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The external tank and Space Shuttle Solid Rocket Boosters (SRBs) would be combined with a cargo module that took the place of the shuttle orbiter and included the Space Shuttle Main Engines. A ballistic return pod would be used as the main engine structure and carry 2-4 SSMEs as well as mount the payload/booster stage. It would be recovered via ...
Original North American Rockwell Shuttle delta wing design, 1969: fully reusable, with a flyback crewed booster Maxime Faget's DC-3 concept employed conventional straight wings. During the early shuttle studies, there was a debate over the optimal shuttle design that best-balanced capability, development cost, and operational cost.
The Space Shuttle Solid Rocket Booster (SRB) was the first solid-propellant rocket to be used for primary propulsion on a vehicle used for human spaceflight. [1] A pair of them provided 85% of the Space Shuttle's thrust at liftoff and for the first two minutes of ascent.
The booster's 14 engines would be located in clusters of seven, at the bottom of both halves of the booster. Unlike the final design for the Space Shuttle, the Spacemaster would lack an external tank, and the boosters would be joined, by means of connecting struts which would also serve as the mounting for the orbiter.
A solid rocket booster (SRB) is a solid propellant motor used to provide thrust in spacecraft launches from initial launch through the first ascent. Many launch vehicles, including the Atlas V, [1] SLS and Space Shuttle, have used SRBs to give launch vehicles much of the thrust required to place the vehicle into orbit.
NASA started the Space Shuttle design process in 1968, with the vision of creating a fully reusable spaceplane using a crewed fly-back booster. This concept proved expensive and complex, therefore the design was scaled back to reusable solid rocket boosters and an expendable external tank .
Like the Space Shuttle's RSRM, operating voltage for the electrical system was 28V DC. [7] An electrical detonator is used to activate pyrotechnics for booster ignition and staging, and for the flight termination system, which consists of a shaped charge explosive designed to destroy the booster in flight. [ 7 ]
Originally developed for the Space Shuttle, different versions of the PAM were developed: PAM-A (Atlas class), development terminated; originally to be used on both the Atlas and Space Shuttle, designed for satellites up to 4,400 lb (2,000 kg) PAM-D (Delta class), uses a Star-48B rocket motor, designed for satellites up to 2,750 lb (1,250 kg) [2]