The engine runs for 5 seconds before exploding, producing a thrust of 719 kgf. A second test the following day produces 650 kgf for only four seconds before exploding. Thermal transfer from the engine to the missile structure is found to be the cause, and changes are made.

Batt. SS Abt. 500, Hellendoorn, Eelerberg, rocket fired, Target Remagen. Disintegrated in the air near Kasbach. Part of the rocket penetrated the roof of a house; other parts fell on a farm 800m from the Ludendorff Rail Bridge injuring 18 farm animals. Warhead impacted 300m from the bridge, shaking it very strongly. Three American soldiers killed.

The NACA Special Committee on Space Technology held its second meeting at the Ames Aeronautical Laboratory, and preliminary reports were presented by the committee working groups on objectives and vehicular programs. The committee as a whole was briefed on the work that had been accomplished by the former NACA Committee on Aerodynamics over the past 6 years. It was stated that between 1952 and 1956, approximately 10 percent of NACA's research efforts were applicable directly or indirectly to astronautics. In 1957, the percentage of space flight research rose to 23; and at the time of the meeting, 30 percent of the aerodynamic effort and 20 percent of propulsion research was applicable to astronautics problems. The committee also heard special papers on research being conducted in fluid mechanics, satellite studies, spacecraft design proposals, boost-glide and hypersonic vehicle studies, and missiles.

Vanguard I completed third year in orbit and was still transmitting. Vanguard I provided much useful data on orbits, including the slight pear-shape of the Earth and the effect of solar pressure. Vanguard also provided the second stage for the Able, Delta, and Able-Star, as well as the third stage of Scout, pioneering solid-propellant stages used in Polaris and Minuteman.

Texas Instruments, Inc., presented a progress report on their lunar surface experiments study to the MSC Lunar Surface Experiments Panel. Thus far, the company had been surveying and rating measurements to be made on the lunar surface. Areas covered included soil mechanics, mapping, geophysics, magnetism, electricity, and radiation. Equipment for gathering information, such as hand tools, sample return containers, dosimeters, particle spectrometers, data recording systems, seismometers, gravity meters, cameras, pentrometers, and mass spectrometers had been considered. The next phase of the study involved integrating and defining the measurements and instruments according to implementation problems, mission needs, lunar environment limitations, and relative importance to a particular mission. Texas Instruments would recommend a sequence for performing the experiments.

Last of three suborbital flight tests of the FOBS system. The second stage of the booster placed the third stage and dummy warhead on a depressed trajectory with a range of 8500 km but an altitude of only 220 km (versus 800 to 1200 km for an optimum ballistic trajectory). The third stage than executed a 180 degree turn and its engines were fired to further brake the warhead to an impact on the Kamchatka peninsula. The second stage meanwhile continued on to reentry over the Pacific Ocean.

The third Athena H rocket was launched from the Green River, Utah, launch complex. The flight test completed qualification of the vehicle for operational use in the Advanced Ballistic Reentry Vehicle (ABRES) program managed by SAMSO's Deputy for Reentry Systems (RS).

Indian remote sensing; 1st Soviet commercial launch. Indian Remote Sensing Satellite (IRS-1A). Operational remote sensing of the Earth for natural resources management applications. Also registered by the USSR as object no. 2387 in ST/SG/SER.E/182 and orbital parameters 102.7 min, 863 x 917 km x 99.01 deg.

This space object is intended for assignments on behalf of the Ministry of Defense of the Russian Federation. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission.

Successful docking at Mir; The docking took place on 17.03.1998 at 00.31.17 UTC. The last 20 Meters and the docking itself were manually executed by Musabayev with the system TORU. From 0000 UTC the operation could be monitored via Altair-2. Musabayev observed the manoeuvres of the Progress-M38. All went according to calculations. The system Kurs was in use, but Musabayev and Budarin were at the control panel of the TORU system ready to take over if necessary. The crew followed the operation via several systems: the monitor of the TORU, the LIV-camera, via a camera on board of the Progress-M38 and also visually.

Andy Thomas made images with a video-camera. Musabayev reported all distances, approach speeds, deviations along the 3-axes and also that there were no 'emergency instructions' so Kurs was STILL functioning well. At 0015 UTC the link via Altair-2 ceased and a few minutes later the VHF window opened. At 0024 UTC just before LOS for my position the distance to Mir was still 150 Meters with an approach speed of 4 CM/sec. All went well until the distance of 40 Meters. Then Kurs showed fluctuations which might be an indication that the Kurs system was no longer reliable.

Musabayev decided to switch over to the manual guidance by TORU and from 20 Meters he steered Progress-M38 to the aft docking port (+X-axis) and accomplished a perfect docking. During the pass in the next orbit the air seal checks were still going on. Via VHF-2 (130.165 mc) Andy Thomas spoke with his leads and he said that there had been no surprises. When Progress-M38 was docking he had felt a slight bump. At 0206 UTC the crew was opening the hatch.

Progress-M37:

This old freighter separated from Mir on 15.03.1998 at 19.16.01 UTC and burned up in the atmosphere east of New-Zealand at 23.03.46 UTC. 1st Spacewalk (EVA) crew 25th Main Expedition. For the time being on schedule for 1.04.1998. A final decision will be made soon.

Chris v.d. Berg, NL-9165/A-UK3202.

First commercial flight of Rokot booster. Launch delayed from November 23-30, 2001, February 27, March 15 and 16. The Briz-KM upper stage ignited 5 minutes after launch and after a ten minute burn reached a 300 x 500 km orbit at about 0936 UTC. A second burn at 1042 UTC placed the satellites in a 483 x 506 km x 89 deg orbit; the two GRACE gravimetric satellites separated from the dispenser at 1047 UTC. A third Briz burn then lowered the rocket stage orbit to 146 x 487 km x 89 deg so that it would reenter quickly.

The astronauts completed assembly of the Dextre robotic manipulator, installed the LWAPA adapter plate on the External Payload Facility of the Columbus module, and transferred spare equipment from Endeavour's payload bay to the station's External Stowage Platform 2. They were unable to complete the planned installation of the MISSE 6 sample exposure experiment on the LWAPA.