Robotic Lunar Exploration Home Page
Lunar Reconnaissance Orbiter Overview: The Instrument Suite and Mission
Apollo Laser Altimeter
Size:
C&T Board: 4" x 6" (Command and Telemetry)
RMU Board: 6" x 8" (Range Measurement Unit)
Mass:
without (staking and conformal coat): 613 grams
with staking and conformal coat: 628 grams
Power:
In flight the 1.5V supply (for the FPGA's core) is derived from the 3.3V supply via a low voltage dropout regulator.
The +5V supply is used for the MIL-STD-1553B transceiver.
The +12V supply is used for the TDC-S1 microcircuits; a significantly lower supply could be used to save power. +12V was an available system voltage.
Current (mA)
12V 5V 3.3V and 1.5V
(combined)3.3V 1.5V +60 °C 463 40 640 +25 °C 408 38 464 225 236 -30 °C 342 35 438
Data from March 18-19, 2008 Thermal/Air Test: (after rework and after vibe)
Power
Smalley On Smalley Off 12V 5V 3.3V and 1.5V
(combined)1.5V 3.3V and 1.5V
(combined)1.5V 1.5 Legend +81 °C 510 40 737 1809 670 1719 C&T: 18-9 986 986 RMU: 8-9 +60 °C 470 40 619 1385 552 1294 C&T: 18-9 763 763 RMU: 8-9 +25 °C 415 38 536 1046 470 956 C&T: 18-9 577 577 RMU: 8-9 -30 °C 345 36 505 858 441 769 C&T: 18-9 453 453 RMU: 8-9
Thermistors
(GSFC-S-311-P-18 Rev G: Dash -07, -08)
C&T RMU Board
(19-20)MSK
(21-22)LM117
(19-20)TDC
(21-22)Actel
(23-24)Board
(25-26)+81 °C 1.13k
89°C0.99k
93°C1.02k
92°C1.06k
91°C1.11k
89°C1.17k
87°C+60 °C 2.23k
66°C2.01k
69°C1.98k
70°C2.07k
69°C2.18k
67°C2.27k
66°C+25 °C 7.79k
31°C7.05k
34°C6.78k
35°C7.18k
33°C7.60k
32°C7.96k
31°C-30 °C 96.3k
-24°C88.0k
-21°C84.9k
-21°C88.6k
-22°C93.9k
-23°C100k
-24°C
Duty Cycle (%)
TDC No. 0 1 2 3 4 5 6 7 8 9 10 11 +81 °C 80 87 82 88 84 86 84 86 86 86 82 83 +60 °C 64 71 66 71 68 70 68 70 69 70 66 67 +25 °C 42 47 43 48 45 47 45 47 46 47 44 44 -30 °C 13 17 14 17 16 17 15 17 16 17 15 15
Data from March 13, 2008 Thermal/Air Test: (after rework and prior to vibe)
Power
Smalley On Smalley Off 12V 5V 3.3V and 1.5V
(combined)1.5V 3.3V and 1.5V
(combined)1.5V 1.5 Legend +85 °C 510 40 724 1766 mV 658 1670 mV C&T: 18-9 982 mV 982 mV RMU: 8-9 +60 °C 459 40 602 1319 mV 536 1226 mV C&T: 18-9 736 mV 736 mV RMU: 8-9 +25 °C 405 38 529 1025 mV 464 934 mV C&T: 18-9 561 mV 561 mV RMU: 8-9 -30 °C 341 36 504 843 mV 440 754 mV C&T: 18-9 450 mV 450 mV RMU: 8-9
Thermistors
(GSFC-S-311-P-18 Rev G: Dash -07, -08)
C&T RMU Board
(19-20)MSK
(21-22)LM117
(19-20)TDC
(21-22)Actel
(23-24)Board
(25-26)+85 °C 1.19k 1.09k 1.01k 1.08k 1.14k 1.18k +60 °C 2.61k 2.43k 2.17k 2.34k 2.49k 2.57k +25 °C 9.33k 8.74k 7.60k 8.31k 8.86k 9.17k -30 °C 122k 112k 97k 108k 116k 120k
Duty Cycle (%)
TDC No. 0 1 2 3 4 5 6 7 8 9 10 11 +85 °C 80 87 81 88 84 86 83 86 85 86 82 82 +60 °C 62 69 63 69 66 68 65 67 66 68 64 64 +25 °C 40 46 41 46 43 45 43 45 44 45 41 42 -30 °C 12 16 13 16 14 16 14 15 14 15 13 13
May 2, 2008: MIL-STD-1553B Transformer Fix
March 13, 2008: DU Boards Installed Into Housing
March 12, 2008: After replacing reversed cap and Nusil under LM117's
Digital Unit: C&T and RMU
C&T
RMU
The Magnesium Housing
October 16, 2007: Preparation of the Digital Unit box
October 13, 2007: Pictures from coating and staking
Delivery, just prior to conformal coat. October 5, 2007.
LOLA was inspired in part by the old Pioneer probes ... and we've dusted off some test equipment from that era! September 26, 2007.
Running Smalley3, October 19, 2007
FM1, Pre-delivery, August 22, 2007
Range Measurement Board
Command and Telemetry Board
FM Delivery, August 2007
More pictures of the 1553 "Rod Chip", February 16, 2006
Some reading ...
Unmanned Space Project Management: Surveyor and Lunar Orbiter1972
NASA SP-4901
Erasmus H. KlomanIntroduction (excerpt)
One of the valuable byproducts of the U S. space program is the body of knowledge concerning management of large complex development project activities. The brief span of years since the formation of NASA has witnessed the rapid evolution of a variety of systems and techniques for directing the combined efforts of thousands of individuals cooperating in closeknit programs in which Government, university, and private industry play mutually reinforcing roles. Many of the major learning experiences, such as those in the Apollo management system, have been applied to other activities within NASA. There has been only limited effort, however, to distill the generalized management experience gained in other NASA projects for application outside the space agency itself.Note: NASA commissioned the National Academy of Public Administration to undertake this study to look at its innovative management techniques on these complex technological projects.
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Last Revised:
May 02, 2008
Web Grunt: Richard
Katz
