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Caleb

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NOTS
Credit: © Thomas Kladiva - Thomas Kladiva

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AKA: NOTS500. Status: Retired 1962. First Launch: 1960-07-28. Last Launch: 1962-07-25. Number: 7 . Payload: 7.00 kg (15.40 lb). Thrust: 53.30 kN (11,982 lbf). Gross mass: 1,350 kg (2,970 lb). Height: 4.90 m (16.00 ft). Diameter: 0.60 m (1.96 ft). Apogee: 500 km (310 mi).

The 3 stage vehicle was air-launched from an F4H Phantom and consisted of 1 x NOTS 500 + 1 x X-248 motors.

LEO Payload: 7.00 kg (15.40 lb) to a 500 km orbit.

Stage Data - Caleb

• Stage 0. 1 x F-6. Gross Mass: 8,163 kg (17,996 lb). Empty Mass: 6,870 kg (15,140 lb). Thrust (vac): 45.355 kN (10,196 lbf). Isp: 1,414 sec. Burn time: 3,000 sec. Isp(sl): 1,285 sec. Diameter: 3.96 m (12.99 ft). Span: 10.21 m (33.49 ft). Length: 13.93 m (45.70 ft). Propellants: Air/Kerosene. No Engines: 1. Engine: J57-8. Status: Out of Production. Comments: Douglas (Heinemann) designed fighter-delta wing. Used as zero stage for Caleb miniature satellite launcher. Maximum release conditions: 3,628 kg at 1,166 kph at 16,768 m altitude.

• Stage 1. 1 x Caleb-1. Gross Mass: 1,033 kg (2,277 lb). Empty Mass: 194 kg (427 lb). Thrust (vac): 53.357 kN (11,995 lbf). Isp: 204 sec. Burn time: 34 sec. Isp(sl): 204 sec. Diameter: 0.60 m (1.96 ft). Span: 1.39 m (4.56 ft).Propellants: Solid. No Engines: 1. Engine: NOTS-1. Status: Out of Production.

• Stage 2. 1 x Caleb-2. Gross Mass: 267 kg (588 lb). Empty Mass: 23 kg (50 lb). Thrust (vac): 13.778 kN (3,097 lbf). Isp: 254 sec. Burn time: 39 sec. Isp(sl): 204 sec. Diameter: 0.0000 m ( ft). Span: 0.0000 m ( ft).Propellants: Solid. No Engines: 1. Engine: X-248. Status: Out of Production.

• Stage 3. 1 x Caleb-3. Gross Mass: 35 kg (77 lb). Empty Mass: 6.00 kg (13.20 lb). Thrust (vac): 2.265 kN (509 lbf). Isp: 250 sec. Burn time: 25 sec. Isp(sl): 204 sec. Diameter: 0.0000 m ( ft). Span: 0.0000 m ( ft).Propellants: Solid. No Engines: 1. Engine: NOTS-3. Status: Out of Production.

• Stage 4. 1 x Caleb-4. Gross Mass: 5.00 kg (11.00 lb). Empty Mass: 1.00 kg (2.20 lb). Thrust (vac): 706 N (158 lbf). Isp: 250 sec. Burn time: 3.00 sec. Isp(sl): 204 sec. Diameter: 0.0000 m ( ft). Span: 0.0000 m ( ft).Propellants: Solid. No Engines: 1. Engine: NOTS-4. Status: Out of Production.

Photo Gallery

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NOTS 1958

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• TV-1 test - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi). Research and Development Flight (TV-1).

• TV-2 test - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi). Research and Development Flight (TV-2).

• Test mission - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi).

  Satellite Interceptor Program (SIP) test vehicle. This was a follow-on to China Lake's "Notsnik" air-launched satellite and Caleb space-probe projects, SIP was a prototype air-launched satellite-killer system using primarily in-house technology and hardware.

• Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 10 km (6 mi).

• Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 21 km (13 mi).

• Test mission - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi).

• Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 1,166 km (724 mi).