a_v_bw_o_n (unnumbered, 63-Apollo-120 derivative)
Probable NAA artist's concept that demonstrates the changing/evolving development of the Apollo spacecraft.
When compared to a predecessor depiction (63-Apollo-120), some of the subtle changes are evident...the addition of "corrugation", ullage rockets? and/or fairings?, refinement of S-IVB & CSM external appearance (like the addition of RCS thrusters to the SM). To me, pretty cool shit, but then again, I’m easily amused.
Caption for 63-Apollo-120:
“Artist Drawing by N.A. - The second stage (S-II) engines burn about 6½ minutes, then the stage will be separated and fall away. The S-IV B third stage ignites a single J-2 engine, total thrust 200,000 pounds. The third stage will burn for 2 3/4 minutes placing the configuration in earth orbit.”
My pointless previous observations regarding it:
Note the retrorockets at the forward end of the spent S-II stage firing to ensure a proper and clean separation from the S-IVB stage. Excellent diagram, apparently from page 5-27 of the AS-506 (Apollo 11) Saturn V Flight Manual:
web.archive.org/web/20010223045948/www.apollosaturn.com/s...
With what I’m assuming to be the extracted text:
“At the forward end of the S-II stage was the conical interstage connecting to the S-IVB stage. After S-II burnout, the interstage would be severed at the base of the S-IVB, and would remain attached to the S-II. Four retrorockets assured that the S-II would move backwards relative to the S-IVB. Each rocket had 268.2 pounds of solid propellant and produced 34,810 pounds of thrust for 1.52 seconds.”
All courtesy/credit:
UP-SHIP.com website at:
up-ship.com/blog/?p=18233
a_v_bw_o_n (unnumbered, 63-Apollo-120 derivative)
Probable NAA artist's concept that demonstrates the changing/evolving development of the Apollo spacecraft.
When compared to a predecessor depiction (63-Apollo-120), some of the subtle changes are evident...the addition of "corrugation", ullage rockets? and/or fairings?, refinement of S-IVB & CSM external appearance (like the addition of RCS thrusters to the SM). To me, pretty cool shit, but then again, I’m easily amused.
Caption for 63-Apollo-120:
“Artist Drawing by N.A. - The second stage (S-II) engines burn about 6½ minutes, then the stage will be separated and fall away. The S-IV B third stage ignites a single J-2 engine, total thrust 200,000 pounds. The third stage will burn for 2 3/4 minutes placing the configuration in earth orbit.”
My pointless previous observations regarding it:
Note the retrorockets at the forward end of the spent S-II stage firing to ensure a proper and clean separation from the S-IVB stage. Excellent diagram, apparently from page 5-27 of the AS-506 (Apollo 11) Saturn V Flight Manual:
web.archive.org/web/20010223045948/www.apollosaturn.com/s...
With what I’m assuming to be the extracted text:
“At the forward end of the S-II stage was the conical interstage connecting to the S-IVB stage. After S-II burnout, the interstage would be severed at the base of the S-IVB, and would remain attached to the S-II. Four retrorockets assured that the S-II would move backwards relative to the S-IVB. Each rocket had 268.2 pounds of solid propellant and produced 34,810 pounds of thrust for 1.52 seconds.”
All courtesy/credit:
UP-SHIP.com website at:
up-ship.com/blog/?p=18233