Encyclopedia Astronautica
Caleb



nots.jpg
NOTS 1958
American air-launched orbital launch vehicle. Heavily classifed project related to air-launched ASAT development. Launch tests in 1958. NOTS project staff believed they successully orbited a satellite but unconfirmed.

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. Failures: 3. Success Rate: 57.14%. First Fail Date: 1960-10-24. Last Fail Date: 1962-03-26. Launch data is: complete.

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). Length: 0.0000 m ( 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). Length: 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). Length: 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). Length: 0.0000 m ( ft). Propellants: Solid. No Engines: 1. Engine: NOTS-4. Status: Out of Production.

Status: Retired 1962.
Gross mass: 1,350 kg (2,970 lb).
Payload: 7.00 kg (15.40 lb).
Height: 4.90 m (16.00 ft).
Diameter: 0.60 m (1.96 ft).
Thrust: 53.30 kN (11,982 lbf).
Apogee: 500 km (310 mi).
First Launch: 1960.07.28.
Last Launch: 1962.07.25.
Number: 7 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Hi-Hoe American technology satellite. 3 launches, 1961.10.05 (Hi-Hoe 1) to 1962.07.26 (Hi-Hoe 3). US antisatellite tests. More...

Associated Engines
  • J57-8 Pratt and Whitney turbojet engine. 45.4 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1414s. Used on Caleb launch vehicle. First flight 1960. More...
  • NOTS-1 NOTS solid rocket engine. 53.4 kN. Out of production. Isp=204s. Used on Caleb launch vehicle. First flight 1960. More...
  • NOTS-3 NOTS solid rocket engine. 2.260 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...
  • NOTS-4 NOTS solid rocket engine. 0.700 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...
  • X-248 Thiokol solid rocket engine. 12.4 kN. Isp=256s. Used on Atlas Able, Blue Scout 2, Caleb, Delta, Delta A, Delta B, Delta C. First flight 1959. More...

See also
Associated Manufacturers and Agencies
  • USN American agency overseeing development of rockets, spacecraft, and rocket engines. USN Joint Task Force 7, USA. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.

Associated Launch Sites
  • Vandenberg Vandenberg Air Force Base is located on the Central Coast of California about 240 km northwest of Los Angeles. It is used for launches of unmanned government and commercial satellites into polar orbit and intercontinental ballistic missile test launches toward the Kwajalein Atoll. More...
  • San Nicolas Military facility on the California Channel Islands, used for rocket launches in support of other missile tests from Vandenberg or Point Mugu. Known to have been used for 35 launches from 1957 to 2004, reaching up to 443 kilometers altitude. More...

Associated Stages
  • Caleb-2 Solid propellant rocket stage. Loaded/empty mass 267/23 kg. Thrust 13.78 kN. Vacuum specific impulse 254 seconds. More...
  • Caleb-3 Solid propellant rocket stage. Loaded/empty mass 35/6 kg. Thrust 2.27 kN. Vacuum specific impulse 250 seconds. More...
  • Caleb-4 Solid propellant rocket stage. Loaded/empty mass 5/1 kg. Thrust 0.71 kN. Vacuum specific impulse 250 seconds. More...
  • F-6 Turbojet powered rocket launch aircraft. Loaded/empty mass 8,163/6,870 kg. Thrust 45.36 kN. Specific impulse 1414 seconds. 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 More...
  • NOTS-1 Solid propellant rocket stage. Loaded/empty mass 1,033/194 kg. Thrust 53.36 kN. Vacuum specific impulse 204 seconds. More...

Caleb Chronology


1960 July 28 - . Launch Site: Vandenberg. Launch Platform: F4D-1 747. Launch Vehicle: Caleb. LV Configuration: Caleb NOTS EV-II.
  • TV-1 test - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi). Summary: Research and Development Flight (TV-1).

1960 October 24 - . Launch Site: Vandenberg. Launch Platform: F4D-1 747. Launch Vehicle: Caleb. LV Configuration: Caleb NOTS EV-II. FAILURE: Second stage failed..
  • TV-2 test - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi). Summary: Research and Development Flight (TV-2).

1961 October 1 - . Launch Site: San Nicolas. Launch Vehicle: Caleb. LV Configuration: Caleb SIP.
  • 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.

1961 October 5 - . 19:10 GMT - . Launch Site: Vandenberg. Launch Platform: F-4H. Launch Vehicle: Caleb. LV Configuration: Caleb NC17.116. FAILURE: Failure.
  • Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 10 km (6 mi).

1962 March 26 - . 19:03 GMT - . Launch Site: Vandenberg. Launch Platform: F-4H. Launch Vehicle: Caleb. LV Configuration: Caleb NC17.121. FAILURE: Failure.
  • Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 21 km (13 mi).

1962 May 5 - . Launch Site: San Nicolas. Launch Vehicle: Caleb. LV Configuration: Caleb SIP.
  • Test mission - . Nation: USA. Agency: USN NOTS. Apogee: 20 km (12 mi).

1962 July 25 - . 15:41 GMT - . Launch Site: Vandenberg. Launch Platform: F-4H. Launch Vehicle: Caleb. LV Configuration: Caleb NC17.117.
  • Test / aeronomy mission - . Nation: USA. Agency: USN NOTS. Apogee: 1,166 km (724 mi).

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