Version: Trailblazer 1.
The rocket's first three stages would take the upper stage package to a 260 km apogee. The upper stage package was mounted upside-down in relation to the other stages. When it had reached the peak, the three upper stages fired in sequence, ramming the payload, a 13 cm sphere, into the atmosphere at orbital re-entry speeds.
Different materials were used in the sphere in each test, and ground observations were made of the spectra and luminance of the 'artificial meteorites' thus created.
On the 1G mission, an actual 'artificial meteorite' was flown. This was a 5.8 g steel pellet, which was driven into the atmosphere at 6 km/sec by a 'seventh stage', a shaped charge that accelerated the pellet after burnout of the rocket's six stage. This experiment provided a known reference by which the size of actual meteoroids could be measured according to the luminance of their trails.
The vehicle consisted of an Honest John rocket as the first stage, topped by 1 x Nike and 1 x Lance. The upside-down upper-stage package consisted of 1 x T-40 + 1 x T-55 + 1 x Cygnus 5 motors.
Launches: 15. First Launch Date: 1959-03-03. Last Launch Date: 1963-02-16. Payload: 1.00 kg (2.20 lb). Apogee: 280 km (170 mi). Liftoff Thrust: 365.000 kN (82,055 lbf). Total Mass: 3,400 kg (7,400 lb). Core Diameter: 0.58 m (1.90 ft). Total Length: 17.10 m (56.10 ft). Span: 2.61 m (8.56 ft).
- Stage1: 1 x HJ Nike-1. Gross Mass: 1,900 kg (4,100 lb). Empty Mass: 954 kg (2,103 lb). Motor: 1 x M-6. Thrust (vac): 365.000 kN (82,055 lbf). Burn time: 5.00 sec. Length: 4.90 m (16.00 ft). Diameter: 0.58 m (1.90 ft). Propellants: Solid.
- Stage2: 1 x HJ Nike Nike-3. Gross Mass: 599 kg (1,320 lb). Empty Mass: 256 kg (564 lb). Motor: 1 x M5E1. Thrust (vac): 195.600 kN (43,973 lbf). Burn time: 3.40 sec. Length: 3.60 m (11.80 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
- Stage3: 1 x Castor Lance-2. Gross Mass: 800 kg (1,760 lb). Empty Mass: 274 kg (604 lb). Motor: 1 x TX-77. Thrust (vac): 227.000 kN (51,031 lbf). Burn time: 8.70 sec. Length: 4.60 m (15.00 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.
- Stage4: 1 x Double Cajun T40-2. Gross Mass: 100 kg (220 lb). Empty Mass: 15 kg (33 lb). Motor: 1 x T-40. Thrust (vac): 13.300 kN (2,990 lbf). Burn time: 6.00 sec. Length: 1.40 m (4.50 ft). Diameter: 0.20 m (0.65 ft). Propellants: Solid.
- Stage5: 1 x HJ Nike Nike Recruit T55-5. Empty Mass: 12 kg (26 lb). Motor: 1 x T-55. Thrust (vac): 21.000 kN (4,720 lbf). Burn time: 1.30 sec. Length: 1.50 m (4.90 ft). Diameter: 0.15 m (0.49 ft). Propellants: Solid.
- Stage6: 1 x Trailblazer 2 M-5. Empty Mass: 1.00 kg (2.20 lb). Motor: 1 x Cygnus 5. Thrust (vac): 2.300 kN (517 lbf). Burn time: 1.60 sec. Length: 0.20 m (0.65 ft). Diameter: 0.13 m (0.42 ft). Propellants: Solid.
Version: Trailblazer 2.
NASA rocket designed for high-speed re-entry tests.
The Trailblazer 2 continued the work of NASA's Trailblazer 1 in taking re-entry test payloads high into space, then ramming them back down into the atmosphere. However the earlier version had a very small payload, meaning only ground observations could be made of the re-entry. The Trailblazer-2 was much more powerful, meaning instrumentation in the vehicle could send data to the ground. The first two stages of the rocket would take the upper stage package to an altitude of 300 km. The upper two stages would then fire, driving the 18 kg payload into the atmosphere at 6.1 km/sec.
The rocket was also used for further 'artificial meteorite' experiments. 0.7-0.8 gram steel pellets or chunks of explosive would be accelerated by a fifth stage and a shaped charge to up to 11.9 km/sec. The meteorite trails thus created were observed from the ground and gave astronomers a calibrated basis for inferring the size of natural meteorites from the trails they created.
Launches: 12. First Launch Date: 1961-12-14. Last Launch Date: 1973-12-06. Payload: 18 kg (39 lb). Apogee: 300 km (180 mi). Liftoff Thrust: 547.000 kN (122,970 lbf). Total Mass: 6,100 kg (13,400 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 15.70 m (51.50 ft). Span: 3.38 m (11.07 ft).
- Stage0: 2 x Journeyman-0. Gross Mass: 200 kg (440 lb). Motor: 1 x 1.5KS35000. Thrust (vac): 156.000 kN (35,070 lbf). Burn time: 1.50 sec. Length: 2.60 m (8.50 ft). Diameter: 0.23 m (0.75 ft). Propellants: Solid.
- Stage1: 1 x Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Motor: 1 x M33-20-4. Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Length: 5.92 m (19.42 ft). Diameter: 0.79 m (2.59 ft). Propellants: Solid.
- Stage2: 1 x Castor Lance-2. Gross Mass: 800 kg (1,760 lb). Empty Mass: 274 kg (604 lb). Motor: 1 x TX-77. Thrust (vac): 227.000 kN (51,031 lbf). Burn time: 8.70 sec. Length: 4.60 m (15.00 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.
- Stage3: 1 x Altair 1. Gross Mass: 238 kg (524 lb). Empty Mass: 30 kg (66 lb). Motor: 1 x X-248. Thrust (vac): 12.450 kN (2,799 lbf). Isp: 256 sec. Burn time: 38 sec. Length: 1.83 m (6.00 ft). Diameter: 0.46 m (1.50 ft). Propellants: Solid.
- Stage4: 1 x Trailblazer 2 M-4. Gross Mass: 100 kg (220 lb). Empty Mass: 5.00 kg (11.00 lb). Motor: 1 x Cygnus 15. Thrust (vac): 22.000 kN (4,945 lbf). Burn time: 4.80 sec. Length: 0.40 m (1.31 ft). Diameter: 0.38 m (1.24 ft). Propellants: Solid.
Version: Trailblazer 2M.
Five stage version for artificial meteorite launches consisting of 2 x Recruit strap-ons + 1 x Castor first stage + 1 x Skat second stage. The upper stage package consisted of 1 x Altair + 1 x Cygnus 15 + 1 x Cygnus 5
Payload: 0.0008 kg (0.0018 lb). Apogee: 300 km (180 mi). Liftoff Thrust: 547.000 kN (122,970 lbf). Total Mass: 6,100 kg (13,400 lb). Core Diameter: 0.79 m (2.59 ft). Total Length: 15.70 m (51.50 ft). Span: 3.38 m (11.07 ft).
Trailblazer Chronology
1959 March 3 - Wallops Island -. Trailblazer 1 TB I alpha? D58 re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1959 June 5 - 04:15 GMT - Wallops Island -. Trailblazer 1 TB I beta? Re-entry Vehicle test Agency: NASA. Apogee: 260 km (160 mi).
1959 December 1 - Wallops Island -. Trailblazer 1 TB I gamma? Re-entry Vehicle test Agency: NASA. Apogee: 260 km (160 mi).
1960 March 29 - Wallops Island -. Trailblazer 1 TB Ia? D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1960 June 26 - 06:17 GMT - Wallops Island -. Trailblazer 1 TB Ib D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 294 km (182 mi).
1960 August 29 - 03:38 GMT - Wallops Island -. Trailblazer 1 TB Ic D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1960 August 29 - 06:13 GMT - Wallops Island -. Trailblazer 1 TB Id D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1960 October 22 - 03:09 GMT - Wallops Island -. Trailblazer 1 TB Ie D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1961 January 18 - 04:00 GMT - Wallops Island -. Trailblazer 1 TB If D58 Trailblazer re-entry vehicle test flight Agency: NASA. Apogee: 260 km (160 mi).
1961 April 21 - 05:56 GMT - Wallops Island -. Trailblazer 1 TB Ig Re-entry vehicle test Agency: NASA. Apogee: 280 km (170 mi).
1961 May 18 - 06:10 GMT - Wallops Island -. Trailblazer 1 TB Ih Re-entry Vehicle test Agency: NASA. Apogee: 260 km (160 mi).
1961 September 17 - 04:47 GMT - Wallops Island -. Trailblazer 1 TB Ii Re-entry Vehicle test Agency: NASA. Apogee: 260 km (160 mi).
1961 December 14 - 07:09 GMT - Wallops Island -. Trailblazer 2 TB IIa Trailblazer IIa re-entry vehicle test flight Agency: NASA. Apogee: 157 km (97 mi). NASA fired a four-stage solid-fuel Trailblazer rocket from Wallops Station, Virginia, in the first of a series of reentry tests. Two stages boosted the rocket to 167 miles; then the other two drove the nose cone down through the atmosphere at 14,000 miles per hour.
1962 April 3 - 04:57 GMT - Wallops Island -. Trailblazer 1 TB Ij Re-entry Vehicle test Agency: NASA. Apogee: 260 km (160 mi).
1962 May 6 - 05:41 GMT - Wallops Island -. Trailblazer 2-M TB IIb Meteor 1 Re-entry vehicle test Agency: USAF. Apogee: 280 km (170 mi).
1962 July 28 - 02:50 GMT - Wallops Island -. Trailblazer 1 TB Ik Re-entry Vehicle test Agency: NASA. Apogee: 280 km (170 mi).
1963 - Wallops Island -. Trailblazer 2-M TB IId Trailblazer IId re-entry vehicle test flight Agency: NASA. Apogee: 300 km (180 mi).
1963 February 16 - Wallops Island -. Re-entry Vehicle test Agency: NASA. Apogee: 280 km (170 mi).
1965 May 1 - Wallops Island -. Ultraviolet reentry experiment Re-entry vehicle test Agency: NASA. Apogee: 300 km (180 mi).
1966 March 18 - 01:15 GMT - Wallops Island -. Trailblazer 2-M Meteor 8 Re-entry vehicle test Agency: NASA. Apogee: 280 km (170 mi).
1966 October 26 - Wallops Island -. Blackout study re-entry vehicle test flight Agency: USAF. Apogee: 300 km (180 mi).
1967 February 14 - 05:52 GMT - Wallops Island -. Trailblazer 2-M Meteor 10 Re-entry vehicle test Agency: NASA. Apogee: 306 km (190 mi).
1967 June 18 - 20:32 GMT - Wallops Island -. Trailblazer 2 AD21.860 AFCRL TB2-1 Re-entry vehicle test Agency: AFCRL. Apogee: 200 km (120 mi).
1969 June 18 - 01:56 GMT - Wallops Island -. Trailblazer 2 CRL AD21.861 AFRCL TB2-2 Re-entry vehicle test Agency: USAF. Apogee: 299 km (185 mi).
1970 November 21 - 23:56 GMT - Wallops Island -. Trailblazer 2 CRL AD21.862 AFCRL TB2-3 Re-entry vehicle test Agency: USAF. Apogee: 321 km (199 mi).
1972 July 28 - 18:59 GMT - Wallops Island -. Trailblazer 2 CRL A21.011-1 AFCRL TB2-4 Re-entry vehicle test Agency: USAF. Apogee: 314 km (195 mi).
1973 December 6 - 17:59 GMT - Wallops Island -. Trailblazer 2 CRL A21.220-1 AFCRL TB2-5 Re-entry vehicle test Agency: AFCRL. Apogee: 303 km (188 mi).
Bibliography:- McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
- Emme, Eugene M, Aeronautics and Astronautics: An American Chronology of Science and Technology in the Exploration of Space 1915-1960, NASA, 1961. Web Address when accessed: http://www.hq.nasa.gov/office/pao/History/timeline.html.
- Alway, Peter, Rockets of the World, Saturn Press, Ann Arbor, 1995.