(L) Howard Larson (R) Dr Dean Chapman discuss tektite studies during news conference

S64-04925 (September 1964) --- Diagram of Gemini spacecraft location of re-entry communications experiment planned for the Gemini-Titan 3 orbital flight.

S64-36908 (1962) --- Portrait view of astronaut M. Scott Carpenter, wearing Mercury pressure suit, posing for pictures during astronaut training at the Cape Canaveral, Florida. Photo credit: NASA

CAPE KENNEDY, Fla. -- At Cape Kennedy Air Force Station in Florida, a Delta C rocket stands poised for liftoff at Launch Complex 17A to boost the Explorer 21 satellite into orbit. Photo Credit: NASA

Group shot of the nucleus of the 1960 Flight Operations Division for the Mercury Program. Image taken at the Houston Petroleum Center (HPC) in Houston, TX, prior to their move to the Manned Spacecraft Center (MSC). This photo was published in the Space News Roundup, 07/08/1964. The women are (L-R): Doris Folkes, Cathy Osgood, Shirley Hunt and Mary Shep Burton. The men are (L-R): Dick Koos, Paul Brumberg, John O'Loughlin, Emil Schiesser, Jim Dalby, Morris Jenkins, Carl Huss, John Mayer, Bill Tindall, Hal Beck, Charlie Allen, Ted Skopinski, Jack Hartung, Glynn Lunney, John Shoosmith, Bill Reini, Lyn Dunseith, Jerry Engel, Harold Miller and Clay Hicks. ( 26644 ); Houston, TX

Bill Harrison and Bud Meilander check the setup of an Apollo Contour rocket nozzle in the Propulsion Systems Laboratory at the National Aeronautics and Space Administration (NASA) Lewis Research Center. The Propulsion Systems Laboratory contained two 14-foot diameter test chambers that could simulate conditions found at very high altitudes. The facility was used in the 1960s to study complex rocket engines such as the Pratt and Whitney RL-10 and rocket components such as the Apollo Contour nozzle, seen here. Meilander oversaw the facility’s mechanics and the installation of test articles into the chambers. Harrison was head of the Supersonic Tunnels Branch in the Test Installations Division. Researchers sought to determine the impulse value of the storable propellant mix, classify and improve the internal engine performance, and compare the results with analytical tools. A special setup was installed in the chamber that included a device to measure the thrust load and a calibration stand. Both cylindrical and conical combustion chambers were examined with the conical large area ratio nozzles. In addition, two contour nozzles were tested, one based on the Apollo Service Propulsion System and the other on the Air Force’s Titan transtage engine. Three types of injectors were investigated, including a Lewis-designed model that produced 98-percent efficiency. It was determined that combustion instability did not affect the nozzle performance. Although much valuable information was obtained during the tests, attempts to improve the engine performance were not successful.

S64-31455 (1964) --- Astronaut Frank Borman. Photo credit: NASA

CAPE CANAVERAL, Fla. -- Overall aerial view of "Missile Row," Cape Kennedy Air Force Station. The view is looking north, with the Vehicle Assembly Building under construction in the upper left-hand corner. Photo credit: NASA

George Low, Joseph Piland, Philip Hamburger, Congressman Olin Teague from Texas; and, Congressman Joe D. Waggoner from Louisiana at the entrance to Site 1, Clear Lake, prior to briefing for the House Subcommittee on Manned Spaceflight. MSC, Houston, TX

S64-19466 (13 April 1964) --- A press conference was held in the Bldg. 1 auditorium at the NASA Manned Spacecraft Center to announce the first Gemini astronaut selections. Shown left to right are Paul Haney, MSC Public Affairs Officer (standing); astronauts Walter Schirra and Thomas Stafford; Dr. Robert Gilruth, director of MSC; astronauts Virgil Grissom and John Young; and Donald K. Slayton, assistant director of Flight Crew Operations at MSC.

This is a photograph that was made on October 14, 1964 of Dr. von Braun while he toured the Marned Spacecraft Center, now the Johnson Space Center in Houston, Texas. He is shown inspecting a Gemini-Agena Docking Simulator.

S64-16482 (1964) --- At the Manned Spacecraft Center, Wesley Hjornevik, Assistant Director for Administration, with members of House Subcommittee and MSC Officials outside Central Data Building (Building 12) after briefing. Others pictured are Don Fuqua, Bob Casey, Edward J. Patten, Alec C. Bond, Maxime Faget, Wesley Hjornevik, Charles W. Mathews. Photo credit: NASA

Researchers prepare a Centaur-Surveyor nose cone shroud for a separation test in the Space Power Chambers at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Lewis was in the midst of an extensive effort to prepare the Centaur second-stage rocket for its missions to send the Surveyor spacecraft to the moon as a precursor to the Apollo missions. The nose fairing provided an aerodynamic shield for the payload, guidance system, and electronics package as the rocket traveled through the Earth’s atmosphere. Upon entering space, the thruster near the tip of the fairing forced the two pieces away from the space vehicle. The June 30, 1964 launch of Atlas-Centaur-3 was successful. Within a month of the launch, a Centaur shroud was obtained and installed in the Space Power Chambers. The facility was the only space tank in the country large enough to accommodate the hardware. The two halves of the fiberglass fairing were mounted vertically to a platform. Aluminum pads were set up on either side to catch the shroud halves as they were jettisoned, and a myriad of high-speed cameras were installed to record the tests. The shroud was badly damaged during the first test. It was replaced, and the test equipment redesigned. Over the course of 11 runs during the summer of 1964, the redesigned bulkhead was retested and the new fairing was validated by the final jettison on November 24, 1964. Just over two weeks later, Atlas-Centaur-4 successfully launched a mock-up Surveyor spacecraft into orbit. It was the first Centaur mission to have an error-free shroud jettison.

S64-31847 (10 Sept. 1964) --- Astronaut L. Gordon Cooper Jr. portrait

Artist: T Howard Interplanetary Pioneer 6 Spacecraft launched in 1965 to study the sun.

David Reese and Alvin Seiff interpret the results from tests designed to study spacecraft configuration and performance in a particular atmosphere

A researcher fills a small container used to represent a liquid hydrogen tank in preparation for a microgravity test in the 2.2-Second Drop Tower at the National Aeronautics and Space Administration (NASA) Lewis Research Center. For over a decade, NASA Lewis endeavored to make liquid hydrogen a viable propellant. Hydrogen’s light weight and high energy made it very appealing for rocket propulsion. One of the unknowns at the time was the behavior of fluids in the microgravity of space. Rocket designers needed to know where the propellant would be inside the fuel tank in order to pump it to the engine. NASA Lewis utilized sounding rockets, research aircraft, and the 2.2 Second Drop Tower to study liquids in microgravity. The drop tower, originally built as a fuel distillation tower in 1948, descended into a steep ravine. By early 1961 the facility was converted into an eight-floor, 100-foot tower connected to a shop and laboratory space. Small glass tanks, like this one, were installed in experiment carts with cameras to film the liquid’s behavior during freefall. Thousands of drop tower tests in the early 1960s provided an increased understanding of low-gravity processes and phenomena. The tower only afforded a relatively short experiment time but was sufficient enough that the research could be expanded upon using longer duration freefalls on sounding rockets or aircraft. The results of the early experimental fluid studies verified predictions made by Lewis researchers that the total surface energy would be minimized in microgravity.

A Centaur second-stage rocket is lowered into the vacuum tank inside the Space Power Chambers at NASA’s Lewis Research Center. Centaur was to be paired with an Atlas booster to send the Surveyor spacecraft to the moon as a precursor to the Apollo landings. Lewis was assigned responsibility for the Centaur Program after the failure of its first developmental flight in May 1962. Lewis’ Altitude Wind Tunnel was converted into two large test chambers—the Space Power Chambers. The facility’s vacuum chamber, seen here, allowed the Centaur to be stood up vertically and subjected to atmospheric conditions-- pressures, temperature, and radiation--similar to those it would encounter in space. The Centaur for these tests was delivered to Cleveland in a C‒130 aircraft on September 27, 1963. The rocket was set up in the facility’s high bay where Lewis technicians and General Dynamics consultants updated its flight systems to match the upcoming Atlas-Centaur‒4 mission. Months were spent reharnessing the Centaur’s electronics, learning about the systems, and being taught how to handle flight hardware. By early spring 1964, the extensive setup of both the spacecraft and the chamber was finally completed. On March 19 the Centaur was rolled out from the shop, hoisted high into the air by a crane, and lowered into the waiting space tank. Researchers were able to verify that the Centaur’s electronics and electrical systems functioned reliably in a space environment.

This photograph depicts a forward skirt being placed on the liquid oxygen tank for Saturn V S-IC (first) stage in the Manufacturing Engineering Laboratory at the Marshall Space Flight Center. Thirty-three feet in diameter, the fuel tanks hold a total of 4,400,000 pounds of fuel. Although this tankage was assembled at MSFC, the elements were made by the Boeing Company at Wichita and the Michoud Operations at New Orleans.

An inflight view from the left side of the Lunar Landing Research Vehicle, is shown in this 1964 NASA Flight Research Center photograph. The photograph was taken in front of the old NACA hangar located at the South Base, Edwards Air Force Base. When Apollo planning was underway in 1960, NASA was looking for a simulator to profile the descent to the Moon's surface. Three concepts surfaced: an electronic simulator, a tethered device, and the ambitious Dryden contribution, a free-flying vehicle. All three became serious projects, but eventually the NASA Flight Research Center's (FRC) Landing Research Vehicle (LLRV) became the most significant one. Hubert M. Drake is credited with originating the idea, while Donald Bellman and Gene Matranga were senior engineers on the project, with Bellman, the project manager. Simultaneously, and independently, Bell Aerosystems Company, Buffalo, N.Y., a company with experience in vertical takeoff and landing (VTOL) aircraft, had conceived a similar free-flying simulator and proposed their concept to NASA headquarters. NASA Headquarters put FRC and Bell together to collaborate. The challenge was; to allow a pilot to make a vertical landing on earth in a simulated Moon environment, one sixth of the earth's gravity and with totally transparent aerodynamic forces in a "free flight" vehicle with no tether forces acting on it. Built of tubular aluminum like a giant four-legged bedstead, the vehicle was to simulate a lunar landing profile from around 1500 feet to the Moon's surface. To do this, the LLRV had a General Electric CF-700-2V turbofan engine mounted vertically in gimbals, with 4200 pounds of thrust. The engine, using JP-4 fuel, got the vehicle up to the test altitude and was then throttled back to support five-sixths of the vehicle's weight, simulating the reduced gravity of the Moon. Two hydrogen-peroxide lift rockets with thrust that could be varied from 100 to 500 pounds handled the LLRV's rate of descent and horizontal transla

3/4 front view of XV-4A Hummingbird VTOL Research Vehicle in Ames 40x80 wind tunnel with Tom Wills in Photo.

3/4 front view Ryan XV-5A lift-fan VSTOL airplane. Pictured with Tom Wills.

APOLLO CONTOUR ENGINE MOUNTED IN THE PROPULSION SYSTEMS LABORATORY PSL NO. 2 TEST CELL

S64-32110 (1964) --- Astronaut Virgil I. (Gus) Grissom

3/4 front view offull scale X-22A ducted fan model. Chuck Greco

CAPE CANAVERAL, Fla. - The tracking board and consoles are seen inside the Mission Control Center during the early Gemini flights. The Mercury Mission Control Center in Florida played a key role in the United States' early spaceflight program. Located at Cape Canaveral Air Force Station, the original part of the building was constructed between 1956 and 1958, with additions in 1959 and 1963. The facility officially was transferred to NASA on Dec. 26, 1963, and served as mission control during all the Project Mercury missions, as well as the first three flights of the Gemini Program, when it was renamed Mission Control Center. With its operational days behind, on June 1, 1967, the Mission Control Center became a stop on the public tour of NASA facilities until the mid-90s. In 1999, much of the equipment and furnishings from the Flight Control Area were moved to the Kennedy Space Center Visitor Complex where they became part of the exhibit there. The building was demolished in spring 2010. Photo credit: NASA

S64-21560 (8 April 1964) --- Gemini/Titan-II launch vehicle #1 liftoff at Cape Kennedy, Florida.

S64-14286 (11 Feb. 1964) --- An artist's concept of Mercury: Medical effects; develop technology. Photo credit: NASA

Raymond Palmer, of the Electromagnetic Propulsion Division’s Plasma Flow Section, adjusts the traveling magnetic wave plasma engine being operated in the Electric Power Conversion at the National Aeronautics and Space Administration (NASA) Lewis Research Center. During the 1960s Lewis researchers were exploring several different methods of creating electric propulsion systems, including the traveling magnetic wave plasma engine. The device operated similarly to alternating-current motors, except that a gas, not a solid, was used to conduct the electricity. A magnetic wave induced a current as it passed through the plasma. The current and magnetic field pushed the plasma in one direction. Palmer and colleague Robert Jones explored a variety of engine configurations in the Electric Propulsion Research Building. The engine is seen here mounted externally on the facility’s 5-foot diameter and 16-foot long vacuum tank. The four magnetic coils are seen on the left end of the engine. The researchers conducted two-minute test runs with varying configurations and used of both argon and xenon as the propellant. The Electric Propulsion Research Building was built in 1942 as the Engine Propeller Research Building, often called the Prop House. It contained four test cells to study large reciprocating engines with their propellers. After World War II, the facility was modified to study turbojet engines. By the 1960s, the facility was modified again for electric propulsion research and given its current name.

The fuel tank assembly of the Saturn V S-IC (first) stage is readied to be mated to the liquid oxygen tank at the Marshall Space Flight Center. The fuel tank carried kerosene as its fuel. The S-IC stage utilized five F-1 engines that used kerosene and liquid oxygen as propellant. Each engine provided 1,500,000 pounds of thrust. This stage lifted the entire vehicle and Apollo spacecraft from the launch pad.

S64-31472 (1964) --- Astronaut David R. Scott. Photo credit: NASA

S64-31447 (10 Sept. 1964) --- Astronaut Roger B. Chaffee Editor's Note: Astronaut Chaffee died in the Apollo/Saturn 204 fire accident at Cape Canaveral, Florida, on Jan. 27, 1967, along with astronauts Virgil I. Grissom and Edward H. White II.

Developed at MSFC under the direction of Dr. Wernher von Braun, the SA-5 incorporated a Saturn I, Block II engine. Launched on January 29, 1964, SA-5 was the first two stage (Block II) Saturn with orbital capability and performed the first test of Instrument Unit and successful stage separation. Block II vehicles had two live stages, and were basically in the two-stage configuration of the Saturn I vehicle. There were marked changes between the Block I and II versions. The Block II S-I stage had eight fins added for greater aerodynamic stability in the lower atmosphere. All Block II H-1 engines had a thrust of 188,000 pounds each for a combined thrust over 1,500,000 pounds. The Block II second stage (S-IV) had six RL-10 hydrogen-oxygen engines, each producing a thrust of 15,000 pounds for a total combined thrust of 90,000 pounds. A motion picture camera capsule loated on stage I was successful recovered.

Dr Harold P. Klein at backboard

T-33 #351 Cockpit control panel. Feb. 13, 1964

View of a Saturn I on the launch pad for a Radio Frequency Interference Test, to be conducted at LC-37A. Cape Kennedy Missile Test Center

This photograph shows the components for the Saturn V S-IC stage fuel tank assembly in the Manufacturing Engineering Laboratory, building 4707, at the Marshall Space Flight Center (MSFC). Left to right are upper head, lower head, and forward skirt assembly. Thirty-three feet in diameter, they will hold a total of 4,400,000 pounds of fuel. Although this tankage was assembled at MSFC, the elements were made by the Boeing Company at Wichita and the Michould Operations at New Orleans.

S64-03507 (1964) --- Diagrams shows Gemini spacecraft responses to orbital attitude systems's thrusters. Firing of appropriate combination of the thrusters cause pitch, roll and yaw.

S64-40294 (19 Nov. 1964) --- Astronauts Virgil I. Grissom (center) and John W. Young (left), prime crew for the Gemini-Titan 3 mission, are shown inspecting the inside of Gemini spacecraft at the Mission Control Center at Cape Kennedy, Florida. Riley D. McCafferty is at right. Photo credit: NASA

S66-34051 (3 June 1966) --- Astronauts Thomas P. Stafford and Eugene A. Cernan arrive in the White Room atop Pad 19 at the Kennedy Space Center in preparation for the launch of the Gemini-9 spaceflight. Photo credit: NASA

This photograph shows how the fuel tank assembly and the liquid oxygen tank for the Saturn V S-IC (first) stage are placed side by side prior to commencement of the mating of the two stages in the Marshall Space Flight Center, building 4705. The fuel tank carried kerosene as its fuel. The S-IC stage used five F-1 engines, that used kerosene and liquid oxygen as propellant and each engine provided 1,500,000 pounds of thrust. This stage lifted the entire vehicle and Apollo spacecraft from the launch pad.

S64-04919 (September 1964) --- Diagram of reduction of the re-entry ionized plasma about a Gemini spacecraft by fluid injection, an experiment planned for the Gemini-Titan 3 orbital flight.

CAPE CANAVERAL, Fla. - Renamed the Mission Control Center, the facility continued to be the flight control through the first three missions of Project Gemini. The Mercury Mission Control Center in Florida played a key role in the United States' early spaceflight program. Located at Cape Canaveral Air Force Station, the original part of the building was constructed between 1956 and 1958, with additions in 1959 and 1963. The facility officially was transferred to NASA on Dec. 26, 1963, and served as mission control during all the Project Mercury missions, as well as the first three flights of the Gemini Program, when it was renamed Mission Control Center. With its operational days behind, on June 1, 1967, the Mission Control Center became a stop on the public tour of NASA facilities until the mid-90s. In 1999, much of the equipment and furnishings from the Flight Control Area were moved to the Kennedy Space Center Visitor Complex where they became part of the exhibit there. The building was demolished in spring 2010. Photo credit: NASA

Marshall Space Flight Center (MSFC) Director Dr. Wernher von Braun (left) with Kennedy Space Center (KSC) Rocco Petrone prior to the January 29, 1964 launch of SA-5, the first Block II configuration of the Saturn I launch vehicle. Petrone played key roles at KSC in the development of Saturn launch facilities before becoming director of launch operations in 1966.

Temporary quarters in the Huntsville Industrial Center (HIC) building located in downtown Huntsville, Alabama, as Marshall Space Flight Center (MSFC) grew. This image shows drafting specialists from the Propulsion and Vehicle Engineering Laboratory at work in the HIC building.

S64-34357 (22 Oct. 1964) --- Astronaut M. Scott Carpenter. NOTE: Commander M. Scott Carpenter, USN, resigned September 1967, and transferred to the U.S. Navy Project Sealab.

S64-13534 (1964) --- View of a Gemini-Titan spacecraft on launch pad at night. The launch pad lights are all on and there are spotlights in the background.

APOLLO STABILITY TEST IN THE 8X6 FOOT WIND TUNNEL - MODEL IS SHOWN WITH MODULE TOWER AND CANARDS

Portrait: Dr Cyril Ponnamperuma

The Saturn I S-IV stage (second stage) for the SA-7 mission being prepared for shipment to Cape Canaveral, Florida. The S-IV stage had six RL-10 engines, which used liquid hydrogen and liquid oxygen as its propellants, arranged in a circle. Each RL-10 engine produced a thrust of 15,000 pounds for a total combined thrust of 90,000 pounds. The SA-7 mission was launched on September 18, 1964 from Cape Canaveral, Florida, and its S-IV stage made the second orbital flight.

Engineer Bill Peterson fits test pilot Bob Smyth in spacesuit A-3H-024 with the LEM Astronaut restraint harness during suit evaluation study.

XV-5A airplane installed in 40x80ft Subsonic Wind Tunnel at NASA Ames Research Center with Tom Mills. The propulsive lift system was tested to determine power-on performance characteristics in preparation for flight tests.

The components of the Saturn V booster (S-IC stage) fuel tank are shown in this photograph. The liquid oxygen tank bulkhead on the left and both halves of the fuel tank were in the Marshall Space Flight Center (MSFC) Manufacturing Engineering Laboratory, building 4707. These components were used at MSFC in structural testing to prove that they could withstand the forces to which they were subjected in flight. Each S-IC stage has two tanks, one for kerosene and one for liquid oxygen, made from such components as these. Thirty-three feet in diameter, they hold a total of 4,400,000 pounds of fuel. Although this tankage was assembled at MSFC, the elements were made by the Boeing Company at Wichita and the Michoud Operations at New Orleans.

S64-27314 (1964) --- Dr. Mueller & General Funk trying on Apollo & Gemini suits. - Complete Caption Pending

S64-29926 (1964) --- Portrait of astronaut Michael Collins in a business suit. Photo credit: NASA

Originally the Rendezvous was used by the astronauts preparing for Gemini missions. The Rendezvous Docking Simulator was then modified and used to develop docking techniques for the Apollo program. The pilot is shown maneuvering the LEM into position for docking with a full-scale Apollo Command Module. From A.W. Vogeley, Piloted Space-Flight Simulation at Langley Research Center, Paper presented at the American Society of Mechanical Engineers, 1966 Winter Meeting, New York, NY, November 27 - December 1, 1966. The Rendezvous Docking Simulator and also the Lunar Landing Research Facility are both rather large moving-base simulators. It should be noted, however, that neither was built primarily because of its motion characteristics. The main reason they were built was to provide a realistic visual scene. A secondary reason was that they would provide correct angular motion cues (important in control of vehicle short-period motions) even though the linear acceleration cues would be incorrect. Apollo Rendezvous Docking Simulator: Langley s Rendezvous Docking Simulator was developed by NASA scientists to study the complex task of docking the Lunar Excursion Module with the Command Module in Lunar orbit.

S64-03506 (1964) --- Diagrams shows Gemini spacecraft functions of the thrusters in the Gemini spacecraft's re-entry control system. Thrusters may be fired in various combinations to cause yaw, roll and pitch.

APOLLO CONTOUR ENGINE MOUNTED IN THE PROPULSION SYSTEMS LABORATORY PSL NO. 2 TEST CELL

View of CT

A model of the Mariner-C spacecraft at the National Aeronautics and Space Administration (NASA) Lewis Research Center for a June 1964 Conference on New Technology. Mariner-C and Mariner-D were identical spacecraft designed by the Jet Propulsion Laboratory to flyby Mars and photograph the Martian surface. Mariner-C was launched on November 4, 1964, but the payload shroud did not jettison properly and the spacecraft’s battery power did not function. The mission ended unsuccessfully two days later. Mariner-D was launched as designed on November 28, 1964 and became the first successful mission to Mars. It was the first time a planet was photographed from space. Mariner-D’s 21 photographs revealed an inhospitable and barren landscape. The two Mariner spacecraft were launched by Atlas-Agena-D rockets. Lewis had taken over management of the Agena Program in October 1962. There had been five failures and two partial failures in the 17 Agena launches before being taken over by NASA Lewis. Lewis, however, oversaw 28 successful Agena missions between 1962 and 1968, including several Rangers and the Mariner Venus '67.

S64-40113 (1964) --- Astronaut Walter Schirra Jr. (right) and Walter Williams, Deputy Director of Mission Requirements, pictured at the Mercury 7 memorial dedication. Photo credit: NASA

S64-31476 (1964) --- Astronaut Theodore C. Freeman.

John B. McKay was one of the first pilots assigned to the X-15 flight research program at NASA's Flight Research Center, Edwards, Calif. As a civilian research pilot and aeronautical engineer, he made 30 flights in X-15s from October 28, 1960, until September 8, 1966. His peak altitude was 295,600 feet, and his highest speed was 3863 mph (Mach 5.64). McKay was with the NACA and NASA from February 8,1951 until October 5, 1971 and specialized in high-speed flight research programs. He began as an NACA intern, but assumed pilot status on July 11, 1952. In addition to the X-l5, he flew such experimental aircraft as the D-558-1, D-558-2, X-lB, and the X-lE. He has also served as a research pilot on flight programs involving the F-100, F-102, F-104, and the F-107. Born on December 8, 1922, in Portsmouth, Va., McKay graduated from Virginia Polytechnic Institute in 195O with a Bachelor of Science degree in Aeronautical Engineering. During World War II he served as a Navy pilot in the Pacific Theater, earning the Air Medal and Two Clusters, and a Presidential Unit Citation. McKay wrote several technical papers, and was a member of the American Institute of Aeronautics and Astronautics, as well as the Society of Experimental Test Pilots. He passed away on April 27, 1975.

This image shows the Saturn V S-IC-T stage (S-IC static test article) fuel tank being attached to the thrust structure in the vehicle assembly building at the Marshall Space Flight Center (MSFC). The S-IC stage utilized five F-1 engines that used liquid oxygen and kerosene as propellant and provided a combined thrust of 7,500,000 pounds.

Apollo Contour Engine Model being tested in the NASA Lewis Research Center, Propulsion Systems Laboratory, PSL

APOLLO CONTOUR ENGINE MOUNTED IN THE PROPULSION SYSTEMS LABORATORY PSL NO. 2 TEST CELL

The Saturn I S-I stages for the SA-8 and SA-10 mission in final assembly phase in a manufacturing building at the Michoud Assembly Facility in New Orleans, Louisiana. The SA-8 mission was launched on May 25, 1965 with the first industry-built booster, and deployed the Pegasus II Micrometeoroid Detection satellite. The SA-10 mission was the last Saturn I mission, launched on July 30, 1965, and carried the Pegasus III Meteoroid Detection satellite.

R4D-6 (Bu. No. 99827 NACA 18, NASA 701). TAKE-OFF MONITOR TEST, EDWARDS AIR FORCE BASE. Gunsight Tracking and Guidance and Control Displays. Note: Used in publication in Flight Research at Ames; 57 Years of Development and Validation of Aeronautical Technology NASA SP-1998-3300 fig 76

S65-30548 (3-7 June 1965) --- Astronaut Edward H. White II, Gemini IV pilot, is photographed onboard the Gemini-Titan 4 spacecraft during the four-day Earth-orbital mission. Photo credit: NASA

S64-31711 (1964) --- Astronaut Clinton C. Williams.

S64-19430 (13 April 1964) --- Astronauts Virgil I. Grissom (left), Gemini-3 command pilot; and John W. Young, pilot. EDITOR?S NOTE: Astronaut Grissom lost his life in the Apollo 1/Saturn 204 fire at Cape Kennedy on Jan. 27, 1967.

Dr Harold Klein discusses work with Congressman William K Van Pelt during visit and tour of Ames

Engineer Paul Reader and his colleagues take environmental measurements during testing of a 20-inch diameter ion engine in a vacuum tank at the Electric Propulsion Laboratory (EPL). Researchers at the Lewis Research Center were investigating the use of a permanent-magnet circuit to create the magnetic field required power electron bombardment ion engines. Typical ion engines use a solenoid coil to create this magnetic field. It was thought that the substitution of a permanent magnet would create a comparable magnetic field with a lower weight. Testing of the magnet system in the EPL vacuum tanks revealed no significant operational problems. Reader found the weight of the two systems was similar, but that the thruster’s efficiency increased with the magnet. The EPL contained a series of large vacuum tanks that could be used to simulate conditions in space. Large vacuum pumps reduced the internal air pressure, and a refrigeration system created the cryogenic temperatures found in space.

Aerial. Construction progress of the Vehicle Assembly Building (VAB), looking north. MILA.

F-111 LOADS model in 12ft w.t. at Ames Research Center, Moffett Field, CA with Robert Ziesser

Marshall Space Flight Center (MSFC) director, Wernher von Braun, and others examine one concept of a possible Lunar Roving Vehicle (LRV) built by the Bendix Corporation. The data provided by the MTA helped in designing the LRV, developed under the direction of MSFC. The LRV was designed to allow Apollo astronauts a greater range of mobility during lunar exploration missions.

Mechanics are dressed in fire suits because the Lunar Landing Research Vehicle, a simulator to train astronauts for a moon landing, had 90% pure hydrogen peroxide thrusters.

The lunar module design underwent gradual evolution from the first configuration proposed by Grumman in 1962. This model is the 1964 version. Langley had the task of building a simulator for the astronauts to practice lunar landings. The configuration of the initial vehicle used with the Lunar Landing Research Facility (LLRF) was changed in 1967 to more accurately reflect the standing position of the astronauts, cockpit arrangement, instrumentation, controls and field of view.

S64-20199 (10 Sept. 1964) --- View of the Gemini-4 prime crew and backup crew in pressure suits. They are standing around a model of the Gemini spacecraft. From left to right are astronauts Edward H. White II, pilot; James A. McDivitt, command pilot; Frank Borman and James A. Lovell Jr., backup crew.

S64-31845 (10 Sept. 1964) --- Portrait of astronaut Eugene A. Cernan in civilian clothes with model of Gemini spacecraft and launch vehicle on table in front of him. Photo credit: NASA

S64-31443 (1964) --- Astronaut Charles A. Bassett II.

This close-up view of the F-1 engine for the Saturn V S-IC (first) stage shows the engine's complexity, and also its large size as it dwarfs the technician. Developed by Rocketdyne, under the direction of the Marshall Space Flight Center, the F-1 engine was utilized in a cluster of five engines to propel the Saturn V's first stage, the S-IC. Liquid oxygen and kerosene were used as its propellant. Initially rated at 1,500,000 pounds of thrust, the engine was later uprated to 1,522,000 pounds of thrust after the third Saturn V launch (Apollo 8, the first marned Saturn V mission) in December 1968. The cluster of five F-1 engines burned over 15 tons of propellant per second, during its two and one-half minutes of operation, to take the vehicle to a height of about 36 miles and to a speed of about 6,000 miles per hour.

S64-40111 (1964) --- Wide angle view of the Mercury 7 memorial dedication. Photo credit: NASA

Engineers at the National Aeronautics and Space Administration (NASA) Lewis Research Center inspect the nitrogen baffle in the interior of the 22.5-foot diameter dome at the Space Power Chambers. In 1961 NASA Lewis management decided to convert the Altitude Wind Tunnel into two large test chambers and renamed the facility the Space Power Chambers. The conversion, which took over two years, included removing the tunnel’s drive fan, exhaust scoop, and turning vanes from the east end and inserting bulkheads to seal off the new chambers within the tunnel. The eastern section of the tunnel became a vacuum chamber capable of simulating 100 miles altitude. In 1962 NASA management decided to use the new vacuum chamber exclusively to study the second-stage rocket. This required significant modifications to the new tank and extensive test equipment to create a space environment. The Lewis test engineers sought to subject the Centaur to long durations in conditions that would replicate those encountered during its missions in space. The chamber was already capable of creating the vacuum of space, but the test engineers also wanted to simulate the cryogenic temperatures and solar radiation found in space. Six panels of 500-watt tungsten-iodine lamps were arranged around the Centaur to simulate the effect of the Sun’s heat. A large copper cold wall with its interior coated with heat-absorbing black paint was created specifically for these tests and assembled around the Centaur. The 42-foot-high wall had vertical ribs filled with liquid nitrogen which produced the low temperatures.

Dr Cyril Ponnamperuma and Dr Harold Klein discuss work with Congressman William K Van Pelt during visit and tour of Ames

3/4 front view from below, showing Pods and Fan Rotating. March A. Zeiger standing in front. Tandem Dual Ducted Fan V/STOL Model in Ames 40x80 foot Wind Tunnel

The launch of the SA-7 (Saturn I Block II) was on September 18, 1964. The SA-7 mission was the second orbital flight of the S-IV stage (second stage) with the payload consisting of the Apollo command and service module's instrument unit. The Saturn I Block II vehicle had two live stages, and were basically in the two-stage configuration of the Saturn I vehicle. While the tank arrangement and the engine patterns were the same, there were marked changes between the Block I and II versions. The first stage (S-I stage) was an improved version of the Block I S-I stage. The Block II S-1 stage had eight fins added for greater aerodynamic stability in the lower atmosphere.

This photograph is dated October 14, 1964, and shows Dr. von Braun, left, during a tour of the NASA Marned Spacecraft Center, now the Johnson Space Center. He is with Dr. J.P. Kuettner, center, from the Marshall Space Flight Center, and Warren J. North from the Manned Spacecraft Center.

Pilot Earle Boyer and researcher Henry Brandhorst prepare for a solar cell calibration flight in a Martin B-57B Canberra at the National Aeronautics and Space Administration (NASA) Lewis Research Center. Lewis was in the early stages of decades-long energy conversion and space power research effort. Brandhorst, a member of the Chemistry and Energy Conversion Division, led a team of Lewis researchers in a quest to develop new power sources to sustain spacecraft in orbit. Solar cells proved to be an important source of energy, but researchers discovered that their behavior varied at different atmospheric levels. Their standardization and calibration were critical. Brandhorst initiated a standardized way to calibrate solar cells in the early 1960s using the B-57B aircraft. The pilots would take the aircraft up into the troposphere and open the solar cell to the sunlight. The aircraft would steadily descend while instruments recorded how much energy was being captured by the solar cell. From this data, Brandhorst could determine the estimated power for a particular solar cell at any altitude. Pilot Earle Boyer joined NASA Lewis in October 1962. He had flown Convair F-102 Delta Dagger fighters in the Air Force and served briefly in the National Guard before joining the Langley Research Center. Boyer was only at Langley a few months before he transferred to Cleveland. He flew the B-57B, a Convair F-106 Delta Dart, Gulfstream G-1 with an experimental turboprop, Learjet and many other aircraft over the next 32 years at Lewis.

3/4 rear view Ryan XV-5A lift-fan VSTOL airplane. Pictured with Tom Wills.

Aerial view of Gasdynamics facility in 1964 and the 20 inch helium tunnel Part of the Thermal Protection Laboratory used to research materials for heat shield applications and for aerodynamic heating and materials studies of vehicles in planetary atmospheres.  This laboratory is comprised of five separate facilities: an Aerodynamic Heating Tunnel, a Heat Transfer Tunnel, two Supersonic Turbulent Ducts, and a High-Power CO2 Gasdynamic Laser. All these facilities are driven by arc-heaters, with the exception of the large, combustion-type laser. The arc-heated facilities are powered by a 20 Megawatt DC power supply. Their effluent gas stream (test gases; Air, N2, He, CO2 and mixtures; flow rates from 0.05 to 5.0 lbs/sec) discharges into a five-stage stream-ejector-driven vacuum system. The vacuum system and power supply are common to the test faciities in building N-238. All of the facilities have high pressure water available at flow rates up to 4, 000 gals/min. The data obtained from these facilities are recorded on magnetic tape or oscillographs. All forms of data can be handled whether from thermo-couples, pressure cells, pyrometers, or radiometers, etc. in addition, closed circuit T. V. monitors and various film cameras are available. (operational since 1962)

Photograph taken July 30, 1964. Mary W Jackson, Aerospace Engineer in the Large Supersonic Tunnels Branch of Full-Scale Research Division, explains the facilities used in testing research models such as SCAT. The Guidance Counseling Class from Hampton Institute visited the center on July 30 and toured a number of facilities. The purpose of the visit was to provide the counselors an opportunity to see areas of work representing fields in which their students might be employed. The group, under the direction of Professor Fissell Jones (Left, back row) of Hampton Institute, represented the states of Virginia, North Carolina, South Carolina, and Georgia. In 1958 Mary Jackson became NASA's first black female engineer. The Hampton Institute (now Hampton University) is a Historically Black College. NASA started its EEO office in 1964 and the NASA Administrator at the time, James Webb, was very enthusiastic about reaching out to universities (including HBCUs) to partner with them and to encourage students to become NASA engineers.

This photograph shows the fuel tank assembly for the Saturn V S-IC (first) stage being transported to the Marshall Space Flight Center, building 4705 for mating to the liquid oxygen (LOX) tank. The fuel tank carried kerosene (RP-1) as its fuel. The S-IC stage used five F-1 engines, that used kerosene and liquid oxygen as propellant and each engine provided 1,500,000 pounds of thrust. This stage lifted the entire vehicle and Apollo spacecraft from the launch pad.

S64-29933 (1964) --- Astronaut Elliot M. See Jr.

The fuel tank assembly for the Saturn V S-IC (first) stage arrived at the Marshall Space Flight Center, building 4707, for mating to the liquid oxygen tank. The fuel tank carried kerosene as its fuel. The S-IC stage used five F-1 engines, that used kerosene and liquid oxygen as propellant and each engine provided 1,500,000 pounds of thrust. This stage lifted the entire vehicle and Apollo spacecraft from the launch pad.

Saturn Model in 19 Foot Tunnel

S64-29922 (1964) --- Astronaut James A. Lovell Jr. Photo credit: NASA

S64-31226 (1964) --- Maxime A. Faget, Assistant Director for Engineering and Development, at Manned Spacecraft Center, explains the function of the Lunar Module to Father Patrick J. OBrien, sister-in-law to Father O

S64-25295 (March 1964) --- Astronauts Virgil I. (Gus) Grissom (right) and John W. Young, prime crew for the first manned Gemini mission (GT-3), are shown inside a Gemini mission simulator at McDonnell Aircraft Corp., St. Louis, MO. The simulator will provide Gemini astronauts and ground crews with realistic mission simulation during intensive training prior to actual launch.

XV-5A airplane installed in 40x80ft Subsonic Wind Tunnel at NASA Ames Research Center with Tom Mills. The propulsive lift system was tested to determine power-on performance characteristics in preparation for flight tests. Used in Memoiors of an Aeronautical Engineer, Flight Tests at Ames Research Center 1940-1970 NASA-SP-2002-4526 (Seth B. Anderson)