After several tests indicating the model was too small to permit refinements, Goddard decided to build a rocket twenty-fold larger. During 1926 a new tower was built, and flow regulators, multiple liquid injection into large combustion chambers, means for measurement of pressure and lifting force, electrically fired igniter, and turntable for rotation were developed.

Little is found. Western intelligence is convinced that the Soviets conduct missile tests from Peenemuende in the late 1940's (the Scandinavian 'ghost rockets'). But Russian historical sources available after the downfall of the Soviet Union do not support this belief.

Launched 08:15 local time. Reached 8.9 km. Carried Solar radiation (Naval Research Lab) experiments for General Electric. The warhead section was replaced with an instrumented full-scale replica of the cylindrical GE A-4 ramjet duct planned for the Hermes B ramjet missile.

Robcrt R. Gilruth, Paul E. Purser, James A. Chamberlin, Maxime A. Faget, and H. Kurt Strass of STG met with a group from the Grumman Aircraft Engineering Corporation to discuss advanced spacecraft programs. Grumman had been working on guidance requirements for circumlunar flights under the sponsorship of the Navy and presented Strass with a report of this work.

STG completed the first draft of "Project Apollo, Phase A, General Requirements for a Proposal for a Manned Space Vehicle and System" (Statement of Work), an early step toward the spacecraft specification. A circumlunar mission was the basis for planning.

Integrated research, development, and applied orbital operations program to cost $1 billion through 1970. A NASA Headquarters working group, headed by Bernard Maggin, completed a staff paper presenting arguments for establishing an integrated research, development, and applied orbital operations program at an approximate cost of $1 billion through 1970. The group identified three broad categories of orbital operations: inspection, ferry, and orbital launch. It concluded that future space programs would require an orbital operations capability and that the development of an integrated program, coordinated with Department of Defense, should begin immediately. The group recommended that such a program, because of its scope and cost, be independent of other space programs and that a project office be established to initiate and implement the program.

Astronaut Alan B. Shepard, Jr., made the first United States manned space flight in a Mercury spacecraft launched from Cape Canaveral atop the Mercury-Redstone 3 (MR-3) vehicle. "Freedom 7" completed the suborbital, ballistic flight without incident in this historical first mission of NASA's Project Mercury. Alan Shepard first American in space, less than a month after Gagarin and only on a 15 minute suborbital flight. Only manned flight with original Mercury capsule design (tiny round porthole and periscope a la Vostok). If NASA had not listened to Von Braun, Shepard would have flown on the MR-BD flight of 24 March, beating Gagarin by three weeks and becoming the first man in space (though not in orbit). Shepard's capsule reached an altitude of 115.696 miles, range of 302 miles,and speed of 5,100 miles per hour. He demonstrated control of a vehicle during weightlessness and high G stresses. Recovery operations were perfect; there was no damage to the spacecraft; and Astronaut Shepard was in excellent condition.

Work under the contract was to be completed by May 1, 1964, and initial funding was $6.7 million. This contract reflected a reorientation of the paraglider program. Its primary purpose was to develop a complete paraglider landing system and to define all the components of such a system. Among the major tasks this entailed were: (1) completing the design, development, and testing of paraglider subsystems and building and maintaining mock-ups of the vehicle and its subsystems; (2) modifying the paraglider wings procured under earlier contracts to optimize deployment characteristics and designing a prototype wing incorporating aerodynamic improvements; (3) modifying the two full-scale test vehicles produced under Contract NAS 9-167 to incorporate prototype paraglider landing system hardware, modifying the Advanced Paraglider Trainer produced under Contract NAS 9-539 to a tow test vehicle, and fabricating a new, second tow test vehicle; and (4) conducting a flight test program including half-scale tow tests, full-scale boilerplate parachute tests, full-scale deployment tests, and tow test vehicle flight tests. Contract negotiations were completed on July 12, and the final contract was dated September 25, 1963.

Gagarin and Leonov meet with Kamanin. They discuss the complete inadequacy of Mishin - his excitability, poor knowledge of the Soyuz spacecraft and the details of its operation, his lack of cooperation in working with the cosmonauts in flight and training activities. They urge that these facts be documented in the Komarov crash commission report. Problems are discussed with getting an additional Tu-104 for zero-G/one sixth-G training. Three are needed, and only two have been made available. Even these two can only be used for 23 flights up to 10 August, after which they must be sent away for ejection seat modifications.

Revised Apollo and AAP-integrated program plan shows CSM would be available to support the first four AAP launches. Some significant features of a revised Apollo and AAP-integrated program plan were: CSM would be available to support the first four AAP launches; AAP-1/ AAP-2 in early 1969 were to accomplish OWS objectives; AAP-3/AAP-4 in mid-1969 were to accomplish the 56-day ATM objectives in conjunction with reuse of the OWS. Two additional AAP flights were planned for 1969 to revisit the OWS and the ATM using refurbished command modules flown initially on Earth-orbit Apollo flights in 1968. AAP missions planned for low Earth orbit during 1970 would utilize two dual launches (one manned CSM and one unmanned experiment module per dual launch) and two single-launch, long-duration CSM to establish and maintain near- continuous operation of the OWS cluster and a second ATM.

The Soviet of Chief Designers met with the Civil Chief Designer UR500K-L1 and recommended that podsadka be dropped and direct flight become the baseline. This was evidently to make possible the objective of a Soviet man around the moon before 4 October 1967. The reasons given were:
a) The successful flights of the UR-500K and Block D on the L1 2P and 3P and the further 4 separate UR-500 launches provided confidence in the launch vehicle's reliability.
b) The main delays with L1 development will be in relation to development by BTsVM of the Argon-11 digital computer for its control system.
c) The failure of 7K-OK number 4 (Soyuz 1) indicated a delay in development of docking in earth orbit.
It was recommended that the 7K-L1 launch sequence be revised to two missions per month as follows:
- 4L - "Zond" unmanned 17 - 29 June 1966
- 5L - unmanned, circumlunar, 27 June - 5 July
- 6L - "Zond", unmanned, 12 - 17 July
- 7L - unmanned, circumlunar, 25 July - 3 August
Followed by manned launches according to astronomical constraints (which would mean 23 August, 21 September, 19 October). (Mishin Diaries 2-22)

ASPO reported a recent manned-test abort of the portable life support system had been caused by a nonfunctional lithium hydroxide canister. Quality control procedures were in existence and if properly implemented would have precluded the abort incident. To prevent similar incidents from occurring, all manned-test and flight equipment would be accompanied by complete documentation, would be visually inspected, and would be certified by quality assurance personnel before use.

Kamanin notes that on 30 April decree number 0635 of the Ministry of Defence promoted Tereshkova to Colonel. She has risen in rank from Lieutenant to Colonel in only eight years, a record result for a woman (it normally takes more than ten years). Many within the VVS opposed the promotion, but Kamanin feels she deserves it and has served her country well on the Committee of Soviet Women. Later Kamanin has a filmed interview as part of a Riabchikov television project. Shatalov's trip to Cuba has proceeded well - he met Castro several times. Kutakhov is in the hospital.

First generation geosynchronous ballistic missile launch detection satellite. First completely sucessful operational satellite, remained in service for nearly 12 years. Positioned over the Indian Ocean at 75 deg E in 1979-1982. As of 1983 May 11 located at 73.28W drifting at 7.684W degrees per day.

Unmanned resupply vessel to Mir; last of original design Progress spacecraft. Conducted fifth and final test of Buran ejection seat during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Docked with Mir on 7 May 1990 22:45:03 GMT. Undocked on 27 May 1990 07:08:58 GMT. Destroyed in reentry on 27 May 1990 12:27:30 GMT. Total free-flight time 2.31 days. Total docked time 19.35 days.

Unmanned resupply vessel to Mir. Delivered 1,140 kg of fuel and 1,700 kg of cargo to the Mir complex. Docked with Mir on 7 May 1996 08:54:19 GMT. Undocked on 1 Aug 1996 16:44:54 GMT. Destroyed in reentry over the Pacific on 1 Aug 1996 20:33:03 GMT. Total free-flight time 2.23 days. Total docked time 86.33 days.

The Centaur RL-10B-2 second stage engine's combustion chamber ruptured at the beginning of the second burn. The hot gases already in the chamber vented, putting the stage/spacecraft assembly into an uncontrollable tumble. The Orion 3 communications satellite ended up in a useless parking orbit of 162 km x 1378 km x 29.5 deg. It was to have served the Asia-Pacific region for Loral Orion with 33 Ku-band and 10 C-band transponders.

On May 5, 2002, after a week aboard the station, the visting Soyuz TM-34 crew of Gidzenko, Vittori and Shuttleworth moved to the old Soyuz TM-33, docked at the Pirs port. They undocked at 0031:08 UTC on May 5, leaving the EO-4 crew of Onufrienko, Walz and Bursch with the new Soyuz TM-34 as their rescue vehicle. Soyuz TM-33 made its deorbit burn at 0257 UTC and landed successfully at 0352 UTC 25 km SE of Arkalyk.

First launch from new second PSLV pad at Sriharikota. Eleventh satellite in the Indian Remote Sensing satellite series, Cartosat-1 carried two panchromatic cameras, one fore-mounted with a tilt of +26 deg and the other aft-mounted with a tilt of -5 deg from the yaw axis. Together they provided black-and-white stereoscopic pictures in the visible region ( 0.50-0.85 micron) of the electromagnetic spectrum with a spatial resolution of 2.5 metre. The cameras covered a swath of 30 km and a solid state memory recorded up to 120 GB of images for downloading when the satellite passed over the Spacecraft Control Centre at Bangalore or ISTRAC stations at Lucknow, Mauritius, Bears Lake in Russia and Biak in Indonesia. Cartosat 1's sun-synchronous orbit crossed the equator at a local time of 10:30. The spacecraft was 3-axis stabilised using reaction wheels, magnetic torquers and hydrazine thrusters. 1100 W of eectrical power was provided by a 5 sq m solar array and two 24 Ah Ni-Cd batteries. Mission life was 5 years. Launch delayed from February, late April. The multispectral satellite had a 2.5-meter resolution camera.

Microsatellite providing satellite-based Amateur Radio services to the international community of Amateur Radio Operators (HAMs). Primarily intended for HAM operators in South Asia. One of the transponders was developed by Indian amateurs with the assistance of ISRO, and the second by a student at the Higher Technical Institute, Venlo, Netherlands. Hamsat was a 630 mm x 630 mm x 550 mm cube of aluminium-honeycomb structure. Power was provided by body-mounted gallium arsenide solar panels and a lithium ion battery. The satellite was spin-stabilised at 4 rpm. Uplink/downlink frequencies were 435.25 MHz / 145.9 MHz.