1. A method for determining an angle-of-rotation position of a shaft of an internal combustion engine, comprising:
detecting information about at least incremental angles of rotation of the shaft and running times for each incremental angle of rotation, the detecting being performed on the basis of signals that indicate a rotation of the shaft and are spaced with an interval between them and stored at least temporarily as stored information; and
determining an instantaneous angle-of-rotation position in a period of time between two signals by extrapolation of the angle-of-rotation position thus detected, taking into account at least one of an angular velocity and a change in angular velocity extrapolated from the stored information.
2. The method as recited in claim 1, further comprising:
forming mean values for at least one of the angular velocity and the change in angular velocity to reduce an influence of short-term fluctuations in a rotational speed.
3. The method as recited in claim 1, further comprising:
defining an instantaneous period for sequences that repeat during operation of the internal combustion engine; and
analyzing, for the extrapolation, information from at least one of the instantaneous period and at least one period in the past.
4. The method as recited in claim 3, further comprising:
selecting the instantaneous period as one of a working cycle of the internal combustion engine, a crankshaft revolution, and a firing interval.
5. The method as recited in claim 1, wherein a desired angle-of-rotation position resolution is selectable through a number of items of information analyzed in the extrapolation.
6. The method as recited in claim 1, further comprising:
performing the extrapolation of at least one of the angular velocity and the change in angular velocity in a time range.
7. The method as recited in claim 1, further comprising:
performing the extrapolation of at least one of the angular velocity and the change in angular velocity in a frequency range.
8. The method as recited in claim 7, wherein the extrapolation is performed in accordance with a Fourier series whose coefficients are determined by a recursive method.
9. The method as recited in claim 1, further comprising:
assigning a point in time to each of values determined for the angle-of-rotation position.
10. The method as recited in claim 1, further comprising:
when using a sensor wheel that rotates with the shaft and has a tooth gap, determining estimated angular velocities at virtual positions for teeth missing in the tooth gap.
11. The method as recited in claim 1, wherein the angle-of-rotation position of the shaft includes a crank angle of a crankshaft.
12. A device for determining an angle-of-rotation position of a shaft of an internal combustion engine, comprising:
a signaling device that indicates a rotation of the shaft on the basis of signals having time intervals between them;
a detection device allocated to the signaling device and ascertaining information concerning at least incremental angles of rotation of the shaft and running times for each incremental angle of rotation;
a memory for storing at least temporarily the incremental angles of rotation and the running times as stored information; and
a logic circuit for determining an instantaneous angle-of-rotation position in a period of time between two signals by extrapolation of the angle-of-rotation position detected, the determining taking into account at least one of an angular velocity and a change in angular velocity extrapolated from the stored information.
13. The device as recited in claim 12, wherein the angle-of-rotation position of the shaft includes a crank angle of a crankshaft.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A composite structure comprising:
a first unit fiber composite layer having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0;
a second unit fiber composite layer having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0 with respect to the fiber directions of about 0\xb0 of the first unit fiber composite layer and a first side adjacent the first fiber composite layer and a second opposed side in relation to the first composite layer, the layers being secured together adjacent each other in an overlapping manner such that a portion of the fibers from the first unit composite layer is disposed through the second unit fiber composite layer and in locking contact with the second opposed side;
at least a third unit fiber composite layer having a plurality of third fibers having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0 with respect to the fiber directions of about 0\xb0 of the first unit fiber composite layer and a third side adjacent the second fiber composite layer and a fourth opposed side, such that a portion of fibers from the second unit composite layer is disposed through the third layer and in locking contact with the fourth opposed side; and
resin secured to each of the composite unit layers, the unit layers being three-dimensionally woven together with fibers from the first unit composite layer being mechanically linked to fibers from one of the third unit fiber composite layer and a deeper composite layer.
2. The composite structure of claim 1, wherein the composite unit layers comprise at least one of a curved or non-planar section.
3. The composite structure of claim 2, further comprising a fourth skin composite layer attached to only a tangent of the one of the curved or non-planar section.
4. The composite structure of claim 1, wherein the composite layers define a cylindrical shape.
5. The composite structure of claim 1, wherein the composite layers define a substantially semi-spherical shape.
6. The composite structure of claim 1, wherein the composite layers define a repeating corrugated shape.
7. The composite structure of claim 1, wherein the composite layers provide aircraft armor operable to substantially stop complete projectile perforation.
8. The composite structure of claim 1, wherein the composite layers provide land vehicle armor operable to substantially stop complete projectile perforation.
9. The composite structure of claim 1, wherein fibers in one of the composite layers are oriented at or between 60\xb0 and \u221260\xb0 relative to an adjacent composite layer.
10. A composite structure comprising:
a first fiber composite layer having a first reinforcing layer having a plurality of first fibers having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0;
at least a second fiber composite layer having a plurality of second fibers having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0 in relation to the relative fiber direction of about 0\xb0 of the first composite layer, the second layer having a first side adjacent the first fiber composite layer and a second opposed side, a portion of the fibers from the first unit composite layer being disposed through the second layer in contact with the second opposed side;
a third fiber composite layer having a third reinforcing layer having a plurality of third fibers having a respective relative fiber directions of about 0\xb0, and 60\xb0 and \u221260\xb0, in relation to the relative fiber direction of about 0\xb0 of the first composite layer, the third layer having a third layer opposed side, a portion of the fibers from the second unit composite layer being disposed through the third layer and in contact with the third layer opposed side;
resin secured to each of the composite unit layers.
11. The composite structure of claim 10, further comprising an optically clear matrix, and wherein the first fibers and second fibers are optically clear.