#apollo applications program

SCAN AND REMASTERED by Dan Beaumont: link

"Artist's rendering shows how Command Service Module (CSM) will dock with the Orbiting Workshop (OWS) during the Skylab mission. Assisting in the docking is the VHF Ranging System designed and built by RCA Government Communications Systems, Camdem, N.J. The system provides the CMS pilot with the range between the two spacecraft. Ranging is performed by sending radio tones from the CSM to the workshop, which retransmits them to the CSM. The range is determined by measuring the time between the transmission of the tones and receipt of the OWS retransmitted."

Date: May 12, 1973

"The Titan III-L series was a Martin Marietta concept (late 1960’s into early 1970’s) for a heavy lift derivative of the Titan IIIC launch vehicle. The core would be increased in diameter from 10 feet to 15, and the number of liquid propellant rocket engines increased from two to four. Additionally, the vehicle could be given two, four or six solid rocket motors (Titan III-L2, Titan III-L4, Titan III-L6). The Titan III-L6 concept was considered as a first stage booster for the Space Shuttle.

The Titan III-L2 had enough lift capacity to launch an Apollo-derived capsule and service module, providing an alternative to the Saturn IB for space station logistics and crew transfer."

"This photograph, taken during the assembly of the Flight Article of the Skylab Airlock Module (AM) at McDornell Douglas in St. Louis, Missouri, shows the truss assembly. The AM enabled crew members to conduct extravehicular activities outside Skylab as required for experiment support. Separated from the Workshop and the Multiple Docking Adapter by doors, the AM could be evacuated for egress or ingress of a space-suited astronaut through a side hatch. Oxygen and nitrogen storage tanks needed for Skylab's life support system were mounted on the external truss work of the AM. Major components in the AM included Skylab's electric power control and distribution station, environmental control system, communication system, and data handling and recording systems. The Marshall Space Flight Center was responsible for the design and development of the Skylab hardware and experiment management."

"This space station, which appears from the art style to be a Grumman design, is a single-launch space station to be launched atop a Saturn V. The two arms would fold back for storage on the launch vehicle and would deploy once in orbit. An Apollo CSM is shown approaching for docking along the centerline; it’s not clear if the docking cone was rotationally decoupled. if it was not, the two Apollo-like capsules hanging off the sides of the cone are a bit of a head scratcher."

Date: 1969

Portraits of all three Skylab Astronaut crews.

This was a study initiated in 1962 for space stations designs using the Gemini Spacecraft and later on the Apollo CSM. Boeing and Douglas received Phase I contracts in June 1964.

MORL/S-IVB Concept

"A 5 metric ton 'dry' space station, launched by Saturn IB, with Gemini or Apollo being used for crew rotation. The 6.5 meter diameter and 12.6 meter long station included a docking adapter, hangar section, airlock, and a dual-place centrifuge. Douglas was selected by NASA LaRC for further Phase 2 and 3 studies in 1963 to 1966. Although MORL was NASA's 'baseline station' during this period, it was dropped by the late 1960's in preference to the more capable station that would become Skylab.

Different docking concepts studied.

The Manned Orbital Research Laboratory was the brainchild of Carl M Houson and Allen C. Gilbert, two engineers at Douglas. In 1963 they proposed a Mini Space Station using existing hardware, to be launched by 1965. A Titan II or Atlas would be launched with a payload of control system, docking adapter and hangar module. The visiting crew would use the payload to transform the empty fuel tank of the last stage of the rocket into pressurized habitat (a so-called 'wet' space station). Provisions were available for 4 astronauts for a 100 day stay. Crew members would arrive two at a time aboard Gemini spacecraft. Equipment included a two-place centrifuge for the astronauts to readapt to gravity before their return to earth.

An early MORL concert. Artwork by Gordon Phillips.

In June 1964 Boeing and Douglas received Phase I contracts for further refinement of MORL station designs. The recommended concept was now for a 13.5 metric ton 'dry' space station, launched by Saturn IB, with Gemini or Apollo being used for crew rotation. The 6.5 meter diameter and 12.6 meter long station included a docking adapter, Hangar section, airlock, and a dual-place centrifuge.

"Medium-sized orbiting lab is this Manned Orbital Research Laboratory (MORL) developed for NASA's Langley Lab by Douglas Missiles & Spacecraft Division. The lab which weighs about 35,000 pounds, could maintain 3 to 6 men in orbit for a year.

Orbiting Stations: Stopovers to Space Travel by Irwin Stambler, G.P. Putnam's Sons, 1965."

Douglas was selected by NASA LaRC for further Phase 2 and 3 studies in 1963 to 1966. The major system elements of the baseline that emerged included:

A 660-cm-diameter laboratory launched by the Saturn IB into a 370-km orbit inclined at 28.72 degrees to the equator

A Saturn IB launched Apollo logistics vehicle, consisting of a modified Apollo command module, a service pack for rendezvous and re-entry propulsion, and a multi-mission module for cargo, experiments, laboratory facility modification, or a spacecraft excursion propulsion system.

Supporting ground systems.

MORL Phase IIb examined the utilization of the MORL for space research in the 1970s. Subcontractors included:

Eclipse-Pioneer Division of Bendix, stabilization and control

Federal Systems Division of IBM, communications, data management, and ground support systems

Hamilton Standard Division of the United Aircraft Corporation, environmental control/life support

Stanford Research Institute, priority analysis of space- related objectives

Bissett-Berman, oceanography

Marine Advisors, oceanography

Aero Services, cartography and photogrammetry

Marquardt, orientation propulsion

TRW, main engine propulsion.

The original MORL program envisioned one or two Saturn IB and three Titan II launches. Crew would be 6 to 9 Astronauts. After each Gemini docked to the MORL at the nose of the adapter, the crew would shut down the Gemini systems, put the spacecraft into hibernation, and transfer by EVA to the MORL airlock. The Gemini would then be moved by a small manipulator to side of the station to clear docking adapter for arrival of the next crew."

"Docking was to have 3 ports, all Nose Dock config, with spacecraft modifications totaling +405 lbs over the baseline Gemini spacecraft (structure beef-up, dock provisions, added retro-rockets, batteries, a data link for rendezvous, temp. control equip. for long-term, unoccupied Gemini storage on-orbit and removal of R&D instruments)."

"Later concepts including docking a Saturn-IB launched space telescope to MORL. At 4 meter diameter and 15 meter long, this would be the same size as the later Hubble Space Telescope. The crew would have to make EVA's to recover the film from the camera.

In 1965 Robert Sohn, head of the Technical Requirements Staff, TRW Space Technology Laboratories, proposed a detailed plan for early manned flight to Mars using MORL. The enlarged MORL-derived mission module would house six to eight men and be hurled on a Mars flyby by a single Saturn MLV-V-1 launch. MORL-derived Mars mission modules cropped up in other Douglas Mars studies until superseded by the 10-m diameter Planetary Mission Module in 1969.

MORL/Space Telescope

Why was MORL never launched ?

NASA had a need for a Space Station and MORL was little, easy and cheap. But NASA had more ambitious plans, embodied in the Apollo Applications Orbital Workshop (later called Skylab)."

-information from astronautix.com: link

source, source, source

NARA: 6375661, S66-17592

Sketches by W. Taub outlining Soviet and American spacecraft characteristics. Prepared in 1969 for the Apollo Soyuz Test Program. Of note is the Gemini and Big G capsule sketches and the lack of the docking module for the Apollo Capsule.

The Apollo's cabin atmosphere was 100 percent oxygen at 0.34 atmosphere pressure, while that of Soyuz was nitrogen/oxygen at 1.0 atmosphere. This necessitated the docking module for the two crews to interact with one another.

source, source, source

Mission patch for rescue mission for SL-3

Spacecraft: CSM-119

Launch Vehicle: Saturn IB AS-208, later AS-209

Commander: Vance D. Brand

Command Module Pilot: Don L. Lind

Intended launch date: September 1973, (on standby from August 1973 - February 1974)

Skylab rescue mission crewmen Vance Brand (left) and Don Lind.

"Influenced by the stranded Skylab crew portrayed in the book and movie 'Marooned', NASA provided a crew rescue capability for the only time in its history." Prepared for launch during Skylab 3."

"Skylab rescue vehicle phasing - NAR Space Division drawing illustrates phasing of 5-seater Skylab rescue vehicle for a Skylab mission."

Date: April 5, 1971

"A kit was developed to fit out an Apollo command module with a total of five crew couches. In the event a Skylab crew developed trouble with its Apollo CSM return craft, a rescue CSM would be prepared and launched to rendezvous with the station. It would dock with the spare second side docking port of the Skylab docking module."

- information from Astronautix.com: link

"The Apollo Command Module as modified to rescue stranded crews for the Skylab program. Two crew + three rescuees packed like sardines...."

"Skylab 3 astronauts Alan Bean and Jack Lousma helped design the "field modification kit" to use a standard CSM for rescue, and would have flown the CSM for their mission to rescue Skylab 2 if necessary. The standard Skylab Command Module accommodated a crew of three with storage lockers on the aft bulkhead for resupply of experiment film and other equipment, as well as the return of exposed film, data tapes and experiment samples. To convert the standard CSM to a rescue vehicle, the storage lockers were removed and replaced with two crew couches to seat a total of five crewmen."

Posted on Flickr by Mike Acs. NASA ID: 108-KSC-70P-69

"Soon after Skylab 3's launch the crew's CSM developed a problem with Quad B, one of its four reaction control system thrusters. On August 2, 1973, six days later, a snowstorm-like effect outside the station startled the crew during breakfast. What appeared to be 'a real blizzard' was fuel leaking from Quad D, opposite from Quad B. The malfunctions left two available quads, and while the spacecraft could operate with just one, the leaks posed a possible risk to other systems. The fuel for all quads and the main service propulsion system (SPS) engine were from the same batch; if the SPS fuel was contaminated, the CSM might not be able to deorbit.

source

NASA considered bringing the crew home immediately, but because the astronauts were safe on the station with ample supplies and because plans for a rescue flight existed,  the mission continued while the Saturn IB rocket AS-208 with CSM-119 was assembled in the Vehicle Assembly Building at Launch Complex 39 for possible use. It was at one point rolled out to LC-39B.

Illustration of the rescue Apollo spacecraft preparing to dock at Skylab’s lateral port. source

NASA announced on August 4 that Skylab 3 and Skylab 4 backup crewmen Vance Brand and Don Lind would fly any rescue mission; they had immediately begun training for the flight once the second quad had failed on August 2. After engineers found that the leaks would not disable the spacecraft, the two men used simulators to test reentry using two quads. If ground personnel worked 24 hours a day and skipped some tests, the mission could launch on September 10, and would last no more than five days. The astronauts would attempt to prepare Skylab for further use but returning experimental data and diagnosing the cause of the problem were more important, with Lind choosing what would be brought back. Human urine and feces samples and Apollo Telescope Mount and other film were the priorities. Although Skylab had two docking ports the primary one would be used if possible, jettisoning the Skylab crew's CSM if necessary.

Posted on Flickr by Drew Granston: link

While many within NASA believed that the rescue mission would occur, within hours of the failure of the second quad the agency canceled the rescue mission. Beyond NASA's conclusion that the failed quads would not disable the Skylab 3 CSM and the SPS fuel was uncontaminated, Brand and Lind had already shown during their training as backup Skylab crewmen that a reentry with failed quads was safe. They also devised a method to deorbit with the command module's attitude control system. Later joking that they were 'very efficient but perfectly stupid, because we have literally worked ourselves out of the mission', Brand and Lind continued to train for a rescue mission, as well as for their backup roles, but the Skylab 3 crew was able to complete its full 59-day mission on the station and safely return to Earth using the two functional RCS thruster quads,  using the SPS engine once instead of twice as precaution."

- Information from Wikipedia: link

Posted on Flickr by Ed Dempsey: link

Saturn IB SA-208 was used for Skylab 4 and SA-209 was assigned to the standby rescue mission. At one point, CSM-119/SA-209 was slated for the Skylab 5 mission but it was cancelled when SL-4 was extended and completed all of it objectives.

Mission patch for rescue mission for SL-4

Later, CSM-119/SA-209 was the backup launch vehicle for Apollo-Soyuz Test Project mission and standby rescue vehicle. After the Apollo program ended, the surplus rocket and spacecraft were displayed at the Kennedy Space Center, Florida.

NASA ID: 71-H-662, S73-31922