1 esa session4

INTERNATIONAL COOPERATION FOR SUSTAINABLE SPACE EXPLORATION: 

INTERNATIONAL COOPERATION FOR SUSTAINABLE SPACE EXPLORATION Session 4 Enabling Exploration Capabilities / Technologies

Scope of Session 4: 

Scope of Session 4 Discussion of current / planned enabling capabilities / technologies development in support of future human / robotic exploration missions with the aim of: Identifying common areas of interest with regard to international coordination and / or collaboration concerning R & T developments; Identifying some candidate models / approaches for international collaboration / coordination on technology development

Presentation content: 

Presentation content ESA technology development approach Aurora approach ExoMars mission and enabling capabilities ExoMars past/ongoing and future technology activities MSR mission and enabling capabilities The European approach and MSR preparatory activities International cooperation/collaboration Human exploration capabilities (mostly addressed in Session 3)

ESA Technology Development Approach: 

ESA Technology Development Approach ESA’s development approach is to take technologies from initial concepts, through to flight proven systems This process is gauged using ESA’s technology readiness level (TRL) scale

Slide5: 

The Aurora technology development programme is intended to support the preparation of proposed near-term exploration missions e.g. ExoMars, MSR This effort should formulate and timely implement coherent mission specific technology development activities The approach to this consists of: Developing an understanding of a mission design and concepts through systems studies Identifying key enabling capabilities required for a mission Determining where critical gaps exist in technologies available to provide these capabilities Engaging in technology development activities which focus on bridging these gaps, maturing required technologies, and thus capabilities, for use in a specific robotic mission Aurora Approach

Slide6: 

Technology Research Programme (TRP)/General Support Technology Programme (GSTP) Consists of basic development of new concepts and technologies Aurora Technology Maturation/Demonstration Programme Activities focused on technology demonstration programmes including definition of flight experiments/technology demonstration missions System development projects and programmes ESA Technology Development Programmes Flight mission projects

Slide7: 

ExoMars-Lite Mission (2011) Main Scientific Objectives: To search for traces of past and present life on Mars To identify surface hazards to future human missions To characterise the shallow subsurface water/geochemical composition and vertical distribution profile Main Technology Objectives Safe landing of a large size payload Surface mobility (Rover) and access to the subsurface (drill) Rover power generation using solar arrays Forward Planetary Protection

Slide8: 

ExoMars Enabling Capabilities An understanding of the mission helps identify the main enabling capabilities, which for ExoMars are: Entry, Descent and Landing Systems Surface Mobility In-situ Instrumentation Forward Planetary Protection Sample Acquisition and Processing Thermal Control (RHU) Payload Autonomy and Avionics Architecture/Software Surface Power Generation

Slide9: 

Prioritisation of Activity From an understanding of the mission’s enabling capabilities, and considering the status of the technologies supporting these capabilities, it is possible to make an assessment of where focussed technology development is required, for example: Entry, Descent and Landing It is important that current airbag based technologies are advanced, and that new technologies are investigated, to meet the challenges of this critical mission phase Surface Mobility Development is required of sub-systems and technologies which can ensure the performance and reliability of the rover’s mobility system In-situ Instrumentation Supporting activity is required to accelerate instrument development to ensure the technologies are available at the appropriate time Surface Power Generation The efficiency of solar cells requires improvement, through the use of new technologies, which must be developed to a level where they can be integrated into the ExoMars mission

Slide10: 

Past/On-Going Activity In order to address the priorities made in the capabilities identified, a range of activities have already been initiated, with some completed or nearing completion. These activities have begun to bridge the technology gap in critical areas, for example: Alternative Descent/Landing Technologies An assessment is ongoing into the engineering feasibility of an EDLS system comprising vented airbag technologies, in order to allow the ExoMars mission to take advantage of this new technology should it prove to be feasible and advantageous to the mission Mars Rover Chassis Evaluation Tools This activity is developing a series of software tools and system level hardware testbeds in order to evaluate different rover chassis and wheel concepts, and control options, in order to optimise the chassis design and advance the overall rover mobility development Solar Cell Development for Mars Exploration Missions Two ongoing activities in this area cover the development (and ultimately down selection) of silicon and Ga-As cells, and also the panel design and dust mitigation techniques for Mars surface applications

Slide11: 

Preparation of future activities Activities already mentioned will ensure critical technologies have achieved the required readiness level (TRL 5) by the beginning of ExoMars phase B development. However, further technology validation / qualification will be pursued within the framework of the ExoMars project (EDLS & Rover) Future technology development activities within the Aurora programme are proposed to be focused now on the preparation of a European participation in an international Mars Sample Return mission These development activities will be proposed for approval at the upcoming ESA Ministerial Council in December 2005 These proposed activities will be prepared through the application of the Aurora technology development approach to the Mars Sample Return mission.

Slide12: 

Mars Sample Return Mission (2016) Main Scientific Objectives: To search for signs of life with sophisticated on-Earth laboratory To perform geological/mineralogical analyses on samples of Martian soil To perform analyses of samples of Martian atmosphere To identify surface hazards to future human missions Main Technology Objectives: Validation of the next generation of EDLS Mars Ascent Vehicle Backward planetary protection Sample containment Operational aspects of a round trip to Mars Autonomous RdV in Martian orbit High-speed Earth re-entry

Slide13: 

MSR Enabling Capabilities

Slide14: 

MSR – Possible European approach MSR technology development will be based on Exomars heritage as much as possible: surface mobility, sample, acquisition and processing, drilling, forward planetary protection, etc. Additional preparatory activities are however necessary for MSR enabling capabilities which have to be mastered and reach TRL 5 by the beginning of phase B: Sample fetching rover Sample acquisition, processing and transfer technologies Biological containment system Deep drilling Mars Ascent Vehicle High bandwidth communications Validation of Rendezvous and capture/docking systems Soft/Precision landing demonstration

Slide15: 

However, a possible international collaboration/cooperation approach to technology demonstration/flight experiment missions might be envisaged in the following areas: High speed Earth entry (incl. Demonstration of biological containment integrity) Autonomous rendezvous (incl. Docking/capture systems) Ascent vehicle demonstration Precision landing demonstration Etc. International collaboration/cooperation Taking account the prospect of a visible European participation in MSR, technology development activities will be defined, down-selected and mostly performed on a European basis.

Human exploration capabilities: 

Human exploration capabilities ESA activities in the area of ISS Evolution/Human Exploration pertain so far mainly on: Habitats including Life Support Robotics RVD Atmospheric Re-entry The European heritage in those Human exploration capabilities is addressed in detail by ESA in Session 3 “ISS and its evolution in the framework of Space Exploration”

BACKGROUND INFORMATION: 

BACKGROUND INFORMATION

Slide18: 

Estimated Pasteur mass: 40 kg ExoMars: Pasteur Payload Composition The Pasteur Payload includes a drill (1.5 to 2.0 m drilling depth) and a sample-handling device, for collecting and analysing samples from within surface rocks, and from underground

Slide19: 

ExoMars – Lite (Carrier-Option) Launcher: Soyuz 2b (from Kourou) Mass margin at launch: 20% Spacecraft composed of: Carrier to deliver the Descent Module from hyperbolic trajectory Descent Module with rigid front shield technology to carry the Rover and its Pasteur payload EDLS design (MER type) with airbags and retrorockets. International cooperation: NASA: Pasteur Instruments from US / Mars Telecom Orbiter (mandatory) / EDLS and Rover design validation Russia: RHUs / Rover chassis design validation

ExoMars – Lite Mission: 

ExoMars – Lite Mission Long cruise required for achieving: Acceptable mass performance allows arrival after dust storm season Release of Descent Module from hyperbolic trajectory for acceptable mass performance Carrier scientific instruments: None Pasteur instruments: 36 kg Rover exploration range: 10+ km / 180 sols Launch dates: Launch June 2011 / landing June 2013 Launch May 2013 / landing March 2015

EXOMARS relevant studies 1ongoing activities: 

EXOMARS relevant studies 1 ongoing activities

EXOMARS relevant studies 2ongoing and planned activities: 

EXOMARS relevant studies 2 ongoing and planned activities

MSR relevant studies 1ongoing activities: 

MSR relevant studies 1 ongoing activities

MSR relevant studies 2planned activities: 

MSR relevant studies 2 planned activities

MSR relevant studies 3planned activities: 

MSR relevant studies 3 planned activities

Slide26: 

Rationale: Inflatable structures and regenerative life support systems are enabling technologies for future Exploration missions. The Inflatable Habitat activity will develop a set of flight and ground demonstrators which will qualify the designs. An integrated Flight Demonstrator, e.g. life support included, would enhance the ISS and could serve as a back up for the respective ISS system. Flight use can be for the ISS and for future exploration missions (e.g. evolution to Lunar Surface System). Technical Concept: Flight demonstrators comprising the inflatable module, the regenerative life support equipment (air and water), certain crew systems such as the toilet and medical equipment. Combined ground demonstrator for closed loop life support demonstration. Major Options: Combination with ASI FLECS system Inflatable Habitat Possible SpaceHaven Flight System ARES Elegant Breadboard

Slide27: 

Rationale: Crew time for future programmes will be a scarce resource. The Eurobot concept is to develop a robotic assistant, for the ISS and for future exploration missions. Technical Concept: The concept will focus on using the Eurobot on the ISS as assistant to Crew during EVA. The system will use existing aids, e.g. handrails. Eurobot will considerably enhance efficiency and safety of crew operations. Maturity of Data/Heritage: Phase A/B Study resulting in a definition of the Eurobot flight demonstrator. Development (05/06) of a WET Model for test at EAC. Europe has background in developing robotics systems from the ERA programme Exploration capabilities - EUROBOT

Slide28: 

Rationale: Exploration programmes will require a universal design of low impact, berthing and docking mechanism to mate vehicles of varying configurations, masses and inertias. Technical Concept: The IBDM is an actively controlled, androgynous berthing and docking system, with a 6 degree of freedom soft docking table and pressurised tunnel . Major Options: Pressurized and unpressurized configurations of various sizes. Application on CARV, Clipper, and exploration elements . Maturity of Data/Heritage: System concept and scaled limited tests by NASA JSC, Mechanical design made for CRV by Verhaert (B), Simulation by SENER (E). Over 5 years of IBDM related European activities. Cooperation Context/Potential: Co-operation with RSA for Clipper, NASA for Spiral 2 developments, US to European company business for CEV. IBDM