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, 1636'N, 4946'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, 2226' N, 7051' 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, 2744'N, 7411'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, 2944'N, 6945'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, 2335'N, 6750'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, 2525.1'N, 706.7'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, 2513.8'N, 1360'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, 2752'N, 750.4'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, 2644.7'N, 7157'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, 2415.4'N, 700.0'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, 2435' N, 6957'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


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