STSprog/fut_v_c_o_AKP (ca. 1970, prob GAC photo, verso hand-annotated 70 5601)
In this gorgeous ca. 1970 Grumman Aerospace Corporation artist’s concept, a “Design 532” shuttle orbiter is depicted coming in for a powered landing at KSC, using its deployed forward-mounted air-breathing engines. Amongst other things, note the VAB & full shuttle stack rolling out to Launch Complex 39 in the background.
I assume/am hoping the orbiter’s concrete runway (future SLF?) is just outside of the image to the left. 😉
“DESIGN 532
Design 532 is a quite different response which we believe holds promise for answering the question "Can we limit the program risk?" If Design 518 yields a program requiring a funding pattern as shown in Fig. S-2, we will face a situation which may permit neither the development of the space shuttle system nor the development of its payloads. This consideration as well as the NASA/MSC interest in a smaller, simpler, vehicle which could fly earlier, led to the development of Design 532.
Design 532 is a fully reusable, two-stage space shuttle with an initial low cross-range payload of 12,800 lb. Design 532 is also designed for the high aerodynamic cross-range potential and makes provisions for phased implementation of increased payload and performance capability. This approach permits a stepwise increase in capability and growth while decoupling the technical risk and reducing initial cost. Using engines and electronics derived from existing equipment should assure an earlier first flight. Additional performance becomes available with introduction of the high-pressure orbiter engines with a payload of 22,600 lb.
The Design 532 booster is fully reusable with LOX/RP-1 propellants and five F1 engines. A deliberately conservative approach to the design of the booster minimizes technical risk and cost by avoiding development of large-scale hydrogen tankage. Development savings of several hundred million dollars per year appear possible for this orbiter-booster combination.
The Design 532 orbiter will, at first, use three J2S engines, operate at low cross range, and be fitted with first generation avionics. The baseline Design 532 orbiter is achieved by subsequent installation of the high Isp, high-pressure 250,000 lb. thrust engines. Improved thermal protection systems extend cross range, and second-generation electronics improve operational efficiency. We believe that operational experience with the orbiter will show that for certain missions the air-breathing engines are not required. Therefore, the flying qualities have been tailored to accommodate both engine weight in and engine weight out cg positions. Removal of the air-breathing engines and reduction of on-orbit propellant will increase payload capacity to orbit to 52,700 lb. As a further step to make even heavier up-payloads possible, we have made provisions for a potential non-reusable kick stage. This would raise the payload limit to 76,500 lb. In conjunction with this attention to capacity for heavy payloads, the Design 532 cargo bay has been conceived as a "flat-bed" sized for a 10 ft. diameter payload carried internally, 15 ft. diameter carried semi-submerged, and for 22 ft. diameter carried externally.
To summarize, Design 532 is based on the following considerations:
- Reduced initial funding requirements
- Payload flexibility and growth
- Early initial flight date and initial operational capability"
The above, accompanied by supporting figures & diagrams…and a whole lot more, at:
ntrs.nasa.gov/api/citations/20160012503/downloads/2016001...
Context regarding the referenced Design 518 can also be found within the document, to include size, engine configuration, payload capacity, etc.
Last, but not least, as I cautiously suspected, the work is confirmed to be by Craig Kavafes. Fortunately, enough of his distinctive signature ‘made the cut’.
STSprog/fut_v_c_o_AKP (ca. 1970, prob GAC photo, verso hand-annotated 70 5601)
In this gorgeous ca. 1970 Grumman Aerospace Corporation artist’s concept, a “Design 532” shuttle orbiter is depicted coming in for a powered landing at KSC, using its deployed forward-mounted air-breathing engines. Amongst other things, note the VAB & full shuttle stack rolling out to Launch Complex 39 in the background.
I assume/am hoping the orbiter’s concrete runway (future SLF?) is just outside of the image to the left. 😉
“DESIGN 532
Design 532 is a quite different response which we believe holds promise for answering the question "Can we limit the program risk?" If Design 518 yields a program requiring a funding pattern as shown in Fig. S-2, we will face a situation which may permit neither the development of the space shuttle system nor the development of its payloads. This consideration as well as the NASA/MSC interest in a smaller, simpler, vehicle which could fly earlier, led to the development of Design 532.
Design 532 is a fully reusable, two-stage space shuttle with an initial low cross-range payload of 12,800 lb. Design 532 is also designed for the high aerodynamic cross-range potential and makes provisions for phased implementation of increased payload and performance capability. This approach permits a stepwise increase in capability and growth while decoupling the technical risk and reducing initial cost. Using engines and electronics derived from existing equipment should assure an earlier first flight. Additional performance becomes available with introduction of the high-pressure orbiter engines with a payload of 22,600 lb.
The Design 532 booster is fully reusable with LOX/RP-1 propellants and five F1 engines. A deliberately conservative approach to the design of the booster minimizes technical risk and cost by avoiding development of large-scale hydrogen tankage. Development savings of several hundred million dollars per year appear possible for this orbiter-booster combination.
The Design 532 orbiter will, at first, use three J2S engines, operate at low cross range, and be fitted with first generation avionics. The baseline Design 532 orbiter is achieved by subsequent installation of the high Isp, high-pressure 250,000 lb. thrust engines. Improved thermal protection systems extend cross range, and second-generation electronics improve operational efficiency. We believe that operational experience with the orbiter will show that for certain missions the air-breathing engines are not required. Therefore, the flying qualities have been tailored to accommodate both engine weight in and engine weight out cg positions. Removal of the air-breathing engines and reduction of on-orbit propellant will increase payload capacity to orbit to 52,700 lb. As a further step to make even heavier up-payloads possible, we have made provisions for a potential non-reusable kick stage. This would raise the payload limit to 76,500 lb. In conjunction with this attention to capacity for heavy payloads, the Design 532 cargo bay has been conceived as a "flat-bed" sized for a 10 ft. diameter payload carried internally, 15 ft. diameter carried semi-submerged, and for 22 ft. diameter carried externally.
To summarize, Design 532 is based on the following considerations:
- Reduced initial funding requirements
- Payload flexibility and growth
- Early initial flight date and initial operational capability"
The above, accompanied by supporting figures & diagrams…and a whole lot more, at:
ntrs.nasa.gov/api/citations/20160012503/downloads/2016001...
Context regarding the referenced Design 518 can also be found within the document, to include size, engine configuration, payload capacity, etc.
Last, but not least, as I cautiously suspected, the work is confirmed to be by Craig Kavafes. Fortunately, enough of his distinctive signature ‘made the cut’.