USSF-12 | Atlas V 541

Featured image credit: United Launch Alliance
Lift Off Time

July 01, 2022 – 23:15 UTC | 19:15 EDT

Mission Name


Launch Provider
(What rocket company launched it?)

United Launch Alliance (ULA)

(Who paid for this?)

U.S. Space Force’s Space Systems Command (SSC) and the Department of Defense (DoD)


Atlas V 541 

Launch Location

SLC-41, Cape Canaveral SFS, Florida, United States

Payload mass

≥4,100 kg (≥9,040 lb)

Where did the satellites go?

Geosynchronous orbit (GEO)

Did they be attempt to recover the first stage?

No, Atlas V is not capable of recovery

Where did the first stage land?

It crashed into the Atlantic Ocean

Did they be attempt to recover the fairings?

No, Atlas V is not capable of recovery

Were these fairings new?


This was be the:

– 9th flight of the Atlas V 541 configuration
– 4th launch of ULA in 2022
– 78th Atlas V launch from Cape Canaveral
151st ULA’s mission
– 73rd successful orbital launch of 2022

Where to watch

ULA’s Official livestream

How Did It Go?

United Launch Alliance (ULA) launched two spacecrafts for the U.S. Space Force’s Space Systems Command (SSC) and the Department of Defense (DoD). This mission saw the use of an Atlas V 541 launching from Space Launch Complex 41 at Cape Canaveral Space Force Station in Florida, USA. On board of USSF-12 were the Wide Field of View (WFOV) testbed for the SSC and the USSF-12 Ring spacecraft for the DoD’s Space Test Program (STP). Both satellites were ferried directly into a geosynchronous orbit. This mission marked ULA’s fourth launch in 2022, with OFT-2, the third, back in May of 2022.

After the Centaur Upper Stage was put into its initial highly elliptical orbit, it entered a five-hour coast phase after which it reached apogee. At apogee its RL-10 engine fired up for a third and final time to insert both payloads directly into the target orbit. Separated by ten minutes, both satellites were separated from the Centaur Upper Stage, which performed its “Blowdown”. The mission ended approximately seven hours after lift off.

An artist’s render of the Wide Field of View testbed satellite. (Credit: Millennium Space Systems)


USSF-12’s primary payload is the U.S. Space Force’s SSC’s Wide Field of View (WFOV) testbed, with a secondary payload for the DoD’s STP.

Wide Field Of View (WFOV) Testbed

The WFOV testbed is an Overhead Persistent Infrared (OPIR) technology demonstrator that will mature and prove the effectiveness of its 6-degree staring sensor called Wide-Area Six-Degree Payload (WASP). Developed by L3 Harris under a separate contract, WASP will be able to observe nearly one third of Earth’s surface. WFOV will be capable of performing strategic and tactical missions, such as battlespace awareness and missile warning, and directly supporting warfighters by monitoring Earth’s surface respectively. With pathfinding the process to operationalize OPIR data, the WFOV testbed will play an important role as part of the Missile Warning, Tracking, and Defense architecture.

The WFOV testbed is based on Millennium Space System’s Aquila M8 satellite bus. It has two deployable solar arrays offering a baseline payload power of 2500 W (options up to 10 kW), is powered by a bi-propellant propulsion system, and single or dual string avionics. The Aquila M8 satellite bus is Millennium Space System’s biggest satellite bus in their line-up, weighing ~3,000 kg with a payload accommodation of over 350 kg. It’s designed to operate 3 to 5 years on orbit.

The Wide Field of View testbed satellite during testing. (Credit: Millennium Space Systems)

USSF-12 Ring Spacecraft

The secondary payload of the USSF-12 mission is an ESPA (EELV Secondary Payload Adapter) Star platform built by Northrop Grumman weighing 740-780 kg with room for up to six hosted or up to twelve deployable payloads. Each of the six payload slots is designed for payloads of around 320 kg (1,920 kg in total). It has a four-panel deployable solar array providing 1,200 W of power and a hydrazine based hypergolic propulsion system.

The USSF-12 Ring spacecraft is a classified mission that will demonstrate future technology for the DoD.

A render of Northrop Grumman’s ESPA Star platform. (Credit: Northrop Grumman)

USSF-12 Mission Timeline

Hrs:Min:SecEvents-0:00:01.0RD-180 engine ignition+0:00:01.0Liftoff+0:00:06.9Begin pitch/yaw maneuver+0:00:57.8Mach 1+0:01:07.4Maximum dynamic pressure+0:01:48.4Solid rocket booster jettison+0:03:25.6Payload fairing jettison+0:04:24.3Atlas booster engine cutoff (BECO)+0:04:30.3Atlas Centaur separation+0:04:40.2Centaur first main engine start (MES-1)+0:10:58.2Centaur first main engine cutoff (MECO-1)+0:23:13.6Centaur second main engine start (MES-2)+0:28:41.9Centaur second main engine cutoff (MECO-2)+5:43:54.1Centaur third main engine start (MES-3)+5:46:20.0Centaur third main engine cutoff (MECO-3)+5:49:36.0WFOV spacecraft separation+5:59:03.0Booster adapter separation+6:05:21.0USSF-12 ring spacecraft separation+6:31:41.0Start blowdown+7:06:41.0End of mission

What Is The Atlas V?

The Atlas V is an expendable medium-lift launch system and member of the Atlas rocket family. The rocket has two stages. The first is a Common Core Booster (CCB), which is powered by a single RD-180 engine that burns kerosene (RP-1) and liquid oxygen (LOx). This is accompanied by up to five strap-on solid rocket boosters (SRB). The second stage is the Centaur upper stage, which is powered by one or two RL10 engines and burns liquid hydrogen (LH2) and liquid oxygen (LOx).

The stacked Atlas V 541 awaiting roll out to the pad prior to the GOES-T mission. (Credit: ULA)

The CCB is 3.8 m (12.5 ft) in diameter and 32.5 m (106.5 ft) in length. This stage is capable of producing 3.83 MN (860,200 lb) of thrust at sea level. Each SRB can provide additional 1.6 MN (371,550 lb) of thrust. The Centaur second stage, in turn, is 3 m (10 ft) in diameter and 12.6 m (41.5 ft) in length and is capable of producing 101.8 kN (22,900 lb) of thrust.

What Does 541 Mean?

Atlas V rockets have a three number configuration code. The first number represents the fairing diameter size in meters. The second number denotes the number of solid rocket motors (SRMs), which attach to the base of the rocket. The number of SRMs for a 4 meter fairing can range from 0 – 3. However, the 5-meter fairing Atlas V can support up to 5 SRMs, due to the different aerodynamic properties of the fairing. For the GOES-T mission, there will be four SRM attached to the center core. The third number denotes the number of engines on the Centaur Upper Stage.

A diagram of the entire Atlas V family with the SRM placement for each number shown. (Credit: NASA)

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