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Satellite Propulsion Systems

Unified bipropellant propulsion systems for orbital satellites and interplanetary spacecraft.

The first bipropellant propulsion system produced at the Lampoldshausen Centre was developed for Symphonie, a joint German-French experimental direct broadcasting telecommunications satellite.

Symphonie was a 3-axis, spin stabilised geostationary satellite that provided the transmission of television and radio programmes, telephone, fax and data.

Two Symphonie satellites were launched from Cape Canaveral by Thor Delta. Symphonie 'A' was launched in 1974 and Symphonie 'B' in 1975. Although the design life of Symphonie was five years, both satellites could be operated for ten years.

At the end of their mission, the two satellites were successfully de-orbited into a graveyard orbit using the remaining propellant of the attitude control system.

Unlike today's modern satellite propulsion systems, Symphonie had three different propulsion systems. One for apogee injection, one for orbit control and one for attitude control.

Unified Propulsion Systems
After Symphonie, the Lampoldshausen Centre pioneered the development of the first Unified Propulsion Systems (UPS) for both orbital satellites and interplanetary spacecraft.

The 'unified' term is attributed to the simple and efficient use of a common propellant tank system that feeds the apogee motor, as well as all of the attitude and orbit control thrusters. The unified satellite propulsion system is therefore compact, more flexible, relatively lightweight and enables maximum possible use of the available propellants.

Today, Unified propulsion systems produced at Astrium Lampoldshausen have become a standard for international satellite and spacecraft manufacturers throughout the world.

The First Orbital Satellite UPS
The first unified propulsion system used on a geostationary satellite was for TV-Sat 1 and 2, launched by Ariane 2 in 1987 and 1989 respectively.

The two TV-Sat's, in combination with two TDF satellites, was a joint German-French collaboration that set the foundations for direct European TV broadcasting.

The First Interplanetary Spacecraft UPS

Galileo Retro-Propulsion Module

The first unified propulsion system used on an interplanetary spacecraft was for the Galileo Retro-Propulsion Module. Galileo was launched by the US Space Shuttle 'Atlantis', in 1989 and was used for exploring Jupiter and its moons Ganymede, Callisto, Io and Europa.

The Retro-Propulsion Module comprised a 400 N engine and twelve 10 N thrusters that controlled Galileo's six year journey to Jupiter. After orbiting Jupiter for two years, it then steered Galileo to within 400 km of the Jovian moons.

The Galileo propulsion system performed flawlessly throughout its 14-year mission, which covered just over 4.6 billion kilometres.

On 21st September 2003, the Galileo spacecraft was steered toward Jupiter for a planned disintegration and burn-up in the planet's dense atmosphere.

Unified Propulsion System - Tanks and Thrusters
The UPS propellant tank is a key sub-system feature that minimises propellant residuals and assures a consistent quality and quantity of propellant during all orbital manoeuvres throughout the lifetime of the spacecraft. Details of these propellant tanks can be found in the section on Surface Tension Tanks and Propellant tanks.

Details of apogee motors and thrusters, used on unified propulsion systems, can be found in the section on Bipropellant Thrusters.

Satellite Propulsion System Integration Flow

Unified Propulsion System - Integration Flow
Unified Propulsion systems produced at the Lampoldshausen Centre are supplied as complete functional modules. This modular approach enables the customer to spend more time working on the spacecraft without being held-up by propulsion system integration. Consequently, the Assembly, Integration and Test of the UPS at spacecraft level is reduced to an absolute minimum.

The overall integration flow of the propulsion system, showing the tasks performed at Lampoldshausen and the customer facilities, is shown in the chart, right.

Unified Propulsion System - Modules

The modular elements of a typical unified propulsion system are shown below:

Satellite Propulsion Sub-system Elements
Helium Pressure Vessels Propellant Tanks See also: Surface Tension Tanks Propellant Tanks Fill and Drain Valves Satellite Propulsion System   Modular Elements Pressure Control Assembly Propellant Isolation Assembly Tube and Fittings   400 N Apogee Engine Assembly 10 N Thrusters   See also: Bipropellant Thrusters

Pressure Control Assembly - Module Components

Pressure Control Assembly (PCA)

Components Pressure Transducer   Helium Filter   High Accuracy Pressure Transducer Pressure Control Assembly (PCA) Components Pyro Valve   Pressure Regulator   Check Valve Functions: The functions of the PCA include: Regulation of helium pressure from the helium vessels to the propellant tanks. Prevention of backflow of propellant liquid and vapour during coast phases. Health monitoring during ground, flight and orbital phases. Isolation of pressurant before first operation and after station acquisition.

Propellant Isolation Assembly - Module components

Propellant Isolation Assembly (PIA)
Components Pressure Transducer Propellant Filter Propellant Isolation Assembly (PIA) Components Pyro Valve Functions: The functions of the PIA include: Isolation of propellant and thrusters before first operation. Propellant flow control to the main apogee engine and thrusters.

Complete UPS Integration at the Lampoldshausen Centre

Customarily, UPS modules are delivered to the customer facilities for integration to the spacecraft. Some customers however, prefer this work to be performed at the Lampoldshausen Centre, which provides all of the necessary facilities and expertise. In these cases, the complete propulsion Assembly, Integration and Testing is performed on the spacecraft structure which is delivered in advance to the Lampoldshausen Centre.

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