JPSS-1 (NOAA-20) – Delta II 7920-10C – Vandenberg SLC-2W – 18.11.2017

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Ball Aerospace‏ @BallAerospace 9 ч. назад

Built by Ball, OMPS tracks the health of the ozone layer, measuring ozone concentration in Earth's atmosphere #JPSS1 http://ow.ly/jljo30fYwUv 

omps_factsheet.pdf

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Ball Aerospace‏ @BallAerospace 9 ч. назад

Built by @Raytheon, VIIRS collects visible/IR imagery and global observations of Earth's land, oceans & atmosphere. http://ow.ly/LZhw30g9BzS 

viirs_factsheet.pdf

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Ball Aerospace‏ @BallAerospace 13 ч. назад

Today we're highlighting #JPSS1's advanced instruments, built by Ball, @HarrisCorp, @Raytheon and @NorthropGrumman. http://ow.ly/Anpy30g8doV 

http://ow.ly/Anpy30g8doV --> http://www.jpss.noaa.gov/mission_and_instruments.html

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NASA_LSP‏Подлинная учетная запись @NASA_LSP 34 мин. назад

The Flight Readiness Review for #JPSS1 on a ULA #Delta II rocket is complete. Proceeding with launch on Nov. 10. Seven days and counting!

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https://blogs.nasa.gov/jpss/2017/11/06/jpss-1-marches-toward-launch/

или

https://blogs.nasa.gov/kennedy/2017/11/06/jpss-1-marches-toward-launch/

JPSS-1 Marches Toward Launch
Anna Heiney
Posted on November 6, 2017


Packaged in a protective container, the Joint Polar Satellite System-1, or JPSS-1, spacecraft is about to be mated atop a United Launch Alliance Delta II rocket at Space Launch Complex 2 at Vandenberg Air Force Base in California. Built by Ball Aerospace and Technologies Corp. of Boulder, Colorado, JPSS is the first in a series four next-generation environmental satellites in a collaborative program between the NOAA and NASA. Liftoff is scheduled to take place fr om Vandenberg's Space Launch Complex 2. Photo credit: NASA/Billy Vinnedge

Mission and launch officials for NOAA's Joint Polar Satellite System-1 (JPSS-1) have convened today at Vandenberg Air Force Base in California in preparation for the satellite's upcoming launch aboard a United Launch Alliance Delta II rocket.

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Photo credit: NASA/Billy Vinnedge

During its time in the Astrotech Payload Processing Facility, JPSS-1 has undergone a series of routine prelaunch tests and checkouts, followed by mating to the Payload Attach Fitting and transport to the launch pad, wh ere the Delta II rocket stood already assembled. The spacecraft then was hoisted into  position atop the rocket. Also installed were a trio of Poly-Picosat Orbital Deployers, or P-PODs, which will deploy a host of small CubeSat payloads after the JPSS-1 satellite is released to begin its mission. The entire payload has been enclosed within the two-piece fairing that will protect it during the climb to space.

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NOAA Satellites‏Подлинная учетная запись @NOAASatellites 4 мин. назад

The launch of JPSS-1 has been delayed. More at: https://www.nesdis.noaa.gov/JPSS-1#LAUNCHINFO ...

https://www.nesdis.noaa.gov/JPSS-1#LAUNCHINFO

JPSS-1 Launch Delayed
Nov 6, 2017

(Vandenberg Air Force Base, Calif., Nov. 6, 2017) – The ULA Delta II rocket carrying the JPSS-1 mission for NASA and NOAA is delayed due to a faulty battery. The delay allows the team time to replace the battery on the Delta II booster. The vehicle and spacecraft remain stable. Launch of the JPSS-1 mission is scheduled for no earlier than Tuesday, Nov. 14, 2017.

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ULA‏Подлинная учетная запись @ulalaunch 3 мин. назад

Launch update: #DeltaII #JPSS-1 launch for @NASA and @NOAASatellites is delayed due to a faulty battery.

3 мин. назад

The delay allows the team time to replace the battery on the #Delta II booster. The #DeltaII rocket and #JPSS1 spacecraft remain stable.

3 мин. назад

#DeltaII #JPSS1 launch is scheduled for no earlier than Tuesday, Nov. 14, 2017.

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https://spaceflightnow.com/2017/11/06/battery-changeout-delays-weather-satellite-launch-from-california/

Battery changeout delays weather satellite launch fr om California
November 6, 2017 Stephen Clark


The JPSS 1 satellite, closed inside a transport container, arrived at the Delta 2 launch pad at Vandenberg on Oct. 24 after being fueled and prepared for flight at a nearby processing facility. Credit: NASA/Billy Vinnedge

The launch of a new U.S. weather satellite from Vandenberg Air Force Base in California has been delayed at least four days to Nov. 14, allowing time for technicians to remove and replace a faulty battery on the payload's Delta 2 rocket, United Launch Alliance said Monday.

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The satellite is set to head into an orbit circling over Earth's poles, replenishing NOAA's fleet of space-based meteorological sentinels and inaugurating a new generation of weather observatories to collect images of clouds and measurements of atmospheric temperature and moisture profiles.

The launch was set for Friday, but officials ordered a delay to swap out a faulty battery on the Delta 2 rocket set to carry the JPSS 1 satellite into orbit, ULA said in a statement Monday. The launcher and the spacecraft remain stable, the company said.

Liftoff from Space Launch Complex 2-West at Vandenberg is now targeted for no sooner than next Tuesday, Nov. 14, at 1:47 a.m. PST (4:47 a.m. EST; 0947 GMT). The launch window extends for approximately one minute, and the time remains fixed each day.

The first spacecraft in NOAA's Joint Polar Satellite System was mounted atop the Delta 2 rocket Oct. 24, and technicians have encapsulated the satellite inside the launcher's payload shroud at the seaside launch complex on California's Central Coast. The encapsulation milestone completed assembly of the 128-foot-tall (39-meter) rocket, which will take off with a boost from nine solid-fueled strap-on motors.

Officials gave approval to proceed with final launch preparations during a flight readiness review last week, but managers ordered the battery swap Monday.


File photo of a Delta 2 rocket on its launch pad at Vandenberg before a 2011 mission with the Suomi NPP weather satellite. Credit: ULA

The launch will mark the penultimate flight of a Delta 2 rocket, which entered service in 1989 and has launched numerous military, commercial and scientific missions with 151 successful flights to date. One more launch of the medium-class Delta 2 rocket is slated for next year with NASA's ICESat 2 satellite.

The nearly 5,000-pound (2,200-kilogram) JPSS 1 satellite was manufactured by Ball Aerospace and Technologies Corp. for a seven-year mission. Five instruments aboard JPSS 1 will gather data on storms, clouds, fog, smoke plumes and snow and ice cover, measure atmospheric temperature and moisture content, and study the health of Earth's ozone layer.

The measurements will aid medium-range forecasts by feeding data into numerical computer models formulating three-to-seven-day weather outlooks.

The Delta 2 rocket's upper stage will deliver the JPSS 1 satellite into a 500-mile-high (800-kilometer) orbit, wh ere it will join — and eventually replace — the predecessor Suomi NPP weather craft launched in October 2011.

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Tory Bruno‏Подлинная учетная запись @torybruno 2 ч. назад

Flight profile for the upcoming #JPSS1 launch

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http://www.ulalaunch.com/delta-ii-to-launch-jpss1.aspx

Delta II to Launch JPSS-1

[/li]
• Launch Date: Tuesday, Nov. 14, 2017
• Launch Time: 1:47 a.m. PST
  

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Harris Corporation - CrIS Temperature Animation

HarrisCorporation

Опубликовано: 19 июн. 2017 г.

Built by Harris Corporation, the Cross-track Infrared Sounder (CrIS) is one of the top contributors to weather forecast accuracy out to seven days. CrIS produces detailed three-dimensional temperature, pressure, and moisture profiles from space. Understanding how each element varies with altitude is critical to producing an accurate weather forecast. This animation of CrIS data shows temperature at different altitudes as the earth spins.

CrIS captures data across more than 2,000 "slices" of the atmosphere from near Earth's surface up to around 30 kilometers, compared to only 19 slices by previous instruments. This allows CrIS to observe the vertical structure of the atmosphere in much finer detail than ever before. The first CrIS instrument operates on board the NOAA/NASA Suomi National Polar-orbiting Partnership (Suomi NPP) satellite which launched in 2011. The second instrument is ready to launch on NOAA's JPSS-1 satellite.

(1:00)

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https://www.nasa.gov/press-release/jpss-1-now-scheduled-for-nov-14

Nov. 9, 2017
MEDIA ADVISORY M17-17

JPSS-1 Now Scheduled for Nov. 14

The Joint Polar Satellite System-1 (JPSS-1), the first in a new series of four highly advanced National Oceanic and Atmospheric Administration (NOAA) polar-orbiting satellites, is now scheduled to launch on Tuesday, Nov. 14, from Vandenberg Air Force Base, California. Liftoff aboard a United Launch Alliance Delta II rocket from Space Launch Complex 2 is targeted for 1:47 a.m. PST (4:47 a.m. EST). Launch coverage will begin on NASA Television and the agency's website at 1:15 a.m. PST.

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JPSS represents significant technological and scientific advancements in observations used for severe weather prediction and environmental monitoring. JPSS is a collaborative effort between NOAA and NASA. The JPSS system will help increase weather forecast accuracy from three to seven days.

NOAA's National Weather Service uses JPSS data as critical input for numerical forecast models, providing the basis for mid-range forecasts. These forecasts enable emergency managers to make timely decisions to protect American lives and property, including early warnings and evacuations.

JPSS satellites circle the Earth from pole-to-pole and cross the equator 14 times daily--providing full global coverage twice a day. Polar satellites are considered the backbone of the global observing system.

For more information, please visit https://www.nesdis.noaa.gov/jpss-1.
...

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L-2 Day (Sunday, Nov. 12)

Prelaunch News Conference and Science Briefing

A prelaunch status briefing will be held at 1 p.m. PST, followed by a science briefing at 2:30 p.m. PST. Both briefings will be held at Vandenberg's Press Site TV Auditorium and air live on NASA Television and the agency's website. ...

L-0 Day (Tuesday, Nov. 14)

Launch Viewing

... A post-launch news conference will not be held.

NASA TV Launch Coverage

NASA TV live coverage will begin at 1:15 a.m. PST. Coverage will conclude after CubeSat deployment. There is no planned post-launch news conference. A post-launch news release will be issued as soon as the state-of-health of the spacecraft can be verified. For NASA TV downlink information, schedules and links to streaming video, visit http://www.nasa.gov/ntv.
...
NASA Web Prelaunch and Launch Coverage

Prelaunch and launch day coverage of the JPSS-1 flight will be available on http://www.nasa.gov.  Coverage will include live streaming and blog updates beginning at 1:15 a.m. PST as the countdown milestones occur. You can follow countdown coverage on our launch blog at https://blogs.nasa.gov/jpss.

Спойлер

Learn more about the JPSS-1 mission by visiting:

www.jpss.noaa.gov

https://www.nesdis.noaa.gov/jpss-1

Join the conversation and follow the JPSS-1 mission on social media by using Twitter and Facebook at:

https://twitter.com/NOAASatellites

https://www.facebook.com/NOAANESDIS/

- end -

Tori McLendon
 Kennedy Space Center, Florida
 321-867-2468
tori.n.mclendon@nasa.gov

Steve Cole
 Headquarters, Washington
 202-358-0918
stephen.e.cole@nasa.gov

John Leslie
 NOAA, Washington
 301-713-0214
john.leslie@noaa.gov

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Last Updated: Nov. 9, 2017
Editor: Kay Grinter

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http://spaceflight101.com/jpss-1/mirata/

MiRaTA Satellite Overview

MiRaTA (Microwave Radiometer Technology Acceleration) is an Earth observation technology demonstration CubeSat mission developed at MIT Lincoln Lab to test a miniaturized multi-band microwave radiometer and compact GPS occultation payload that could build the foundation of a future CubeSat constellation for the collection of global weather data at very rapid revisit intervals.

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Photo: MIT/LL

The MiRaTA project is part of NASA's InVEST (In-Space Validation of Earth Science Technologies) Program aiming to develop and test small instruments and remote-sensing subsystems that can advance the current state of technology to enable relevant Earth science measurements via smaller satellite platforms. MiRaTA will validate a new ultra-compact and low-power microwave radiometer for the collection of atmospheric profiles, a GPS occultation receiver and antenna for tropospheric radio occultation sounding and a novel approach to radiometer calibration using GPS radio occultation measurements. The goal is to advance the technology readiness level of both components fr om TRL 5 to 7 at the conclusion of the mission.


Image: MIT/LL

MiRaTA is the first ever implementation of co-located radiometer and occultation sounding and the first CubeSat implementation of temperature/humidity radiometric sounding and occultation sounding. The mission will not only validate multiple subsystem technologies but also demonstrate a new sensing technique that could dramatically enhance the capabilities of future weather and climate observatories. Shrinking an operational radiometer and GPS RO system to fit onto a nanosatellite platform furthermore enables new architectural approaches for low-cost, high-return missions in the field of operational meteorology.

The calibration approach developed for MiRaTA calls for a pitch up/down maneuver once per orbit to complete a radiometer pass and GPS occultation across overlapping volumes of the atmosphere through Earth's limb where sensitivity, calibration, and dynamic range are optimal. For an operational mission, this type of measurement will allow for an intra-satellite calibration approach no-longer relying on blackbodies and other calibration sources. For MiRaTA, concurrent radiometer and GPS RO data will be compared with ground-based radiosondes and other satellite observations to validate the measurements.


Image: MIT/LL

MiRaTA is a three-unit CubeSat, 10 x 10 x 34 centimeters in size with a mass of under 4.5 Kilograms, using a platform that builds on the MicroMAS (Micro-sized Microwave Atmospheric Satellite) though with a number of simplifications, e.g. eliminating active scanning mechanisms and reducing deployable structures to a pair of solar panels and a simple tape-spring UHF communications antenna. Per the instrument requirements, the radiometer resides on the nadir-facing panel of the satellite while the GPS antennas face toward zenith.

Electrical power is provided by two double deployed solar panels that are hinged on the zenith-pointed satellite panel and feed power to a 20 Watt-hour Li-Ion battery assembly. An EPS card conditions the power buses at 3.3, 5 and 12 Volts and provides bus protection with the overall EPS design calling for a typical energy requirement per orbit around 8.3 Watts and a 20% design margin at satellite end of life. The two solar panels can deliver a peak power of 24.8 Watts.


MicroMAS Block Diagram, much of it used on MiRaTA – Image: MIT/LL

The attitude control system of the satellite consists of reaction wheels that are used to stabilize the 3U satellite bus and keep it in an Earth-pointing attitude for normal data collection and facilitate the once-per-orbit pitch maneuver for instrument cross-calibration.

Attitude determination is provided by a series of sensors – an Inertial Measurement Unit and magnetometer are used in the initial attitude acquisition and de-tumble before the satellite begins processing sun sensor data in a TRIAD navigation method with Earth horizon sensors in use for verification of the correct attitude for science operations.

Attitude actuation uses a combination of torque rods and reaction wheels integrated within the MAI-400 assembly provided by Maryland Aerospace. In addition to two Earth horizon sensors within MAI-400, the MiRaTA satellite hosts a third sensor to assist in the pitch-up maneuver.

The satellite motherboard is a standard CubeSat board provided by Pumpkin using a PIC24 microcontroller as flight computer that runs on Pumpkin's Salvo Real Time Operating System. The satellite uses CubeSat-Kit interfaces for the reaction wheels, communication system and mass memory while the PCB is used for the attitude sensors, motor controller and payload. Payload Data is stored in an SD card.


Image: MIT/LL

Communications are accomplished with a half-duplex L-3 Communications Cadet UHF Nanosatellite radio. Operating at a frequency of 450MHz for uplink, the system achieves a data rate of 9.6kbit/s with GFSK modulation and 19.2kbit/s with FEC. Downlink uses the 468MHz UHF frequency for low data volumes as the payload generates a data volume of about 19 kbit/s when operating.

The MiRaTA nanosatellite hosts two complete instrument systems: MWR – the Microwave Radiometer, a tri-band atmospheric sounder, and CTAGS – the Compact TEC (Total Electron Count)/Atmosphere GPS Sensor. Both are operated to allow cross-comparison and cross-calibration to validate a new approach for potential future exploitation.

A microwave radiometer observes the radiance of the atmosphere at microwave wavelengths that are detected by an antenna which uses support electronics to amplify and record the signals of given frequency bands. The detected power level for each frequency band is used to generate temperature and moisture profiles through the various regions of the atmosphere. Elements present in the atmosphere have different absorption spectra, allowing radiometers to observe different atmospheric constituents.


MWR Instrument – Image: MIT/LL


MWR Electronics Block Diagram – Image: MIT/LL

The MWR instrument is a passive microwave radiometer collecting co-registered observations over three frequency bands via two radiometer subsystems. Two scalar feed horns illuminate an offset parabolic reflector that yields pitch-plane-aligned beam widths of 1.25 and 5.0° for the G- and V-Band systems, respectively with a beam efficiency higher than 95. The system has been designed with scalability in mind, allowing the aperture to be enlarged for a 6U CubeSat mission

The first subsystems hosts the systems of the 52-58 GHz V-Band channel, comprising the V-Band front end, low-noise amplifier, mixer coupled to a 81.47 GHz Local Oscillator, intermediate frequency amplifier and a compact back-end to provide six channels with temperature weighting functions approximately uniformly distributed over the troposphere and lower stratosphere up to an altitude of 20 Kilometers.

The second subsystem builds the G-Band sensing system covering a pair of channels at 175-191 and 206-208 GHz with a front end operating between 175.3 and 208.4 GHz and subharmonic detection chain with a 91 GHz Local Oscillator and conventional intermediate frequency spectrometer and back end. Both MWR subsystems share a common redundant dielectric resonator oscillator with multiplication stages in each of the local chains to match the required frequencies.

The addition of the CTAGS instrument allows MiRaTA to combine the benefits of passive sounding and GPS Radio Occultation measurements to achieve highly accurate calibration with dense geospatial sampling. Benefits of using GPS RO are primarily found in the accuracy of measurements which easily achieves 0.1 K for vertical temperature profiles in the upper troposphere and lower stratosphere; however, GPSRO measurements have sparse geospatial coverage with daily measurements ranging between a few hundred and a few thousand while traditional microwave radiometers can conduct continuous measurements and easily achieve global coverage.


GPS Occultation Measurement – Image: Tyvak/NASA

The issue that arises for microwave instruments is an elaborate calibration requirement to ensure radiometric accuracy which, for typical missions, relies on internal blackbodies as a hot reference point and soundings of cold space as cold reference as well as solar irradiance and lunar calibration measurements. The combination of a radiometer and GPSRO instrument will allow a two-way calibration without Internal Calibration Targets which often drive the instrument design and add mass to the sensors.

GNSS occultation measurements for atmospheric and ionospheric measurements is a proven method for the acquisition of temperature, pressure and humidity profiles from high altitude to near-ground level. The science and methodology behind GNSS occultation measurements is well established and has been employed for many scientific projects as well as operational meteorology systems.

GPS operates a constellation of approximately 30 active satellites in six orbital planes, 20,000 Kilometers in altitude, transmitting different L-Band signals used for navigation and precise timing applications as well as a wide variety of other applications including meteorology. At least four satellites are simultaneously visible from any position on Earth, an observer in Low Earth Orbit will usually see 12 satellites at any time.


GPS Occultation – Image: Nanyang Technological University

Occultation measurements make use of the fact that Earth's atmosphere can alter the properties of a GPS signal to extract relevant meteorological parameters. The measurement is done by a satellite that sees its line of sight to a GPS satellite penetrate Earth's atmosphere as the GPS satellite either rises for sets from the receiver's vantage point.

CTAGS flown on MiRaTA is based on the successful CTECS (Compact Total Electron Content Sensor) hosted by the OSIRIS-3U CubeSat. The advanced system employs a more compact and capable GPS receiver and a high-gain patch antenna array to extend measurements from the ionosphere into the lower atmosphere, allowing CTAGS to collect ionospheric and atmospheric measurements down to at least 20 Kilometers in altitude. The instrument consists of four primary components: a multi-element antenna array, single patch antenna for precise orbit determination, low-noise amplification stage and a NovaTel OEM628 GPS receiver.


GPS Receiver & Patch Antenna Segment – Image: MIT/LL

CTAGS combines multiple heritage CTECS antenna elements and the higher gain allows the instrument to remain locked on GPS satellites as they set behind the Earth's dense atmospheric layers for low-altitude measurements. The receiver can track up to 60 dual-frequency satellites at any time, allowing for simultaneous atmospheric, ionospheric, and navigation observations, utilizing the L1, L2 and L2c signals for refraction measurements from which the total electron content/atmospheric properties and their vertical profiles can be extracted. CTAGS makes measurements of the L1/L2 pseudorange and L1/L2/L2c phase, taking advantage of the satellite's relatively low orbit to measure a large amount of density above the satellite.

The calibration of radiometers has proven to be challenging even for flagship missions like the ATMS (Advanced Technology Microwave Sounder) on the NPP and JPSS satellites and the GMI (Microwave Imager) on GPM (Global Precipitation Mission). Research has shown that biases, despite high-fidelity calibration approaches, may be as high as 2 Kelvin.


Image: MIT/LL

MiRaTA proposes a two-pronged calibration approach that promises much greater accuracy while reducing complexity and instrument size through the use of the combination of a noise diode for frequent calibration of the radiometer and the less-frequent GPSRO measurement as a through-the-antenna end-to-end calibration of the instrument and as cross-check for the noise diode to calibrate its accuracy and stability.

Noise diodes are used in the radiometer front end to inject a calibration signal into the radiometer with relatively low loss, though susceptible to signal drifts and not representing a complete through-the-antenna calibration. Furthermore, integrating noise diodes into the signal path requires a switch which adds signal losses that can be of significance when aiming for large-area coverage over short time scales.


MiRaTA Operational Sequence – Image: MIT/LL

Operationally, the MiRaTA concept will be realized by slewing the spacecraft from a radiometer-nadir attitude to a 90-105-degree pitch angle and back so that the radiometer and GPSRO instrument can sound the same area of Earth's limb with very little time difference. The sequence will take between 22 and 32 minutes to complete and requires at least one or two GPS satellites to set behind the atmosphere, as seen by the CTAGS instrument.

The mission ground software is in charge of computing favorable opportunities by cross checking the satellite's orbital parameters, CTAGS and MWR look angles and relative geometry with GPS satellites to isolate opportunities wh ere the GPSRO and MWR fields overlap sufficiently – also taking into account onboard resources like power and reaction wheel saturation. These are then uplinked to the satellite as time-tagged command sequences and executed autonomously. Mission simulations predict two to three favorable opportunities to be available per day with overlaps of five to seven minutes.

The MiRaTA mission aims to collect at least 100 concurrent GPSRO and MWR measurements with a radiometric accuracy achieved through the new cross-calibration process matching that of the Joint Polar Satellite System (1.5K rms) down to 20 Kilometers (requirement) or 10 Kilometers (goal).

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http://spaceflight101.com/jpss-1/buccaneer-rrm/

Buccaneer RRM

Project Buccaneer is a joint initiative of the University of New South Wales and the Australian Defence Science and Technology Group within the Department of Defence dedicated to the calibration of the Jindalee over-the-horizon radar network.

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Image: DSTO

The Jindalee Operational Radar Network (JORN) is used by the Australian Defence Forces to observe air and sea activity north of Australia to distances of up to 4,000 Kilometers – including Java, Papua New Guinea and the Solomon Islands.

In practice, the radar has shown to be even more sensitive, capable of observing a single-engine Cessna taking off and landing at a distance of 2,600 Kilometers and observations of missile launches more than 5,500 Kilometers away have proven feasible. Further improving the system's sensitivity by a factor of ten is underway and will employ a space-based mission to conduct high-fidelity calibration.


JORN Transmission Station – Photo: Australian Air Force


Image: Lockheed Martin

The A$2 billion system consists of two active radar stations in Queensland with 90° coverage and Western Australia with 180° coverage to form an overlapping coverage cone to the north, a control center in South Australia, seven transponders and a dozen vertical ionosondes to deliver ionospheric measurements, and a research radar station in Northern Territory. JORN can be temporarily expanded to three stations using the Alice Springs radar.

Signals sent by the transmitters are bounced off by the ionosphere and the echoes recorded by receiving stations at sufficient distance to the transmitter to avoid interference. Moving objects are detected using the Doppler principle.

JORN uses frequencies of 5 to 30 MHz, much lower than conventional civilian and military microwave radars. To achieve high sensitivity in changing ionospheric conditions, the ionosonde network operated by JORN, plus additional DSTO stations, generate complete ionospheric maps at a refresh rate of under four minutes.

Project Buccaneer has the overall goal of deploying an advanced high-frequency receiver into orbit to provide performance calibration for JORN at different distances and varying ionospheric conditions to help improve the system's sensitivity. Given the complexities involved in a space mission, the project was baselined for a pair of flights – the Buccaneer Risk Mitigation Mission RRM and the operational Buccaneer flight around one year later. RRM primarily deals with the deployment and stability of the radar antenna.


Buccaneer Architecture – Image: DSTO


Photo: DSTO


Image: DSTO

Both Buccaneer satellite use a commercially-available 3U Satellite Platform (10 x 10 x 34 centimeters) from Pumpkin Inc. to provide electrical power generation via body-mounted solar cells and two deployable solar arrays, attitude determination and control via magnetic torquers with sufficient pointing control for the experiment, and housekeeping and payload communications.

The payload of the satellites is a high-frequency receiver optimized for the JORN frequencies and a HF antenna deploying from a purpose-built mechanism on the satellite's forward panel.

The bowtie antenna consists of commercially available spring steel measuring tape, allowing the individual antenna segments to be wound up for launch and deploy to their full extension using a self-driving deployment system to unwind the antenna arms. Each antenna section measures 1.73 meters from its tip to the satellite body and 3.46 from tip to tip, exceeding the satellite's body length by a factor of ten.

Extensive analysis was performed into the stability of the antenna system given the very thin and flexible nature of the material which can not support its own weight in a gravity environment but will be able to remain stable when being deployed in space. Analysis focused on a buckling failure of the antenna even in the small loads present in Low Earth Orbit due to aerodynamic drag in the upper atmosphere, solar radiation pressure or internal loads on the satellite.


Image: DSTO


BRRM Antenna Assembly – Image: DSTO

Chosen for Buccaneer is a commercial measuring tape 0.1 mm thick with a flattened width of 19 mm, a broadened cross section of 18 mm and a narrow-cross section of 2.5 mm when in its rigidized state. When deployed, the antenna will be in a stable equilibrium using the manufactured curvature of the tape to provide the stiffness needed to remain in a deployed state. For deployment, the strain energy within the tape will be used to deploy the antenna to full length with burn wires holding the system in its compressed state until deployment is commanded.

The Buccaneer RRM mission will employ a flight-like antenna subsystem but substitutes the HF receiver with an on-board camera to document the antenna deployment and its stability in the actual flight environment to eliminate risk for the operational mission. The flight will also provide a platform to conduct photometric experiments with the Falcon Telescope Network operated by the University of New South Wales for astrodynamics assessments.

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http://spaceflight101.com/jpss-1/jpss-1-secondary-payloads/

JPSS-1 Mission – 1U CubeSat Secondary Payloads

MakerSat 0

Спойлер

MakerSat 0 is a 1U CubeSat designed at Northwest Nazarene University for a technology demonstration of a fully 3D printed satellite structure with a common power, control, computing, and radio communication architecture connected to four science boards that integrate into the platform in a modular manner to allow it to host payloads fr om different operators. Two demonstration launches are planned to qualify the MakerSat for operational use in hosting single-board payloads fr om commercial and educational operators.


Photo: Northwest Nazarene University

Extending the MakerSat concept, designers foresee a capability of launching CubeSat components to the Space Station, manufacturing structural frames as needed using 3D printing and having ISS crew members assemble modular platform components and integrate them with single- or multi-board payloads on ISS for deployment.


Image: Northwest Nazarene University

The MakerSat 0 satellite hosts science payloads looking into the degradation of different additively-manufactured polymers in orbit as a result of mass loss due to atomic oxygen, UV radiation, ionizing radiation and outgassing.

Structurally, the MakerSat design employs four polyetherimide (PEI) 3D printed rails that slide and snap together with six Printed Circuit Boards without the use of any tools, allowing the satellite to be put together in a period of minutes, also avoiding any free-floating small components that could pose a danger for in-space assembly of the satellite. Once the six PCBs are ingrated, the satellite platform can be powered up via a USB port and go through checkouts prior to deployment.

MakerSat 0 was manufactured by a Made In Space Additive Manufacturing Facility similar to that on the Space Station while MakerSat 1 will demonstrate the ISS-based assembly process.

The MakerSat platform comprises a central Hub that interfaces with the four Science Boards which reside on the back of the four solar side panels with the Hub itself facilitated on the bottom panel and the combined EPS, Comms and Onboard Computer package on the topmost panel. The Hub hosts a microcontroller to build the central interface for all CubeSat subsystems and also facilitates an Inertial Measurement Unit to provide attitude data in addition to the solar cells on all outer panels that can be used to determine the solar vector. The solar boards include cut-outs for any external sensors of the payloads, e.g. cameras.


MakerSat Structure – Image: Northwest Nazarene University

The individual components (Hub, EPS/COMMS/OBC, solar panels and science boards are pre-assembled on Earth and fly to ISS in a low-vibration environment, protected by packaging inside an ISS cargo vehicle.

The central Hub concept was chosen to provide a single connection point for all satellite components and thus reduce the probability of assembly errors. It also allows for equal access to the satellite's resources for all four science payloads.

The Hub provides sequencing, control and data return to all four science boards, operated in a peer-to-peer design with the OBC/EPS wh ere the Hub is in charge of commanding the EPS to cycle power to the payloads according to their duty cycle. The Hub also offers additional computing power and memory for the science boards and collects all science data from the boards and prepares it for transmission to Earth via the COMMS section.

An 8-bit PIC microcontroller with extensive flight heritage serves as onboard computer and handles all payload operations as well as science board commanding. Power is generated by 28% Ultra-Triple-Junction solar cells with two cells in series per solar panel to deliver 4.7 V, 2 W from each board under full illumination. Four Li-Polymer batteries with a 4.4-Ah capacity at 7.4 V provide power storage. Attitude stabilization is accomplished with a simple solution using a permanent magnet to keep the satellite aligned with Earth's magnetic field.


MakerSat Hub – Image: Northwest Nazarene University

Communications are handled by an EyeStar Simplex radio to communicate through the GlobalStar satellite constellation and provide a 24/7 data downlink capability with near global coverage via 14 ground gateways from wh ere the downlinked data is uploaded to the Internet for access by the science teams. The EyeStar radio will transmit 18-byte satellite health packets with telemetry values such as temperature and bus voltage and 39-byte science data packets containing data from the science boards. The total data volume per day is expected to be around 50 to 100 kbyte/day, limited by the power budget and data rate costs. The Simplex radio will also allow insight into satellite status via a beacon signal should the Hub or combined OBC/EPS suffer a failure.

The science boards can either use I²C or SPI interfaces to communicate with the Hub and MakerSat also supports General Purpose Input/Output (GPIO) digital logic lines and serial communications. The Hub, based on the duty cycles for each science board, will cycle the 3.3 V power supplies of each of the boards to switch it on/off and it also isolates the I²C and SPI lines of boards that are inactive.

MakerSat 0 hosts two science boards for the Polymer Loss Experiment, an Imaging Board with an Earth observation camera, and a science board designed and built at Caldwell High School, Idaho.


Polymer Loss Experiment – Image: Northwest Nazarene University

The Imaging Board Integrates a Commercial Off-The-Shelf imaging sensor integrated in the science board and viewing outside the satellite through a 32 x 9-millimeter port in the outer solar array panel. Images taken by the camera will be analyzed on board to discard any images that only show dark space and compression is completed using lightweight algorithms given the very limited memory on the satellite.

The Polymer Loss Experiment will subject samples of 3D printed polymers to mass loss measurements at regular intervals to track how the space environment (oxygen radicals, UV radiation, ionizing radiation, vacuum outgassing) degrades different polymer materials. The mass of the test objects is measured by placing the 3D printed polymers at the end of piezo-electric cantilevers and measuring the change in resonant vibrational frequency of each cantilever from which the mass at the end of the beam can be calculated.

MakerSat 0 features a slightly different design than the operational MakerSats due to it being launched conventionally and having to withstand the launch G and vibration environment. Therefore, it uses a more rigid structure to survive the launch forces but retains the electronics boards from the operational satellites.

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RadFxSat

Спойлер

RadFxSat (Radiation Effects Satellite) or Fox 1B is a joint 1U CubeSat Mission by AMSAT and Vanderbilt University, combining an amateur communications payload by AMSAT and a technology demonstration payload from Vanderbilt to explore the effect of space radiation on electronics.


Photo: AMSAT

The Fox 1B designation is for AMSAT's payload on the satellite which is identical to that on the Fox 1A satellite launched as a secondary payload on an Atlas V in 2015. It comprises an FM analog transponder for digital data rates of up to 9600 bps, serving in a U/v repeater function for amateur radio users. The satellite hosts a two-meter and 70-centimeter whip antenna.

"Uplink for Fox-1B is 435.250 MHz FM (67.0 Hz CTCSS); Downlink is 145.960 MHz FM (with subaudible slow speed telemetry data); 145.960 MHz 9600 baud FSK data." (AMSAT)

The Vanderbilt payload is designed to advance the understanding of the effects of space radiation on electronic components, demonstrating an on-orbit platform for radiation qualification of components for space flight and collecting radiation data to validate computer models used to predict radiation tolerance of semiconductor manufacturing processes.

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Eagle Sat

Спойлер

EagleSat is a 1U (10 x 10 x 10 centimeter) CubeSat designed, built, and operated by students at Embry-Riddle Aeronautical University in a project aimed to bring together all engineering disciplines as well as business majors for hands-on experience in the conduct of a satellite mission. The technology demonstration aspect of the mission is looking into space-induced bit flipping in various types of memory as a result of radiation.


Photo: Embry-Riddle Aeronautical University

The Eagle Sat Project was selected to fly under NASA's ELaNa program in 2013 as a primarily student-run extracurricular project. The satellite uses a conventional 1U CubeSat design with six stacked circuit boards inside the satellite hosting the various subsystems while the external side panels facilitate solar cells for power generation. The power system employs super capacitors for energy storage and communications are provided via UHF at 436MHz.

EagleSat hosts a pair of payloads, a GPS receiver to track the decay of the cube's orbit to provide information for decay and re-entry modeling. The primary science payload is a RAM memory stack to be monitored for space-induced bit flips with a solid state radiation detector providing information on the radiation environment experienced by the satellite.

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NOTMAR, зоны A и B

NAVAREA XII 499/2017 (18,83)

EASTERN NORTH PACIFIC.
CALIFORNIA.
1. HAZARDOUS OPERATIONS, ROCKET LAUNCHING
   140917Z TO 141027Z NOV, ALTERNATE 0917Z TO 1027Z
   DAILY 15 AND 16 NOV IN AREAS BOUND BY:
   A. 30-45N 121-30W, 30-49N 121-53W,
   31-44N 121-39W, 31-39N 121-15W.
   B. 06-53N 126-21W, 07-13N 127-53W,
   13-21N 126-35W, 13-01N 125-01W.
2. CANCEL NAVAREA XII 497/17.
3. CANCEL THIS MSG 161127Z NOV 17.

( 072029Z NOV 2017 )

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Зоны A, B
 

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NOTMAR, зона С

HYDROPAC 3841/2017 (83)

SOUTH PACIFIC.
DNC 06.
1. HAZARDOUS OPERATIONS, SPACE DEBRIS
   141138Z TO 141208Z NOV, ALTERNATE
   1138Z TO 1208Z DAILY 15 AND 16 NOV
   IN AREA BOUND BY
   50-00S 166-00W, 50-00S 168-00W,
   32-00S 163-00W, 32-00S 161-00W.
2. CANCEL HYDROPAC 3810/17.
3. CANCEL THIS MSG 161308Z NOV 17.

( 072032Z NOV 2017 )

NOTAM, зона С

NZZO

B5593/17 - TEMPO DANGER AREA NZD028 (EAST AUCKLAND OCEANIC FIR) IS PRESCRIBED
AS FLW:
ALL THAT AIRSPACE BOUNDED BY A LINE JOINING
S 32 00, W 161 00
S 50 00, W 166 00
S 50 00, W 168 00
S 32 00, W 163 00
S 32 00, W 161 00.
ACTIVITY: SPACE DEBRIS RETURN
USER AGENCY: FOREIGN SPACE AGENCY
PRESCRIBED PURSUANT TO CIVIL AVIATION RULE PART 71 UNDER A DELEGATED
AUTHORITY ISSUED BY THE DIRECTOR OF CIVIL AVIATION. SFC - FL999, 14 NOV 11:30
2017 UNTIL 14 NOV 12:15 2017. CREATED: 07 NOV 21:35 2017

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Общая картина полей падения отделяемых частей РН