1. An imaging system, comprising:
an optical system;
an imaging device including a two-dimensional sensor array of pixel elements configured to capture an image created by energy incident upon the sensor array through the optical system;
a memory system; and
a processor device coupled to both the memory system and the imaging device, at least one of the imaging device, the memory system and the processor device including a sequential access memory device on which pixel data may be stored, the sequential access memory device comprising:
a memory array configured to store a group of bytes on each of a plurality of rows;
a plurality of bit-lines for transferring each of the group of bytes into and out of the memory array; and
a pre-charging unit configured to pre-charge the plurality of bit-lines once per each transfer of one of the group of bytes into or out of one of the plurality of rows of the memory array.
2. The imaging system of claim 1, wherein the sequential access memory device further comprises an address unit configured to generate a row select signal to select a predetermined row of the plurality of rows.
3. The imaging system of claim 2, wherein the row select signal is timed to select a row of the plurality of rows prior to the pre-charging of the plurality of bit-lines.
4. The imaging system of claim 2, wherein the address unit is further configured to generate a write-column signal to direct a byte of the group of bytes to a predetermined memory cell within the predetermined row.
5. The imaging system of claim 2, wherein the address unit is further configured to generate a read-column signal to direct a byte of the group of bytes from a predetermined memory cell within the predetermined row.
6. The imaging system of claim 1, wherein the pre-charging unit of the sequential access memory device further comprises a read-pre-charge unit configured to generate a read-pre-charge signal once for every transfer of one of the group of bytes out of one of the plurality of rows of the memory array.
7. The imaging system of claim 1, wherein the pre-charging unit of the sequential access memory device further comprises a write-pre-charge unit configured to generate a write-pre-charge signal once for every transfer of one of the group of bytes into one of the plurality of rows of the memory array.
8. The imaging system of claim 1, wherein the sequential access memory device further comprises a signal decoder and driver unit configured to transfer one of the group of bytes into or out of one of the plurality of rows of the memory array once per each pre-charge of the plurality of bit-lines.
9. A method of operating an imaging system, comprising:
capturing an image created by energy incident upon a two-dimensional sensor array of pixel elements within an imaging device;
transferring pixel data from the two-dimensional sensor array to a memory array located within a sequential access memory device, wherein access to the memory array is by a method comprising:
activating a selected row in the memory array, wherein the selected row is configured to store a group of bytes in a corresponding group of memory cells;
pre-charging a plurality of bit-lines a first time that provide access to the corresponding group of memory cells; and
accessing each of the group of memory cells before pre-charging the plurality of bit-lines a second time.
10. The method of claim 9, wherein activating a selected row comprises using an address unit row pointer to activate the selected row prior to the pre-charging of the plurality of bit-lines.
11. The method of claim 9, wherein pre-charging a plurality of bit-lines comprises using a read-pre-charge signal prior to reading the group of bytes from the corresponding group of memory cells.
12. The method of claim 9, wherein pre-charging a plurality of bit-lines comprises using a write-pre-charge signal prior to writing the group of bytes to the corresponding group of memory cells.
13. The method of claim 9, wherein accessing the group of memory cells comprises using a signal decoder and driver unit configured to transfer one of the group of bytes into or out of the selected row of the memory array once per each pre-charge of the plurality of bit-lines.
14. The method of claim 9, wherein accessing the group of memory cells comprises generating a write-column signal to direct a byte of the group of bytes to a selected memory cell within the selected row.
15. The method of claim 9, wherein accessing the group of memory cells comprises generating a read-column signal to direct a byte of the group of bytes from a selected memory cell within the selected row.
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 method of cleaning a liquid hydrocarbon-cooled bipropellant rocket engine, the method comprising:
heating the engine to a given temperature;
applying ozone to flow through channels in the engine wall for a period of time; and
determining the given temperature and the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
2. The method of claim 1 wherein the step of heating the engine to the given temperature comprises the given temperature in a range from 150\xb0 C. to 200\xb0 C.
3. The method of claim 1 wherein the step of heating the engine to the given temperature comprises the given temperature in a range from 160\xb0 C. to 180\xb0 C.
4. The method of claim 1 wherein the step of applying ozone to flow through channels in the engine wall for a period of time comprises the period of time within a range of 10 to 60 minutes.
5. The method of claim 1 wherein the step of applying ozone to flow through channels in the engine wall for a period of time comprises the period of time within a range of 10 to 20 minutes.
6. The method of claim 1 wherein the step of applying ozone to flow through channels in the engine wall for a period of time comprises the period of time within a range of about 15 minutes.
7. The method of claim 1 wherein the step of determining the given temperature and the period of time are each sufficient to remove the carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine comprises maintaining the engine at the given temperature and flowing the ozone through the channels for the period of time based on a size of the engine.
8. The method of claim 1 wherein the step of determining the given temperature and the period of time are each sufficient to remove the carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine comprises maintaining the engine at the given temperature and flowing the ozone through the channels for the period of time based on a size of the engine.
9. The method of claim 1 wherein the step of determining the given temperature and the period of time are each sufficient to remove the carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine comprises maintaining the engine at the given temperature and flowing the ozone through the channels for the period of time based on thermal imaging of the heat transfer surfaces.
10. The method of claim 1 further comprising placing an insulating jacket on an outside surface of the rocket engine so as to maintain the engine at the given temperature.
11. The method of claim 1 further comprising placing an electric heating mantle on an outside surface of the rocket engine so as to maintain the engine at the given temperature.
12. The method of claim 1 further comprising placing an insulating jacket and an electric heating mantle on an outside surface of the rocket engine so as to maintain the engine at the given temperature.
13. The method of claim 11 further comprising placing a heating manifold insert within an interior region of the rocket engine so as to maintain the engine at the given temperature.
14. The method of claim 1 further comprising placing a heating manifold insert within an interior of the rocket engine so as to maintain the engine at the given temperature.
15. The method of claim 1 further comprising directing a path of heat flow from a propane burner within an interior of the rocket engine so as to maintain the engine at the given temperature.
16. The method of claim 1 further comprising purging the engine with nitrogen to remove fuel prior to applying ozone.
17. The method of claim 1 further comprising thermally imaging the heat transfer surfaces.
18. The method of claim 17 wherein the thermal imaging of the heat transfer surfaces includes directing a thermal camera toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
19. The method of claim 18 wherein the thermal imaging of the heat transfer surfaces includes a mirror guide disposed within the interior region of the rocket engine, a mirror selectively moveable along the mirror guide, and an actuator to reposition the mirror along the mirror guide at different distances from the thermal camera with the thermal camera being directed toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
20. The method of claim 19 further comprising processing a position of the mirror with respect to the mirror guide so as to determine a position of an imaged location of the heat transfer surfaces of the rocket engine.
21. A method of cleaning a liquid hydrocarbon-cooled bipropellant rocket engine, the method comprising:
heating the engine to a given temperature;
applying ozone to flow through channels in the engine wall for a period of time; and
thermally imaging the heat transfer surfaces to determine the given temperature and the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
22. The method of claim 21 wherein the thermal imaging of the heat transfer surfaces includes directing a thermal camera toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
23. The method of claim 22 wherein the thermal imaging of the heat transfer surfaces includes a mirror guide disposed within the interior region of the rocket engine, a mirror selectively moveable along the mirror guide, and an actuator to reposition the mirror along the mirror guide at different distances from the thermal camera with the thermal camera being directed toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
24. The method of claim 23 further comprising processing a position of the mirror with respect to the mirror guide so as to determine a position of the thermal camera with respect to an imaged location on the heat transfer surfaces of the rocket engine.
25. The method of claim 23 further comprising purging the engine with nitrogen to remove fuel prior to applying ozone.
26. A method of cleaning a liquid hydrocarbon-cooled bipropellant rocket engine, the method comprising:
heating the engine to a given temperature;
applying ozone to flow through channels in the engine wall for a period of time; and
monitoring at least one of carbon dioxide and water emitted from the channels to determine the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
27. The method of claim 26 further comprising monitoring infrared thermal imaging of the engine to determine the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
28. The method of claim 26 further comprising purging the engine with nitrogen to remove fuel prior to applying ozone.
29. A method of cleaning a liquid hydrocarbon-cooled bipropellant rocket engine, the method comprising:
heating the engine to a given temperature;
applying ozone to flow through channels in the engine wall for a period of time; and
monitoring infrared thermal imaging of the engine to determine the period of time is sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
30. The method of claim 29 further comprising monitoring carbon dioxide emitted from the channels to determine the period of time is sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
31. The method of claim 29 further comprising mapping coke deposits based on the step of monitoring infrared thermal imaging to determine where the coke deposits are located in the channels in the engine wall.
32. The method of claim 29 further comprising purging the engine with nitrogen to remove fuel prior to applying ozone.
33. The method of claim 29 further comprising purging the engine with nitrogen to remove fuel prior to applying ozone.
34. Apparatus for cleaning a liquid hydrocarbon-cooled bipropellant rocket engine, the apparatus comprising:
a heater configured to heat the engine to a given temperature; and
an ozone source configured to apply a flow of ozone to channels in the engine wall for a period of time.
35. Apparatus according to claim 34 further comprising a thermal camera configured to thermally image the heat transfer surfaces to determine the given temperature and the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
36. Apparatus according to claim 34 further comprising a carbon dioxide detector configured to monitor carbon dioxide emitted from the channels to determine the period of time are each sufficient to remove carbonaceous deposits from heat transfer surfaces of the liquid hydrocarbon-cooled bipropellant rocket engine.
37. Apparatus according to claim 34 further comprising a nitrogen source configured to purge the engine with nitrogen to remove fuel prior to applying ozone.
38. The apparatus of claim 34 wherein the thermal camera has a lens directed toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
39. The apparatus of claim 38 further including a mirror guide disposed within the interior region of the rocket engine, a mirror selectively moveable along the mirror guide, and an actuator to reposition the mirror along the mirror guide at different distances from the thermal camera with the lens of the thermal camera being directed toward an interior region of the rocket engine so as to image the heat transfer surfaces of the rocket engine.
40. The apparatus of claim 39 further comprising a processor configured to receive a position of the mirror with respect to the mirror guide so as to determine a position of an imaged location of the heat transfer surfaces of the rocket engine.
41. The apparatus of claim 34 further comprising an insulating jacket configured to cover an outside surface of the rocket engine so as to maintain the engine at the given temperature.
42. The apparatus of claim 34 further comprising an electric heating mantle configured to cover an outside surface of the rocket engine so as to maintain the engine at the given temperature.
43. The apparatus of claim 34 further comprising an insulating jacket and an electric heating mantle configured to cover an outside surface of the rocket engine so as to maintain the engine at the given temperature.
44. The apparatus of claim 43 further comprising a heating manifold insert configured to position within an interior region of the rocket engine so as to maintain the engine at the given temperature.
45. The apparatus of claim 34 further comprising a heating manifold insert configured to position within an interior of the rocket engine so as to maintain the engine at the given temperature.
46. The apparatus of claim 34 further comprising a propane burner configured to direct a path of heat flow from within an interior of the rocket engine so as to maintain the engine at the given temperature.
47. The apparatus of claim 34 further comprising a source of nitrogen configured to purge the engine with the nitrogen to remove fuel prior to applying ozone.