Scout X3

4 stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair

Manufacturer: Vought. Launches: 10. Failures: 3. Success Rate: 70.00%. First Launch Date: 1962-08-31. Last Launch Date: 1964-10-09. Launch data is: complete. LEO Payload: 87 kg (191 lb). to: 185 km Orbit. Associated Spacecraft: Ariel, Program 35, S-55, Transit. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,350 kg (38,250 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 24.00 m (78.00 ft). Flyaway Unit Cost $: 8.910 million. in: 1985 unit dollars.

4 stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair

LEO Payload: 87 kg (191 lb). to: 185 km Orbit. Liftoff Thrust: 513.400 kN (115,417 lbf). Total Mass: 17,350 kg (38,250 lb). Core Diameter: 1.01 m (3.31 ft). Total Length: 24.00 m (78.00 ft).

5 stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x Altair + 1 x Cetus

Apogee: 220 km (130 mi). Liftoff Thrust: 380.000 kN (85,420 lbf). Total Mass: 17,000 kg (37,000 lb). Total Length: 22.00 m (72.00 ft).

3 stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2

Apogee: 1,300 km (800 mi). Liftoff Thrust: 380.000 kN (85,420 lbf). Total Mass: 17,000 kg (37,000 lb). Total Length: 22.00 m (72.00 ft).

4 stage vehicle consisting of 1 x Algol 2A + 1 x Castor + 1 x Antares 2 + 1 x MG-18

Apogee: 900 km (550 mi). Liftoff Thrust: 380.000 kN (85,420 lbf). Total Mass: 17,000 kg (37,000 lb). Total Length: 22.00 m (72.00 ft).

• Stage Number: 1. 1 x Stage: Algol 2. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 1,650 kg (3,630 lb). Thrust (vac): 564.245 kN (126,847 lbf). Isp: 255 sec. Burn time: 47 sec. Isp(sl): 232 sec. Diameter: 1.01 m (3.31 ft). Span: 1.01 m (3.31 ft). Length: 9.09 m (29.82 ft). Propellants: Solid. No Engines: 1. Engine: Algol 2.

• Stage Number: 2. 1 x Stage: Castor 1. Gross Mass: 3,852 kg (8,492 lb). Empty Mass: 535 kg (1,179 lb). Thrust (vac): 286.001 kN (64,296 lbf). Isp: 247 sec. Burn time: 27 sec. Isp(sl): 232 sec. Diameter: 0.79 m (2.59 ft). Span: 0.79 m (2.59 ft). Length: 5.92 m (19.42 ft). Propellants: Solid. No Engines: 1. Engine: M33-20-4.

• Stage Number: 3. 1 x Stage: Antares 2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Thrust (vac): 93.094 kN (20,928 lbf). Isp: 293 sec. Burn time: 36 sec. Isp(sl): 233 sec. Diameter: 0.78 m (2.55 ft). Span: 0.78 m (2.55 ft). Length: 2.90 m (9.50 ft). Propellants: Solid. No Engines: 1. Engine: X-259.

• Stage Number: 4. 1 x Stage: Altair 1A. Gross Mass: 390 kg (850 lb). Empty Mass: 181 kg (399 lb). Thrust (vac): 13.788 kN (3,100 lbf). Isp: 255 sec. Burn time: 40 sec. Isp(sl): 232 sec. Diameter: 0.46 m (1.50 ft). Span: 0.46 m (1.50 ft). Length: 2.50 m (8.20 ft). Propellants: Solid. No Engines: 1. Engine: X-248A.

1962 August 31 - Launch Site: Wallops Island. Launch Complex: LA3. Launch Pad: LA3. Launch Vehicle: Scout X-3. Model: Scout X-3A. LV Configuration: Scout X-3A S114. FAILURE: Late stage 3 ignition.

• Reentry 2 Nation: USA. Class: Technology. Type: RV. Agency: NASA. Apogee: 217 km (134 mi). Decay Date: 1962-08-31. References: 0.

• Explorer 16 Nation: USA. Program: Explorer. Payload: S-55B. Mass: 100 kg (220 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: S-55. Agency: NASA. Perigee: 744 km (462 mi). Apogee: 1,159 km (720 mi). Inclination: 52.00 deg. Period: 104.10 min. COSPAR: 1962-B-Chi-1. USAF Sat Cat: 506. Micrometeoroid data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• Transit 5A Nation: USA. Program: Transit. Payload: Transit 5A-1. Mass: 61 kg (134 lb). Class: Navigation. Spacecraft: Transit. Agency: U.S. Navy. Perigee: 336 km (208 mi). Apogee: 347 km (215 mi). Inclination: 90.60 deg. Period: 91.40 min. COSPAR: 1962-B-Psi-1. USAF Sat Cat: 509. Decay Date: 1986-09-25. First operational solar-powered prototype; failed first day. The satellite verified a new technique for deploying the solar panels and for separating from the rocket, but otherwise it was not successful because of trouble with the power system. References: 1, 2, 5, 6.

• P 35-3 Nation: USA. Program: DMSP. Mass: 40 kg (88 lb). Class: Earth. Type: Weather. Spacecraft: Program 35. Agency: USAF. Perigee: 488 km (303 mi). Apogee: 810 km (500 mi). Inclination: 100.50 deg. Period: 97.80 min. COSPAR: 1963-005A. USAF Sat Cat: 533. Decay Date: 1979-12-26. Military weather satellite to provide targetting information for reconnaisance satellites. References: 1, 2, 5, 6.

• Transit 5A-2 Nation: USA. Program: Transit. Payload: Transit 5A-2. Mass: 84 kg (185 lb). Class: Navigation. Spacecraft: Transit. Agency: U.S. Air Force. COSPAR: F630405A. Decay Date: 1963-04-05. Replacement for the failed Transit 5A; failed to reach orbit. References: 5, 126.

• RFD-1 re-entry vehicle test flight Nation: USA. Class: Technology. Agency: NASA. Apogee: 145 km (90 mi). References: 5, 799.

• Transit 5A-3 Nation: USA. Program: Transit. Payload: Transit 5A-3. Mass: 55 kg (121 lb). Class: Navigation. Spacecraft: Transit. Agency: USN. Perigee: 350 km (210 mi). Apogee: 360 km (220 mi). Inclination: 89.80 deg. Period: 91.60 min. COSPAR: 1963-022A. USAF Sat Cat: 594. Decay Date: 1990-08-03. First operational prototype with a redesigned power supply. A malfunction of the memory occurred during powered flight that kept it from accepting and storing navigation messages, and the oscillator stability was degraded during launch. The satellite could not be used for navigation, but it was the first to achieve gravity-gradient stabilization, and its other subsystems performed well.References: 1, 2, 5, 6.

• Reentry 3 re-entry vehicle test flight Nation: USA. Class: Technology. Type: RV. Agency: NASA. Apogee: 2.00 km (1.20 mi). NASA launched a Scout rocket with a nose cone of experimental heatshield material from Wallops Island, Va. The rocket was intentionally destroyed when it deviated from its course a few seconds after liftoff. The nose cone had been expected to reenter the atmosphere at 27,934 kilometers (18,600 miles) per hour to test the material's thermal performance under heating loads near those of a lunar reentry.References: 5, 16, 126, 159.

• Ariel 2 Nation: UK. Payload: UK 2 (UK-C). Mass: 68 kg (149 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Ariel. Agency: UK DSIR. Perigee: 287 km (178 mi). Apogee: 1,349 km (838 mi). Inclination: 51.70 deg. Period: 101.30 min. COSPAR: 1964-015A. USAF Sat Cat: 771. Decay Date: 1967-11-18. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). References: 1, 2, 5, 6.

• RFD-2 re-entry vehicle test flight Nation: USA. Class: Technology. Agency: NASA. Apogee: 132 km (82 mi). References: 5, 868.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Wilson, Andrew, Spaceflight, "Scout - NASA's Small Satellite Launcher", 1979, Volume 21, page 446.