Tag Archives: Three-Stage Rocket

12 August 1960, 09:39:43 UTC

The Thor Delta launch vehicle at Launch Complex 17A, Cape Canaveral Air Force Station. The spherical capsule containing the Echo 1A is visible at the top of the Altair solid fuel third stage. (NASA)

12 August 1960: At 5:39:43 a.m., Eastern Daylight Savings Time, the Echo 1A experimental passive communications satellite was launched from LC-17A at Cape Canaveral Air Force Station, Florida. The launch vehicle was a Thor-Delta three stage rocket. It entered a nearly circular 944 mile × 1,048 mile orbit (1,519 × 1,687 kilometers). The orbital period was 118.3 minutes.

The satellite was a 100 foot diameter (30.48 meter) Mylar polyester balloon with a reflective surface. The material was just 0.0127 millimeters thick. The mass of the satellite was 66 kilograms (145.5 pounds). In orbit, the balloon envelope was kept inflated by gas from evaporating liquid. It had been constructed by the G.T. Schjeldahl Company, Northfield, Minnesota. This was the second Echo satellite. The first had failed to reach orbit when launched 13 March 1960.

Later the same day, a microwave transmission from the Jet Propulsion Laboratory, Pasadena, California, was reflected off the Echo 1A satellite and received at the Bell Laboratories, Homdel, New York.

According to NASA, “The success of Echo 1A proved that microwave transmission to and from satellites in space was understood and demonstrated the promise of communications satellites. The vehicle also provided data for the calculation of atmospheric density and solar pressure due to its large area-to-mass ratio. Echo 1A was visible to the unaided eye over most of the Earth (brighter than most stars) and was probably seen by more people than any other man-made object in space.”

Echo 1A remained in Earth orbit until 24 May 1968.

An Echo satellite undergoing static inflation tests inside a blimp hangar at Weeksville NAS, North Carolina. The vehicle, which shows scale, is a 1959 Plymouth Suburban 4-door station wagon. (NASA)

The Delta was a three-stage expendable launch vehicle which was developed from the Douglas Aircraft Company’s SM-75 Thor intermediate-range ballistic missile.

Designated Thor DM-19, the first stage was 60.43 feet (18.42 meters) long and 8 feet (2.44 meters) in diameter. Fully fueled, the first stage had a gross weight of 108,770 pounds (49,337 kilograms). It was powered by a Rocketdyne LR-79-7 engine which burned liquid oxygen and RP-1 (a highly-refined kerosene rocket fuel) and produced 170,565 pounds of thrust (758.711 kilonewtons). This stage had a burn time of 2 minutes, 45 seconds.

The second stage was an Aerojet General Corporation-built Delta 104. It was 19 feet, 3 inches (5.88 meters) long with a maximum diameter of 4 feet, 6 inches (1.40 meters). The second stage had a gross weight of 9,859 pounds (4,472 kilograms). It used an Aerojet AJ10-104 rocket engine which burned a hypergolic  mixture of nitric acid and UDMH. The second stage produced 7,890 pounds of thrust (35.096 kilonewtons) and burned for 4 minutes, 38 seconds.

The third stage was an Allegany Ballistics Laboratory Altair 1. It was 6 feet long, 1 foot, 6 inches in diameter and had a gross weight of 524 pounds (238 kilograms). This stage used a solid-fuel Thiokol X-248 rocket engine, producing 2,799 pounds of thrust (12.451 kilonewtons). Its burn time was 4 minutes, 16 seconds.

© 2016, Bryan R. Swopes

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27 October 1961: 15:06:04 UTC, T minus Zero

The first Saturn I three-stage heavy-lift rocket on the launch pad at Cape Canaveral, 27 October 1961. (NASA)

27 October 1961: At 15:06:04 UTC, (10:06 a.m., EST) the first Saturn I heavy launch vehicle (SA-1) lifted off from Launch Complex 34 at Cape Canaveral, Florida. This was a test of the first stage, only. The upper stages were dummies.

The Saturn I was bigger than any rocket built up to that time. The three-stage rocket was 180 feet (54.9 meters) tall with a maximum diameter of 21.39 feet (6.52 meters). All-up weight was 1,124,000 pounds (509,838 kilograms).

S-I first stage of a Saturn I heavy launch vehicle. (NASA)
S-I first stage of a Saturn I heavy launch vehicle. (NASA)

The first stage of the Saturn I was powered by eight Rocketdyne H-1 engines producing 205,000 pounds of thrust, each. The S-I stage was built up with Jupiter rocket fuel tank in the center for liquid oxygen, surrounded by eight Redstone rocket tanks filled with RP-1 propellant. The S-IV second stage was powered by six Rocketdyne RL-10 engines producing a total of 90,000 pounds of thrust. This stage was fueled with liquid hydrogen and liquid oxygen. The S-V third stage had two RL-10 engines for 30,000 pounds of thrust.

For the first flight, the fully-fueled Saturn I weighed 925,000 pounds (419,573 kilograms). It contained 41,000 gallons (155,200 liters) of RP-1, a refined kerosene fuel, with 66,000 gallons (249,837 liters) of liquid oxygen oxidizer— 600,000 pounds (272,155 kilograms) of propellants. The dummy S-IV second stage, weighing 25,000 pounds, (11,340 kilograms) was filled with 90,000 pounds (40,823 kilograms) of water for ballast. The S-V third stage, weighing 3,000 pounds (1,361 kilograms), carried 100,000 pounds (45,359 kilograms) of water.

SA-1 reached a maximum altitude of 84.8 miles (136.5 kilometers) and impacted in the Atlantic Ocean 214.8 miles (345.7 kilometers) down range. The duration of the flight was 15 minutes, 0 seconds.

Saturn I SA-1 lifts off at Launch Complex 34, 15:06:04 UTC, 27 October 1961. (NASA)
Saturn I, SA-1 lifts off at Launch Complex 34, 15:06:04 UTC, 27 October 1961. (NASA)

© 2015, Bryan R. Swopes

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