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Derivation of the FSOA in Ariane 6 Specifications

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Presentation on theme: "Derivation of the FSOA in Ariane 6 Specifications"— Presentation transcript:

1 Derivation of the FSOA in Ariane 6 Specifications
Nathalie DIAS– CleanSpace Industrial Days October 2017

2 03 SOME EXAMPLES OF debris mitigations 09
01 Introduction 03 Ariane 6 characteristics and MAIN performances 04 Ariane 6 CONFIGURATIon and Mission domain 05 French space operation act and space debris mitigation 06 02 FSOA derivation 07 Safety from ARIANE 6 launcher system to products 08 03 SOME EXAMPLES OF debris mitigations 09 Space debris mitigations 10 ULPM de-orbitation 11 CASUALTY risks 12 04 Conclusion 13-14 ARIANE 6 SAFETY 24/10/2017

3 01 Introduction ARIANE 6 SAFETY 24/10/2017

4 Ariane 6 CHARACTERISTICS & MAIN PERFORMANCES
Ariane A62 (2 boosters) 4,5t – 5t GTO / 7,0t SSO 530t lift-off mass 800t thrust at lift-off Ariane A64 (4 boosters) 10,5t – 12t GTO / 20t LEO* 8,5t Moon transfer 860t lift-off mass 1500t thrust at lift-off Common booster with VEGA-C 35 per year Fairing 20m high (14m option for A62) 5,4m Dual Launch Structure Usable diameter: 4,5m Upper Stage “ULPM” 30t LOX-LH2 Vinci re-ignitable engine 18t / 13t thrust 62m Lower Stage “LLPM” 150t LOX-LH2 * With de-orbitation A64 A62 2/4 solid rocket boosters “ESR” 142t propellant – single segment 350t thrust Vulcain 2.1 engine 137t thrust VEGA-C ARIANE 6 SAFETY 24/10/2017

5 Ariane 6 configurations and mission domain
Ariane 6 Domain Mission Covers large market expectation both commercial and institutional SSO, GTO, sub-GTO, GTO+, LEO, MEO Galileo,… Missions Single, dual and multiple payload configurations Ariane 6 features additional upper part configurations Galileo Mission LEO microsat constellations Single launch Main and auxiliary payloads Dual launch LEO constellations Heavy LEO missions ARIANE 6 SAFETY 24/10/2017

6 French space operation act and space debris mitigations
Act n° relating to Space Operations of 3rd of June 2008 Safety of people and property and the protection of public health and the environment during Space Operations from launch preparation up to disposal Order related to the Technical Regulation [RT] of 31st of March 2011 1st application of the Space Law from the beginning of the development (without interim provisions identified in article 55 of the Technical Regulation) meets Space Debris Mitigation Policy for European Space Agency projects adopting the 2nd edition of ISO Projects ARIANE 6 SAFETY 24/10/2017

7 02 FSOA derivation ARIANE 6 SAFETY 24/10/2017

8 Safety from ARIANE 6 launcher system to products
Space Debris Mitigations LEO&GEO region protection Missions requirements and analysis Launcher System Technical Specification De-orbitation Disposal Program split into Main Function among which one dedicated to Safety. Accidental break-up Technical Specification down to Products Passivation Casualty risks ARIANE 6 SAFETY 24/10/2017

9 03 Some examples of debris mitigations ARIANE 6 SAFETY 24/10/2017

10 Ariane 6 – Space debris mitigations
LEO and GEO regions protection De-orbitation of launcher elements crossing LEO region by controlled re-entry If not possible : Removal from LEO region < 25 years Orbit not interfering the GEO region beyond one year and during at least 100 years Upper Liquid Propulsive Module de-orbitation for many missions within the Mission Domain Dual Launch Structure removed from LEO region within 25 years Mission Domain elaborated considering regions protection requirements Mission profiles include de-orbitation phase if required ARIANE 6 SAFETY 24/10/2017

11 Ariane 6 - Upper Liquid Propulsive Module de-orbitation
Identification of de-orbitation system Vinci re-ignitable engine Used for missions requiring a high de-orbitation delta-V Auxiliary Power Unit (APU) Use for GTO/Sub-GTO missions  low delta-V required New capability allowing better use of propellant ARIANE 6 SAFETY 24/10/2017

12 Ariane 6 – Casualty risks
Launcher elements fallback Fallback zone (with a probability of %) outside territories, including the territorial waters, of any State Early evaluations of Upper Liquid propulsive Module (ULPM) fallout zone opportunities in case of de-orbitation Casualty risks in ascent phase and at de-orbitation Casualty risk lower than at direct de-orbitation Casualty risk lower than 10-4 at natural re-entry Launcher fragmentation and associated debris survivability evaluation Passivation Depletion of Upper Liquid Propulsive Module (ULPM) tanks Before in orbit and at re-entry De-activation of energy sources ARIANE 6 SAFETY 24/10/2017

13 04 Conclusion ARIANE 6 SAFETY 24/10/2017

14 Ariane 6 – SpaCe debris mitigations
Space debris mitigations embedded in Ariane 6 program since the beginning Safety development fully integrated in Launcher System Development and in coherence with Launcher System Development milestones Safety requirements considered at the same level as other requirements Ariane 6 paves the way for space debris elimination at source ARIANE 6 SAFETY 24/10/2017

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