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Antares-2
Antares 2 (X-259) was an American solid rocket engine stage and engine built by Hercules/ ABL / Thiokol. It was used from the mid-1960s to 1995, in the Scout and Strypi family of rockets, and on the Project FIRE Velocity Packages. It burned solid propellant – the stage was also the engine's fuel chamber - and was used about 96 times. Details Basic details of the X-259 engine: * Thrust: * Gross mass: * Unfuelled mass: * Specific impulse: 293 s. * Specific impulse sea level: 233 s. * Burn time: 36 s. * Height: * Diameter: Variants There were various variants: * Antares 2 was used on Scout X-2 1C, B 2A, B-1 F, D-1 F and D; Strypi Tomahawk, XI and IX; SPARTA and Athena H * Antares 2A was used on Scout-X2, X2B, X2M, X3, X3A, X3C, X3M, X4, X4A, X5C, A, A1, B, B1, C, and D1; and Project FIRE A project is a type of assignment, typically involving research or design, that is carefully planned to achieve a specific objective. An alternative view sees a pr ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Strypi
Strypi is a family of US re-entry vehicle test boosters, anti-missile targets and sounding rockets. They use a Castor first stage with two Recruit strap-on boosters, plus a range of upper stages. It is 31 inches (79 centimeters) in diameter, and has a maximum flight height of 124 miles (200 kilometers). History It was originally designed and built in 1962 by teams from the Sandia National Laboratories in an around-the-clock program that was a part of a larger nuclear weapons testing program, undertaken prior to the imposition of the Limited Test Ban Treaty (LTBT) in October, 1963. It was designed to take a nuclear warhead into space for extra-atmospheric testing. Though it performed this function only once, in Test Checkmate of Operation Fishbowl, it became the "workhorse" of Sandia's rocket research program. The rocket's name came from the efforts of the Sandia teams, which had "taken the tiger by the tail". In 1968, a modified Strypi was used in Material Test Vehicle (MTV) ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Sparta (rocket)
The Sparta (or Redstone Sparta) was a three-stage rocket that launched Australia's first Earth satellite, WRESAT, on 29 November 1967. Sparta used surplus American Redstone rockets as its first stage, a Thiokol Antares 2 from Scout rocket as a second stage, and a WRE BE-3 Alcyone solid-propellant engine as a third stage. A first stage was recovered from the Simpson Desert in 1990 after being found in searches by explorer Dick Smith the previous year. Launches Several Spartas were launched between 1966 and 1967 from Woomera Test Range LA8 in Woomera, South Australia as part of a joint United States–United Kingdom–Australian research program aimed at understanding re-entry phenomena, and the US donated a spare for the scientific satellite launch into polar orbit. The first launch was a failure, while the rest were successful. Gallery File:Redstone Sparta.jpg, Redstone-Sparta at Woomera LA8 File:Redstone Sparta CC-2029 3.jpg, Preparation for launch of Re ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Scout D-1
The Scout family of rockets were American launch vehicles designed to place small satellites into orbit around the Earth. The Scout multistage rocket was the first orbital launch vehicle to be entirely composed of solid fuel stages. It was also the only vehicle of that type until the successful launch of the Japanese Lambda 4S in 1970. The original Scout (a backronym for Solid Controlled Orbital Utility Test system) was designed in 1957 at the NACA, at Langley center. Scout launch vehicles were used from 1961 until 1994. To enhance reliability the development team opted to use "off the shelf" hardware, originally produced for military programs. According to the NASA fact sheet: "... the first stage motor was a combination of the Jupiter Senior and the Navy Polaris; the second stage came from the Army MGM-29 Sergeant; and the third and fourth stage motors were designed by Langley engineers who adapted a version of the Navy Vanguard." The first successful orbital launch of a Scou ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Antares X259 Rocket Stage
Antares is the brightest star in the constellation of Scorpius. It has the Bayer designation α Scorpii, which is Latinisation of names, Latinised to Alpha Scorpii. Often referred to as "the heart of the scorpion", Antares is flanked by Sigma Scorpii, σ Scorpii and Tau Scorpii, τ Scorpii near the center of the constellation. Distinctly reddish when viewed with the naked eye, Antares is a slow irregular variable star that ranges in brightness from an apparent visual magnitude of +0.6 down to +1.6. It is on average list of brightest stars, the fifteenth-brightest star in the night sky. Antares is the brightest and most evolved stellar member of the Scorpius–Centaurus association, the nearest Stellar association#OB associations, OB association to the Sun. It is located about from Earth at the rim of the Upper Scorpius subgroup, and is illuminating the Rho Ophiuchi cloud complex in its foreground. Classified as stellar classification#Spectral types, spectral type Stellar ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Scout X-2M
Scout X-2M was an American expendable launch system which was flown three times between May 1962 and April 1963. It was a four-stage rocket, based on the earlier Scout X-2, but with an MG-18 upper stage instead of the Altair used on the X-2. It was a member of the Scout family of rockets. The Scout X-2 was an all-solid rocket, with an Algol 1D first stage, a Castor 1A second stage, an Antares 2A third stage, and an MG-18 fourth stage. It was launched from Launch Complex D at Point Arguello, and was used for the launch of P-35 weather satellites. The first Scout X-2M was launched 24 May 1962, carrying P35-1, but failed to reach orbit. The second flight, launched at 11:44 GMT on 23 August, was the only successful launch to be made by an X-2M, placing P35-2 into low Earth orbit A low Earth orbit (LEO) is an geocentric orbit, orbit around Earth with a orbital period, period of 128 minutes or less (making at least 11.25 orbits per day) and an orbital eccentricity, eccentrici ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Scout X-2B
The Scout X-2B was an American expendable launch system which was flown during 1963. It was a four-stage rocket, based on the earlier Scout X-2, but with an Altair 2A fourth stage in place of the Altair 1A used on the X-2. It was a member of the Scout family of rockets. The Scout X-2 was an all-solid rocket, with an Algol 1D first stagea Castor 1A Castor is a family of solid-fuel rocket Multistage rocket, stages and solid rocket booster, boosters built by Thiokol (now Northrop Grumman) and used on a variety of launch vehicles. They were initially developed as the second-stage motor of the S ... second stage, an Antares 2A third stage, and an Altair 2A fourth stage. It made only one flight, which was launched from Launch Complex D at Point Arguello, carrying a P-35 weather satellites, P35-5. The launch occurred on 27 September 1963, and failed to achieve orbit. References * * * * 1963 in spaceflight X-2B {{rocket-stub ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Scout X-2
Scout X-2 was an American expendable launch system and sounding rocket which was flown twice in 1962. It was a four-stage rocket, based on the earlier Scout X-1, uprated first and third stages. It was a member of the Scout (rocket family), Scout family of rockets. The Scout X-2 used an Algol 1D first stage, instead of the earlier Algol 1B used on the Scout X-1. The third stage was the Antares 2A, a more powerful version of the Antares 1A used on earlier variants of the Scout rocket. The second and fourth stages were the same as those used on the Scout X-1; a Castor 1A and an Altair 1A respectively. The first Scout X-2 was launched on a suborbital flight at 07:27 GMT on 29 March 1962. It flew from Wallops Flight Facility Launch Area 3, Launch Area 3 of the Wallops Flight Facility. The flight carried plasma (physics), plasma and aeronomy experiments to an apogee of , and was successful. The second flight, launched on 26 April, carried the Solrad 4B satellite. It failed to reach orbi ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Thrust
Thrust is a reaction force described quantitatively by Newton's third law. When a system expels or accelerates mass in one direction, the accelerated mass will cause a force of equal magnitude but opposite direction to be applied to that system. The force applied on a surface in a direction perpendicular or normal to the surface is also called thrust. Force, and thus thrust, is measured using the International System of Units (SI) in newtons (symbol: N), and represents the amount needed to accelerate 1 kilogram of mass at the rate of 1 meter per second per second. In mechanical engineering, force orthogonal to the main load (such as in parallel helical gears) is referred to as static thrust. Examples A fixed-wing aircraft propulsion system generates forward thrust when air is pushed in the direction opposite to flight. This can be done by different means such as the spinning blades of a propeller, the propelling jet of a jet engine, or by ejecting hot gases f ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Specific Impulse
Specific impulse (usually abbreviated ) is a measure of how efficiently a reaction mass engine, such as a rocket engine, rocket using propellant or a jet engine using fuel, generates thrust. In general, this is a ratio of the ''Impulse (physics), impulse'', i.e. change in momentum, ''per mass'' of propellant. This is equivalent to "thrust per massflow". The resulting unit is equivalent to velocity. If the engine expels mass at a constant exhaust velocity v_e then the thrust will be \mathbf = v_e \frac . If we integrate over time to get the total change in momentum, and then divide by the mass, we see that the specific impulse is equal to the exhaust velocity v_e . In practice, the specific impulse is usually lower than the actual physical exhaust velocity inefficiencies in the rocket, and thus corresponds to an "effective" exhaust velocity. That is, the specific impulse I_ in units of velocity *is defined by* : \mathbf = I_ \frac , where \mathbf is the average thrust. ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
