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SpaceX CRS-7, also known as SpX-7, [1] was a private American Commercial Resupply Service mission to the International Space Station, contracted to NASA, which launched and failed on June 28, 2015. It disintegrated 139 seconds into the flight after launch from Cape Canaveral , just before the first stage was to separate from the second stage. [ 2 ]
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Section 301 cases can be self-initiated by the United States Trade Representative (USTR) or as the result of a petition filed by a firm or industry group.. As an amendment by section 1302 of the Omnibus Foreign Trade and Competitiveness Act, Super 301 required the USTR for 1989 and 1990 to issue a report on its trade priorities and to identify priority foreign countries that practiced unfair ...
The only failed mission of the Falcon 9 v1.1 was its 14th, SpaceX CRS-7, 28 June 2015, which was lost during its first stage operation, due to an overpressure event in the second stage oxygen tank. [53] (After CRS-7 there was one final launch of V1.1, on 17 January 2016, to launch the Jason-3 payload.)
90-301-EEC- Commission Decision of 20 December 1989 on the establishment of the Community support framework for Community structural assistance in the areas eligible under Objective 2 in Zuid-Limburg (the Netherlands) (Only the Dutch text is authentic)
This United States Congress image is in the public domain.This may be because it was taken by an employee of the Congress as part of that person’s official duties, or because it has been released into the public domain and posted on the official websites of a member of Congress.
OA-7, previously known as Orbital-7, is the eighth flight of the Orbital ATK uncrewed resupply spacecraft Cygnus and its seventh flight to the International Space Station (ISS) under the Commercial Resupply Services contract with NASA. [5] The mission launched on 18 April 2017 at 15:11:26 UTC. Orbital and NASA jointly developed a new space ...
The Falcon 1e was to be 6.1 m (20 ft) longer than the Falcon 1, with an overall length of 27.4 m (90 ft), but with the same 1.68 m (5 ft 6 in) diameter. Its first stage had a dry mass of 2,580 kg (5,680 lb), and was powered by an upgraded [ 42 ] pump-fed [ 43 ] Merlin 1C engine burning 39,000 kg (87,000 lb) of RP-1 and liquid oxygen .