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Mars Ice Access Mission Study

Mars Ice Access Mission is a key robotic precursor mission to future human exploration planning. It is part of ESA’s Exploration Programme, named “Terrae Novae”, encompassing all ESA’s human and robotic activities related to the exploration and utilisation of Earth Orbit, Moon and Mars. The “Mars Ice Access Mission Study” is a Pre-Phase A level study. The objective of the study was to propose a preliminary design of a mission aiming to:

France

22-P-M-HRE-04-a

AIRBUS DEFENCE AND SPACE...
Star Tracker Based Generic Safe Mode for Science Missions

A previous study (TRP Star sensing based safe mode) confirmed the interest of using star tracker as primary sensor in a generic safe mode: versatility, suitability to complex requirements and constraints (e.g.

France

T205-119SA

AIRBUS DEFENCE AND SPACE...
Preliminary design of on-orbit manufacturing of large antenna reflectors

This study aims to carry out the conceptual design of a large-parabolic-antenna reflector that is manufactured and assembled on-orbit.

Through its Clean Space initiative, ESA has been devoting an increasing amount of attention to the environmental impact of its activities, including its own operations as well as operations performed by European industry in the frame of ESA programmes. In its Technology Strategy, ESA identified 'Inverting Europe’s contribution to space debris by 2030' as one of the four technology development targets.

France

19-D-S-TEC-07

Airbus
Securing NG-Ultra FPGA development through innovative System-on-a-Chip (SoC) validation
The BRAVE series of reprogrammable FPGA’s represent an entirely new area of development for microelectronics. These high performance, very advanced electronics could revolutionise the manufacturing process and performance of multiple missions. Alongside their development there is a current industry initiative to standardise avionics systems. As part of this venture, GSTP Element 2 has initiated an activity to develop a standardised box, which will contain all the different computer modules, such as power boards, and ensure they are all compatible.
France

GT27-046ED

AIRBUS DEFENCE AND SPACE...
Enhancement of Loop Heat Pipe (LHP) Modelling Tool
The current Loop Heat Pipe (LHP) module is increasingly needed to support thermal control design and modelling activities for various missions such as Aeolus, MTG and ExoMars. It is fully operational but only for a limited number of LHP architectures and analytical scenarios and they do not cover current needs. The proposed activity aims to further develop and extend this module the following ways:
  • Tuning of the module to improve performance and steady state convergence.
 
    France

    G617-111MT

    AIRBUS DEFENCE AND SPACE...
    High-Altitude pseudo-satellites for telecommunication and complementary space applications

    The interest in HAPS is increasing in many areas, from military and security to commercial services. On the telecommunications side, HAPS are seen as relays to provide internet services worldwide, and as a possible complement to satellites. On the Earth observation side, the near-space location of the HAPS enables new services or could improve the existing satellite ones. From the satellite or from the HAPS market sides, it is important to understand how both systems can offer complementary services, and what the possible synergies between them are.

    France

    15/708-b

    Airbus Defence &...
    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 &...
    IOD of techniques and technologies for M2M Telecom missions

    Generally speaking DIAMS has been an opportunity to secure the feasibility of the IOD in technical, programmatic and financial terms. More specifically DIAMS has allowed to define the end-to-end mission concept for this IOD, covering the design of various associated segments : Space Segment (Payload, Platform), and Ground Segment. Both interest and programmatic aspects have also been consolidated.

    - On the technical plane :
    Both the requirements and the design of the system have been refined to validate the IOD concept :

    France

    13/701

    Airbus Defence &...
    Simplified models for spacecraft vulnerability assessments in early design phase

    All spacecraft in Earth orbit are exposed to the risk of impact with Micrometeoroids and Orbital Debris (M/OD). Because of the large collision velocities, Hypervelocity Impacts (HVI) with M/OD may cause significant damage to various subsystems and components up to mission failure.

    France

    12-601-A

    Airbus Defence &...

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