Appendix B

Flight Data Summary

This Appendix is based on Edward A. Armstrong and John E. Williams, “Gemini Program Flight Summary Report,” MSC-G-R-66-5, July 1966, and Changes 1, November 1966, and 2, January 1967.

A - Achieved; PA - Partially achieved; NA - Not achieved

Mission Description Primary Objectives Result Secondary Objectives Result
Gemini 1,
8 April 1964		 Unmanned, not recovered (mission terminated after 3 orbits), reentered 12 April, during 64th revolution; launch time 11:00:01.69 a.m., e.s.t.; apogee, 320.3 km (173 n.m.), perigee, 160.3 km (86.6 n.m.) Demonstrate GLV performance; flight-qualify subsystems A Evaluate operational procedures for GLV trajectory and cutoff conditions A
'' '' Determine exit heating on GLV and spacecraft A Verify orbital insertion by tracking C-band transponder in spacecraft A
'' '' Demonstrate structural integrity of GLV and spacecraft A Demonstrate performance of launch and tracking networks A
'' '' Demonstrate GLV and ground guidance systems performance in achieving proper orbital insertion A Provide training for flight controllers and prelaunch and launch crews and facilities A
'' '' Monitor, evaluate GLV switchover circuits A - -
Gemini 2,
19 Jan. 1965		 Unmanned, suborbital; launch, 9:03:59.861 a.m., e.s.t.; altitude, 171.1 km (92.4 n.m.); range, 3,422.4 km (1,848 n.m.); duration, 18 mins., 16 secs.; landing, 16°36'N, 49°46'W; miss distance (from planned landing point), 62.9 km (34 n.m.) Demonstrate reentry heat protection during maximum heating reentry A Obtain test results on fuel cell and reactant supply, cryogenics, and communications systems PA1
'' '' Demonstrate structural integrity of spacecraft A Demonstrate and further flight-qualify GLV and spacecraft from countdown through insertion A
'' '' Demonstrate satisfactory performance of major subsystems A Train flight controllers and qualify ground communications and tracking systems A
'' '' Demonstrate checkout and launch procedures A - -
'' '' Evaluate backup guidance steering signals through launch A - -
Gemini 3,
23 March 1965		 Grissom and Young; 3 orbits; launch, 9:24:00.064 a.m., e.s.t.; highest apogee, 224 km (121 n.m.), lowest perigee, 158.5 km (85.6 n.m.); duration, 4 hours, 52 mins., 31 secs.; landing, 22°26' N, 70°51' W; miss distance, 111.1 km (60 n.m.) Demonstrate manned orbital flight; evaluate two-man design A Evaluate flight crew equipment, biomedical instrumentation, and personal hygiene system PA3
'' '' Demonstrate and evaluate tracking network A Perform 3 experiments PA4
'' '' Demonstrate OAMS capability in orbital maneuvers and in retrofire backup A Evaluate low-level longitudinal oscillations (Pogo) of the GLV A
'' '' Demonstrate controlled reentry and landing PA2 General photographic coverage in orbit PA5
'' '' Evaluate major spacecraft subsystems A - -
'' '' Demonstrate systems checkout, prelaunch, and launch procedures A - -
'' '' Demonstrate and evaluate recovery procedures and systems A - -
Gemini 4,
3-7 June 1965		 McDivitt and White; 62 revolutions; launch, 10:15:59.562 a.m., e.s.t.; highest apogee, 296.1 km (159.9 n.m.), lowest perigee, 159.4 km (86.l n.m.); duration, 97 hours, 56 mins., 12 secs.; EVA time, 36 mins.; landing, 27°44'N, 74°11'W; miss distance, 81.4 km (44 n.m.) Evaluate effects of prolonged space flight A Demonstrate and evaluate EVA and control by use of HHMU and tether A
'' '' Demonstrate and evaluate performance of spacecraft and systems in 4-day flight PA6 Stationkeep and rendezvous with second stage of GLV PA7
'' '' Evaluate procedures for crew rest and work cycles, eating schedules, and realtime flight planning A Evaluate spacecraft systems A
'' '' - - Make in- and out-of-plane maneuvers A
'' '' - - Further test OAMS retro backup capability A
'' '' - - Perform 11 experiments A
Gemini V,
21-29 Aug.1965		 Cooper and Conrad; 120 revolutions; launch, 8:59:59.518 a.m., e.s.t.; highest apogee, 349.8 km (188.9 n.m.), lowest perigee, 161.8 km (87.4 n.m.); duration, 190 hours, 55 mins., 14 secs.; landing, 29°44'N, 69°45'W; miss distance, 170.3 km (92 n.m.) Evaluate rendezvous G&N system with REP NA8 Demonstrate controlled reentry guidance NA9
'' '' Demonstrate 8-day capability of spacecraft and crew A Evaluate fuel cell A
'' '' Evaluate effects of weightlessness for 8-day flight A Demonstrate all phases of guidance and control system operation needed for rendezvous A
'' '' - - Evaluate capability of both crewmen to maneuver spacecraft to rendezvous NA10
'' '' - - Checkout rendezvous radar A
'' '' - - Execute 17 experiments PA11
Gemini VI-A12,
15-16 Dec. 1965		 Schirra and Stafford; 16 revolutions; launch, 8:37:26.471 a.m., e.s.t.; highest apogee, 311.3 km (168.1 n.m.), lowest perigee, 160.9 km (86.9 n.m.); duration, 25 hours, 51 mins., 24 secs.; landing, 23°35'N, 67°50'W; miss distance, 12.9 km (7 n.m.) Rendezvous with Gemini VII A Perform closed-loop rendezvous in fourth orbit A
'' '' - - Stationkeep with Gemini VII A
'' '' - - Evaluate reentry guidance capability A
'' '' - - Conduct visibility tests for rendezvous, using Gemini VII as target A
'' '' - - Perform 3 experiments PA13
Gemini VII,
4-18 Dec. 1965		 Borman and Lovell; 206 revolutions; launch, 2:30:03.702 p.m., e.s.t.; highest apogee, 327.9 km (177.1 n.m.), lowest perigee, 161.4 km (87.2 n.m.); duration, 330 hours, 35 mins., 1 sec.; landing, 25°25.1'N, 70°6.7'W; miss distance, 11.8 km (6.4 n.m.) Conduct 14-day mission and evaluate effects on crew A Provide target for Gemini VI-A A
'' '' - - Stationkeep with VI-A and with second stage of GLV A
'' '' - - Conduct 20 experiments A
'' '' - - Evaluate lightweight pressure suit A
'' '' - - Evaluate spacecraft reentry capability A
'' '' - - Conduct systems tests A
Gemini VIII,
16-17 March 1966		 Armstrong and Scott; 7 revolutions; launch, 11:41:02.389 a.m., e.s.t.; highest apogee, 298.7 km (161.3 n.m.); lowest perigee, 159.8 km (86.3 n.m.); duration, 10 hours, 41 mins., 26 secs.; landing, 25°13.8'N, 136°0'E; mission terminated early for electrical short in control system Rendezvous and dock with GATV A Rendezvous and dock in 4th revolution A
'' '' Conduct EVA NA14 Perform docked-vehicle maneuvers NA14
'' '' - - Evaluate systems and conduct 10 experiments PA14
'' '' - - Conduct docking practice and re-rendezvous NA14
'' '' - - Evaluate auxiliary tape unit A
'' '' - - Demonstrate controlled reentry A
'' '' - - Park GATV in 407.4-km (220-n.m.) circular orbit A
Gemini IX-A15,
3-6 June 1966		 Stafford and Cernan; 45 revolutions; launch, 8:39:33.335 a.m., e.s.t.; highest apogee, 311.5 km (168.2 n.m.), lowest perigee, 158.7 km (85.7 n.m.); duration, 72 hours, 20 mins., 50 secs.; EVA time, 2 hours, 7 mins.; landing, 27°52'N, 75°0.4'W; miss distance, 704 m (0.38 n.m.) Rendezvous and dock PA16 Rendezvous with ATDA in 3rd revolution A
'' '' Conduct EVA A Conduct systems evaluation and equiperiod rendezvous A
'' '' - - Execute 7 experiments PA17
'' '' - - Practice docking NA16
'' '' - - Rendezvous from above A
'' '' - - Demonstrate controlled reentry A
Gemini X,
18-21 July 1966		 Young and Collins; 43 revolutions; launch, 5:20:26.648 p.m., e.s.t.; highest apogee, 753.3 km (412.2 n.m.), lowest perigee, 159.8 km (86.3 n.m.); duration, 70 hours, 46 mins., 39 secs.; EVA time, 1 hour, 29 mins.; landing, 26°44.7'N, 71°57'W; miss distance, 6.2 km (3.4 n.m.) Rendezvous and dock with GATV A Rendezvous and dock in 4th revolution A
'' '' - - Rendezvous with GATV 8, using Agena propulsions stems A
'' '' - - Conduct EVA A
'' '' - - Practice docking NA18
'' '' - - Perform 14 experiments PA18
'' '' - - Systems evaluation: bending-mode tests; docked maneuvers; static discharge monitoring; postdocked Agena maneuvers; reentry guidance; park GATV in 352.4 km (190.3 n.m.) orbit A
Gemini XI,
12-15 Sept. 1966		 Conrad and Gordon; 44 revolutions; launch, 9:42:26.546 a.m., e.s.t.; highest apogee, 1,368.9 km (739.2 n.m.), lowest perigee, 160.3 km (86.6 n.m.); duration, 71 hours, 17 mins., 8 secs.; EVA time, 2 hours, 43 mins.; landing, 24°15.4'N, 70°0.0'W; miss distance, 4.9 km (2.65n.m.) Rendezvous and dock with GATV in 1st revolution A Practice docking A
'' '' - - Perform EVA
'' '' - - Conduct 11 experiments PA19
'' '' - - Maneuver while docked (high apogee excursion) A
'' '' - - Conduct tethered vehicle test A
'' '' - - Demonstrate automatic reentry A
'' '' - - Park GATV 10 in 352.4 km orbit A
Gemini XII,
11-15 Nov. 1966		 Lovell and Aldrin; 59 revolutions; launch, 3:46:33.419 p.m., e.s.t.; highest apogee, 301.3 km (162.7 n.m.), lowest perigee, 160.7 km (86.8 n.m.); duration, 94 hours, 34 mins., 31 secs.; EVA time, 5 hours, 30 mins.; landing, 24°35' N, 69°57'W; miss distance, 4.8 km (2.6 n.m.) Rendezvous and dock A Conduct tethered vehicle operation A
'' '' Evaluate EVA A Perform 14 experiments A
'' '' - - Rendezvous and dock in 3rd revolution A
'' '' - - Demonstrate automatic reentry A
'' '' - - Perform docked maneuvers NA20
'' '' - - Practice docking A
'' '' - - Conduct systems tests A
'' '' - - Park GATV 12 in 555.6 km (300 n.m.) orbit NA21
  1. Fuel cell deactivated before liftoff
  2. Angle of attack during reentry lower than expected
  3. Personal hygiene system only partially tested
  4. Operating mechanism failed on S-2, Synergistic Effect of Zero Gravity on Sea Urchin Eggs
  5. Improper lens setting on 16mm camera
  6. Computer-controlled reentry not flown because of inadvertent alteration of computer memory
  7. Separation and rendezvous not attempted because of fuel consumption
  8. REP rendezvous not attempted because of decision to power down fuel cells
  9. 89-mile overshoot caused by incorrect navigation coordinates transmitted to spacecraft computer by ground
  10. Depended on rendezvous with REP
  11. D-2, Nearby Object Photography, not conducted when REP rendezvous was canceled
  12. GATV propulsion failure on 25 Oct. 1965; mission rescheduled
  13. Stationkeeping with Gemini VII interfered with conduct of D-8, Radiation in Spacecraft
  14. Mission terminated early
  15. Atlas failure on 17 May 1966, mission rescheduled
  16. Docking impossible when shroud failed to jettison
  17. S-10, Agena Micrometeorite Collection, not attempted because EVA did take place near GATV
  18. Fuel consumption already too high
  19. D-16, Power Tool Evaluation, canceled when EVA was terminated early
  20. Docked maneuvers canceled because of a propulsion anomaly during GATV insertion
  21. GATV attitude control gas depleted by earlier maneuvers