Encyclopedia Astronautica
26KS20000


Solid propellant rocket stage. Loaded/empty mass 1,264/268 kg. Thrust 75.70 kN. Four-finned version.

AKA: Black Brant 5C.
Status: Active.
Gross mass: 1,264 kg (2,786 lb).
Unfuelled mass: 268 kg (590 lb).
Height: 5.30 m (17.30 ft).
Diameter: 0.44 m (1.44 ft).
Thrust: 75.70 kN (17,018 lbf).
Burn time: 27 s.
Number: 578 .

More... - Chronology...


Associated Countries
Associated Engines
  • 26KS20000 Bristol Aerospace solid rocket engine. 75.7 kN. Four-finned version. More...

Associated Launch Vehicles
  • Black Brant 5B Canadian sounding rocket. Three-fin version. The Black Brant VB provided slightly improved performance over the VC. The burnout roll rate for the Black Brant V was 4 cycles per second. Maximum longitudinal acceleration varied with payload weight; for a typical payload weight of 270 kg, maximum thrust axis acceleration is approximately 12g's. More...
  • Black Brant 10 Canadian sounding rocket. Three stage vehicle consisting of 1 x Terrier + 1 x Black Brant VB or VC + 1 x Nihka. Payload 90 kg to 1,200 km or 317 kg to 550 km. More...
  • Black Brant 9 Canadian sounding rocket. Two stage vehicle consisting of 1 x Terrier Mk 70 + 1 x Black Brant VB. More...
  • Black Brant 12 Canadian sounding rocket. The Black Brant XII rocket system was a four stage system used primarily to carry a variety of payloads to high altitudes. Its development is a spin-off of the Black Brant X development. Four stage vehicle consisting of 1 x Talos + 1 x Taurus + 1 x Black Brant VB + 1 x Nihka. Payload 136 kg to 1,500 km or 522 kg to 500 km. More...
  • Black Brant 11 Canadian sounding rocket. Three stage vehicle. Payload weights of 320 kg to 500 km or 550 kg to 350 km altitude. More...

Associated Manufacturers and Agencies
  • Bristol Canadian manufacturer of rocket engines and rockets. Bristol Aerospace Limited, Winnipeg, Manitoba, Canada. More...

Associated Propellants
  • Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...

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