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The propellant used in a rocket engine plays an important role in both engine design and in design of the launch vehicle and related ground equipment to service the vehicle. Weight, energy density, cost, toxicity, risk of explosions, and other problems make it important for engineers to design rockets with appropriate propellants. The major ...
Several propellants were tried in various programs: One of the later (1991) successful gun fuels was a saturated solution of ammonium perchlorate in ammonia.This has a vapor pressure of one atmosphere at 20 °C (68 °F), and generally forms a convenient liquid that is stable and possible to handle.
The aerosol spray canister invented by USDA researchers, Lyle Goodhue and William Sullivan.. The concepts of aerosol probably go as far back as 1790. [1] The first aerosol spray can patent was granted in Oslo in 1927 to Erik Rotheim, a Norwegian chemical engineer, [1] [2] and a United States patent was granted for the invention in 1931. [3]
Liquid propellants provide greater propulsive thrust and power, but require more complex technology and extra weight. Solid fuel is dense and burns quite quickly, generating thrust over a short time.
About 170 different propellants made of liquid fuel have been tested, excluding minor changes to a specific propellant such as propellant additives, corrosion inhibitors, or stabilizers. In the U.S. alone at least 25 different propellant combinations have been flown. [2] Many factors go into choosing a propellant for a liquid-propellant rocket ...
Red fuming nitric acid (RFNA) is a storable oxidizer used as a rocket propellant. It consists of nitric acid (H N O 3), dinitrogen tetroxide (N 2 O 4) and a small amount of water. The color of red fuming nitric acid is due to the dinitrogen tetroxide, which breaks down partially to form nitrogen dioxide. The nitrogen dioxide dissolves until the ...
A liquid-propellant rocket or liquid rocket uses a rocket engine burning liquid propellants. (Alternate approaches use gaseous or solid propellants.) Liquids are desirable propellants because they have reasonably high density and their combustion products have high specific impulse (I sp). This allows the volume of the propellant tanks to be ...
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