CAPE CANAVERAL SPACE FORCE STATION, Fla. (ULA PR) — A United Launch Alliance (ULA) Atlas V 541 rocket will launch the USSF-12 mission for the U.S. Space Force’s Space Systems Command (SSC). Liftoff will occur from Space Launch Complex-41 at Cape Canaveral Space Force Station, Florida.
Launch Date and Time: Thursday, June 30, 2022 at 6:00 p.m. EDT (2200 UTC)
Webcast begins Thursday at 5:40 p.m. EDT (2140 UTC)
A United Launch Alliance (ULA) Atlas V 541 rocket is launching the USSF-12 mission for the U.S. Space Force’s Space Systems Command (SSC). USSF-12 features two satellite payloads: the Wide Field of View (WFOV) Testbed for SSC’s Space Sensing Directorate and the USSF-12 Ring spacecraft for the Defense Department’s Space Test Program. Atlas V will deliver both spacecraft directly to geosynchronous orbit approximately 22,000 miles (35,500 km) above the equator approximately 6 hours after liftoff. Liftoff will occur from Space Launch Complex-41 at Cape Canaveral Space Force Station, Fla.
The forward payload, WFOV, is a testbed spacecraft that informs the Next Gen Overhead Persistent Infrared program (OPIR). The Next Gen OPIR program will succeed the Space Based Infrared Systems program and is designed provide a resilient space-based global missile warning capability against emerging missile and counter-space threats. Sponsored by Space Systems Command and managed by the NASA Ames Research Center, the mid-sized WFOV spacecraft is based on Millennium’s AQUILA M8 affordable platform series and hosts a transformational OPIR six-degree staring sensor developed under a separate contract by L3Harris Technologies. The WFOV testbed is designed for a 3- to 5-year life with a total mass up to 6,613 lbs (3,000 kg) and a payload accommodation over 771 lbs (350 kg). WFOV’s primary mission in orbit is to explore future missile warning algorithms with data collected in space.
The aft payload is a propulsive ESPA named the USSF-12 Ring. The Ring is a classified mission to demonstrate future technology for the Department of Defense.
Payload Fairing (PLF)
The spacecraft are encapsulated in a 17-ft (5-m) diameter short payload fairing produced in the advanced Out-of-Autoclave manufacturing process. The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur and the satellite. The vehicle’s height with the 5-meter short PLF is approximately 196 ft (59.7 m).
The Centaur second stage is 10 ft (3 m) in diameter and 41.5 ft (12.6 m) in length. Its propellant tanks are pressure-stabilized and constructed of corrosion-resistant stainless steel. Centaur is a cryogenic vehicle, fueled with liquid hydrogen and liquid oxygen, powered by an RL10C-1 engine producing 22,900 lbs (101.8 kilo-Newtons) of thrust. The cryogenic tanks are insulated with a combination of helium-purged blankets, radiation shields and spray-on foam insulation (SOFI). The Centaur forward adapter (CFA) provides structural mountings for the fault-tolerant avionics system and structural and electrical interfaces with the spacecraft.
The booster is 12.5 ft (3.8 m) in diameter and 106.5 ft (32.5 m) in length. The booster’s tanks are structurally rigid and constructed of isogrid aluminum barrels, spun-formed aluminum domes and intertank skirts. Booster propulsion is provided by the RD-180 engine system (a single engine with two thrust chambers). The RD-180 burns RP-1 (Rocket Propellant-1 or highly purified kerosene) and liquid oxygen and delivers 860,200 lbs (3.83 mega-Newtons) of thrust at sea level. Four solid rocket boosters (SRBs) generate the additional power required at liftoff, with each providing 371,550 lbs (1.6 mega-Newtons) of thrust. The Centaur avionics system, provides guidance, flight control and vehicle sequencing functions during the booster and Centaur phases of flight.