Screenshot from ULA Webcast of the launch of SES 20 & 21
Mission Rundown: ULA - Atlas V 531 - SES 20 & 21
Written: December 8, 2022
Darling. We got twins this time
United Launch Alliance (ULA) has launched the dual-manifested telecommunication satellites SES-20 & 21 on the final Atlas V 531 rocket to almost a geosynchronous orbit (GSO). The Atlas V 531 launched from Space Launch Complex-41 (SLC-41) at the Cape Canaveral Space Force Station (CCSFS) on October 4, 2022 at the opening of the window at 5:36 PM EDT (21:36 UTC).
SES-20 & SES-21 was ULA’s first launch for SES and Atlas V’s third for the company. The two satellites are the latest of up to six satellites for the company’s accelerated C-band clearing plan to meet the FCC’s 5G rollout plan.
The SES-20 & SES-21 mission is ULA’s first commercial communications satellite launch since the Jupiter 2 / EchoStar XIX mission. Jupiter 2 / EchoStar XIX reached GTO atop an Atlas V 431 (AV-071) in December 2016. It was also the first mission directly contracted to ULA for a commercial launch.
The SES-20 & SES-21 Payloads
SES-20 & SES-21 are near-identical satellites owned and operated by the commercial satellite operator SES. SES is a leading global broadband satellite company operating a multi-orbit satellite constellation in medium and geostationary orbits.
The SES S. A. company was founded in 1985 and operated as Europe’s private satellite provider in Luxembourg. SES began launching satellites under the Astra series in the 80s using European, Russian, and American launch vehicles.
The Atlas V’s third flight supported an SES flight in July 2003 with the AMC-16 satellite. The first Atlas V 411 supported the Astra 1KR mission three years later.
Since then, SES has been growing its constellation with geostationary SES and medium Earth orbit (MEO) O3B satellites. SES has partnered with other launch providers, including Arianespace and SpaceX, to keep up with the growing constellation.
Since 2010, SES has seen 28 launches from multiple launch providers for its SES, Astra, and O3B satellites. Most recently, SpaceX launched the SES-22 mission as the first of multiple missions in the next few years for SES.
SES-22 was the first of up to six satellites for SES’s C-band satellites. Since its launch in late June, SES-22 has already entered service.
The SES-20 & 21 satellites are the next in the C-band satellites. The two satellites are based on the Boeing 702 Small Platform (SP) all-electric propulsion satellite bus. The Boeing 702 satellites series is Boeing’s modular offering for GEO and MEO operations, introduced in 1997 and used for commercial and military customers. SES has previously used 13 satellites using the Boeing 702 bus.
The Boeing 702SP is the smallest variant in the 702 satellites series. Each satellite has a mass of 1,500-2,300 kg with its customer’s payload. Since its introduction in March 2015, five satellites have used this variant. SES is one of the previous customers of this variant, with the SES-15 satellite.
SES-20 & SES-22 being encapsulated in the 5.4 meter fairing, who will be filled with dry N2 gas
A feature of the lightweight 702SP bus allows two satellites of the same type to launch simultaneously—the dual satellite configuration for two Falcon 9 flights in 2015 and 2016. SES-20 & 21 is the third flight using this configuration.
In June 2020, SES announced Northrop Grumman (NG) and Boeing received contracts to build four C-band SES satellites. NG and Boeing will build the SES-18 & 19 satellites under or around the GEOStar-3 satellite bus.
The four C-band satellites will help SES to clear 280 MHz of mid-band spectrum for 5G use while seamlessly migrating SES’s existing C-band customers. SES will use these satellites as a part of the company’s accelerated C-band clearing plan to meet the FCC’s objectives to roll out FG services, with a deadline at the end of 2023.
On the satellites are 10 C-band transponders. The transponders, controlled by multiple steerable antennas, will have thousands of narrow steerable beams and the ability to isolate interference sources. The antennas will allow SES and customers to expand, extend, or change the satellite coverage area and its mission.
Equipped on each satellite are four all-electric xenon-ion propulsion system (XIPS) thrusters for on-orbit orbital adjustments and maneuvering. Twin solar arrays provide power to each spacecraft. Both spacecraft will have an orbital lifespan of 15 years.
After separating from Centaur, the two SES satellites will begin their mission. Using the XIPS thrusters, the satellites will maneuver themselves to their GEO orbital position above the equator. SES-20 will take the 103.05 degrees West GEO position slot above the continental United States.
SES-21 will position 131 degrees west, above the United States West coast.
Both satellites will undergo standard on-orbit testing to ensure all of the satellite systems are functional. Once through testing, SES will declare the satellites operational and begin using them for customer services. The two satellites will be able to deliver C-band broadcast, radio services, and critical data networks to said customers.
In August 2020, SES selected Atlas V to launch the SES-20 & 21 satellites for its ability to deliver both satellites in a near-circular GSO. This near-circular GSO will dramatically reduce the time leading to the two satellites’ entry into service. SES and ULA selected the Atlas V 531 variant to place the satellites in this specific orbit.
SES have also ordered SES-22 and SES-23 from Thales Alenia Space (TAS) as backup “spare” satellites. These satellites are used as backups if the other satellites suffer a launch or satellite failure.
SES-22 has launched; however, SES-23 is a on-ground-ready spare until needed. SES-18 & 19 will embark on a flight-proven Falcon 9 in a similar configuration to SES-20 & 21.
The Atlas V 531 Rocket Launch
The launch readiness review LRR was completed on October 2, allowing the MLP to roll the Atlas V from the VIF to the launch site 550 meters south on October 3. Arriving at the launch site, ULA loaded room-temperature RP-1 onto the rocket.
The final launch countdown begins a few hours before launch, with the pad teams clearing the launch site. At L-3 hours, the first of two planned holds begins. This hold allows the team to check all the systems and conduct a poll for final propellant loading.
The countdown resumes two hours before launch, and LOX loading begins on both rocket stages. Just under 90 minutes before the launch, Centaur begins LH2 loading. Launch teams conduct guidance, engine gimbals, and system checks around this time.
Primary propellant loading is complete around L-40 minutes, with the teams transitioning to propellant topping. At L-34 minutes or T-4 minutes, the second and final planned hold begins. This 30-minute hold allows teams to complete the last checkouts before launch.
Weather balloons are released, and the Denver Operations Support Center collects the data to determine what steering profile Atlas should use with the predicted winds.
At L-7 minutes, the ULA Launch Conductor and launch team complete the final Go/No-Go poll. Once the poll is complete and authorization to proceed is received, the countdown resumes at T-4 minutes. The range and rocket are ready to launch at T-55 seconds, with the final status check at T-25 seconds.
The RD-180 engine ignites at T-2.7 seconds, and four seconds later, the three GEM-63 boosters ignite, generating the thrust to lift the vehicle off the pad.
5.6 seconds later, Atlas begins a pitch and roll program to reach the proper flight profile while minimizing the loads on the rocket.
Atlas V reaches the speed of sound 40.2 seconds into flight. Eighteen seconds later, Atlas V passes maximum aerodynamic pressure (Max-Q), where the aerodynamic forces against the rocket are at their peak.
At T+94 seconds into the flight, the three GEM-63 SRBs burn out their solid propellant. Atlas jettisons the three GEM-63 boosters 23 seconds after burnout.
Once out of the densest parts of the atmosphere, the payload fairing is no longer needed to protect the satellites and is jettisoned three minutes and 23 seconds into the flight.
With propellant levels depleted on the first stage, Atlas engine shutdown occurs at T+4 minutes and 19 seconds. Six seconds later, the Atlas separation system activates, and Atlas separates from Centaur. Centaur’s RL-10 engine ignited for its first burn 10 seconds after stage separation from Atlas.
The RL-10 engine burned for eight minutes to reach an initial low Earth parking orbit. Centaur completed a 12-minute coast in this orbit before its second of three burns.
Just above the west African coast, Centaur completed a second five-minute burn to reach a geostationary transfer orbit with an apogee near 36,000 km.
Following the burn, Centaur completed a five-hour coast to apogee. Centaur reignited for its third and final time at five hours, 33 minutes, and 38 seconds into the flight.
This burn lasted two minutes and 14 seconds to reach a near-circular 35,000 km with an inclination of 1.91 degrees.
SES-20 was released from SES-21 three minutes after the last burn was complete.
During a 40-minute coast, Centaur’s reaction control system (RCS) changed the orbit to 34,746 by 35,003 km with an inclination of 1.92 degrees. At T+6 hours, 18 minutes, and 25 seconds, Centaur released SES-21 from its payload adapter.
Centaur changes orbit again when it vents all its remaining propellants as cold gas through the RL-10 engine nozzle 30 minutes after SES-21 separation. There doesn't seem to be any power left in the battery pack left to ignite a fourth burn.
Its mission is complete just over seven hours after launch.
The Atlas V 531 rocket
With 21 launches remaining before Atlas V’s retirement, the Atlas V has a near-spotless record since its maiden flight. The Atlas V designated for SES-20 & 21 was AV-099.
Atlas V is a two-stage liquid-fueled launch vehicle with up to five optional solid rocket boosters (SRBs). This mission used three of these boosters.
On the Atlas V first stage, up to five GEM-63 boosters can support the initial part of the flight. These boosters first supported the NROL-101 mission during an earlier Atlas V 531 flight in November 2020.
Manufactured by Northrop Grumman, the GEM-63s are smaller versions of the GEM-63XL boosters to be used for the Vulcan rocket. Each booster generates 1,652 kN of thrust and burns for about 94 seconds.
The first stage uses a single Russian-built kerolox RD-180 engine. This engine generates 3,828 kN of thrust with a specific impulse of 337 seconds. This stage is 32.5 meters long, 3.81 meters in diameter, and burns for about four minutes.
The second stage is the Centaur upper stage, an iconic staple of the Atlas family. Centaur took its first flight in May 1962 and has evolved in its 60-year flight history. Atlas V uses the Centaur III/Common Centaur introduced with Atlas III.
The historic Aerojet Rocketdyne RL10C-1-1 engine powered Centaur to place the SES 20 & 21 satellites into their intended orbit. The RL-10 uses liquid hydrogen (LH2) and liquid oxygen (LOX) generating 106 kN of thrust with a specific impulse of 453.8 seconds. The RL10C-1-1 variant first supported the SBIRS GEO-5 mission in May 2021.
Centaur also houses the avionic systems for the Atlas V rocket. The upper stage is 3.05 meters in diameter and 12.6 meters in length.
The Atlas V’s 5.4-meter payload fairing encapsulates the Centaur and the two satellites, protecting the payloads during ascent. Manufactured by Beyond Gravity, this payload fairing supports the 500-series of Atlas V rockets. The Atlas V fairing comes in three lengths, with the short version being used on this mission.
For this mission, Atlas V launched in its 531 configuration. The first digit denotes the diameter of the payload fairing, the second indicates the number of solid rocket motors, and the third represents the number of RL-10 engines on the Centaur upper stage.
On SES-20 & SES-21, the Atlas V had a five-meter fairing with three GEM-63 boosters and a single RL10C-1-1 engine. The 531 configuration’s final flight before Atlas V’s retirement.
Facts on the Atlas V launch vehicle
Height of Atlas V 531: 196 feet (59.7 meters)
Fuel onboard: 91,000 gallons of liquid propellant
First stage Atlas: 25,000 gallon RP-1 - 48,800 gallon LOX
Second Stage Centaur: 13,050 gallon LH2 - 4,150 gallon LOX
LOX+LH2 = 66,000 gallon of cryogenic liquid propellant
150 kg (340 lb) of Hydrazine is stored in a pair of bladder tanks
Helium storage tanks: Unknown so far
3 GEM-63 SRB: 300,000 pounds of solid fuel
Mass at liftoff: 1,079,743 pounds (489,763 kg)
Thrust at liftoff: 2.0 million pounds (9.0 mega-Newtons)
Orbit: Near Geosynchronous Orbit - 21,993 x 22,000 miles (35,218 x 35,500 km)
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