THE FIRST INTERNATIONAL LARES WORKSHOP
VEGA LAUNCH VEHICLE & QUALIFICATION ( LARES) MISSION CHARACTERISTICS
LARES WS 3-4/July/2009 1 THE FIRST INTERNATIONAL LARES WORKSHOP
¾ Vegaaisis aafoufour stage vehicle mainl y based on solid propulsion, with ahigh a high level of integration within the Ariane LV family
Design drivers are: • P/L & customer comfort • Launch Cost • Missi on fl exibilit y ••RReeabtyliability
LARES WS 3-4/July/2009 2 VEGA LV CHARACTERISTICS
¾ The Vega LV is designed for a range of missions covering the ijinjecti on of one payldload itintocilircular Low EthEarth ObitOrbits (LEO), with altitudes ranging from 300 km to 1500 km and with inclinations ranging from nearly equatorial (5.2°)uptoSun Sy nchronous Orbits
¾ The injected Payload masses range is required from a miiinimum of 300 Kguptoamaximum of 2500 Kg, as appropriate according to orbit altitude and inclination.
¾ The Vega LV is designed to be compatible, in the above mentioned range of orbits, with the capability for multiple payloads delivery, defined as follows :
- Injection of two payloads, in the mass range of 300 – 1000 Kg; - Injection of one main ppyayload and up to six micro-satellites, in a piggyback configuration, with mass of the order of 100 kg.
LARES WS 3-4/July/2009 3 VEGA LV TYPICAL MISSION PROFILES
¾ Earth observation, scientific and meteorological satellites delivered directly into Sun Synchronous Orbit (SSO), Polar Circular Orbit or Circular Orbits with varied inclinations and in Low Earth Orbit (LEO).
¾ Vega AVUM’s multiple burn cappyability offers excellent flexibility to a wide range of elliptical and circular orbits. ¾ A typical flight profile begins with a sub-orbital ascent performed by Vega’s three solid propellant stages, followed by several (up to five) burns of the AVUM.
¾ The final AVUM burn is made for the stage’s own reentry or orbit disposal, in order to comply with the stringent rules to reduce the orbital debris risk.
LARES WS 3-4/July/2009 4 VEGA LV PERFORMANCE
Vega Performance Map - Circular Low Earth Orbits
Vega Performance 2350 Requirement: 1500 kg in a 700 km cilircular polar l orbit bit 2100 g] kk 1850
300 km
ad Mass [ 1600
500 km Paylo 700 km 1350
1100 1200 km
1500 km 850 0 102030405060708090100
Orbit Inclination Inclination [degrees] [degrees]
LARES WS 3-4/July/2009 VEGA LV REFERENCE MISSION
LARES WS 3-4/July/2009 Present Candidates for VEGA Missions
2011 2012 QF 1st Half 2d2nd HHlfalf 1st Half 2d2nd HHlfalf 2016 2017
SENTINEL 2A SENTINEL 2B LARES LISA VEGA PATHFINDER Qualification SWARM Flight
IXV SENTINEL 3B
PRISMA - ASI AEOLUS
MIOSAT - ASI SENTINEL 3A
LARES WS 3-4/July/2009 7 VEGA MARKET for short term (up to 2015)
VEGA Main Missions Earth Observation & Technology from European Institutional agency
Market’s interest on the VEGA P/L classes considering its performances vs cost per Launch
Potential Market linked to the new constellation of satellite • Galileo • Globalstar • Iridium plus microsatellites
LARES WS 3-4/July/2009 8 VEGA MARKET for medium term ( 2015÷2020)
VEGA Main Missions Earth Observation & Technology
Market’s growing for the P/L class up to 2500 kg
Potential Market linked to the replacement of old satellites plus microsatellites
LARES WS 3-4/July/2009 9 VEGA LV OVERALL CHARACTERISTICS
Overall height [m] 30.2 MiMaximum diete[]diameter [m] 303.0 Payload P/L envelope (diameter) [m]2.3 composite P/L envelope (cyl . length) [m] 303.0 Lift-off mass [kg] 137 000 Z9 SRM P/L mass @@,[g] 700km, PEO [kg] 1500
Z23 SRM
AVUM & P80 SRM IS34 IS 23
IS 01 IS 12
LARES WS 3-4/July/2009 10 VEGA LV FAIRING
Ø 430
EXTERNAL STRUCTURE PAYLOAD ENVELOPE P/L ADAPTER VG937B
2800
The Fairing of VEGA has been designed to accommodate : ¾ N° 1 Single Main P/L 3050 P/L ¾ N° 2 Single Main P/L (VESPA) ¾ N° 1 Single Main P/L + microsatellites 450
Ø 720
Ø 2380
LARES WS 3-4/July/2009 VEGA LV STD P/L ADAPTER
¾ The figure represent the standard P/L adapter so called 937 that has the same interfce derived from ARIANE ppgrogramme
¾ It is designed to withstand all the structural loads deriving from the main P/L mass ranging from 300÷2500 kg and relevant environmental loads
LARES WS 3-4/July/2009 VEGA LV VESPA SYSTEM
VESPA (VEga Secondary Payload Adapter) general view
LPSS 937 VESPA SECTION VIEW (Separation System) MAIN P/L
Upper Part Mass ≤ 1000 kg
LPSS 2105 SECONDARY (Separation P/Ls System) Mass ≤ 200 kg for one Boat-tail and the maximum aggregated mass shall not exceed 600 kg DERIVED FROM 937
LARES WS 3-4/July/2009 LARES system CHARACTERISTICs
LARES SAT ALMASat-1
Heat flux sensor SSEP support SSUP Heat flux sensors PPOD/Cubesats conditioners
PPOD/Cubesats
Heat flux sensor support Video-camera Accelerometer conditioners
A&H Lares S/C mass: 400 kg Lares Support System mass: 300 kg Total Lares P/L mass: 700kg
LARES WS 3-4/July/2009 14 LARES MISSION CHARACTERISTICs
The VEGA QQgpjualification Flight is optimized to inject the LARES Satellite in its nominal operational orbit : z Circular Orbit zApogee/Perigee Altitude = 1450 x 1450 [km] z Inclination = 71 [deg]
In addition a set of micro satellite : z N° 9 CubeSats microsatellite z ALMASat-1. shall be also released at the end of AVUM Deorbiting phase with Apogee/Perigee altitude 1450x340 [km]
LARES WS 3-4/July/2009 15 LARES MISSION CHARACTERISTICs
LARES MISSION FLIGHT TIMELINE
LARES INJECTION TIME
LARES WS 3-4/July/2009 16 LARES MISSION CHARACTERISTICs
P80 flight
LARES WS 3-4/July/2009 17 LARES MISSION CHARACTERISTICs
P80 flight
LARES WS 3-4/July/2009 18 LARES MISSION CHARACTERISTICs
Z23 flight
LARES WS 3-4/July/2009 19 LARES MISSION CHARACTERISTICs
Z9 flight
LARES WS 3-4/July/2009 20 LARES MISSION CHARACTERISTICs
AVUM 1° boost
LARES WS 3-4/July/2009 21 LARES MISSION CHARACTERISTICs
LARES INJECTION POINT
AVUM 2° boost
LARES WS 3-4/July/2009 22 LARES MISSION CHARACTERISTICs
CUBESATs ALMASAT AVUM 3° INJECTION boost : POINT Deorbiting
LARES WS 3-4/July/2009 23 LARES MISSION CHARACTERISTICs
Z9 flight
Z9 re-entry Path
LARES WS 3-4/July/2009 24 LARES MISSION CHARACTERISTICs
LARES WS 3-4/July/2009 25 LARES MISSION CHARACTERISTICs
VEGA TIPICAL MISSION SIMULATION Vega Presentation.wmv
LARES WS 3-4/July/2009 26