AS-201

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AS-201
AS-201 launch.jpg
Launch of AS-201, the first flight of the Apollo spacecraft and Saturn IB launch vehicle
Mission type Suborbital test flight
Operator NASA
Mission duration 37 minutes, 19.7 seconds
Range 8,477 kilometers (4,577 nautical miles)
Apogee 492.1 kilometers (265.7 nautical miles)
Spacecraft properties
Spacecraft Apollo CSM-009
Manufacturer North American Aviation
Launch mass 15,294 kilograms (33,718 lb)
Start of mission
Launch date February 26, 1966, 16:12:01 (1966-02-26UTC16:12:01Z) UTC
Rocket Saturn IB SA-201
Launch site Cape Canaveral LC-34
End of mission
Landing date February 26, 1966, 16:49:21 (1966-02-26UTC16:49:22Z) UTC
Landing site North Pacific Ocean
16°07′N 168°54′E / 16.117°N 168.900°E / 16.117; 168.900 (AS-202 splashdown)

Apollo program
← AS-105 AS-203

AS-201 (or SA-201), flown February 26, 1966, was the first unmanned test flight of an entire production Block I Apollo Command/Service Module and the Saturn IB launch vehicle. The spacecraft consisted of the second Block I command module and the first Block I service module. The suborbital flight was a partially successful demonstration of the service propulsion system and the reaction control systems of both modules, and successfully demonstrated the capability of the Command Module's heat shield to survive re-entry from low Earth orbit.

Vehicle configuration[edit]

Spacecraft[edit]

The Command and Service Module CSM-009 was a Block I version, designed before the Lunar Orbit Rendezvous method was chosen for the Apollo lunar landing; therefore it lacked capability to dock with the Apollo Lunar Module. Block I also employed preliminary designs of certain subsystems, and was heavier than the Block II version with lunar mission capability. All previous command and service modules flown (with one exception) were boilerplate versions.

CM-009 was the second production Block I command module to fly, the first being CM-002 flown on a Little Joe 2 rocket for the final Launch Escape System abort test, designated A-004. CM-009 varied from the production configuration by the omission of the guidance and navigation system; crew couches, displays, and associated equipment; and by the addition of a control programmer and open-loop emergency detection system.

SM-009 was the first production Block I service module to fly. It varied from the production configuration by replacement of the electrical power-generating fuel cells with batteries, and omission of the S-band communication equipment.

The launch also included a Block I Launch Escape System (LES), and the first flight of the Spacecraft-LM Adapter (SLA) which connected the spacecraft to the launch vehicle.

Launch vehicle[edit]

Main article: Saturn IB

The Saturn IB was the uprated version of the Saturn I rocket flown in ten earlier Apollo missions. It featured an upgrade of the first stage engines to increase thrust from 1,500,000 lbf (6,700 kN) of thrust to 1,600,000 lbf (7,100 kN), and replacement of the second stage with the S-IVB. This stage used a new liquid hydrogen-burning J-2 engine which would also be used on the S-II second stage of the Saturn V lunar launch vehicle. A modified version of the S-IVB, with an in-space restartable J-2, would also be used as the third stage of the Saturn V. It also used a new model of the guidance and control system known as the Instrument Unit, which would also be used on the Saturn V.

Objectives[edit]

The objectives of the mission were to:

  • Demonstrate the Saturn IB launch vehicle propulsion, guidance and electrical systems
  • Demonstrate structural compatibility between the launch vehicle and CSM, ensuring the spacecraft's design loads weren't exceeded
  • Demonstrate appropriate separation of all vehicle elements
  • Demonstrate the CSM's heat shield, service propulsion system (including in-space restart), CM and SM reaction control systems, environmental control of cabin pressure and temperature, partial communications, stability and control, Earth landing system, and electrical power subsystem.
  • Evaluate the Emergency Detection System in an open-loop configuration
  • Demonstrate the CM heat shield ablator at a 200 BTU/ft2/sec heat transfer rate
  • Demonstrate support facilities for launch, mission control, and recovery

The mission profile called for the Saturn IB to launch the spacecraft on an east-by-southeast heading into a high ballistic trajectory; then the CSM would separate from the SLA. The service module engine would be fired twice, then the command module would re-enter and land in the south Atlantic ocean.

Preparation for flight[edit]

The first piece of the rocket to arrive at the Cape was the S-IB stage on August 14, 1965 by the barge Promise. It was built by Chrysler and featured eight H-1 engines built by Rocketdyne. The S-IVB second stage arrived next on September 18. The Instrument Unit that would control the launch vehicle arrived October 22, the Command Module arrived three days later and the Service Module on October 27.

The first stage was erected at the pad soon after arriving at Cape Canaveral. The second stage joined it on October 1. After fixing some problems in the Instrument Unit it was mated to the S-IVB on October 25. The CSM was mated on December 26.

The first problem encountered by NASA came on October 7. The RCA 110A computer which would test the rocket and thus automating the process was ten days behind schedule meaning that it would not be at the Cape before November 1. This meant that by the middle of October little could be done at the pad. When the computer finally did arrive it continued to have problems with the punch cards and also the capacitors that did not operate well under a protective coating. In the end however the testing of the launch vehicle was still on schedule.

Testing was running around the clock during December. Technicians were testing the CSM's fuel systems during the day and the testing was running on the rocket at night.

There was even an instance of a variant of the Y2K bug in the computer. As it ran past midnight, when the time changed from 2400 to 0001 the computer could not handle it and "turned into a pumpkin" according to an interview with Frank Bryan, a Kennedy Space Center Launch Vehicle Operations Engineering staff member.

In the end the testing regimen slowly completed and the plugs-out tests were completed proving that the rocket could function by itself.

Flight[edit]

Launch attempt[edit]

The first launch attempt on 25 February 1966 looked as though it would be the real thing. As always there were several small delays, but when the pressure in one of the fuel tanks in the S-IVB fell below the allowed limits, the onboard computer aborted the launch with 4 seconds left.

The problem was easily fixable but it was thought that it could not be done in the launch window. However, some members of the launch team thought that it could and convinced the managers to let them run a simulated launch and 150 seconds of flight to show that the rocket could operate with the lower pressure in the fuel tank. They found it could be and the launch was de-scrubbed.

Flight[edit]

Finally, after months of delays and problems, the first flight of the Saturn IB lifted off from Pad 34. The first stage worked perfectly lifting the rocket to 57 km, when the S-IVB took over and lifted the spacecraft to 425 km. The CSM separated and continued upwards to 488 km.

The CSM then fired its own rocket to accelerate the spacecraft towards Earth. The first burn lasted for 184 seconds. It then fired ten seconds later for ten seconds. This proved that the engine could restart in space, a crucial part of any manned flight to the Moon.

It entered the atmosphere traveling 8300 m/s. It splashed down only 37 minutes after launch, 72 km from the planned touch down point, and was on board the USS Boxer two hours later.

Problems[edit]

AS-202 CM-009 exhibited at the Strategic Air and Space Museum.

There were three problems encountered on the flight. The Service Module engine only worked properly for 80 seconds, interrupted by the presence of helium pressurant gas in the combustion chamber. Helium was used to pressurize the fuel tanks but should not have been in the combustion chamber. This was caused by a break in an oxidizer line that allowed helium to mix with the oxidizer.

The second problem was an electrical system failure which caused the Command Module to lose steering control during reentry. Lastly, measurements that were meant to be taken during reentry failed due to a short circuit. Both of these problems were found to be due to bad wiring, and were easily fixed.

Capsule location[edit]

After the flight the capsule was also used for drop tests at White Sands Missile Range. It is now on display at the Strategic Air and Space Museum, Ashland, Nebraska.

See also[edit]

External links[edit]

 This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.