Gemini 9 Press Kit - heroicrelics Mirror

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At 27 hours into thc f'liekit, ttlcl crcw will Lc;:j n prcpraLiori f'or the first of two planned re-rcndczvous mancuvcr:;. 'I'hc cqu i pcriod rcrendezvous is the same type o[' manl:UVcr wllich had bccn p1;liiiic.d l'or Gc:ini~~i 8. It will be a complctely onboard operation using Lhc compuLcr and n hand-held sextant to obtain guidance informaLion. The purposc of' Lhi:; rcrendezvous is to simulate the terminal phasc oI' il passivc I,argcL rcntlc;.- VOUS which will be performed on a later Gemini mission. 'Chc T':L(.Lxr wiL1. not be used except as a backup if visual contact is lost wiLh the tar'i~,ct. At 27 hours 27 minutes (27:27) GET in the 18th rwolution ovcr lil\T, the Gemini spacecraft will perform an upward radial translation of 20 i'ps. The new orbit will be equiperiod with the ATDA orbit, i.e.: the pcrifiet. and apogee points of the two orbits do not coincide, but thc orbital period is the same. Gemini will have a perigee of 182 milcs and an apogee Of 188 miles. The spacecraft will travel above and behind thc ATDA ilito sunset. The maximum separation distance will be 13 miles behind thc A'i.'DA. A midcourse correction may be made if necessary At 28 hours and 40 minutes (28:k)) GET, the terminal phnsc iIlit,i;Ltiun will begin. A 1.9 fps burn retrograde will bc made to put I,hc> SI);LCc'Cra1'tj on ar. %JO-degree intercept, i.e.: rendezvous will occur 80 tkp-eCS around tne Earth from that point: The pilots will bc in a heads-down attitude to . - C C ~ the ~ ~ spacecraft ' ~ windows from direct sunlight. Thc target must, be -JiSLh>Y acquired to perform terminal phase maneuvers. Line of sigrlt ele- 'latior, and sun-angle time histories will be scaled for a passive rendezvous, SO the side of the ATDA toward the spacecra€t is illuminated. nan@e an2 range rate will be scaled at 40 per cent. -I ;-
Cormonly known as rcndczvous ['r'om above, tliis rc-rc.ixJc:zvous is designed to simulate a lunar rcndczvous which cou1.d take place il' the hnar module had descended to the 50,000 rooL :level abov(> Ltie Moon's surface and a decision not to conI,i niic ['or a 1;Ltldin,D; was nr~c!c:. 'I'k LM's highly elliptical orbi t would carry it above Llic Coiruntlnd arid Service Module before the two orbits could bu mstclicd. In the Ccmirii maneuver, the spacecraft will make it small rcL1wgraiie maneuver on tlic second day to allow the Gemini to pull npproxiinatcly 86 miles nhca.d of the ATDA during the astronaut rest period. On the following day, thc crew will perform maneuvers which will put the spacecraft in a circular orbit approximately eight miles above the ATDA. The rendezvous l'rom above will begin from this position. The sequence of maneuvcrs is: Separation maneuver -- At 29h.5 GET in the-lgth revolution, the spacecraft will perform a 2.5 fps retrograde burn. approximately one and a half mile:: below the perigee oI' the ATDA and the apogee will be the same as the ATDA. g3in approximately 7.8 miles on the ATDA every revolution. closing maneuver is performed in the 30th revolution, Gemini should be approximately 86 miles ahead of the ATDA. f'ormed The pcrigcie will be With the lowcr perigee, Gemini will When tiit. Closing maneuver - -- Also called the height adjustment maneuver, per- at 47:05 GET in the 30th revolution over Africa. It is a 13.2 fps psigrade maneuver which raises the apogee of the Gemini spacecrar't to i93 miles. %-elliptical maneuver -- Performed over Hawaii on the 30th rcvolutior,, ;TA~ eo-elliptical maneuver executed at 47~50 GET is a 15.7 YpS ban pcsigrace which circularizes the Gemini orbit at 193 miles. Terrfiinal Dhase initiation -- Prior to Canarvon on the 31st revolution, tLe terminal phase maneuver of 16 fps retrograde is performed at 48: 52xinutes. The resulting orbit is 194 by 183 miles.
Page 2 and 3: GEMINI 9A lTl*;SS KIT ADDENPA In th
Page 4 and 5: will remain on a 25-foot unbilical
Page 6 and 7: 9A TURNAIIGUK! CIIRGNOLOGY The foll
Page 8 and 9: T-285 minutes ................... P
Page 10 and 11: -- IAlJNCl I Launch Timer, -- Atlas
Page 12: Intermediate C0rrer.t j on:; -- Twc
Page 17 and 18: Gemini Intermediate Corrections - -
Page 19 and 20: MANNED SPACE FLIGHT TRACKING NETWOR
Page 21 and 22: Other Computer Support The Goddard
Page 23 and 24: - ATDA The ATDA will contain 2 C-ba
Page 25 and 26: In addition to real time commands a
Page 27 and 28: and predicated HF radio propagation
Page 29 and 30: X xxx xx xx : - X 1 xi X x x x x x

Gemini 9 Press Kit - heroicrelics Mirror

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