assemblies (76, 90, 92, 102, 106) at the top of the rotor element, positioning another of the stator assemblies (76, 90, 92, 102, 106) at the bottom of the rotor element (72), and energizing the electrical windings of the respective stator assemblies to generate roll and pitch torques in the rotor element (72). A method according to claim 18, which includes, positioning one of the stator assemblies (76, 90, 92, 102, 106) at one side of the rotor element (72), positioning another of the stator assemblies (76, 90, 92, 102, 106) at the opposite side of the rotor element (72), and energizing the electrical windings of the respective stator assemblies to generate roll and yaw torques in the rotor element (72).

Inventors: LORDO ROBERT E, MCSPARRAN LLOYD W, LORDO, ROBERT E., MCSPARRAN, LLOYD W.
Applicants: CONTRAVES INC, CONTRAVES INC.
Application year: 1989
Main classification: B64G7
IPC codes: B64G7, H02K41, G09B9, G01C25, H02K7