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PPS ® 1350-G SPACE PROPULSION STATIONARY PLASMA THRUSTER

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Page 1: SPACE PROPULSION PPS 1350-G - Safran Aircraft … PPS®1350-G stationary plasma thruster is ... records for this type of propulsion. The PPS®1350-G is the first plasma thruster used

PPS®1350-GSPACE PROPULSION

STATIONARY PLASMA THRUSTER

Page 2: SPACE PROPULSION PPS 1350-G - Safran Aircraft … PPS®1350-G stationary plasma thruster is ... records for this type of propulsion. The PPS®1350-G is the first plasma thruster used

Power (nominal) (W) 1,500 Thrust (mN) 90Specific impulse (s) 1,660Total impulse delivered (N.s) 3.4 106

Number of cycles 7,300Discharge current (A) 4.28 Efficiency (%) 55Supply voltage (V) 350Xenon supply pressure (bar) 2.50 à 2.80Mass (including 2 Xe flow control systems) (kg) 5.30

FEATURES

The PPS®1350-G stationary plasma thruster is designed for orbit control and orbital transfer of satellites and other spacecraft.

Its main advantage is very high specific impulse, which means significant weight savings over conventional chemical propulsion systems for all types of spacecraft. The PPS®1350-G also offers an excellent thrust-to-electrical power ratio, which enables limiting pulse lengths or reducing the total number of thrusters needed.

It generates thrust by ejecting xenon ions at very high speed. These ions are accelerated by an electrical field produced by the magnetic containment of electrons. The PPS®1350 comes with a xenon flow control system.

The PPS®1350-G has amply demonstrated its capabilities by propelling the European Space Agency’s Smart-1 probe from Earth orbit into orbit around the Moon. During this mission from September 2005 to August 2006, it operated for a total of 5,000 hours, setting one of three new world records for this type of propulsion.

The PPS®1350-G is the first plasma thruster used as the primary propulsion system on a space probe; it operated continuously for 260 hours during the mission; and it is the engine having logged the longest cumulated operating time in space.

Cathode

125 mm maxi

Anode

104 mm maxi

210

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i

135

mm

max

iCathode 2 Cathode 1

Anode

Simulated altitude test

Stable operation over a wide power range: 1,200 to 1,600 W

Low startup power

Proven performance at extreme temperatures, from -45°C to +160°C

Reduced beam divergence (40°)

Ions leaving the thruster are neutralized to avoid transferring an electric charge to the satellite

DESCRIPTION

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Snecma10, allée du Brévent - CE1420 Courcouronnes91019 Evry Cedex - FranceTel: + 33 (0)1 69 87 09 00 - Fax: + 33 (0)1 69 87 09 02www.snecma.com

PPS®1350-GSPACE PROPULSION

STATIONARY PLASMA THRUSTER