Screenshot from ULA Webcast of the launch of SMAP. Aw man. Why must I always get up so early?
Mission Rundown: ULA - Delta II 7320-10C - SMAP
Written: January 14, 2023
How wet is the ground really?
United Launch Alliance (ULA) successfully conducted a rare Delta II launch January 31, 2015 on Saturday morning, at 06:22 PST - 14:22 UTC, following a scrub on Thursday, along with a debonding of insulation on the booster, suffered during the subsequent detanking.
The aging rocket orbited the Soil Moisture Active Passive, or SMAP, satellite for NASA’s mission to produce a global map of the moisture content in the Earth’s soil.
During its planned three-year mission the spacecraft will take repeated measurements of the Earth’s surface as it orbits the planet, allowing scientists to study the distribution of water in soil around the world and its role in the water cycle.
NASA envisions that this data will improve weather forecasts, add to research into Earth’s climate and help with agricultural, resource management and emergency planning.
Development of the SMAP spacecraft was authorized in 2008, based on the Hydros mission which had been canceled three years earlier.
Hydros, which had been slated for a 2010 launch at the time of its cancellation, formed part of NASA’s Earth System Science Pathfinder (ESSP) program however it had been canceled due to budget cuts.
The mission was still in early development at the time of its cancellation.
The SMAP Payload
The SMAP satellite has a mass of 944 kilograms (2,081 lb) and is powered by a three panel solar array which generates 1.45 kilowatts of power. It will use active and passive remote sensing techniques to infer surface water content from radar backscatter and microwave emissions.
The active element of the spacecraft’s instrument suite is an L-band synthetic aperture radar (SAR) while a radiometer forms the passive component of the payload. A six meter (19.7-foot) mesh antenna will be deployed after launch for these instruments.
The synthetic aperture radar emits signals and then analyzes the backscattered signal, determining the water content of the soil from the amount of radiation that it reflects.
The instrument can image at a resolution of 1-3 kilometers (0.6-1.8 miles) but the data it returns will be less accurate than the radiometer, whose data comes from studying microwave radiation emitted from the surface. Although more accurate, the radiometer operates at a lower resolution of 40 kilometers (25 miles) than the radar.
SMAP will fly in a 426-mile (685-kilometer) altitude, near-polar, sun-synchronous orbit that crosses the equator near 06:00 a.m. and 18:00 p.m. local time. That gives a local moisture content in moist cold mornings and after dry warm sunny days.
SMAP is designed to operate for at least three years, producing a global map of soil moisture every two to three days.
Artist’s rendering of NASA's Soil Moisture Active Passive (SMAP) spacecraft in orbit near Panama
Mission scientists hope to use the data from the two instruments to produce a combined output with a resolution of around 10 kilometer (6.2 miles). The radar payload has a mass of 49 kilograms (108 lb), while the radiometer has a mass of 30 kilograms (66 lb).
The mission is being conducted by NASA’s Jet Propulsion Laboratory, who constructed the spacecraft in-house apart from the radiometer, which was developed by NASA’s Goddard Space Flight Center.
ELaNa X CubeSat program
In addition to SMAP, the launch carried four miniature satellites under NASA’s Educational Launch of Nanosatellites (ELaNa) program.
Designated ELaNa-X, the payload consists of the ExoCube, FIREBIRD-II and GRIFEX spacecraft which are deployed from three Poly Picosatellite Orbital Deployers (PPODs) attached to the Delta II upper stage.
ExoCube, also known as CP-10, is a three-unit CubeSat flown as a partnership between NASA, the California Polytechnic State University and the University of Wisconsin.
The spacecraft will be used to monitor the density of oxygen, hydrogen and helium atoms and ions, nitrogen molecules and nitrosonium ions in the upper atmosphere.
The CubeSat will use a suite of instruments called EXOS, which consists of a Neutral State Energy Angle Analyzer or NSEAA, an Ion Static Energy Analyzer or ISEAA and a Total Ion Monitor (TIM), to take measurements which its operators hope will contribute to ongoing space weather research.
Focused Investigations of Relativistic Electron Burst, Intensity, Range and Dynamics (FIREBIRD) II consists of a pair of 1.5 unit CubeSats, FIREBIRD-IIA and IIB.
The second half of a four-satellite constellation, these spacecraft will join the FIREBIRD-A and FIREBIRD-B spacecraft orbited by an Atlas V in December 2013. FIREBIRD-B remains operational, however FIREBIRD-A suffered a power system failure six weeks after launch.
The FIREBIRD program, which is funded by the National Science Foundation and the Montana Space Grant Consortium, is led by the Universities of Montana and New Hampshire and is aimed at studying disruptions known as microbursts within the Van Allen radiation belts.
The two satellites are similar to their predecessors, however with a completely new power subsystem and an additional solar cell technology demonstration experiment.
The final CubeSat, the Geostationary Coastal and Air Pollution Events Read-Out Integrated Circuit In-Flight Performance Experiment, or GRIFEX, is a technology demonstration mission which is being conducted by the Jet Propulsion Laboratory and the University of Michigan as a precursor to proposed the Geostationary Coastal and Air Pollution Events (GEO-CAPE) environmental research mission.
The satellite will take regular spectroscopic measurements of atmospheric pollution as a test of the Read-out Integrated Circuit (RIOC) being developed for the GEO-CAPE mission.
The Delta II 7320-10C launch
The rocket used was the 370th Delta II vehicle flying in the 7320-10C configuration. This is why the mission name Delta 370 is used instead of Delta II 7320-10C.
The launch, which took place from Space Launch Complex 2W at Vandenberg Air Force Base in California, will began with ignition of Delta 370’s first stage main engine and verniers three seconds in advance of liftoff.
When the countdown reached zero the three solid rocket motors ignited and the vehicle rose from the launch pad to begin its ascent into orbit. Flying downrange at an azimuth of 196 degrees Delta 370 reached the speed of sound, Mach 1, 35.8 seconds after liftoff – passing through the area of maximum dynamic pressure fourteen and a half seconds later.
The GEM-40 motors burned for the first minute and 4.7 seconds of flight before exhausting their supply of propellant. The spent boosters remained attached to the first stage for 34.3 seconds after burnout in order to ensure that debris does not hit oil rigs downrange of Vandenberg.
First stage flight concluded with Main Engine Cut-Off, or MECO, four minutes and 21.8 seconds after liftoff, when the RS-27A was shut down. The Vernier engines followed suit a few seconds later in an event designated Vernier Engine Cut-Off or VECO.
Around 6.2 seconds after MECO the spent first stage separated from the vehicle, with the second stage igniting eight seconds later.
Separation of Delta 370’s payload fairing occurred nineteen seconds into the first of two second stage burns.
Six minutes and 7.6 seconds in duration, this first burn established the vehicle in a 185 by 709 kilometer (115 by 440 miles, 99.9 by 383 nautical miles) parking orbit.
The mission then entered a coast phase lasting 40 minutes and 54.4 seconds before the AJ-10 engine restarted for its second burn. Lasting just 12.1 seconds, this second circularization burn raised the orbit’s perigee in preparation for spacecraft separation which occurred five minutes and 0.4 seconds after its conclusion.
From launch to separation, Delta 370’s mission lasted 56 minutes and 50.5 seconds.
SMAP was deployed into a near-sun-synchronous orbit with a perigee of 669.7 kilometers (416.1 miles, 361.6) and an apogee of 684.5 kilometers (425.3 miles, 369.6 nautical miles) at 98.116 degrees inclination. The spacecraft will complete its circularization, entering a final 685 kilometer orbit.
Following spacecraft separation, Delta 370’s second stage made two further burns. The first, around three quarters of an hour after spacecraft separation, lasting eight seconds to put distance between itself and SMAP’s operational orbit in preparation for CubeSat deployment.
The CubeSats were released at 100-second intervals some time after the end of the third burn – with the two FIREBIRD spacecraft being deployed together from the same PPOD.
The final burn was intended to deorbit the second stage in order to avoid leaving unnecessary debris in orbit. The burn began at 112 minutes and 30 seconds mission elapsed time, with a planned duration of about 48 seconds. About seventeen minutes after this burn ends, the spent stage reentered the atmosphere over the south Pacific.
The Delta II 7320-10C rocket
SMAP was launched on Delta 370, a Delta II rocket flying in the 7320-10C configuration.
Graphic view of a Delta II rocket split in its major parts. This is from a later mission though
This is a two stage vehicle, consisting of an Extra-Extended Long Tank Thor first stage and a Delta-K second stage. Three GEM-40 solid rocket motors are clustered around the first stage to provide additional thrust at liftoff and for the first minute of flight.
The mission was the 153rd flight of the Delta II rockets and the 130th flight of a rocket in the 7000-series vehicle, excluding the six Delta II Heavy launches.
The Extra-Extended Long Tank Thor is the final evolution of the Thor missile, which was developed as an intermediate-range ballistic missile during the 1950s, first flying from Cape Canaveral in early 1957.
The stage is powered by an RS-27A engine, burning RP-1 propellant oxidized by liquid Oxygen, with two LR101 Vernier engines used to control the rocket’s roll.
The three GEM-40 motors are solid-fuelled and designed to give the rocket extra thrust during the early stages of flight when it is at its heaviest and climbing through the thickest part of the atmosphere.
The second stage Delta-K powered by an AJ-10-118K engine is seen here hanging from a loft crane with the avionics, struts supporting the fairing, the interstage and red Helium pressure vessels
The Delta K second stage AJ-10-118K engine is restartable, allowing several burns to be made to reach a higher orbit after an initial parking orbit. The engine burns hypergolic propellant; Aerozine-50 is a mixture of hydrazine and unsymmetrical dimethylhydrazine (UDMH) in equal parts by weight. This is oxidized by dinitrogen tetroxide.
A nozzle extension will be added to the AJ-10-118K engine later on before stacking it on the 18 foot interstage that is used to house the Delta K second stage.
The rocket is completed with a three meter (10-foot) composite payload fairing which protects the SMAP vehicle during its ascent through the atmosphere.
