PGM-19 Jupiter
The Jupiter, first tested in 1957, was the United States' second IRBM (Intermediate Range Ballistic Missile). It was a liquid-fueled (LOX and RP-1) rocket, with one engine producing 66 kN of thrust.
In September 1955, Dr. Wernher von Braun, briefing the Secretary of Defense on long range missiles pointed out that a 1,500 mi (2,415 km) missile was a logical extension of the Redstone.
Modified Redstone missiles with small clustered solid fuel upper stages, were named Jupiter-C. Jupiter-C rockets were used to test Jupiter IRBM nosecones and orbit early Explorer satelites. Jupiter IRBM and Jupiter-C were totally different missiles.
A product of the Army Ballistic Missile Agency at Redstone Arsenal, under the leadership of Wernher von Braun, it was designed as a intermediate range ballistic mobile missile for the U.S. Army. The missile was taken over by the U.S. Air Force when the Army was prohibited from having missiles with a greater range than 200-miles. The Jupiter was capable of flights up to 1,500 miles (2,415 km). It burned RP-1 (kerosene) and liquid oxygen.
A Jupiter IRBM rocket tank was used in combination with eight Redstone missile tanks clustered around it, to form the first stage of the Saturn I and Saturn IB rockets.
The Jupiter IRBM was modified by adding upper stages in the form of clustered Sergent rocktets to create a satellite/space probe launch vehicle. This modified Jupiter IRBM' was called the Juno-II.
Biological Flights
Jupiter IRBM missiles were used in a series of suborbital biological test fights. On December 13, 1958, a Jupiter IRBM was launched from Cape Canaveral, Florida with a South American squirrel monkey named "Gordo" onboard. The nosecone recovery parachute failed to operate and "Gordo" did not survive the flight.
Another biological flight was launched on May 28, 1959. Aboard Jupiter IRBM AM-18, were a 7-pound (3.18 kg) American-born rhesus monkey, "Able" and an 11-ounce (311.9 gram) South American squirrel monkey, "Baker". The monkeys rode in the nosecone of the missile to an altitude of 360-miles (579-km) and a distance of 1,700-miles (2,735-km) down the Atlantic Missile Range from Cape Canaveral, Florida. They withstood forces 38 times the normal pull of gravity and were weightless for about 9 minutes. A top speed of 10,000-miles per hour (14,00-kph) was reached during their 16-minute flight.
The monkeys survived the flight in good condition. "Able" died four days after the flight, from a reaction to the anesthesia, while undergoing surgery to remove an infected medical electrode. "Baker" lived until November 29, 1984 in Huntsville, Alabama.
Military Deployment
Two squadrons totaling 30-missiles were deployed at 10-sites in Italy from 1961 to 1963. They were operated by Italian Air Force crews, but U.S. Air Force personnel controlled arming of the nuclear warheads. These missiles were deployed around the Italian countryside and operated by the 36^Aerobrigata Interdizione Strategica ( 36th Strategic Interdiction Air Squadron, Italian Air Force.), stationed out of the Gioia Del Colle Air Base, Italy. In 1962, a Bulgarian MiG-17 reconnaissance airplane is reported to have crashed into an olive grove near one of the US Jupiter missile launch sites in Italy, after overflying the site.
One squadron totaling 15-missiles was deployed at 5-sites near Izmir, Turkey from 1961 to 1963. They were operated by U.S. Air Force personnel. The first flight of three Jupiter missiles were turned over to the Turkish Air Force in late October 1962, during the Cuban Missile Crisis. U.S. Air Force personel controlled arming of the nuclear warheads. The actual deployment locations of the Jupiter IRBM missiles within Turkey are still secret more than 40-years later. According to an individual that took part in the Turkish missile deployment in 1961, one of the five sites was in the mountains near Manisa, Turkey and another site was in the mountains near Akhisar, Turkey. The central deployment base was Cigli Air Force Base, Turkey.
On four occasions between mid-October 1961 and August 1962, Jupiter IRBM mobile missiles carrying 1.4-megaton nuclear warheads were struck by lightning at their bases in Italy. In each case, thermal batteries were activated, and on two occasions, tritium-deuterium "boost" gas was injected into the warhead pits, partially arming them. After the fourth lightning strike on a Jupiter IRBM, the U.S. Air Force placed protective lightning strike-diversion tower arrays at all of the Italian and Turkish Jupiter IRBM missiles sites.
These Jupiter missiles are sometimes called "The Other Missiles Of October". Their deployment in Italy and Turkey prompted the Soviet Union to place it's missiles in Cuba in 1962 causing the Cuban Missile Crisis.
As part of a secret agreement, John F. Kennedy agreed to dismantle and remove the Jupiter missiles from Italy and Turkey within 6-months. In return the Soviet Union agreed to immediate removal of it's missiles from Cuba. This agreement was kept secret over 30-years in order not to embarrass the host nations (Italy and Turkey). All Jupiter IRBM's were removed from service by April 1963.
Jupiter IRBM Specifications
and Jupiter IRBM.
Length: 60 ft - 18.3 m
Diameter: 8 ft 9 in - 2.67 m
Total Fueled Weight: 108,804 lb - 49,800 kg
Empty Weight: 13,715 lb - 6,220 kg
Oxygen (LOX) Weight: 68,760 lb - 31,186 kg
RP-1 (kerosene) Weight: 30,415 lb - 13,795 kg
Thrust: 150,000 lbs - 758.70 kN
Engine: Rocketdyne LR70-NA (Model S-3D)
ISP: 247.5 sec
Burning time: 157.8 sec
Propellant consumption rate: 627.7 lb/sec - 284.7 kg/sec
Range: 1,500 mi - 2,415 km
Flight time: 1,016.9 sec
Cutoff velocity: 8,984 mph - 14,464 km/hr - Mach 13.04
Reenty velocity:10,645 mph - 17,138 km/hr - Mach 15.45
Peak Acceleration: 13.69 g
Peak Deceleration: 44.0 g
Peak altitude: 390 mi - 628 km
CEP 4,925 ft - 1,500 m
Warhead: 1.45 MT Thermonuclear W-49 - 1,650 lbs - 2,390 kg
Fusing: Proximity and Impact
Guidance: Inertial
Juno II Launch Vehicle Specifications
The Juno II was a satellite launch vehicle derived rom the Jupiter IRBM. It was used for 10 satelite launches. Six of those launches failed. Juno II was a 4-stage rocket. Launched Pioneer 3, Pioneer 4, Explorer 7, Explorer 8, Explorer 11.
Juno II Total Length: 24.0 m
Orbit Payload to 200 km: 41 kg
Escape Velocity Payload: 6 kg
First Launch Date: December 6, 1958
Last Launch Date: May 24, 1961
| Parameter | 1st Stage | 2nd Stage | 3rd Stage | 4th Stage |
|---|---|---|---|---|
| Gross Mass | 54,431 kg | 462 kg | 126 kg | 42 kg |
| Empty Mass | 5,443 kg | 231 kg | 63 kg | 21 kg |
| Thrust | 68,040 kgf | 7,480 kgf | 2,040 kgf | 680 kgf |
| Isp | 248 sec | 214 sec | 214 sec | 214 sec |
| Burn time | 182 sec | 6 sec | 6 sec | 6 sec |
| Length | 18.28 m | 1.0 m | 1.0 m | 1.0 m |
| Diameter | 2.67 m | 1.0 m | 0.50 m | 0.30 m |
| Engine: | Rocketdyne S-3D | Eleven Sergents | Three Sergents | One Sergent |
| Propellant | LOX/RP-1 | Solid Fuel | Solid Fuel | Solid fuel |
Test Launches
All test launches were from Cape Canaveral, Florida.
| Serial Number | Mission | Launch Date | Notes |
|---|---|---|---|
| AM-1A | AM-1A | March 1, 1957 | Test Launch 1. Missile test. Failure. Apogee 14 mi - 20 km. |
| AM-1B | AM-1B | April 26, 1957 | Test Launch 2. Missile test. Failure. Apogee 18 mi - 26 km. |
| AM-1 | AM-1 | May 31, 1957 | Test Launch 3. Missile test. Success. Apogee 500 mi - 725 km. |
| AM-2 | AM-2 | August 28, 1957 | Test Launch 4. Missile test. Success. Apogee 500 mi - 725 km. |
| AM-3 | AM-3 | October 23, 1957 | Test Launch 5. Missile test. Success. Apogee 500 mi - 725 km. |
| AM-3A | AM-3A | November 27, 1957 | Test Launch 6. Missile test. Failure. Apogee 20 mi - 29 km. |
| AM-4 | AM-4 | November 27, 1957 | Test Launch 7. Missile test. Failure. Apogee 63 mi - 92 km. |
There were 46 test launches. More to be listed later.