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originally posted by: Bhadhidar
From the diagrams in the linked document, the payload capacity of the orbital vehicle appears disproportionately limited given the size of orbital vehicle itself.
It doesn’t appear to be an economically reasonable solution.
originally posted by: PhantomTwo
a reply to: t34r3b
How does the orbiter separate from the mothership without breaking it’s vertical stabilizers?
Doesn’t the pdf read like the Boeing Beta actually existed in some form since that program gave them so much data they deem reliable?
In spite of these weight increases, the Beta II vehicle was able to complete the design mission of delivering and returning a 10,000 lb payload to low Earth polar orbit with a gross weight of approximately 1.1 Mlb utilizing only airbreathing propulsion for the initial ascent
The results of this study are shown in Figure 13. The dotted line indicates the point at which redesign of the orbiter internal packing, i.e., resizing of the fuel tanks and payload bay, would be required to fulfill the mission. For payloads above the dotted line, no repackaging would be necessary. For those below the dotted line, resizing of the fuel tanks and payload bay and repackaging would be necessary to complete the mission. As can be seen, performing the design mission to low Earth polar orbit when staging at a Mach number below 6.5 would require repackaging of the orbiter. This result was expected, since the Beta-131 orbiter was designed for staging at Mach 6.5. The maximum payload capability of the orbiter ascending to a nominal Space Station orbit is approximately 17,500 lb when staging at Mach 6.5. A 20,000 lb payload could be delivered to a low equatorial orbit at the same staging Mach number.