Encyclopedia Astronautica
Lambda 4S

Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S

LEO Payload: 26 kg (57 lb). Failures: 4. First Fail Date: 1966-09-26. Last Fail Date: 1969-09-22.

Gross mass: 9,400 kg (20,700 lb).
Payload: 26 kg (57 lb).
Height: 16.50 m (54.10 ft).
Diameter: 0.74 m (2.42 ft).
Thrust: 970.00 kN (218,060 lbf).
Apogee: 5,000 km (3,100 mi).
First Launch: 1966.09.26.
Last Launch: 1970.02.11.
Number: 5 .

More... - Chronology...
Associated Countries
Associated Spacecraft
  • Ohsumi Japanese technology satellite. 4 launches, 1966.09.26 (Ohsumi 1) to 1969.09.22 (Ohsumi 4). Small engineering test satellites lofted by Japan's first indigenous launch vehicle. More...
  • Osumi Japanese technology satellite. One launch, 1970.02.11, Ohsumi 5. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E. More...
See also
  • Lambda All solid-propellant vehicle, Japan's first satellite launcher. The L-4S project simulated the procedures and demonstrated the capabilities required for orbital satellite launch essential to the follow-on Mu project. More...
Associated Manufacturers and Agencies
  • ISAS Japanese agency overseeing development of rockets, spacecraft, and rocket engines. Institute of Space and Astronautical Science, Japan. More...
Associated Launch Sites
  • Kagoshima Japanese launch center for solid fueled sounding rockets and satellite launchers. Limited to two months a year due to disturbance of local fisheries. More...
Associated Stages
  • Lambda 4T-4 Solid rocket stage. 7.80 kN (1,754 lbf) thrust. Mass 100 kg (220 lb). More...
  • Lambda 3-1 Solid rocket stage. 410.00 kN (92,172 lbf) thrust. Mass 5,000 kg (11,023 lb). More...
  • Mu-3C-0 Solid rocket stage. 95.00 kN (21,357 lbf) thrust. Mass 500 kg (1,102 lb). More...

Lambda 4S Chronology
1966 September 26 - . 02:58 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-1. FAILURE: Fourth stage attitude control failed.. Failed Stage: 4.
  • Ohsumi 1 - . Payload: L-4S-1. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1966-09-26 . COSPAR: F660926A. Apogee: 400 km (240 mi).
1966 December 20 - . 02:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-2. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 2 - . Payload: L-4S-2. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1966-12-19 . COSPAR: F661220A. Apogee: 400 km (240 mi).
1967 April 13 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-3. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 3 - . Payload: L-4S-3. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1967-04-13 . COSPAR: F670413A. Apogee: 200 km (120 mi).
1969 September 22 - . 02:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-4. FAILURE: Fourth stage control system malfunction after third stage collided with fourth stage.. Failed Stage: 4.
  • Ohsumi 4 - . Payload: L-4S-4. Mass: 25 kg (55 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1969-09-22 . COSPAR: F690922A. Apogee: 400 km (240 mi).
1970 February 11 - . 04:25 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-5.
  • Ohsumi 5 - . Payload: L-4S-5. Mass: 12 kg (26 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Osumi. Decay Date: 2003-08-02 . USAF Sat Cat: 4330 . COSPAR: 1970-011A. Apogee: 2,440 km (1,510 mi). Perigee: 323 km (200 mi). Inclination: 31.0000 deg. Period: 113.40 min. Summary: Engineering tests. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E .
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