The Journeyman was a 5 stage sounding rocket and research vehicle consisting
of 2 Recruit, 1 Sergeant, 2 Lance and 1 Altair stages.
- Launches: 8
- First Launch Date: 19 September 1960
- Last Launch Date: 30 June 1965
- Apogee: 3,000 km
- Total Mass: 6,300 kg
- Core Diameter: 0.79 m
- Total Length: 18.90 m.
During the first year of the existence of Goddard's Sounding Rocket Branch,
several sounding rockets, whose development predated NASA, came into the
"stable" of vehicles readily available to NASA. Among these were the
D-4 and D-8, both of the so-called Argo series. "Argo" was from the
name of Jason's ship in the ancient Greek myth of Jason's travels in search of
the Golden Fleece, and the name of the first sounding rocket in the series.
Subsequent vehicles in the series were given names also beginning with the
letter "J"; the Argo D-4 and Argo D-8 were named "Javelin"
and "Journeyman." The "D-4" and "D-8" designations
referred to the number of stages - "D" for "four" - and to
the design revision - fourth and eighth.
The Argo series was developed by the Aerolab Development Co. (later a
division of Atlantic Research Corporation) under the sponsorship of NACA/NASA,
with support from the Air Force Special Weapons Center, the Naval Bureau of
Ordnance, and the Allegheny Ballistics Laboratory. In general, the Argos are
rather large by sounding rocket standards. They were all put together from
off-the-shelf military hardware, often following vehicle adaptations by Langley
Research Center.
Argo D-8 Journeyman could carry 20- to 70-kilogram payloads to 1500- to
2100-kilometer altitudes. It weighed 13,938 pounds, and consisted of four
stages. Stage 1 was a Thiokol TX 2-6 (XM-20) Sergeant, plus two side-mounted
Thiokol XM-19 recruits. These boosters burned a solid polysulfide cast
composite. Stages two and three were Grand Central Lance (XM-25) motors, burning
solid polysulfide/ammonium perchlorate. The final fourth stage was an ABL
X-246-A6 Altair. This stage was spin stabilized, and the bird had an overall
length of 62 feet, 1 inch.
The Journeyman helped NASA gather radiation data prior to the Mercury flights
and has also seen some Air Force use. It is interesting to note that the first
three stages of the Journeyman were very similar to the first three stages of
the five stage Sergeant used by NACA in the
investigation of re-entry heat shield design in the late '50s. NASA's use of the
Journeyman was discontinued in 1965 because the Sergeant first stage motor was
becoming increasingly hard to get. It was replaced by the Aerobee 1500.
Chronology
| Date/Time | Round # | Site | Pad | Apogee | Payload | Result |
| 1960 Sep 19 16:35 | 11.01GE | Point Arguello | LC-A | 1,884 km. | NERV I (38 kg) | Success. |
| 1961 Nov 15 13:42 | 11.04GB | Point Arguello | LC-A | 1,057 km | BIOS I (biological payload) | Failure. |
| 1961 Nov 18 13:42 | 11.05GB | Point Arguello | LC-A | 1,057 km | BIOS II (biological payload) | Failure. |
| 1962 Jul 9 Unk. | Unk. | Point Arguello | LC-A | 1,500 km | AEC launch | Unk. |
| 1962 Sep 22 6:45 | 11.02UR | Wallops Island | Unk. | 1,691 km | Radio astronomy | Success |
| 1963 Feb 12 1:47 | 11.06UE | Point Arguello | LC-A | 1,675 km | Electron Spectrometer for radiation belt studies | Success. |
| 1965 Apr 14 14:39 | 11.07UE | Wallops Island | Unk. | 1,660 km | Plasma physics; no data returned | Failure |
| 1965 Jun 30 5:33 | 11.03UR | Wallops Island | LA4 | 1,708 km | Ionospheric studies | Success |
Typical Flight Profile
| Event | Time | Altitude | Velocity | Thrust | Weight | Acceleration |
| (sec) | (feet) | (ft/sec) | (pounds) | (pounds) | (G) |
| 1st Stage Ignition | 0.0 | 0 | 0 | 132,200 | 13,964 | 9.5 |
| Booster Burnout | 1.8 | - | - | 56,200 | 13,428 | 4.2 |
| 1st Stage Burnout | 27.5 | 42,242 | 2,822 | 56,200 | 6,402 | 8.8 |
| 1st Stage Detaches | 35.0 | 60,000 | 2,450 | 0 | 4,306 | -1.0 |
| 2nd Stage Ignition | 37.5 | 66,576 | 2,284 | 44,000 | 4,306 | 10.2 |
| 2nd Stage Burnout | 43.9 | 87,337 | 4,603 | 44,000 | 3,106 | 14.2 |
| 3rd Stage Ignition | 43.9 | 87,337 | 4,603 | 44,000 | 2,497 | 17.6 |
| 3rd Stage Burnout | 50.3 | 128,755 | 9,197 | 44,000 | 1,298 | 34.0 |
| 4th Stage Ignition | 63.0 | 237,227 | 8,772 | 3,040 | 702 | 4.3 |
| 4th Stage Burnout | 101.8 | 676,557 | 17,596 | 3,040 | 198 | 15.4 |
| Nose Cone Separation | 180.0 | 1,750,149 | 14,300 | 0 | 166.5 | 0 |
| Apogee | 922.0 | 6,965,563 | 5,198 | 0 | 166.5 | 0 |
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