A successful water flow test with the mobile launcher at Kennedy Space Center’s Pad 39B on July 2, 2019, put NASA one step closer to returning astronauts to the Moon by 2024, with the goal of sending humans to Mars. It was the first of nine tests to verify the sound suppression system is ready for launch of NASA’s Space Launch System for the first Artemis mission.
Approximately 450,000 gallons of water was released from an elevated water tank and distributed through large diameter piping and valves to water nozzles located in the Pad B flame deflector, the mobile launcher flame hole and on the launcher’s blast deck in just 45 seconds. That’s enough water to fill 45 residential swimming pools! The system reached a peak flow rate of 1.1 million gallons per minute.
A fully functional Launch Abort System (LAS) with a test version of the Orion spacecraft attached, launches on NASA’s Ascent Abort-2 (AA-2) atop a Northrop Grumman provided booster on July 2, 2019, at 7 a.m. EDT, from Launch Pad 46 at Cape Canaveral Air Force Station in Florida. During AA-2, the booster will send the LAS and Orion to an altitude of 31,000 feet at Mach 1.15 (more than 1,000 mph). The flight test will prove that the abort system can pull crew to safety in the unlikely event of an emergency during ascent.
Omega, stylized as “OmegA”, is a launch vehicle in development by Northrop Grumman as an NSSL replacement program intended for national security and commercial satellites.
Omega is similar to the defunct Ares I and Liberty projects, both of which consisted of a five segment Space Shuttle Solid Rocket Booster (SRB) and a cryogenic second stage. Ares I would have combined a five-segment SRB with a J-2X powered second stage, while Liberty would have used a five-segment SRB with the core stage of the European Ariane 5 as a second stage. By comparison, Omega consists of Space Shuttle-derived solid stages with a cryogenic upper stage provided by Aerojet Rocketdyne (replacing earlier plans to use an upper stage provided by Blue Origin). It is intended to be launched from Kennedy Space Center LC-39B or Vandenberg Air Force Base SLC-2.
Omega is proposed as a vehicle to launch national security satellites for the United States Air Force, and could launch other government and commercial payloads, including to geostationary transfer orbit. Crewed spacecraft could also be launched, just as the predecessor Ares I and Liberty rockets, which were designed to launch the Orion space capsule.
The Proton-M launch vehicle consists of three stages; all of them powered by liquid rocket engines using the hypergolic propellant combination of dinitrogen tetroxide as the oxidizer, and unsymmetrical dimethylhydrazine for fuel.
The first stage is unique in that it consists of a central cylindrical oxidizer tank with the same diameter as the other two stages with six fuel tanks attached to its circumference, each carrying an engine. The engines in this stage can swivel tangentially up to 7° from the neutral position, providing full thrust vector control. The rationale for this design is logistics: the diameter of the oxidizer tanks and the two following stages is the maximum that can be delivered by railroad to Baikonur. However, within Baikonur the fully assembled stack is transported again by rail, as it has enough clearance.
The second stage uses a conventional cylindrical design. It is powered by three RD-0210 engines and one RD-0211 engine. The RD-0211 is a modified version of the RD-0210 used to pressurize the propellant tanks. The second stage is joined to the first stage through a net instead of a closed inter-stage, to allow the exhaust to escape because the second stage begins firing seconds before separation. Thrust vector control is provided by engine gimballing.
The third stage is also of a conventional cylindrical design. It contains the avionics system that controls the first two stages. It uses one RD-0213 which is a fixed (non-gimballed) version of the RD-0210, and one RD-0214 which is a four nozzle vernier engine used for thrust vector control. The nozzles of the RD-0214 can turn up to 45°; they are placed around (with some separation), and moderately above the nozzle of the RD-0213.
The Proton-M features modifications to the lower stages to reduce structural mass, increase thrust, and utilise more propellant (less of it remains unused in the tanks). A closed-loop guidance system is used on the first stage, which allows more complete consumption of propellant. This increases the rocket’s performance slightly compared to previous variants, and reduces the amount of toxic chemicals remaining in the stage when it impacts downrange. It can place up to 21 tonnes (46,000 lb) into low Earth orbit. With an upper stage, it can place a 3 tonne payload into geosynchronous orbit, or a 5.5 tonne payload into geosynchronous transfer orbit. Efforts were also made to reduce dependency on foreign component suppliers.
Yamal 601 (Russian: Ямал-601) is a geostationary communications satellite ordered by Gazprom Space Systems to ISS Reshetnev on the Ekspress-2000 platform for its Yamal program. The Ekspress-2000 platform is the heavy version, which can weigh up to 3,500 kg (7,700 lb) and generate up to 14 kW of power on an unpressurized bus designed for direct GEO injection with 15 years of design life. Its payload will be supplied by Thales Alenia Space and is composed of 38 C band, and 32 Ka band transponders. It will replace Yamal 202 on 49°E when it reaches its end of service around 2018.
NASA’s Orion, Space Launch System (SLS), and Exploration Ground Systems (EGS) programs are continuing work on one of the most complex and sophisticated space systems ever built. Across America and in Europe, teams are developing and building the spacecraft, rocket, and infrastructure necessary to send humans to deep space destinations including the surface of the Moon and beyond.
Some major recent milestones include: Orion – Crew Module Uprighting System Test at Atlantic Beach, North Carolina; European Service Module Solar Array Expanded; Fit Check in the Super Guppy Aircraft; Ascent Abort-2 Launch Abort System Stacking and Integration at Kennedy Space Center in Cape Canaveral, Florida; Launch Abort System Attitude Control Motor Test in Elkton, Maryland. SLS – Liquid Oxygen Tank and Forward Skirt join at Michoud Assembly Facility in New Orleans, Liquid Hydrogen Tank Structural Test Article Unload from Pegasus Barge at Marshall Space Flight Center in Huntsville, Alabama; RS-25 Engine Testing at Stennis Space Center in Bay St. Louis, Mississippi; Core Stage-1 Engine Section and Boat Tail Completed and Mated at Michoud. EGS – at NASA’s Kennedy Space Center: Core Stage Intertank Umbilical Swing Testing; Launch Pad 39B Upgrades; Crawler Engine Maintenance.
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