AS-103
{{Short description|Third orbital flight test of a boilerplate Apollo spacecraft, February 16, 1965}}
{{use mdy dates|date=September 2021}}
{{More citations needed|date=December 2013}}
{{Infobox spaceflight
| name = AS-103
| image = Pegasus satellite.jpg
| image_caption = Pegasus micrometeoroid detection satellite as flown aboard AS-103
| insignia =
| mission_type = Spacecraft aerodynamics;
Micrometeoroid investigation
| operator = NASA
| COSPAR_ID = 1965-009B
| SATCAT = 1088
| mission_duration = 3 years, 6 months, 13 days
| orbits_completed = ~75,918
| distance_travelled = {{convert|3114579139|km|mi|sp=us}}
| spacecraft = Apollo BP-16
Pegasus 1
| manufacturer =
| launch_mass = {{convert|15375|kg|lb}}
| landing_mass =
| launch_date = {{start date text|February 16, 1965, 14:37:03|timezone=yes}} UTC
| launch_rocket = Saturn I SA-9
| launch_site = Cape Kennedy LC-37B
| disposal_type = Decommissioned
| deactivated = {{end date text|August 29, 1968}}
| decay_date = July 10, 1985
| orbit_epoch = 22 March 1965{{cite web|url=https://nssdc.gsfc.nasa.gov/nmc/spacecraft/displayTrajectory.action?id=1965-009A |title=NSSDCA Pegasus-1 Trajectory Details | website=NASA|access-date=26 May 2025}}
| orbit_reference = Geocentric
| orbit_regime = Low Earth orbit
| orbit_periapsis = {{convert|430|km|mi|sp=us}}
| orbit_apoapsis = {{convert|523|km|mi|sp=us}}
| orbit_inclination = 31.7 degrees
| orbit_period = 94.10 minutes
| apsis = gee
| previous_mission = AS-102
| next_mission = AS-104
| programme = Apollo program
}}
AS-103 was the third orbital flight test of a boilerplate Apollo spacecraft, and the first flight of a Pegasus micrometeoroid detection satellite. Also known as SA-9, it was the third operational launch of a two-stage Saturn I launch vehicle.
Objectives
Of 12 flight objectives assigned, two were concerned with the operation of the Pegasus satellite, eight with launch vehicle systems performance, one with jettisoning the launch escape system, and one with separation of the boilerplate spacecraft. The satellite objectives were (1) demonstration of the functional operations of the mechanical, structural, and electronic systems and (2) evaluation of meteoroid data sampling in near-Earth orbit. Since the launch trajectory was designed to insert the Pegasus satellite into the proper orbit, it differed substantially from the trajectory used in missions AS-101 and AS-102.
Launch
The launch vehicle consisted of an S-I first stage, an S-IV second stage, and an instrument unit. The spacecraft consisted of a boilerplate command and service module, a launch escape system, and a service module/launch vehicle adapter (BP-16). The Pegasus 1 satellite was enclosed within the service module, attached to the S-IV stage. The orbital configuration consisted of the satellite mounted on the adapter, which remained attached to the instrument unit and the expended S-IV stage.{{cite web|url=https://nssdc.gsfc.nasa.gov/nmc/spacecraft/display.action?id=1965-009A |title=NSSDCA - SA-9 |website=NASA |access-date=May 25, 2025}}
The vehicle was launched from Cape Kennedy Launch Complex 37B at 9:37:03 a.m. EST (14:37:03 GMT) on February 16, 1965. A hold of 1 hour and 7 minutes was caused by a power failure in the Eastern Test Range flight safety computer. A built-in hold of 30 minutes was also used to discharge and recharge a battery in the Pegasus satellite as a check that it was functioning properly.{{cite report|url=https://ntrs.nasa.gov/api/citations/19660020046/downloads/19660020046.pdf |title=SA-9/Apollo firing test report |first=E.R. |last=Matthews |date=March 10, 1965 |publisher=NASA |access-date=May 25, 2025}}{{rp|5}}
The launch was normal, and the spacecraft was inserted into orbit approximately 10.5 minutes after launch. The launch escape system was jettisoned during launch and the command module was jettisoned after orbital insertion. The Pegasus satellite weighed approximately {{convert|3980|lb|kg}} and was {{convert|208 by 84 by 95|inch|m}}. The width of the deployed wings was {{convert|96|ft|m}}. The total mass placed in orbit was {{convert|33,895|lb|kg}}. The perigee was {{convert|307.8|mi|km}}, the apogee was {{convert|461.9|mi|km}}, and the orbital inclination was 31.76°.
Results
The trajectory and space-fixed velocity were very nearly as planned. The Apollo shroud separated from the Pegasus satellite about 804 seconds after lift-off, and deployment of two meteoroid detection panel wings of the Pegasus satellite commenced about 1 minute later. The predicted useful lifetime of Pegasus A in orbit was 1188 days. The satellite was commanded off (decommissioned) on August 29, 1968. Although minor malfunctions occurred in both the launch vehicle and the Pegasus A satellite, mission AS-103 was a success in that all objectives were met. The spacecraft remained in orbit until July 10, 1985, when it re-entered the atmosphere and landed in the ocean.{{cite web |url=https://ntrs.nasa.gov/api/citations/19650016419/downloads/19650016419.pdf |title=Saturn SA-9/Pegasus A Postflight Trajectory |first1=Jonathan B. |last1=Haussler|first2=Robert H. |last2=Benson |publisher=NASA |access-date=May 25, 2025}}
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References
{{Include-NASA}}
{{Reflist}}
{{Portal|Spaceflight}}
{{Apollo program| before=AS-102| after=AS-104
A-003}}
{{Orbital launches in 1965}}
{{Use American English|date=January 2014}}
Category:Spacecraft launched in 1965
Category:1965 in the United States