1. A method for determining a flight characteristic of an object in a flight path, the flight characteristic being at least one of a position, a linear velocity, a rotational velocity, and an acceleration, the method comprising:
arranging a radiation source in a plane, the plane being located to intersect the flight path of the object, the radiation source irradiating the object at least at the intersection with the flight path;
providing at least first and second surface features on the object, the at least first and second surface features having a predetermined configuration;
measuring, with a sensor, reflected radiation from the at least first and second surface features; and
determining the flight characteristic based on the measured reflected radiation and the predetermined configuration.
2. The method of claim 1, wherein said flight characteristic is determined at one or more positions of said object’s flight path.
3. The method of claim 1, wherein said first and second surface features are a single surface feature having a prescribed thickness and a first and second edge for measuring reflected radiation therefrom.
4. The method of claim 1, wherein said radiation source is an optical transmitter operable to transmit optical radiation.
5. The method of claim 4, wherein the optical transmitter is a laser.
6. The method of claim 1, wherein said radiation source is an infrared transmitter operable to transmit infrared radiation.
7. The method of claim 6, wherein the infrared transmitter is a low-power infrared laser.
8. The method of claim 1, wherein said at least first and second surface features are protrusions on the surface of said object.
9. The method of claim 1, wherein said at least first and second surface features are grooves embedded within said object’s surface.
10. The method of claim 1, wherein said at least first and second surface feature are reflective paint applied to the surface of said object.
11. The method of claim 1, wherein said first surface features comprise a plurality of equally spaced parallel measurement lines applied to a surface of said object oriented parallel to said flight path.
12. The method of claim 1, wherein said second surface features comprise a plurality of equally spaced parallel measurement lines applied to a surface of said object oriented perpendicular to said flight path.
13. The method of claim 1, wherein said at least second surface features comprise a plurality of equally spaced parallel measurement lines applied to a surface of said object, said measurement lines oriented perpendicular to said flight path.
14. The method of claim 1, wherein said determining step further comprises calculating a velocity flight characteristic of said object in accordance with the following equation:
VL=Da-bTDa\u2212TDb
where:
Da-b\u2014is the physical distance between said two adjacent equally spaced parallel measurement lines;
TDa\u2014is the time of detection of said incident illumination reflected from a first measurement line; and
TDb\u2014is the time of detection of said incident illumination reflected from a second measurement line.
15. The method of claim 1, wherein said determining step further comprises calculating said object’s position during flight by determining a time at which a first measurement line included among said first surface feature on said object is intersected by an illumination line emitted by said radiation source.
16. The method of claim 1, wherein said determining step further comprises calculating an acceleration flight characteristic of said object in accordance with the following equation:
AL=(VL1\u2212VL2)TD1-2
where:
VL1\u2014a first linear velocity measurement,
VL2\u2014a second linear velocity measurement, and
TD1-2\u2014the time elapsed between the first and second linear velocity measurements.
17. The method of claim 1, wherein said determining step further comprises calculating an average angular velocity flight characteristic of said object in accordance with the following equation:
VR1=\u03b812TR1-2
where:
\u03b812\u2014is the angle corresponding to the arc of the circle that a plane of intersection normal to the axis of rotation X\u2032 would make with a cylindrical object between two angular velocity measurement lines, and
TR1-2 an elapsed time interval between the two intersected lines.
18. The method of claim 1, wherein said detecting step further comprises illuminating said first and second surface features with incident energy from said radiation source, wherein said energy is reflected from portions of said first and second measurement surface features.
19. A method for determining a rotational speed of an object as the object moves in a direction of linear motion, comprising the steps of:
arranging at least one transceiver in a plane, said plane being located to intersect said flight path of said object;
detecting, with said at least one transceiver, in order, a first, a second and a third surface feature on said projectile, wherein said first and third surface features are straight lines perpendicular to the direction of motion and said second surface feature is an equilateral triangle perpendicular to the direction of motion;
determining time differences for arrival of reflections of said first, second and third detected surface features with said at least one transceiver; and
calculating said rotational speed from said determined time differences and from a geometry of said first, second and third surface features.
20. A method for determining the linear velocity and rotational velocity of an object of arbitrary shape, comprising:
arranging a first transceiver in a first plane, said first plane being located to intersect said flight path of said projectile along a first tracing line passing through the center of said object;
arranging a second transceiver in a second plane, said second plane being located to intersect said flight path of said object along a second tracing line being a distance D from said first ray tracing line;
determining a first linear velocity of said object along a first tracing line,
determining a second linear velocity of said object along a second tracing line; and
calculating said rotational velocity from of said object as the difference between said first and second linear velocities.
21. Apparatus for determining, without contact, at least one of a position, a velocity, and an acceleration of an object in a flight path, said apparatus comprising:
at least one radiation source and corresponding receiver arranged in a first plane, said first plane being located to intersect said flight path of said projectile;
means for illuminating with said radiation source, at least a first and a second surface feature on said object;
means for detecting, with said receiver, at least a first and a second surface feature on said object;
means for determining time differences for arrival of reflections of said at least first and second detected surface features with said receiver; and
means for calculating a flight characteristic from said determined time differences and a known spacing of said at least first and second detected surface features.
22. The apparatus of claim 21, wherein the radiation source is an optical transmitter and the receiver is an optical receiver.
23. The apparatus of claim 18, wherein the radiation source is an infrared transmitter and the receiver is an infrared receiver.
24. A projectile comprising:
a casing having at least first and second surface features provided on a surface thereof for reflecting radiation from a source to a sensor, the at least first and second surface features having a predetermined configuration.
25. The projectile of claim 24 wherein said surface features comprise a one-dimensional geometric shape.
26. The projectile of claim 25, wherein the one-dimensional geometric shape is a line.
27. The projectile of claim 26, wherein the line is one of a straight or curved line.
28. The projectile of claim 27, wherein the line is applied to the surface of the projectile by one of painting, etching and machining.
29. The projectile of claim 24 wherein at least said second surface features comprise a two-dimensional geometric shape.
30. The projectile of claim 29, wherein the two-dimensional geometric shape is a triangle.
31. The projectile of claim 24 wherein the surface features comprise a plurality of detector-wells embedded in said surface and configured to regulate an amount of radiation reaching detectors embedded in said detector wells.
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 filter having a fibrous ceramic component and a coating treated with inert nanoparticles or vapor deposited inerting agent for monitoring ambient environments for determination of carbon fractions.
2. The filter of claim 1 having a coating containing at least one transition metal.
3. The filter of claim 1 having a coating containing an inorganic compound that does not decompose below 1100 degrees and is inert.