Man In Space

Here are some images of AMT/Round 2 Model's 1/200 scale Man in Space rocket series from the Mercury Redstone up to the Saturn V.
The stand did not come with the kit. I built it from disused model parts and the signage I made from my printer. The kit also comes with a paper model launch tower and base but I never bothered using it as I felt it was to cheap looking.
From Wikipedia"

Mercury Redstone:

NASA chose the U.S. Army's Redstone liquid-fueled ballistic missile for its sub-orbital flights because it was the most reliable of any U.S. ballistic missile at the time, with many successful test flights.

The standard military Redstone lacked sufficient thrust to lift a Mercury capsule into the ballistic sub-orbital trajectory needed for the project; however, the first stage of the Jupiter-C, which was a modified Redstone with lengthened fuel tanks, could carry enough propellant to reach the desired trajectory. Therefore this Jupiter-C first stage was used as the starting point for the Mercury-Redstone design. The Jupiter-C's engine, however, was being phased out by the Army, so to avoid potential complications such as parts shortages or design revisions, the Mercury-Redstone designers chose the Rocketdyne A-7 engine used on the latest military Redstones.

The standard Redstone was fueled with a 75 percent ethyl alcohol solution, but the Jupiter-C first stage had used hydyne fuel, a blend of 60 percent unsymmetrical dimethylhydrazine (UDMH) and 40 percent diethylenetriamine (DETA) This was a more powerful fuel than ethyl alcohol, but it was also more toxic, which could be dangerous for an astronaut in a launch pad emergency. Furthermore, hydyne had never been used with the new A-7 engine. The Mercury-Redstone designers rejected hydyne and returned to the standard ethyl alcohol fuel.

The most important change in making the Mercury-Redstone a suitable vehicle for an astronaut was the addition of an automatic in-flight abort sensing system. In an emergency where the rocket was about to suffer a catastrophic failure, an abort would activate the launch escape system attached to the Mercury capsule, which would rapidly eject it from the booster. Either the astronaut or the ground controllers could initiate an abort manually, but some potential failures during flight could lead to disaster before an abort could be manually triggered.

The Mercury-Redstone's automatic in-flight abort sensing system solved this problem by monitoring the rocket's performance during flight. If it detected an anomaly which might threaten the astronaut, such as loss of flight control, engine thrust, or electrical power, it would automatically abort, shutting down the engine and activating the capsule's escape system. (To keep the rocket from falling on people or facilities in the launch area, automatic engine shutdown was disabled during the first 30 seconds of flight, while the rocket was still over land.)

Mercury Atlas D:

 The Atlas LV-3B, Atlas D Mercury Launch Vehicle or Mercury-Atlas Launch Vehicle, was a man-rated expendable launch system used as part of the United States Project Mercury to send astronauts into low Earth orbit. It was derived from the SM-65D Atlas missile, and was a member of the Atlas family of rockets. It first flew on 29 July 1960, conducting the suborbital Mercury-Atlas 1 test flight. The rocket suffered a structural failure shortly after launch, and as a result failed to place the spacecraft onto its intended trajectory.

Nine LV-3Bs were launched, two on unmanned suborbital test flights, three on unmanned orbital test flights, and four with manned Mercury spacecraft.In addition to the maiden flight, the first orbital launch, Mercury-Atlas 3 also failed. This failure was due to a problem with the guidance system failing to execute pitch and roll commands, necessitating that the Range Safety Officer destroy the vehicle. The spacecraft separated by means of its launch escape system and was recovered 1.8 kilometres (1.1 mi) from the launch pad.

Atlas LV-3B launches were conducted from Launch Complex 14 at the Cape Canaveral Air Force Station, Florida. A further series of Mercury launches were planned, which would have used additional LV-3Bs; however these flights were canceled after the success of the initial Mercury missions. The last LV-3B launch was conducted on 15 May 1963.

 Gemini Titan:

 Project Gemini was the second human spaceflight program of NASA, the civilian space agency of the United States government. Project Gemini was conducted between projects Mercury and Apollo, with ten manned flights occurring in 1965 and 1966.

Its objective was to develop space travel techniques in support of Apollo, which had the goal of landing men on the Moon. Gemini achieved missions long enough for a trip to the Moon and back, perfected extra-vehicular activity (working outside a spacecraft), and orbital maneuvers necessary to achieve rendezvous and docking. All manned Gemini flights were launched from Cape Canaveral, Florida using the Titan II GLV launch vehicle.

 Gemini was designed by a Canadian, Jim Chamberlin, formerly the chief aerodynamicist on the Avro Arrow fighter interceptor program with Avro Canada. Chamberlin joined NASA along with 25 senior Avro engineers after cancellation of the Arrow program, and became head of the U.S. Space Task Group’s engineering division in charge of Gemini. The prime contractor was McDonnell Aircraft, which had also been the prime contractor for the Project Mercury capsule.

In addition, astronaut Gus Grissom was heavily involved in the development and design of the Gemini spacecraft. He writes in his posthumous 1968 book Gemini! that the realization of Project Mercury's end and the unlikelihood of his having another flight in that program prompted him to focus all of his efforts on the upcoming Gemini Program.

The Gemini program was managed by the Manned Spacecraft Center, Houston, Texas, under direction of the Office of Manned Space Flight, NASA Headquarters, Washington, D.C, Dr. George E. Mueller, Associate Administrator of NASA for Manned Space Flight, served as acting director of the Gemini program. William C. Schneider, Deputy Director of Manned Space Flight for Mission Operations, served as mission director on all Gemini flights beginning with Gemini VI.

Guenther Wendt was a McDonnell engineer who supervised launch preparations for both the Mercury and Gemini programs and would go on to do the same for the manned section of the Apollo program. His team was responsible for completion of the complex pad close-out procedures just prior to spacecraft launch, and he personally closed the hatches before flight. The astronauts appreciated his taking absolute authority over, and responsibility for, the condition of the spacecraft and developed a good-humored rapport with him.

 The Gemini-Titan launch vehicles, like the Mercury-Atlas vehicles before them, were ordered by NASA through the U. S. Air Force and were in reality missiles. The Gemini-Titan II rockets were assigned U.S. Air Force serial numbers, which were painted in four places on each Titan II (on opposite sides on each of the first and second stages). U.S. Air Force crews maintained Launch Complex 19 and prepared and launched all of the Gemini-Titan II launch vehicles.

The USAF serial numbers assigned to the Gemini-Titan launch vehicles are given in the tables above. Fifteen Titan IIs were ordered in 1962 so the serial is "62-12XXX", but only "12XXX" is painted on the Titan II. The order for the last three of the 15 launch vehicles was cancelled on July 30, 1964, and they were never built. Serial numbers were, however, assigned to them prospectively: 12568 - GLV-13; 12569 - GLV-14; and 12570 - GLV-15.

 Saturn 1B:

 The Saturn IB (pronounced "one B", also known as the Uprated Saturn I) was an American launch vehicle commissioned by the National Aeronautics and Space Administration (NASA) for the Apollo program. It replaced the S-IV second stage of the Saturn I with the much more powerful S-IVB, able to launch a partially fueled Apollo Command/Service Module (CSM) or a fully fueled Lunar Module (LM) into low Earth orbit for early flight tests before the larger Saturn V needed for lunar flight was ready.

By sharing the S-IVB upper stage, the Saturn IB and Saturn V provided a common interface to the Apollo spacecraft. The only major difference was that the S-IVB on the Saturn V burned only part of its propellant to achieve earth orbit, so it could be restarted for translunar injection. The S-IVB on the Saturn IB needed all of its propellant to achieve earth orbit.

The Saturn IB launched two unmanned CSM suborbital flights, one unmanned LM orbital flight, and the first manned CSM orbital mission (first planned as Apollo 1, later flown as Apollo 7). It also launched one orbital mission, AS-203, without a payload so the S-IVB would have residual liquid hydrogen fuel. This mission supported the design of the restartable version of the S-IVB used in the Saturn V, by observing the behavior of the liquid hydrogen in weightlessness.

In 1973, the year after the Apollo lunar program ended, three Apollo CSM/Saturn IBs ferried crews to the Skylab space station. In 1975, one last Apollo/Saturn IB launched the Apollo portion of the joint US-USSR Apollo Soyuz Test Project. A backup Apollo CSM/Saturn IB was assembled and made ready for a Skylab rescue mission but never flown.

 Saturn V:

 The Saturn V (pronounced "Saturn Five") was an American human-rated expendable rocket used by NASA's Apollo and Skylab programs from 1967 until 1973. A multistage liquid-fueled launch vehicle, NASA launched 13 Saturn Vs from the Kennedy Space Center, Florida with no loss of crew or payload. It remains the tallest, heaviest, and most powerful rocket ever brought to operational status and still holds the record for the heaviest launch vehicle payload.

The largest production model of the Saturn family of rockets, the Saturn V was designed under the direction of Wernher von Braun and Arthur Rudolph at the Marshall Space Flight Center in Huntsville, Alabama, with Boeing, North American Aviation, Douglas Aircraft Company, and IBM as the lead contractors. Von Braun's design was based in part on his work on the Aggregate series of rockets, especially the A-10, A-11, and A-12, in Germany during World War II.

To date, the Saturn V is the only launch vehicle to transport human beings beyond low Earth orbit. A total of 24 astronauts were launched to the Moon, three of them more than once, in the four years spanning December 1968 through December 1972.

 The Saturn V's size and payload capacity dwarfed all other previous rockets which had successfully flown at that time. With the Apollo spacecraft on top it stood 363 feet (111 m) tall and without fins it was 33 feet (10 m) in diameter. Fully fueled it had a total mass of 6.5 million pounds (3,000 metric tons) and a payload capacity of 260,000 pounds (120,000 kg) to LEO. Comparatively, at 363 feet (111 m), the Saturn V is about 58 feet taller than the Statue of liberty from the ground to the torch, and is just one foot shorter than St Paul's Cathedral in London, and only cleared the doors of the Vehicle Assembly Building (VAB) at Kennedy Space Center by 6 feet (1.8 m) when rolled out.

In contrast, the Mercury-Redstone Launch Vehicle used on Freedom 7, the first manned American spaceflight, was just under 11 feet (3.4 m) longer than the S-IVB stage, and delivered less sea level thrust (78,000 pounds-force (350 kN)) than the Launch Escape System rocket (147,000 pounds-force (650 kN) sea level thrust) mounted atop the Apollo command module.

The Saturn V was principally designed by the Marshall Space Flight Center in Huntsville, Alabama, although numerous major systems, including propulsion, were designed by subcontractors. It used the powerful new F-1 and J-2 rocket engines for propulsion. When tested, these engines shattered the windows of nearby houses. Designers decided early on to attempt to use as much technology from the Saturn I program as possible. Consequently, the S-IVB-500 third stage of the Saturn V was based on the S-IVB-200 second stage of the Saturn IB. The Instrument Unit that controlled the Saturn V shared characteristics with that carried by the Saturn IB.

Blueprints and other Saturn V plans are available on microfilm at the Marshall Space Flight Center.

The Saturn V's size and payload capacity dwarfed all other previous rockets which had successfully flown at that time. With the Apollo spacecraft on top it stood 363 feet (111 m) tall and without fins it was 33 feet (10 m) in diameter. Fully fueled it had a total mass of 6.5 million pounds (3,000 metric tons) and a payload capacity of 260,000 pounds (120,000 kg) to LEO. Comparatively, at 363 feet (111 m), the Saturn V is about 58 feet taller than the Statue of liberty from the ground to the torch, and is just one foot shorter than St Paul's Cathedral in London, and only cleared the doors of the Vehicle Assembly Building (VAB) at Kennedy Space Center by 6 feet (1.8 m) when rolled out.

In contrast, the Mercury-Redstone Launch Vehicle used on Freedom 7, the first manned American spaceflight, was just under 11 feet (3.4 m) longer than the S-IVB stage, and delivered less sea level thrust (78,000 pounds-force (350 kN)) than the Launch Escape System rocket (147,000 pounds-force (650 kN) sea level thrust) mounted atop the Apollo command module.

The Saturn V was principally designed by the Marshall Space Flight Center in Huntsville, Alabama, although numerous major systems, including propulsion, were designed by subcontractors. It used the powerful new F-1 and J-2 rocket engines for propulsion. When tested, these engines shattered the windows of nearby houses. Designers decided early on to attempt to use as much technology from the Saturn I program as possible. Consequently, the S-IVB-500 third stage of the Saturn V was based on the S-IVB-200 second stage of the Saturn IB. The Instrument Unit that controlled the Saturn V shared characteristics with that carried by the Saturn IB.

Blueprints and other Saturn V plans are available on microfilm at the Marshall Space Flight Center.