Kosmos 155

  1967-033A

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Zenit-4 No. 28 was the first Zenit launch to 51.8 degrees during 1967.

Kosmos-155
Date	Time	Event	Orbit
1967 Apr 12	1051:02	Launch by 11A57	KB
	1055	Blok-I burn
	1100	Blok-I sep	89.1 193 x 272 x 51.8 (RAE)
1967 Apr 12	1806		89.29 202 x 276 x 51.8
1967 Apr 19	2227		89.11 199 x 261 x 51.8
1967 Apr 20	1027?	Deorbit
	1052?	Landed

Kosmos 133

  1966-107A

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The first Soyuz 7K-OK test flight  was spacecraft 11F615 No. 2, launched on 1966 Nov 28 and designated Kosmos-133. It was the first flight of the 11A511 Soyuz launch vehicle. 7K-OK No. 1, the passive target, was to be launched the next day but after orbit insertion 7K-OK No. 2's DPO attitude control system fired to depletion sending the craft tumbling at two revs per min. The DPO engines were also used by the SKD main engine, so the backup DKD engine was considered for deorbit, but its attitude control system turned out to be connected up wrong. A first deorbit burn was made on Rev 18 with a cutoff at 10s, and another on the next rev failed after 15s. An attempt to counteract decay until the next passes over the USSR also failed.

The next day's burn was mostly nominal except that it cut off late. One report says that the descent module was exploded on command when it was discovered that the trajectory was taking it on course for an impact in China or South Korea. The Kamanin diaries suggest the auto destruct cut in when it overshot the USSR and fell in the Pacific east of the Mariana Is.

Kosmos-133
Date	Time	Event	Orbit
1966 Nov 28	1100	Launch by 11A511	KB
	1104	Blok-I burn
	1109	Blok-I sep	88.39 141 x 249 x 51.78
1966 Nov 29	0000		174 x 220 x 51.83
	1430?	Rev 18 SKD burn deorbit, 10s
	1620?	Rev 19 SKD burn deorbit, 15s
	1750?	Rev 20? SKD burn raise, 20s
1966 Nov 30	0200		148 x 173 x 51.82
	0945?	Rev 33 SKD burn deorbit, early cutoff
	1120?	Rev 34 SKD deorbit
	1135?	PAO, BO sep
	1140?	Reentry

Apollo AS-203

  1966-059A

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The Apollo-Saturn 203 (AS-203) mission was launched at 1453 on 1966 Jul 5 by Uprated Saturn I from LC37B at Cape Kennedy. The rocket carried the S-IVB-203 stage, the S-IU-203 instrument unit (a new design), and a special nose fairing. The fairing was a double angle cone with a Q-ball tip. Length of the fairing was 9.53m with base diameter 6.60m.

The inboard S-I engines cut off at T+2:18, followed by the outboard ones at T+2:22. Two camera capsules were ejected from the S-IB. The S-IVB ignited at 1455, cutting off at 1500 (T+4:50), and entering an 88.3 min 183 x 212 km x 32.0 deg. The LH2 tank was about half full at orbit insertion. The engine restart capability was briefly demonstrated but no ignition was performed. On the 4th orbit a pressure differential test on the LOX/LH2 common bulkhead was performed; the LOX tank had been depressurized, and the LH2 tank valves were closed while pressure built up due to external heating. Pressure rose well in excess of design values and the stage disintegrated at 2114 on 1966 Jul 5.

AS-203
Date	Time	Event	Orbit
1966 Jul 5	1453:17	Launch by Saturn IB	CK LC37B
	1455:36	T+2:19 IECO
	1455:39	T+2:22 OECO, 3.059m/s
	1455:40	T+2:23 Staging	-5930 x 134
	1455:41	T+2:24 S4B MES
	1455:52	T+2:35 Ullage case jettison
	1456:05	T+2:48 Camera capsules eject from SIB
	1456:12	Panel sep
	1457:48	S-IB apogee
	1500:30	T+7:13 S4B MECO
	1501:25	T+8:08 LH2 CVS on
	1501		88.21 185 x 187 x 32.0 (MPR)
	1503:01	S-IB impact
	1625	T+1:32 LH2 CVS off
	1627	Rev 2	88.42 193 x 200 x 32.0 (MPR)
	1631	Engine restart prep
	1738		88.49 184 x 214 x 32.0 (TLE)
	1754	T+3:01 Begin fuel chilldown
	1800	T+3:07 Venting tests
	1803	Rev 3	88.56 196 x 209 x 32.0 (MPR)
	1936	Rev 4	88.70 202 x 217 x 32.0 (MPR)
	1937	T+4:44 Venting tests end
	2045	LH2 Pressure test
	2108	Final data
	2114	Disintegrated