PDS_VERSION_ID = PDS3 LABEL_REVISION_NOTE = "20090626, L. Gaddis - Initial Version 20101001, C. Isbell - Post Review" RECORD_TYPE = STREAM OBJECT = MISSION MISSION_NAME = "LUNAR ORBITER V" OBJECT = MISSION_HOST INSTRUMENT_HOST_ID = "LO5" OBJECT = MISSION_TARGET TARGET_NAME = MOON END_OBJECT = MISSION_TARGET END_OBJECT = MISSION_HOST OBJECT = MISSION_INFORMATION MISSION_START_DATE = 1967-08-01 MISSION_STOP_DATE = 1968-01-31 MISSION_ALIAS_NAME = "LO5" MISSION_OBJECTIVES_SUMMARY = "As described in MISSION_DESC below." MISSION_DESC = " THE LUNAR ORBITER V MISSION =========================== Overview -------- Much of the information in this document was abstracted from the Lunar Orbiter mission pages of the National Space Science Data Center (NSSDC) Web site (http://nssdc.gsfc.nasa.gov/nmc/spacecraftDisplay.do?id=1967-075A). See references cited for more detail. The Lunar Orbiter V was the last of the Lunar Orbiter missions, one of the most successful projects ever run by NASA [e.g., Boeing Company, 1968a, b; Hansen, 1970; Kosofsky and El-Baz, 1970; Bowker and Hughes, 1971; Byers, 1977].. The first three missions achieved the program's primary objective, to provide necessary information to meet the requirements for Apollo landing sites. Mission IV contributed to broader scientific goals, achieving near-vertical photography of virtually all of the nearside, most at a ground resolution of 60 to 80 meters. The success of the previous missions allowed Mission V to further extend the project objectives. Lunar Orbiter V was designed to fill in where gaps were left by the previous missions with near vertical, convergent telephoto stereo and oblique images and. In addition, Mission V was to obtain close up photographs of geologically interesting features in 36 areas of the Moon's nearside and to provide broad survey images of the previously unphotographed parts of the Moon's far side. LO V also collected selenodetic, radiation intensity, and micrometeoroid impact data and was used to evaluate the Manned Space Flight Network tracking stations and Apollo Orbit Determination program. The Lunar Orbiter V spacecraft was launched from Cape Kennedy on 1967-08-01 by an Atlas-Agena launch vehicle. The spacecraft was placed in a cislunar trajectory and on 1967-08-05 was injected into an elliptical near-polar lunar orbit, 194.5 km by 6023 km, with an inclination of 85 degrees and a period of 8 hours, 30 minutes. On 1967-08-07 the perilune was lowered to 100 km and on 1967-08-09 the orbit was lowered to 99 km x 1499 km with a 3 hour, 11 minute period. The closest approach was 97 km. The spacecraft acquired photographs between 1967-08-06 and 1967-08-18, and readout occurred through 1967-08-27. A total of 633 high resolution and 211 medium resolution frames at resolution down to 2 meter resolution were taken. Lunar Orbiter V had a highly inclined orbit of 85o and an increase in the number of individual photographic sites and in the number of frames used for farside photography. Mission V required operation beyond the initial program requirements and, with few exceptions, each of the 213 photo exposures required individual two- or three-axis spacecraft maneuvers. The spacecraft took 174 photographs in 50 sequences during 69 orbits. Specific targets of interest included 45 sites on the nearside and 24 sites on the farside. The photo mission was accomplished according to permission plans with the addition of the Earth photo site and some photo relocations. A significant amount of photo data was read using priority readout mode prior to Bimat cut. The constant solar radiation created additional temperature and attitude control requirements. Objectives ---------- Mission V was executed precisely as planned and accomplished each of its assigned objectives. Since the three previous Lunar Orbiters had completed the required needs for Apollo mapping and site selection, the last two flights were able to focus more on broadening scientific knowledge of the Moon. Lunar Orbiter IV provided coverage of over 99% of the lunar nearside and LO IV results were used to identify targets for LO V so that about 50% of the Mission V sites were altered. The primary objective of Mission V was to obtain scientifically interesting photographs on the near and far side of the Moon and to complete the photo requirements for the candidate Apollo sites. This combination necessitated two orbital changes. Photographic altitudes for the near side were on the order of 100 to 250 km in order to provide adequate aerial coverage and acceptable ground resolution with the limited film supply and to fill the remaining Apollo requirements for converging coverage. The increase in altitude enabled these photographs to be taken with less cross-track tilt than used previously [Hansen, 1970]. One dual frame was also taken that shows a nearly full Earth. The secondary objectives were to provide precision trajectory information to better define the lunar gravitational field, measurements of micrometeoroid flux and radiation dose, and a spacecraft to be tracked in lunar orbit to evaluate its effectiveness for Apollo. Accurate data were acquired from these experiments throughout the mission. The radiation dosimetry measurement system functioned normally and radiation dosage during the 27-day photo mission was extremely low. One micrometeoroid hit struck the detectors on the periphery of the tank deck with no apparent effect. MISSION OPERATIONAL PHASES ========================== Mission phases were defined for significant spacecraft activity periods. For all five Lunar Orbiter missions, phases included at least the launch, trajectory, orbit insertion, orbital operations (primarily photographic imaging), and surface impact phases. The Lunar Orbiter V spacecraft was a three-axis stabilized vehicle with three-axis stabilization and attitude control provided by four one-lb nitrogen gas jets. The attitude reference for yaw and pitch was provided by a Sun sensor in the equipment mounting plate so that the solar panels normally faced the Sun. The roll axis reference was provided by an electro-optical sensor that tracked the star Canopus, although in this mission Canopus was used as a reference only and the roll axis was maintained in inertial hold. Because of the continued solar illumination, the spacecraft was pitched from 30 to 54 degrees away from sunline about two thirds of the mission to maintain temperature control. Launch ------ The Lunar Orbiter V spacecraft was launched from Cape Canaveral, Florida on 1967- 08-01 22:23:00 GMT [e.g., Boeing, 1968a, b]. The launch window was only four hours, from 1600 to 2000 EDT, but fortunately a rainstorm improved, allowing the launch at 22:33 GMT. A delay of one day would have meant the loss of a 13 degree portion of the far side to photography. Launch was achieved using an Atlas-Agena D vehicle. Following separation from the Atlas, the Agena engine put the spacecraft into Earth orbit. The first- and second-stage boosters performed as programmed. Tracking and telemetry for the launch were provided by the Air Force Eastern Test Range (AFETR) Deep Space Network (DSN) and Manned Space Flight Network (MSFN) as elements of the Tracking and Data System (TDS). Spacecraft Id : 67-075A Target Name : MOON Mission Phase Start Time : 1967-08-01 Mission Phase Stop Time : 1967-08-01 Spacecraft Operations Type : ORBITER Cislunar Trajectory ------------------- Lunar Orbiter V was injected into the cislunar trajectory at the end of the Agena second burn, approximately 33 minutes after liftoff. The Deep Space Net Tracking Station at Woomera, Australia, acquired the spacecraft about 46 minutes after liftoff and the sun acquisition sequence was completed 4 minutes later. A star map was completed and Canopus located and verified at 19:00 GMT. 1967-08-02. A single midcourse trajectory correction at 31 hours, 27 minutes after launch of a velocity change of 29.76 meters per second was successful. Systems were normal and temperatures were within acceptable limits. Spacecraft Id : 67-075A Target Name : MOON Mission Phase Start Time : 1967-08-01 Mission Phase Stop Time : 1967-08-05 Spacecraft Operations Type : ORBITER Lunar Orbit Insertion --------------------- Accomplishing the objectives of Mission V required three different orbits for photography. The spacecraft was first injected into an elliptical near-equatorial lunar orbit on 1967-02-08 at 21:54 UT, 90.25 hours after liftoff with a velocity reduction of 643 meters per second. This initial orbit had an apolune of 6,028 km, a perilune of 195 km, and an orbital inclination of 85.01 degrees to the lunar equator and a period of 8 hours, 21 minutes. Spacecraft Id : 67-075A Target Name : MOON Mission Phase Start Time : 1967-08-05 Mission Phase Stop Time : 1967-08-06 Spacecraft Operations Type : ORBITER Orbit Transfer and Lunar Imaging -------------------------------- Photography was initiated in the second orbit approximately 18.5 hours after lunar injection on 1967-08-06 and began with the farside. At apolune of Orbit 4, the velocity was reduced 15.97 meters per second to reduce the intermediate orbit perilune to 100 km with an inclination of 85.61 degrees and a period of 8 hours, 21 minutes. The third orbit was achieved with a 233.66 meter per second velocity change at perilune of Orbit 10 to place the spacecraft in the final elliptical orbit, of apolune 1,499 km, perilune 99 km and inclination of 84.76 degrees with a period of 3 hours, 12 minutes. Each orbit photographed the far side and nearside photography was initiated during Orbit 15. The spacecraft maintained its final ellipse for 74 orbits and 41 nearside and 13 farside photo sites were photographed during 63 separate sequences. Photography ended 1967-08-18 and the photographic portion of the mission was terminated on 1967-08-26 with the completion of the final readout. The craft had successfully covered five Apollo sites, 36 science sites, 23 previously un-photographed areas on the far side, and a view of the nearly fully illuminated Earth. Of the total of 213 dual-frame exposures, 174 were made of 41 sites located on the nearside and 37 of previously unphotographed areas on the far side. One frame was used to obtain the near full Earth photo from near apolune of the intermediate ellipse and one frame was used for film-set. The spacecraft was tracked to prepare for manned lunar missions. Spacecraft Id : 67-075A Target Name : MOON Mission Phase Start Time : 1967-08-06 Mission Phase Stop Time : 1967-08-26 Spacecraft Operations Type : ORBITER Surface Impact -------------- Lunar Orbiter V began its extended mission in late August. To survive the umbral eclipse of October 18 the craft's orbit was changed. A sudden loss of pressure in the nitrogen tank forced flight controllers to destroy the spacecraft prematurely to avoid losing it in orbit. Lunar Orbiter V was commanded to impact the moon at 2.79 degrees S latitude, 83.04 degrees W longitude on 1968-01-31. Spacecraft Id : 67-075A Target Name : MOON Mission Phase Start Time : 1967-08-26 Mission Phase Stop Time : 1968-01-31 Spacecraft Operations Type : ORBITER LUNAR ORBIT SUMMARY =================== The Agena placed the spacecraft on an extremely accurate trajectory so that on 1967-08-05 orbit determination by the Deep Space Instrumentation Facility (DSIF) showed the uncorrected spacecraft trajectory passing the trailing edge of the Moon [e.g., Boeing Company, 1968a, b]. Engine ignition for the deboost maneuver was on 1968-08 based on 42 hours of two-way Doppler data. The design philosophy was to guide the spacecraft from its approach trajectory into an elliptical orbit with the correct parameters. Orbit determinations and predictions were based on two orbit data arcs of two-way Doppler tracking data, but did not use ranging data, as there was no time during the complex mission. Mission V photography was conducted as planned except for the addition of an Earth photo and a slight relocation of some photo sites locations. Due to mission objectives requiring broad coverage of the farside and high resolution of the nearside, three different orbits were needed. The spacecraft was first injected into an elliptical near-equatorial lunar orbit on 1967-08-05 and photography was initiated in the second orbit approximately 18.5 hours after lunar injection on 1967-08-06. This initial orbit was designed for farside photography: a highly elliptical 85o-inclination orbit with about a 6,000 km apolune and a 200-km perilune, which allowed the camera axis to be tilted toward the illuminated portion over the farside, although tilt was not excessive due to the high altitude. At apolune of Orbit 4, the velocity was reduced 15.97 meters per second to reduce the intermediate orbit perilune to 100 km with an inclination of 85.61 degrees and a period of 8 hours, 21 minutes. Additional farside photography was accomplished during the intermediate orbit. The third orbit was achieved with a 233.66 meter per second velocity change at perilune of Orbit 10 to place the spacecraft in the final elliptical orbit, of apolune 1,499 km, perilune 99 km and inclination of 84.76 degrees with a period of 3 hours, 12 minutes. The spacecraft maintained its final ellipse for 74 orbits and 41 nearside and 13 farside photo sites were photographed during 63 separate sequences. Photo sites on the nearside were located between 42oS latitude and 50oN latitude. Apollo site photography was from altitudes between 96 and 103 km. The wide variations in latitude of the science sites resulted in photo altitudes ranging between 96 and 273 km. For nearside photography, the final orbit had a 1,500 km apolune and a 100-km perilune. Since the perilune altitude was about twice that of the first three missions the resolution for images would be 2 meters for the telephoto lens and 16 meters for the wide-angle lens, which was chosen to enable stereo coverage without excessive camera tilt. The higher altitude also allowed near-equatorial sites to be photographed with half the number of frames as o the first three missions, so a larger number of sites could be photographed. Photographic altitude depended on the latitude of the site. Photography ended 1967- 08-18 and the photographic portion of the mission was terminated on 1967-08-26 with the completion of the final readout. OBSERVATIONAL STRATEGY AND RESULTS ================================== Lunar Orbiter V was similar to the first three Lunar Orbiter missions but it had two important differences: a highly inclined (85 degree) orbit (as was the case for Lunar Orbiter IV) and the number of targeted photographic sites was higher [Boeing Company, 1968a, b]. Mission photography began August 6, 1967 at 11:24 GMT and ended August 18 at 21:40 GMT after 212 frames had been exposed. The photographic portion of the mission was terminated on August 26, 1967 after completion of the final readout. Photographic altitudes for the near side photos were two to five times greater (on the order of 100 km to 250 km) than for Missions I, II, and III to provide adequate areal coverage and acceptable ground resolution of each of the numerous sites with the limited film supply of the spacecraft [e.g., Hansen, 1970]. The increase in altitude was also desirable because most of the remaining Apollo requirements were for converging coverage and increased altitude enabled the photographs to be taken with less cross-track tilt than previously. All photo objectives for Mission V were accomplished [e.g., Beeler and Michlovitz, 1969; Boeing Company, 1968a, b; Hansen, 1970; Anderson and Miller, 1971]. Lunar Orbiter V provided detailed photos of ~40% of the far side which had not been photographed previously. Photo quality was extremely good. Nearside photo resolution was from 2 to 7 meters depending on spacecraft altitude and slant range. By the end of this mission, all Apollo landing sites had photographic coverage in vertical, oblique and convergent telephoto views." END_OBJECT = MISSION_DESC OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "ANDERSON&MILLER1971" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "BEELER&MICHLOVITZ1969" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "BOEINGCO1968A" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "BOEINGCO1968B" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "BOWKER&HUGHES1971" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "BYERS1977" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "HANSEN1970" END_OBJECT = MISSION_REFERENCE_INFORMATION OBJECT = MISSION_REFERENCE_INFORMATION REFERENCE_KEY_ID = "KOSOFSKY&ELBAZ1970" END_OBJECT = MISSION_REFERENCE_INFORMATION END_OBJECT = MISSION_INFORMATION END_OBJECT = MISSION END