February the 17° 2011 Business Unit Space Infrastructures & Transportation All rights reserved © 2011, Thales Alenia Space Date: SPARTAN Grant Agreement n. 262837 SPARTAN SPARTAN
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February the 17° 2011
Business Unit Space Infrastructures & Transportation
All rights reserved © 2011, Thales Alenia Space
Date:
SPARTAN Grant Agreement n. 262837
SPARTANSPARTAN
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
From 3rd Fp7 Space CallGrant Agreement n. 262837Start date: 1st March 2011Planned duration 3 yearsProject Coordinator: Thales Alenia Space – Italia
(Business Segment Space Infrastructures & Transportation Torino)Project Partners:
UNIVERSITA degli STUDI PADOVA – ItalyNAMMO RAUFOSS AS – NorwayBRADFORD Engineering BV – The NetherlandPOLITECNICO di MILANO – ItalyVysoke uceni technicke v Brne – Czech RepublicGMV Aerospace and Defence SA – SpainSTUDIEL – France
Project Overview Project Overview
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ScopeScope
Aimed at the development of a new throttling propulsion technology enabling a Lander to perform a soft and precision landing on a planetary surface, and a new low-cost highly realistic test bed to qualify precision landing capability on ground.
The Hybrid propulsion technology has been selected, because of its peculiarities (safety, minimum environmental impact, low life cycle costs, responsiveness, competitive performances, increased reliability, soft ignition and shutdown).
The landing test requirements are derived from the soft and precision landing requirements on the mars planet surface (i.e. Exomars and Mars Sample Return missions), adapted to the earth environment and to the proposed test specific objectives.
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ObjectivesObjectives
Focuses on three major objectives, that are the key to achieve the soft and precision landing capabilities:
Engine design, specific for throttling functionality,Oxidizer throttable device development,Design of the landing case: test bench and testing procedures.
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
Expected ResultsExpected Results
SPARTAN Project expected results are aimed at enabling soft and precision landing capabilities on Mars by:
Development of an innovative engine design, specific for throttling functionality,Development of an oxidizer throttable device,Design of the landing case including test bench and testing procedures.Perform the demonstration of these high level technologies making the first, but horizontally extended, step up to the throttablepropulsion capability.Demonstrate the first European soft landing drop test, by means of a throttable engine and of a Lander module, autonomously guided.It is expected that these results will trigger an upstream research aimed at improving, in the long-term, the capability for access to planet surfaces in the frame of Space Exploration activities.
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
Work Plan Work Plan -- WBSWBS
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ProductProduct
LanderStructure (Design STUDIEL; Production TAS-I & VUT)
Propulsion (see next)
GNC (see next)
Telemetry & data acquisition (GMV; VUT)
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ProductProduct
PropulsionMotor caseInternal thermal insulationCasted solid fuel grainInjector (UNIPD Design)Ignition systemWeather seal (burst disc)Rocket motor attachment surfaceNozzle
NAMMO
Pressure Regulation ValveBRADFORD
Piping and Harness (TAS-I Design)VUT
Tankage & Auxiliary componentsTAS-I
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ProductProduct
GNCAlgorithm
TAS-I
Onboard computer (one board)Mass Memory Units (MMU)Data Acquisition Units (DAU)-for the laser altimeter, on board sensors and engine throttling devicesBatteryPower, Control and Distribution unitengine ignition device actuation board with safe and arm deviceSerial interfaces for the IMU, GPS, and Attitude and Heading Reference System (AHRS)
GMV
Independent telemetry system and recovery system for safety redundancy during test
VUT
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
ProductProduct
Assembly Integration & Test
Components Assembly
Interconnection
Systems functional tests
Structural test (Small scale drop test to verify landing gear functionality)
Integration of independent data acquisition system and test
VUT
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
Mission ProfileMission Profile
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
Main Results AchievedMain Results Achieved
A specific regression rate measurement device has been designed and tested; the measurement device foreseen in the proposal was supposed to be acquired from the US but this is no longer available for the external market. This is an important added value brought by the project since no such device existed in Europe.Advanced Coding: a CFX code has been developed and extensively used to support the engine design, allowing the engine and engine injection design optimisation (leading to L/D optimization).A detailed design of the Flow Control valve has been carried out and the breadboard model is now being manufactured for verification testing.
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
Main Results AchievedMain Results Achieved
The preliminary Flight Dynamics System design has been performed, allowing for detailed requirements definition and mission profile characterization. GNC components have been selected and preliminarily tested.After a preliminary test aimed at consolidating the test plan for the Throttable Engine validation campaign, an additional representative test in preparation for the validation campaign has been planned and specified. This will be performed with a dummy structure to verify and validate the recovery system, the aerodatabase and the helicopter wake effect.
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
First Year ResultsFirst Year Results
Overall the project is proceeding as expected, the following are the results achieved in the first year:
• Definition of System requirements• Fuel and Oxidiser selection the oxidiser has been changed with respect to
the proposal: HTPB and H2O2• Throttling Concept Selection and preliminary Throttling Device Design• Cold test set-up• CFX code development and validation • Subscale experimental activities • Fuel Regression Rate Characterisation • Fuel Diagnostics development• Preliminary Flight Dynamics Algorithm• Preliminary GNC Architecture• Structure Design and related Analysis
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Date: 29th May 2012SPARTAN Grant Agreement n. 262837 Spartan Project Presentation
First Year ResultsFirst Year Results
Results achieved in the first year (continued):• Preliminary oxidiser tank definition• Engine Preliminary Design• Recovery System Design and component selection• Flight Dynamics Architecture• Flight Software Architecture• GNC Architecture and component selection• Mission profile trade-off and selection• Helicopter wake test together with Dummy Test with helicopter• Aero database definition.
The first annual review with REA went well, some improvements are required in the annual report but the overall performance of the project has been judged positively and accepted by the reviewer.
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