Lambda home
topic index
Lamda-4S
All-solid orbital launch vehicle. Country: Japan. Status: Retired 1977.

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.

Manufacturer: Mitsubishi. Launches: 35. Failures: 6. Success Rate: 82.86%. First Launch Date: 1963-08-10. Last Launch Date: 1977-08-16. Launch data is: complete. Version:

LS-A.
LS-A rocket
Credit - NASDA
Test vehicle.

Early suborbital test version of the Lambda rocket series.

2 stage vehicle consisting of 1 x LS-A Booster + 1 x LS-A

Launches: 4. First Launch Date: 1963-08-10. Last Launch Date: 1965-11-22. Apogee: 150 km (90 mi). Liftoff Thrust: 60.000 kN (13,488 lbf). Total Mass: 800 kg (1,760 lb). Core Diameter: 0.35 m (1.14 ft). Total Length: 7.50 m (24.60 ft).

  • Stage1: 1 x LS-A-1. Gross Mass: 400 kg (880 lb). Motor: 1 x LS-A Booster. Thrust (vac): 60.000 kN (13,488 lbf). Burn time: 10 sec. Length: 3.00 m (9.80 ft). Diameter: 0.35 m (1.14 ft). Propellants: Solid.
  • Stage2: 1 x LS-A-2. Gross Mass: 300 kg (660 lb). Motor: 1 x LS-A. Thrust (vac): 10.000 kN (2,248 lbf). Burn time: 35 sec. Length: 4.50 m (14.70 ft). Diameter: 0.30 m (0.98 ft). Propellants: Solid.
Version:

LS-C. Test vehicle.

Two stage vehicle consisting of 1 x LS-C Booster + 1 x LS-C

Launches: 8. First Launch Date: 1968-09-19. Last Launch Date: 1974-02-09. Apogee: 100 km (60 mi). Liftoff Thrust: 0 N ( lbf). Total Mass: 2,300 kg (5,000 lb). Core Diameter: 0.60 m (1.96 ft). Total Length: 10.30 m (33.70 ft).

  • Stage1: 1 x LS-C-1. Gross Mass: 300 kg (660 lb). Motor: 1 x LS-C. Length: 2.50 m (8.20 ft). Diameter: 0.60 m (1.96 ft). Propellants: Solid.
  • Stage2: 1 x LS-C-2. Gross Mass: 300 kg (660 lb). Motor: 1 x LS-C. Length: 4.00 m (13.10 ft). Diameter: 0.60 m (1.96 ft). Propellants: Solid.
Version:

LSC-3.
LSC-3 rocket
Credit - NASDA
Test vehicle.

Early suborbital test version of the Lambda rocket series.

Version:

Lambda 2. Test vehicle.

3-4 stage vehicle series.

Manufacturer: ISAS. Launches: 2. Failures: 1. First Launch Date: 1963-08-24. Last Launch Date: 1963-12-11. Payload: 180 kg (390 lb). Apogee: 500 km (310 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 6,300 kg (13,800 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 15.50 m (50.80 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 2-2. Gross Mass: 1,400 kg (3,000 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x K420. Thrust (vac): 110.000 kN (24,720 lbf). Burn time: 17 sec. Length: 8.70 m (28.50 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
Version:

Lambda 3. Test vehicle.

Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x K420 + 1 x Kappa 8

Manufacturer: ISAS. Launches: 3. First Launch Date: 1964-07-11. Last Launch Date: 1965-03-18. Apogee: 2,150 km (1,330 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 7,000 kg (15,400 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 17.40 m (57.00 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 3-2. Gross Mass: 1,800 kg (3,900 lb). Empty Mass: 300 kg (660 lb). Motor: 1 x K420. Thrust (vac): 110.000 kN (24,720 lbf). Burn time: 17 sec. Length: 11.00 m (36.00 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
  • Stage3: 1 x Lambda 3-3. Gross Mass: 500 kg (1,100 lb). Empty Mass: 100 kg (220 lb). Motor: 1 x K420. Thrust (vac): 110.000 kN (24,720 lbf). Length: 4.80 m (15.70 ft). Diameter: 0.42 m (1.37 ft). Propellants: Solid.
Version:

Lambda 3H. Test vehicle.

Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500

Manufacturer: ISAS. Launches: 9. First Launch Date: 1966-03-05. Last Launch Date: 1977-08-16. Apogee: 2,000 km (1,200 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 8,200 kg (18,000 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 16.50 m (54.10 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 4SC-2. Gross Mass: 2,500 kg (5,500 lb). Motor: 1 x L735(1/3). Thrust (vac): 118.000 kN (26,527 lbf). Burn time: 38 sec. Length: 3.90 m (12.70 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage3: 1 x Lambda 4S-3. Gross Mass: 800 kg (1,760 lb). Motor: 1 x L500. Thrust (vac): 69.000 kN (15,511 lbf). Burn time: 27 sec. Length: 2.50 m (8.20 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
Version:

Lambda 4. Status: Out of production.

First Japanese orbital launch vehicle.

Manufacturer: Nissan. LEO Payload: 26 kg (57 lb). Associated Spacecraft: Ohsumi, Osumi. Version:

Lambda 4S.

Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S

Manufacturer: ISAS. Launches: 5. Failures: 4. First Launch Date: 1966-09-26. Last Launch Date: 1970-02-11. LEO Payload: 26 kg (57 lb). Apogee: 5,000 km (3,100 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 9,400 kg (20,700 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 16.50 m (54.10 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 4SC-2. Gross Mass: 2,500 kg (5,500 lb). Motor: 1 x L735(1/3). Thrust (vac): 118.000 kN (26,527 lbf). Burn time: 38 sec. Length: 3.90 m (12.70 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage3: 1 x Lambda 4S-3. Gross Mass: 800 kg (1,760 lb). Motor: 1 x L500. Thrust (vac): 69.000 kN (15,511 lbf). Burn time: 27 sec. Length: 2.50 m (8.20 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
  • Stage4: 1 x Lambda 4T-4. Gross Mass: 100 kg (220 lb). Empty Mass: 15 kg (33 lb). Motor: 1 x L480S. Thrust (vac): 7.800 kN (1,754 lbf). Burn time: 32 sec. Length: 0.50 m (1.64 ft). Diameter: 0.48 m (1.57 ft). Propellants: Solid.
Version:

Lambda 4SC.

Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S

Manufacturer: ISAS. Launches: 3. Failures: 1. First Launch Date: 1971-08-20. Last Launch Date: 1974-09-01. Apogee: 2,000 km (1,200 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 9,400 kg (20,700 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 16.50 m (54.10 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 4SC-2. Gross Mass: 2,500 kg (5,500 lb). Motor: 1 x L735(1/3). Thrust (vac): 118.000 kN (26,527 lbf). Burn time: 38 sec. Length: 3.90 m (12.70 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage3: 1 x Lambda 4S-3. Gross Mass: 800 kg (1,760 lb). Motor: 1 x L500. Thrust (vac): 69.000 kN (15,511 lbf). Burn time: 27 sec. Length: 2.50 m (8.20 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
  • Stage4: 1 x Lambda 4T-4. Gross Mass: 100 kg (220 lb). Empty Mass: 15 kg (33 lb). Motor: 1 x L480S. Thrust (vac): 7.800 kN (1,754 lbf). Burn time: 32 sec. Length: 0.50 m (1.64 ft). Diameter: 0.48 m (1.57 ft). Propellants: Solid.
Version:

Lambda 4T.

Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S

Manufacturer: ISAS. Launches: 1. First Launch Date: 1969-09-03. Last Launch Date: 1969-09-03. Apogee: 2,000 km (1,200 mi). Liftoff Thrust: 970.000 kN (218,060 lbf). Total Mass: 9,400 kg (20,700 lb). Core Diameter: 0.74 m (2.42 ft). Total Length: 16.50 m (54.10 ft).

  • Stage0: 2 x Mu-3C-0. Gross Mass: 500 kg (1,100 lb). Empty Mass: 190 kg (410 lb). Motor: 1 x SB-310. Thrust (vac): 95.000 kN (21,356 lbf). Burn time: 7.40 sec. Length: 5.80 m (19.00 ft). Diameter: 0.31 m (1.01 ft). Propellants: Solid.
  • Stage1: 1 x Lambda 3-1. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 2,945 kg (6,492 lb). Motor: 1 x L735. Thrust (vac): 410.000 kN (92,170 lbf). Burn time: 29 sec. Length: 8.40 m (27.50 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage2: 1 x Lambda 4SC-2. Gross Mass: 2,500 kg (5,500 lb). Motor: 1 x L735(1/3). Thrust (vac): 118.000 kN (26,527 lbf). Burn time: 38 sec. Length: 3.90 m (12.70 ft). Diameter: 0.74 m (2.42 ft). Propellants: Solid.
  • Stage3: 1 x Lambda 4S-3. Gross Mass: 800 kg (1,760 lb). Motor: 1 x L500. Thrust (vac): 69.000 kN (15,511 lbf). Burn time: 27 sec. Length: 2.50 m (8.20 ft). Diameter: 0.50 m (1.64 ft). Propellants: Solid.
  • Stage4: 1 x Lambda 4T-4. Gross Mass: 100 kg (220 lb). Empty Mass: 15 kg (33 lb). Motor: 1 x L480S. Thrust (vac): 7.800 kN (1,754 lbf). Burn time: 32 sec. Length: 0.50 m (1.64 ft). Diameter: 0.48 m (1.57 ft). Propellants: Solid.
Lambda Chronology

1963 August 10 - 03:17 GMT - Niijima -. LS-A Sustainer Test mission Agency: STA. Apogee: 50 km (31 mi).

1963 August 24 - 02:00 GMT - Kagoshima L. Lambda 2 L-2-1 FAILURE: Failure. Ionosphere / test Agency: ISAS. Apogee: 51 km (31 mi).

1963 December 11 - 05:00 GMT - Kagoshima L. Lambda 2 L-2-2 Ionosphere mission Agency: ISAS. Apogee: 410 km (250 mi).

1964 July 11 - 02:02 GMT - Kagoshima L. Lambda 3 L-3-1 Ionosphere mission Agency: ISAS. Apogee: 857 km (532 mi).

1964 July 22 - 02:50 GMT - Niijima -. LS-A-1 Test mission Agency: STA. Apogee: 150 km (90 mi).

1964 July 22 - 08:55 GMT - Niijima -. LS-A-2 Test mission Agency: STA. Apogee: 150 km (90 mi).

1965 January 31 - 05:01 GMT - Kagoshima L. Lambda 3 L-3-2 Ionosphere mission Agency: ISAS. Apogee: 1,040 km (640 mi).

1965 March 18 - 10:07 GMT - Kagoshima L. Lambda 3 L-3-3 X-ray astronomy mission Agency: ISAS. Apogee: 1,085 km (674 mi).

1965 November 22 - 06:35 GMT - Niijima -. LS-A-3 Test mission Agency: STA. Apogee: 150 km (90 mi).

1966 March 5 - 04:50 GMT - Kagoshima L. Lambda 3H L-3H-1 X-ray astronomy mission Agency: ISAS. Apogee: 1,829 km (1,136 mi).

1966 July 23 - 06:35 GMT - Kagoshima L. Lambda 3H L-3H-2 Gyro-plasma probe Ionosphere / aeronomy mission Agency: ISAS. Apogee: 1,800 km (1,100 mi).

1966 September 26 - 02:58 GMT - Kagoshima L. Lambda 4S L-4S-1 FAILURE: Fourth stage attitude control failed. Ohsumi 1 Mass: 26 kg (57 lb). Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi).

1966 December 20 - 02:20 GMT - Kagoshima L. Lambda 4S L-4S-2 FAILURE: Fourth stage failed to ignite. Ohsumi 2 Mass: 26 kg (57 lb). Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi).

1967 February 6 - 02:10 GMT - Kagoshima L. Lambda 3H L-3H-3 Ionosphere / chemical release / x-ray astronomy mission Agency: ISAS. Apogee: 2,150 km (1,330 mi).

1967 April 13 - Kagoshima L. Lambda 4S L-4S-3 FAILURE: Fourth stage failed to ignite. Ohsumi 3 Mass: 26 kg (57 lb). Spacecraft: Ohsumi. Agency: ISAS. Apogee: 200 km (120 mi).

1968 September 19 - 01:58 GMT - Tanegashima T. LS-C-D Test mission Agency: STA. Apogee: 100 km (60 mi).

1969 January 16 - Kagoshima L. Lambda 3H L-3H-4 Ionosphere mission Agency: ISAS. Apogee: 1,800 km (1,100 mi).

1969 February 6 - 06:31 GMT - Tanegashima T. LS-C-1 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1969 September 3 - Kagoshima L. Lambda 4T L-4T-1 Test mission Agency: ISAS. Apogee: 400 km (240 mi).

1969 September 10 - 06:30 GMT - Tanegashima T. LS-C-2 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1969 September 22 - 02:10 GMT - Kagoshima L. Lambda 4S L-4S-4 FAILURE: Fourth stage control system malfunction after third stage collided with fourth stage. Ohsumi 4 Mass: 25 kg (55 lb). Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi).

1970 January 21 - 02:10 GMT - Kagoshima L. Lambda 3H L-3H-6 Ionosphere / plasma mission Agency: ISAS. Apogee: 1,848 km (1,148 mi).

1970 February 3 - 06:03 GMT - Tanegashima T. LS-C-3 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1970 February 11 - 04:25 GMT - Kagoshima L. Lambda 4S L-4S-5 Ohsumi 5 Mass: 12 kg (26 lb). Spacecraft: Osumi. Agency: ISAS. Perigee: 323 km (200 mi). Apogee: 2,440 km (1,510 mi). Inclination: 31.00 deg. Period: 113.40 min. Engineering tests. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E

1970 September 9 - 06:40 GMT - Tanegashima T. LS-C-4 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1970 September 19 - 11:30 GMT - Kagoshima L. Lambda 3H L-3H-5 X-ray / ultraviolet astronomy mission Agency: ISAS. Apogee: 2,017 km (1,253 mi).

1971 August 20 - Kagoshima L. Lambda 4SC L-4SC-1 FAILURE: Failure. TVC test Agency: ISAS. Apogee: 1,500 km (900 mi).

1971 September 3 - 12:00 GMT - Kagoshima L. Lambda 3H L-3H-7 Aeronomy / ionosphere / x-ray astronomy mission Agency: ISAS. Apogee: 1,718 km (1,067 mi).

1971 September 10 - 06:47 GMT - Tanegashima T. LS-C-5 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1972 September 25 - 06:05 GMT - Tanegashima T. LS-C-6 Test mission Agency: NASDA. Apogee: 100 km (60 mi).

1973 January 28 - Kagoshima L. Lambda 4SC L-4SC-2 TVC test Agency: ISAS. Apogee: 1,500 km (900 mi).

1974 January 22 - 11:00 GMT - Kagoshima L. Lambda 3H L-3H-8 St 2: 329 km X-ray astronomy mission Agency: ISAS. Apogee: 1,571 km (976 mi).

1974 February 9 - 06:30 GMT - Tanegashima T. LS-C-7 LE-3 test Agency: NASDA. Apogee: 100 km (60 mi).

1974 September 1 - Kagoshima L. Lambda 4SC L-4SC-3 TVC test Agency: ISAS. Apogee: 1,500 km (900 mi).

1977 August 16 - 11:15 GMT - Kagoshima L. Lambda 3H L-3H-9 Aeronomy / ionosphere / plasma mission Agency: ISAS. Apogee: 1,294 km (804 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.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: http://msl.jpl.nasa.gov/home.html.
  • Gatland, Kenneth, Missiles and Rockets, Macmillan, New York, 1975.
  • Ley, Willy, Rockets Missiles and Men in Space, Viking Press, New York, 1968.
  • Bramscher, Robert G, Spaceflight, "A Survey of Launch Vehicle Failures", 1980, Volume 22, page 351.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.

© Mark Wade, 1997 - 2008 except where otherwise noted.