Abstract:
A control moment gyro comprising a wheel support structure which is mounted on a base by a motor, which is used to rotate the support around a first axis and bearing a wheel arrangement for driving the wheel spinner at a high speed around a second axis perpendicuIar to the first. The support structure includes a tubular part which rotates on the base and a flange which is disposed on only one side of the wheel and which is fixed both to the wheel and the tubular part. The diameter of the wheel and the point at which the wheel is fixed to the flange are proportioned such that the wheel penetrates the tubular part.

Description:
FIELD OF INVENTION 
   The present invention relates to gyrodynes or gyroscopic actuators (often designated by the initials cmg standing for control moment gyro); they differ from the reaction wheels commonly used to control the attitude of a space vehicle and in particular of a satellite by exchange of angular momentum, in that the wheel is mounted on a support, called a gimbal, that can be oriented by at least one motor about at least one axis which is orthogonal to the axis of rotation of the wheel. In most cases the spinner of the wheel rotates at constant speed or at least has a speed that varies little during its deployment. 
   BACKGROUND OF THE INVENTION 
   The orientation of a reference trihedron tied to the body of a satellite can be controlled about three axes by a cluster of at least three gyroscopic actuators whose gimbal exhibits just one axis of orientation of the axis of the wheel; two gyroscopic actuators suffice for 2-axis control. In practice, in general at least four gyroscopic actuators are used in a cluster to ensure redundancy for 3D control. A particularly advantageous example of an attitude control system using gyroscopic actuators is given in patent FR 98 14548 or U.S. Pat. No. 6,305,647 to which reference may be made. 
   Most existing gyroscopic actuators have an architecture of the kind shown diagrammatically in  FIG. 1 . The gyroscopic actuator comprises a plinth  10  intended to be fixed to the body of the satellite. It can moreover define, with a leaktight envelope (not represented), a volume in which the active part of the actuator is placed. Mounted on the plinth is a wheel support  12  that a motor can orient on the plinth about an axis z. Hereinafter the term “wheel”  14  will designate an assembly which comprises a part secured to the support and a spinner that can rotate on the support about an axis x orthogonal to the axis z of rotation of the support. An electric motor drives the wheel, generally at constant and regulated speed. 
   The support, that is generally referred to as a gimbal, although it can only orient the axis of the wheel about a single axis, generally exhibits an annular shape centered on the z axis. It completely surrounds the wheel or spinner. Consequently, the assembly occupies a considerable volume and has a high mass for given maximum angular momentum and rigidity. Now, due to the constraints encountered on board a satellite, the space required for the gyroscopic actuators and their mass must be reduced as much as possible for given angular momentum capacity. 
   SUMMARY OF THE INVENTION 
   The present invention is aimed in particular at providing a gyroscopic actuator having a reduced mass and requiring a reduced space, having a high overall structural rigidity, able to be embodied in a form facilitating the construction of the interfaces with the body of the satellite and the integration of the assembly. 
   The invention proposes in particular, for this purpose, a gyroscopic actuator comprising a wheel support structure mounted on a plinth by means making it possible to rotate it about a first axis and carrying a wheel equipped with means making it possible to drive the spinner of the wheel at high speed about a second axis orthogonal to the first, characterized in that the support structure comprises a tubular piece rotating on the plinth and a flange placed on one side of the wheel and fixed on the one hand to the wheel and on the other hand to the tubular piece, the diameter of the wheel and the location of fixing of the wheel to the flange being proportioned in such a way that the wheel penetrates axially into the tubular piece, and possibly into the plinth. 
   By virtue of this arrangement, it is possible to reduce the space required along the axis of rotation of the gimbal since the wheel penetrates inside the tubular piece and often also the plinth. The space required for play and the footprint on the satellite are also reduced since the diameter of the support structure is equal to the diameter of the wheel and the diameter of the plinth can be markedly less than the diameter of the wheel. 
   The flange advantageously has the general shape of an angular fraction of a truncated cone whose wider end part is fixed to the tubular piece and whose narrower end part carries the wheel. 
   The flange can exhibit a semicylindrical part for fixing the wheel (on the side of the narrower end face) and a rim for fixing onto the tubular piece (on the side of the wider end part). 
   The flange advantageously exhibits internal ribs giving it a high rigidity, making it possible to bring the first overall mode of vibration of the structure to a high value, for a given mass, in particular beyond 100 Hertz. These ribs can comprise two partitions disposed at 90° to one another, one facing the wheel, the other perpendicular to the first. 
   The tubular piece—that will subsequently sometimes be referred to as the “cone”, exhibits a first fraction, advantageously in the shape of a truncated cone whose large base is fixed to the flange. This conical shape participates in the high rigidity of the support structure. The large diameter part of the cone advantageously carries the rotor of the motor for orienting the support structure, that is to say the gimbal. The cone proper is advantageously extended by a tubular part which carries in succession the rotating part of a bearing for mounting on the plinth, the rotating part of an angular coder and a part of means for transferring power and signals between the support structure and the plinth. The tubular part extending the cone advantageously exhibits several cylindrical portions of diameters that decrease from the level of the bearing up to the level of the transfer of power and of signals. 

   
     BRIEF DESCRIPTION OF THE DRAWINGS 
     The above characteristics as well as others will become better apparent on reading the description which follows of a particular embodiment of the invention, given by way of nonlimiting example. The description refers to the drawings which accompany it, in which: 
       FIG. 1 , already mentioned, is a sectional view through the axis of the gimbal of an actuator of known type; 
       FIG. 2  is a basic representation of a gyroscopic actuator according to an embodiment of the invention, in section through a plane passing through the axis of the gimbal; 
       FIG. 3  is a view in elevation of a gyroscopic actuator having the basic construction shown in  FIG. 2 ; 
       FIGS. 4A and 4B  are two perspective views of the flange of the actuator of  FIG. 3 ; 
       FIG. 5  is a view in elevation and a partial sectional view of an actuator according to a variant embodiment. 
   

   DESCRIPTION OF THE PREFERRED EMBODIMENTS 
   In  FIG. 2 , which shows the basic architecture of an actuator, there is a plinth  10  which during use can be in any orientation, on which a support structure  12  to which the wheel  14  is fixed rotates. The support structure is in several assembled pieces. These pieces comprise a tubular piece  19  (at the bottom in  FIG. 2 ) whose top part is truncated cone shaped, carried on the plinth  10  by a bearing  18 , and a flange  20  placed on one side of the wheel and fixed on the one hand to the nonrotating part of the wheel, and on the other hand to the tubular piece. The diameter of the wheel  14 , the relative dimensions of the support structure  12  and of the plinth  10  and the location at which the wheel is fixed on the flange are proportioned in such a way that the wheel projects into the tubular piece and that the volume swept by the wheel when operational (indicated by broken lines) does not have a diameter about the axis z greater than that of the rim  21  of the plinth. Thus the space required is minimized on account of the penetration of the cantilevered mounting and of the penetration of the wheel into the gimbal. 
   The tubular piece  19  comprises, in addition to a truncated cone shaped fraction whose large base is fixed to the flange, a tubular extension exhibiting a stepped shape, with diameters that decrease progressively from the truncated cone to the bottom end. A first cylindrical span  22  is secured to the rotating part of the bearing  18  whose fixed part is mounted on the plinth  10 . The second span  24 , of smaller diameter than the first, carries the rotating part of an angular coder (not represented). Finally, a third span  26  exhibits, in the case of  FIG. 2 , an even more reduced diameter so as to leave free, between this span and the bottom part of the plinth  10 , an annular zone  28  of sufficient dimension to house therein means for transferring signals and power by flexible cable, winder or rotating commutator. 
   The construction of the particular embodiment illustrated by way of example in  FIG. 3  et seq. will now be described, where the elements corresponding to those of  FIG. 2  bears the same reference number. 
   The plinth  10  exhibits a bottom cylindrical part furnished with the rim  21  and a top flared part, which carries the stator of the electric motor  30  for orienting the gimbal. This motor  30  is for example a torque motor with permanent magnets, which is controlled by a control loop whose input is linked to an outside system. This torque motor can be replaced with a stepper motor. 
   In a particular embodiment the bearing  18  ( FIG. 2 ) comprises a set of two aligned journals, mounted back to back. These journals can in particular consist of ball or roller bearings. In the latter case, the circle of balls of each journal is devised in such a way as to be supported obliquely on the rings, so that the forces exerted on the balls occupy the generatrices of a cone. By virtue of the mounting of two bearings back to back, the vertices of the two cones can be distanced from one another, for example, one at the level of the center of the wheel and the other inside the zone  28 . Through an appropriate choice of the diameter of the bearings and of the angle of contact (angle between the direction of support of the balls and the rings of the bearing), it is possible to achieve the best possible compromise between the picking up of the loads during launch, the reducing of friction during in-flight use and the volume occupied by the bearing as a whole. 
   The angular position of the gimbal is given at any instant by the coder exhibiting a part fixed rigidly to the plinth  10  and a rotor part linked to the support structure. 
   It is in particular possible to use an optical coder, with incremental output in the form of quadrature signals that can be processed by proximity electronics capable of operating in fine pointing mode. 
   An optical coder exhibits numerous advantages relative to electrical coders such as resolvers. It makes it possible to obtain high accuracy. It is possible to obtain accuracy of better than plus or minus three seconds of angle, amply sufficient for satisfactory positioning of the angular momentum. 
   The means for passing the measurement signals and the power supply, controlled from outside, have to tolerate the rotation of the gimbal, at least within a limited angular domain. 
   As indicated earlier, it is possible to use a rotating connector with rings and brushes. It has the advantage of not limiting the rotation of the gimbal, but the drawback of a frictional torque that may become high when the number of signals to be transferred is considerable. Another advantage of transmission by rings and brushes is the fact that the wheel can be allowed to drift freely in rotation during the launch phase. 
   It is also possible to use means for passing signals by multiconductor flexible cable and cable winder. Customary cable winders comprise a flexible cable containing a bundle of conductors, linking two drums that can rotate with respect to one another. Each end of the cable is fixed to one of the drums and the cable winds up and unwinds when the drums rotate with respect to one another. The frictional torque of such a winder is much smaller than that of a rotating connector and the contacts are better. 
   The flange  20  exhibits, in the case illustrated, a complex shape. It consists of a single piece for reasons of rigidity and robustness. Its outside surface takes the form of an angular sector of a surface of revolution. It has a truncated cone shaped fraction, ending in the rim  23  for fixing onto the tubular piece and a semicylindrical fraction also furnished with a reinforcing rim  51 . 
   To give the flange  20  high rigidity for low weight, the lateral wall of the flange is reinforced by ribs. These ribs comprise a partition  52 , linking the edges of the flange, and a partition  54  orthogonal to the first, placed in the mid-plane of the flange. The flange is fixed to the tubular piece by a row of regularly distributed screws  56 . 
   The casing of the wheel  14  is fixed to the flange by four screws  58  offset with respect to the mid-plane of the flange, so as to be close to the stiffening ribs. The wheel can have a construction of known type. For example, it comprises a leaktight casing and a spinner. The casing is furnished with a support plate which carries the bearings on which the spinner rotates, the stator of the spinner drive motor and a tachometer. The internal construction of the wheel will not be described in detail since it may be of known type. 
   In a general manner, the spinner is rotated at high speed, generally constant. The spinner drive motor comprises, for example, a torque motor with no brushes and no iron, generally electronically switched, whose torque compensates for the frictional energy dissipations. 
   During operation, it is necessary to remove the heat dissipated, in particular by the motors, and that due to the friction without excessive heating and without excessive thermal gradient in components that are sensitive thereto. Additionally, it is advisable to seek good compatibility of the thermal expansion coefficients of the various components. 
   In a satellite, thermal dissipation can occur only by conduction or by radiation to the cold wall of the body of the satellite. The flange  20  is interposed between the wheel and the wall. It can be constructed from a good heat conducting material, such as aluminum, and its external face can be blackened to improve emission. To decrease the thermal gradient in the bearings of the gimbal, the cone is advantageously made of a material having low conductivity, such as titanium. 
     FIG. 5 , where the components corresponding to those of  FIGS. 2 to 4B  are designated by the same reference number, shows a variant embodiment. This variant is more suited than the previous embodiment to the use of a thick wheel, that is to say of a wheel whose thickness/diameter ratio is increased. 
   In this case, the penetration of the wheel  14  into the cone of the tubular piece  19  is reduced and there is no penetration of the wheel into the plinth  10 . 
   The arrangement shown in  FIG. 5  makes it possible moreover for the vertical space required to be less than that of an actuator exhibiting the construction shown in  FIG. 2 . The bearing  18  and the motor  30  are placed substantially at the same height, coaxially with one another. The means for transferring signals and power to the outside comprise a rotating commutator with ring  34 , placed inside the spans  24  and  26  of the tubular piece  19 . An optical sensor is then placed under the span  26 . 
   In another variant, the relative arrangement of the motor  30  and of the bearing  18  is reversed with respect to that shown in  FIG. 1 . From a mechanical point of view, the arrangement in which a bearing of large diameter is arranged radially outside the motor is favorable from the mechanical point of view. However, on the other hand this arrangement leads to high initial friction on commencing operation, while the actuator is cold. 
   In yet another embodiment, the rotating commutator is placed at the same axial level as the motor and the bearing, radially inside them. 
   Yet other embodiments are possible. In particular for satellites of relatively small size and small weight (a few hundred kg), it may be appropriate to use yet thicker wheels than in the case of  FIG. 5 , thereby reducing the possibility of penetration. 
   In a general manner, it is desirable for the actuator to comply with the following conditions:
         the maximum diameter of the gimbal, in the zone closest to the axis of rotation of the wheel, is less than or equal to the diameter of the cylinder swept by the wheel during the rotation of the gimbal, but at the same time be greater than the thickness of the wheel,   the diameter of the plinth, just where it is fixed to the platform of the satellite, is less than or at most equal to the maximum diameter of the support structure.