Editing AS-103 (section)

==Launch==
[[Image:Saturn SA9 launch.jpg|left|thumb|230px|AS-103 (SA-9) 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 [[Apollo command module|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.<ref>{{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}}</ref>

The vehicle was launched from Cape Kennedy Launch Complex 37B at 9:37:03&nbsp;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.<ref>{{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}}</ref>{{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 (spacecraft)|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°.