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Feasibility of ultra low thrust transfers in L1, L2, Sun, Earth & Moon Systems

A set of tools has been developed to enable assessment of the feasibility of ultra-low thrust transfers in regions of multi-body gravity field influence. Aspects include:

France

15/723-a

Airbus Defence &...
System impacts of propulsion Passivation

Propulsion passivation is most of the time feasible for running missions, using thrusters and existing AOCS modes, whatever the number of tanks and for both monopropellant and bipropellant systems.
For monopropellant systems the propulsion passivation may be:
-Partial for tank(s) with membrane. All the hydrazine under the membrane may be depleted but the pressurant gas above the membrane cannot be depleted. The final tank pressure is close to typically 5 bars at the end of mission.

France

13-060-b

Airbus Defence &...
System impacts of propulsion Passivation

Space debris mitigation requirements specific to propulsion systems are scrutinized and compliance of OHB reference propulsion architectures is assessed. The risk of generating debris due to a failure in a propulsion system is assessed with a focus on the specific risk of a hypervelocity impact on a propulsion tank containing residuals.

The engineering activities, delta-qualifications or hardware development which can support the recommended propulsion passivation strategies are presented and prioritized.

Germany

13-060-a

OHB System AG
Helicon Plasma Thruster For Space Missions

The use of helicon sources as thrusters for space propulsion has been envisaged as a robust, scalable, reliable and long-life device. The Helicon Plasma Thruster (HPT) is presented as a potentially durable, throttlable and high thrust-to-power ratio device, with intermediate specific impulse and competitive thrust efficiency.

Spain

11-10/075

SENER INGENIERIA Y...
Hybrid Propulsion Transfer Strategies

Low energy transfers have shown that it is possible to reduce the ∆v cost (and therefore the propellant mass) for a number of transfer types. This is possible by exploiting the natural n-body dynamics characterizing the spacecraft motion within the Solar System. In particular, the concept of ballistic capture makes it possible to reduce the hyperbolic excess velocity upon moon/plant arrival, and allows the spacecraft to perform few orbits at zero cost. Low energy transfers are designed by using impulsive maneuver, and therefore they inherently use chemical propulsion (Figure 1).

Italy

2012-11

DINAMICA SRL
Modelling Solid Propulsion Stages

The goal of this project was to evaluate the state-of-the-art of European and US solid propulsion stages and to create an Excel-based design model/workbook for solid propulsion stages. The tool is intended to be used, amongst others, by the ESA CDF for either selecting existing solid rocket motors from a suitably populated database or creating preliminary designs for new solid rocket motors. Having a workbook to model stages based on solid propulsion will help assessment studies to perform trade-offs taking solid propulsion stages into account.

Italy

2011-27

ALTA S.P.A
FEEP Microthruster Component Development: Ultraprecise Indium Thruster

In-FEEP ion beam profiles were obtained for a variety of thrust values ranging from 0.49 up to 115.5 μN. The beam shape was found to be close to a cosine in low thrust levels and resembled a Gaussian distribution at high thrust levels. Data processing of the obtained profiles to evaluate the thrust correction factor which is in close agreement to direct thrust measurements. Thrust vector angle and beam divergence were within the expected ranges.

Austria

000

Seibersdorf GmbH

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