Black Horse Profile Mission profile for the proposed Black Horse air-refuelable launch vehicle. The Black Horse would, lightly loaded, take off horizontally from a runway and rendezvous with a tanker for in-flight fuelling of non-cyrogenic lower specific impulse propellants. The Black Horse would then boost itself to suborbital velocity, releasing an upper stage for orbital insertion of its payload. The winged vehicle would then return to its base for a runway landing and reuse. 48,800 bytes. 611 x 450 pixels.

Winged, single stage to orbit launch vehicle using aerial refueling and lower performance, non-cryogenic propellants. Takes off from runway at 22,000 kg gross weight; rendezvous with tanker to load 66,760 kg oxidizer; then flies to orbit.

---

Black Horse Credit: © Mark Wade. 3,280 bytes. 296 x 400 pixels.

---

LEO Payload: 450 kg. to: 200 km Orbit. at: 0.0 degrees. Liftoff Thrust: 45,193 kgf. Total Mass: 84,100 kg. Core Diameter: 6.3 m. Total Length: 69.0 m.

• Stage Number: 1. 1 x Black Horse Gross Mass: 83,560 kg. Empty Mass: 6,883 kg. Thrust (vac): 45,193 kgf. Isp: 335 sec. Burn time: 560 sec. Diameter: 6.3 m. Span: 39.5 m. Length: 57.5 m. Propellants: H2O2/Kerosene No Engines: 7. JP-5/H2O2

  ---

  Black Horse - Black Horse Launch Vehicle 3 View Credit: © Mark Wade. 4,944 bytes. 502 x 542 pixels.

  ---

• 213 - Zubrin, Robert M, and Clapp, Mitchell B, Black Horse Web Site, "Black Horse: One Stop to Orbit", . HTML when accessed: http://www.im.lcs.mit.edu/bh/analog.html