Started to lift at 13 sec; rose at 14 1/2 sec; reached top of flight (90 ft) at 17 sec; hit ground at 18 1/2 sec; landed 171 ft from tower. The rocket carried a small camera, thermometer, and a barometer which were recovered intact after the flight. Flight was bright and noisy, attracted public attention. The result was a great deal of "moon rocket" publicity. This resulted in prohibition of further test flights from Aunt Effie's Farm by the local fire marshall. Length 11 ft 6 in.; maximum diameter 26 in.; weight 32 lb; gasoline 14 lb; liquid oxygen 11 lb; total loaded weight 57 lb. Up to that time Goddard had achieved numerous proving-stand tests of liquid rockets, and 10 attempts at flight tests, of which four achieved flight. References: 17 , 482 .

Static test: duration 34 sec; average thrust 825+ lb; gas ejection velocity 4060 ft/sec; average thrust per pound of fuel per second 128; mechanical horsepower 3040; liquid oxygen 131.7 lb; gasoline 91.5 lb; ratio oxygen to gasoline 1.43. References: 482 .

Fired from AMR at 0404 hours EST to a pre-calculated range of 1,241.3 nm. The nose cone impacted 1.0 nm short and 1.5 nm to the right of the predicted impact point. This was the first flight test of the complete inertial guidance system. The nose cone recovery mission was successful. This was also the second successful flight test of a full scale tactical type nose cone, as well as a successful flight test of the Jupiter lightweight, high explosive warhead. References: 439 .

In an address to the American Rocket Society lunar missions meeting in Cleveland, Ohio, James A. Van Allen, Chairman of the Department of Physics and Astronomy, State University of Iowa, said that protons of the inner radiation belt could be a serious hazard for extended manned space flight and that nuclear detonations might be able to clean out these inner belt protons, perhaps for a prolonged period, making possible manned orbits about 300 miles above the earth. References: 16 .

FAI world altitude record. Maximum Speed - 6166 kph. Maximum Altitude - 95940 m. First astronaut wings flight (USAF definition). References: 33 , 38 , 49 , 97 .

Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 , 278 .

Decay date suspect Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 , 278 .

Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). References: 1 , 2 , 5 , 6 , 278 .

Fractional Orbital Bombardment system test. Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 .

Maximum Speed - 803 kph. Maximum Altitude - 13716 m. Flight Time - 252 sec. References: 49 , 97 .

An Orbital Workshop all-systems test began on 17 July 1972 and was completed on 7 August 1972 at McDonnell Douglas' Huntington Beach Vehicle Checkout Laboratory. Following the test, which lasted 309 hours, a meeting was held to verify that the OWS all-systems test had been successfully completed. At the conclusion of the meeting, it was agreed that pending closeout of the test anomalies, all test requirements had been satisfied.

Start long-lead fabrication (MPTA-098) References: 15 .

Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 , 99 .

First test of TKS manned shuttle. Maneuvered extensively. TKS-VA capsule returned to earth August 16, 1977. Deorbited February 2, 1978.
Maneuver Summary:
214 km X 261 km orbit to 215 km X 279 km orbit. Delta V: 5 m/s
207 km X 261 km orbit to 208 km X 264 km orbit. Delta V: 1 m/s
208 km X 260 km orbit to 209 km X 267 km orbit. Delta V: 2 m/s
192 km X 222 km orbit to 219 km X 232 km orbit. Delta V: 9 m/s
219 km X 232 km orbit to 303 km X 327 km orbit. Delta V: 51 m/s
303 km X 327 km orbit to 312 km X 318 km orbit. Delta V: 4 m/s
312 km X 319 km orbit to 314 km X 325 km orbit. Delta V: 1 m/s
284 km X 294 km orbit to 290 km X 301 km orbit. Delta V: 3 m/s
288 km X 300 km orbit to 286 km X 305 km orbit. Delta V: 1 m/s
285 km X 303 km orbit to 439 km X 447 km orbit. Delta V: 84 m/s
437 km X 448 km orbit to 335 km X 437 km orbit. Delta V: 31 m/s
335 km X 437 km orbit to 337 km X 438 km orbit. Delta V: 1 m/s
337 km X 438 km orbit to 90 km X 337 km orbit. Delta V: 100 m/s
Total Delta V: 193/293 m/s
Officially: Investigation of the upper atmosphere and outer space. References: 1 , 2 , 5 , 6 , 67 , 274 , 439 .

3rd generation, medium resolution photo surveillance; film capsule; also performed earth resources tasks. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. References: 1 , 2 , 6 .

Docked with Salyut 7. Transported a crew comprising ship's commander V A Dzhanibekov, flight engineer S E Savitskaya and cosmonaut-research I P Volk to the Salyut-7 orbital station to conduct scientific and technical studies and experiments. Recovered July 29, 1984 12:55 GMT. References: 1 , 2 , 6 , 32 , 33 , 51 .

Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network and within the framework of international cooperation. References: 1 , 2 , 5 , 6 .

High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. References: 1 , 2 , 6 , 179 .

Repaired Soyuz TM-9 insulation rip. References: 66 .

Investigation of the natural resources of the Earth in the interests of various branches of the national economy of the USSR; solution of problems relating to ecology and international cooperation. References: 1 , 2 , 6 .

Microwave, IR imaging of oceans, ice and land; SAR. ERS-1 is an Earth exploration satellite, using active and passive sensors for oceanography etc. Frequency plan: 2048.85/2225 MHz (TTC), 7225.2960/8489 MHz (PRARE), 8040, 8140 MHz (data transmission). Launch time 0146:31 UT. Designator ESA/91/02. References: 1 , 2 , 5 , 6 .

Customer: SateLife. Carried store and forward communications and Earth observation payloads, replacing those lost on UoSAT-4. Still operational in 2000. References: 1 , 2 , 5 , 6 .

Radioastronomy. References: 1 , 2 , 5 , 6 .

Store and forward communication. References: 1 , 2 , 5 , 6 .

Store and forward communication. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

Test of LEO network for global communications. References: 1 , 2 , 5 , 6 .

The module was transferred by the small manipulator arm on Mir to its final location at the Mir transfer compartment's starboard radial port.

First of a new generation of larger Okean oceanographic satellites, carried a side-looking radar (RSL-BO), and a set of visible and infrared scanners and radiometers. It is built by the Ukrainian Yuzhnoye company and is a joint project of the Russian Aviation/Space Agency (RAKA) and the Ukrainian National Space Agency (NKAU).