SPACE LAUNCH REPORT Ariane 6 Flight History by Ed Kyle, Last Update March 10, 2024 L(F) = Number of Launches(Number of Failures) Ariane 6 Grand Total Year L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ 2020 - - - - - 2021 - - - - - 2022 - - - - - 2023 - - - - - 2024 - - - - - ------------------------------------------------------------------ Ariane 6 Grand Total L(F) L(F) L(F) L(F) L(F) ------------------------------------------------------------------ Suborb - - - - - Orbit - - - - - Total - - - - - ------------------------------------------------------------------ Ariane 6 Vehicle Configurations Masses in tonnes ------------------------------------------------------------------ LEO GTO GEO Escape Height GLOW (1)200 km 1500 m/s ISS to GEO (2)500 km SSO ================================================================== Ariane 62 10 t (1) 4.5 t - 2.6 t ~63 m 530 t 7.2 t (2) Ariane 64 20 t (1) 11.5 t 5.0 t 7.4 t ~63 m 860 t 15.5 t (2) ================================================================== Ariane 62 = LLPM + 2xP120C + ULPM + PLF Ariane 64 = LLPM + 4xP120C +ULPM + PLF * GEO: Geosynchronous Earth Orbit Ariane 6 Components ------------------------------------------------------------------ P120C Lower Liquid Upper Liquid Solid Rocket Propulsion Module Propulsion Module Motor (Each) (LLPM) (ULPM) ================================================================== Diameter (m) 3.4 m 5.4 m 5.4 m Length (m) 13.5 m ~32 m m Mp (t) 142 t 150 t 30 t GLOW (t) 155.5 t ~165 t ~33.3 t Engine P120C Vulcain 2.1 Vinci Fuel HTPB LH2 LH2 Oxidizer HTPB LOX LOX Thrust ~400 t 139.8 t (vac) 18.35 t (vac) ISP(Vac s) ~241 s ~318/432 s 457 s (SL/Vac) Tburn (s) 135 s 470 s 760 s No. Eng. 1 1 1 ================================================================== Ariane 6 Components, Cont'd ------------------------------------------------------------------ VEB Sylda 5 Speltra Medium Long PLF PLF ================================================================== Dia (m) 5.4 m 5.4 m 5.4 m 5.4 m Len (m) 1.56 m 7 m 14 m 20 m Mass (t) 1.9 t 0.425 0.716 2.13 t 2.5 t -0.5 t -0.822 t ================================================================== Ariane 6 Launch History ------------------------------------------------------------------ DATE VEHICLE ID PAYLOAD MASS(t) SITE* ORBIT** ================================================================== mm/dd/yy Ariane 6 L601 xx nn KO 4 nnn ================================================================== Ariane 6 Development Studies that led to Ariane 6 began in late 2012. One early, seriously considered concept was a CNES "Multi-P" design named Ariane 6 P7C. P7C would use combinations of only one type of solid motor. One 3.7 meter diameter P135 motor would serve as the rocket's second stage. Two or three P135 motors would be combined to work as a first stage, with all of the motors firing and separating together. Although promising lower costs, P7C was also more limited since its two variants could carry a maximum of either 3.4 tonnes or 6.5 tonnes to GTO. One advantage of the P7C is that its "smaller" P135 motors (which would still be the world's largest monolithic solid motors) might offer a path to upgrade Vega, Europe's small all-solid launch vehicle. Vega's then-current first stage was a P80 monolithic, which was at the time the world's largest non-segmented solid motor. CNES favored the solid motor designs, which its studies showed offered better cost competitiveness than the cryogenic core design. The improved Vulcain 2 engine development effort, likely costly, would have been avoided. Ariane 62 Design P7C and other solid motor concepts remained controversial outside France. In July 2014, Airbus-Safran announced a joint venture that proposed an alternative Ariane 6 design. It used two liquid hydrogen stages boosted by two monolithic solid rocket motors. Unlike earlier cryogenic core designs, the first stage was powered only by a single Vulcain 2 engine. An Ariane 6-1 "Heavy" version would use the 5.4 meter diameter Vinci powered upper stage from the planned Ariane 5 ME to lift up to 8.5 tonnes to GTO. An Ariane 6-2 variant would use the ES/Aestus engine powered hypergolic second stage to handle Soyuz-class "Medium" payloads. The rocket would use the existing Ariane 5 launch pad, with modifications. By early October, 2014, the Airbus-Safran design had been further revised with the involvement of ESA to cut costs. The hypergolic upper stage was eliminated, leaving only the Vinci powered upper stage. Two variants were instead created by varying the number of solid rocket motors, which were reportedly "P120" motors loaded with 120 tonnes of propellant. An Ariane 6-2 version would use two of the motors to lift up to 5 tonnes to GTO for a predicted launch cost of $95 million. It would mostly handle single-satellite missions. The Ariane 6-4 version would use four of the motors to lift 11 tonnes to GTO for about $117 million, enough capability to handle two satellites at once like Ariane 5 ECA. The P120 solid rocket motors would be common with Vega-C, a planned evolution of the Vega launcher. The modified Airbus-Safran design would use a 4.6 meter diameter first stage loaded with 149 tonnes of propellant. Each P120 booster would be about 3.022 meters in diameter and 17.74 meters long. The entire rocket would stand about 63 meters tall, more than 5 meters taller than Ariane 5. The resulting joint ESA-industry proposal for Ariane 6 was presented to the Council at Ministerial level in December 2014. The Council was expected to choose between accelerated Ariane 6 development and continued Ariane 5 ME development at that time. A complication that arose was that the new Ariane 6 design would not be able to use the existing Ariane 5 ELA 3 launch site, requiring the costly development of a new facility. Development costs for Ariane 6-2 were, as a result, projected to rise to $5.2 billion. The 2014 Decision On December 2, 2014, the European Space Agency Council at Ministerial level agreed to accelerate Ariane 6 development while foregoing previously planned Ariane 5 ME development. The Council selected a new Ariane 6 design that represented months of engineering and political compromise. The new rocket, expected to enter service in 2020, will replace Ariane 5 and, likely, Soyuz out of Kourou. The new Ariane 6 design would use two liquid hydrogen stages boosted by two to four monolithic solid rocket motors. It wis based on a mid-2014 Airbus-Safran joint venture proposal that won out over the previously approved CNES "Multi-P" design. Unlike earlier cryogenic core designs, the first stage would be powered only by a single Vulcain 2 engine that would produce about 138 tonnes of thrust. It would be loaded with up to 149 tonnes of propellant. The second stage would be loaded with about 30 tonnes of propellant and would be boosted by the Vinci engine originally developed for Ariane 5 ME. Vinci would produce about 18.35 tonnes of thrust. Both stages would be 4.6 meters diameter, smaller than the 5.4 meter diameter Ariane 5 tanks. Early concepts called for a 5.4 meter diameter second stage. Two to four monolithic solid rocket motors would power Ariane 6 off its launch pad. Each P120 composite-case motor would be loaded with about 120 tonnes of propellant and produce about 357 tonnes of thrust. The P120 solid rocket motors would be common with Vega-C. Each P120 booster would be about 3.022 meters in diameter and 17.74 meters long. An Ariane 6-2 variant would use two of the motors to lift up to 5 tonnes to geosynchronous transfer orbit (GTO) for a predicted launch cost of $97 million. It would primarily handle single- satellite government missions. An Ariane 6-4 version would use four of the motors to lift 10.5 to 11 tonnes to GTO for about $140 million, enough capability to handle two satellites at once like Ariane 5 ECA. With seperate bulkhead propellant tanks and a long interstage to allow Vinci to use a fixed nozzle extension, Ariane 6 could end up standing up to 70 meters tall, about 20 meters taller than Ariane 5 ECA. Ariane 6-2 would weigh about 500 tonnes at liftoff while Ariane 6-4 would weigh 800 tonnes. The new Ariane 6 will require an all-new launch complex, which would include a 100 meter tall vertical assembly building. The new launch complex was expected to cost more than $850 million. The entire Ariane 6 development effort was expected to cost nearly $5 billion. Design Evolves in 2015 In early November, 2015, Airbus-Safran released drawings that showed a fatter, shorter Ariane 6. The core diameter had increased to 5.4 meters, the same diameter as the payload fairing and the same as Ariane 5. The fatter core had reduced overall vehicle height to 60 meters, which would make it only slightly taller than Ariane 5. A single Vulcain V2.1 was identified as the core stage propulsion. The strap on solid rocket motors were identified as P120C motors. Their nose fairings were elongated and they tapered in toward the core stage intertank section, another change from earlier plans. Liftoff mass for Ariane 62 was given as "~500 tonnes" and for Ariane 64 as "~800 tonnes". Development Milestones The first full-up Vulcain 2.1 ground test firing was performed on January 22, 2018 at DLR's Lampoldshausen, Germany test site, at the P5 test facility. The first P120C test firing took place on July 16, 2018 at Kourou. It was the first of three such qualification test firings planned to occur before P120C debuts on the inaugural Vega-C flight, expected to take place in 2019. Launch site construction was well underway by early 2018, aiming for a first launch in 2020. References Ariane 6 User's Manual, Arianespace, March 2018