BioSentinel nanosatellite on EM-1
BioSentinel is a 6U nanosatellite under development at NASA/ARC (Ames Research Center). The mission was selected in 2013 as one of the secondary payloads to fly the nanosatellite as a secondary payload aboard NASA's SLS (Space Launch System) Exploration Mission-1 (EM- 1), scheduled for launch in 2019/20. For the first time in over forty years, direct experimental data from biological studies beyond LEO (Low Earth Orbit) will be obtained during BioSentinel's 12 to 18-month mission. BioSentinel will measure the damage and repair of DNA in a biological organism and compare that to information from onboard physical radiation sensors. This data will be available for validation of existing models and for extrapolation to humans. 1) 2)
BioSentinel project objectives: 3)
• The AES (Advanced Exploration Systems) Program Office selected BioSentinelto fly on the SLS EM-1 (Exploration Mission) as a secondary payload
- Payload selected to help fill Strategic Knowledge Gaps in Radiation effects on Biology
- Current EM-1 Launch Readiness Date (LRD): 2019/2020
• Key BioSentinel project objectives
- Develop a deep space nanosatellite capability
- Develop a radiation biosensoruseful for other missions
- Define & validate SLS secondary payload interfaces and accommodationsfor a biological payload
• Collaborate with two other AES selected missions (non-biological) for EM-1
- NEA Scout (Near Earth Asteroid) Scout (MSFC)
- Lunar Flashlight (JPL).
BioSentinel will conduct the first study of biological response to space radiation outside LEO in over 40 years. BioSentinel will address strategic knowledge gaps related to the biological effects of space radiation and will provide an adaptable platform to perform human-relevant measurements in multiple space environments in the future. Yeast is the ideal organism for this mission because of its spaceflight heritage, it is highly capable of repairing DSBs (Double Strand Breaks), and it can be stored in stasis for a long period of time. Moreover, the DSB repair mechanisms in yeast are well studied and highly similar to those in human cells. BioSentinel's results will be critical for improving interpretation of the effects of space radiation exposure, and for reducing the risk associated with long-term human exploration.
Figure 1: The goal is to enable NASA's long-term human exploration missions and also benefit life on Earth 4)
The BioSentinel experiment will use the organism Saccharomyces cerevisiae (yeast) to report DNA DSB (Double-Strand-Break) events that result from space radiation. DSB repair exhibits striking conservation of repair proteins from yeast to humans. The flight strain will include engineered genetic defects that prevent growth and division until a radiation-induced DSB activates the yeast's DNA repair mechanisms. The triggered culture growth and metabolic activity directly indicate a DSB and its repair. The yeast will be carried in the dry state in independent microwells with support electronics. The measurement subsystem will sequentially activate and monitor wells, optically tracking cell growth and metabolism. BioSentinel will also include TimePix radiation sensors implemented by the RadWorks group of NASA/JSC (Johnson Space Center). Dose and LET (Linear Energy Transfer) data will be compared directly to the rate of DSB-and-repair events measured by the S. cerevisiae (yeast) biosentinels.
BioSentinel will mature nanosatellite technologies to include: deep space communications and navigation, autonomous attitude control and momentum management, and micropropulsion systems to provide an adaptable nanosatellite platform for deep space uses. 5)
The BioSentinel spacecraft is being implemented using lessons learned from both the NASA/ARC nanosatellite line as well as from the LADEE (Lunar Atmosphere and Dust Environment Explorer) mission.
The use of small spacecraft in interplanetary missions promises to reduce mission costs and allow more planetary science missions to be conducted. One critical technology to enable these missions are miniaturized propulsion systems, capable of both translational maneuvers and attitude control.
Figure 2: Illustration of the deployed BioSentinel 6U nanosatellite (image credit: NASA/ARC)
Figure 3: Physical overview of the BioSentinel freeflyer spacecraft elemets (image credit: NASA)
RF communications: 6)
Higher data rate CubeSats are transitioning away from Amateur Radio bands to higher frequency bands. A high-level communication architecture for future space-to-ground CubeSat communication was proposed within NASA/GSFC ( Goddard Space Flight Center). This architecture addresses CubeSat direct-to-ground communication, CubeSat to Tracking Data Relay Satellite System (TDRSS) communication, CubeSat constellation with Mothership direct-to-ground communication, and CubeSat Constellation with Mothership communication through KSA (K-Band Single Access). A study has been performed to explore this communication architecture, through simulations, analyses, and identifying technologies, to develop the optimum communication concepts for CubeSat communications. The RF communications network is described in the Ground Segment chapter.
Cold Gas Thrusters: 7)
A cold gas thruster is a propulsion system in which the propellant does not undergo combustion or electromagnetic acceleration. The propellant is held under pressure in the thruster and released through a nozzle to generate thrust. Such systems have lower specific impulse than combustion-based thrusters or electric thrusters, meaning that they generate less total impulse per unit mass of propellant. However, cold gas thrusters may use inert propellants, which reduces handling risks, and have relatively low power consumption compared to electric thrusters.
Cold gas thrusters have been previously used on CubeSats. The first CubeSat-sized spacecraft known to employ a cold gas thruster in space was the MEPSI (Microelectromechanical System-based PICOSAT Inspector ). This mission involved a pair of spacecraft, deployed in 2006, one of which was equipped with a miniature cold gas thruster. The thruster was used to maneuver the first spacecraft relative to the second spacecraft, and achieved a total ΔV of 0.4 m/s. In 2014, a pair of cold gas attitude control thrusters were developed for the INSPIRE mission, a pair of 3U CubeSats developed by the Jet Propulsion Laboratory to demonstrate small satellite capabilities beyond Earth orbit. In 2015, a cold gas thruster was demonstrated in Low Earth Orbit on the POPSAT-HIP1 spacecraft. This propulsion system used pressurized Argon to provide between 2.25 and 3 m/s of ΔV. The BioSentinel thruster draws heavily on heritage from the INSPIRE attitude control thrusters, and employs the same solenoid valves and propellant.
Design overview: The structure of the thruster consists of a 3D-printed component and five steel manifolds attached to the printed component and sealed with O-rings. The 3D-printed structure is printed using the SLA (Selective Laser Ablation) technique, and is made from Accura Bluestone. Bluestone is a ceramic-like composite with a relatively high ultimate tensile strength of 66 MPa. The system is shown in Figure 4.
The printed structure contains two propellant tanks, the main tank and the plenum, as well as the seven nozzles and the propellant feed pipes. The main tank stores the majority of the propellant (up to 200 gram) as a saturated liquid-vapor mixture, while the plenum stores a smaller amount (up to 2 gram) as a vapor alone. The nozzles are supplied directly from the plenum. This arrangement allows the pressure behind the nozzles to be more precisely controlled, and prevents liquid from entering any of the nozzles.
Eight miniature solenoid valves are used to control propellant flow. One valve controls flow from the main tank into the plenum, and each of the other seven valves control flow from the plenum to one of the seven nozzles. These valves are attached with compression fittings to two of the steel manifolds.
Figure 5: Block diagram of propellant tanks, solenoid valves, pipes, and nozzles (image credit: Georgia Tech)
Electronics: The thruster is equipped with two pressure transducers and two thermistors, which are threaded into the steel manifolds. One pair of sensors is allocated to each propellant tank, so the pressure and temperature of each tank is sampled periodically. The thruster has two printed circuit boards, attached to the two valve manifolds. Each manifold holds four valves, and the electrical leads of these valves are soldered directly into plated holes in the circuits boards. These boards contain timing circuits to supply the correct voltage to the valves over very precise intervals.
One of the circuit boards also contains an LPC1549 microcontroller, which operates the thruster. The microcontroller operates the power switches that feed the solenoid valves, reads data from the sensors, and communicates with the BioSentinel flight computer over a serial port.
Figure 6: Circuit board, mounted to the thruster. The microcontroller is located in the RF shield (left, cover removed), image credit: Georgia Tech)
Thruster concept of operations: Upon deployment from the launch vehicle, the main tank will contain the entire propellant load, and the plenum will be at vacuum. Prior to thruster operation, the plenum will be filled from the main tank until it reaches 95% of the main tank pressure. As the thruster is operated, the plenum pressure will fall as propellant is consumed. When the plenum pressure falls below a user-defined threshold, the thruster ceases operations and refills the plenum from the main tank. This threshold is nominally set to 80% of the current main tank pressure. Once the plenum is refilled, the thruster resumes normal operations. Approximately two seconds of continuous firing is needed to reduce the pressure from 95% to 80%, and approximately three seconds is needed to refill the plenum back to 95%, when operating at 25ºC.
An engineering unit has been built and tested on a custom micropropulsion test stand in the Georgia Tech (Georgia Institute of Technology) Space Systems Design Lab.
Figure 7: Artist's rendition of the deployed BioSentinel spacecraft aiming to investigate the pernicious effects of deep-space radiation (image cridit: NASA)
Launch: The launch of the uncrewed EM-1(Exploration Mission-1) is in December 2019 (this is NASA's official launch date, but it is expected to be delayed with a launch in 2020) on the maiden test flight of NASA's SLS (Space Launch System). The launch will be from Launch Complex 39-B at the Kennedy Space Center, Cape Canaveral, FL. 8)
Secondary payloads of Orion/EM-1
The first flight of NASA's new rocket, SLS ( Space Launch System), will carry 13 CubeSats/Nanosatellites to test innovative ideas along with an uncrewed Orion spacecraft in 2020. These small satellite secondary payloads will carry science and technology investigations to help pave the way for future human exploration in deep space, including the journey to Mars. SLS' first flight, referred to as EM-1 (Exploration Mission-1 ), provides the rare opportunity for these small experiments to reach deep space destinations, as most launch opportunities for CubeSats are limited to low-Earth orbit. 9) 10)
The secondary payloads, 13 CubeSats, were selected through a series of announcements of flight opportunities, a NASA challenge and negotiations with NASA's international partners.
All the CubeSats will ride to space inside the OSA (Orion Stage Adapter), which sits between the ICPS (Interim Cryogenic Propulsion Stage) and Orion (Figure 8). The CubeSats will be deployed following Orion separation from the upper stage and once Orion is a safe distance away.
The SPIE ( Spacecraft and Payload Integration and Evolution) office is located at NASA/MSFC (Marshall Space Flight Center) in Huntsville, Alabama, which handles integration of the secondary payloads.
These small satellites are designed to be efficient and versatile—at no heavier than 14 kg, they are each about the size of a boot box, and do not require any extra power from the rocket to function. The science and technology experiments enabled by these small satellites may enhance our understanding of the deep space environment, expand our knowledge of the moon, and demonstrate technology that could open up possibilities for future missions. 13)
A key requirement imposed on the EM-1 secondary payload developers is that the smallsats do not interfere with Orion, SLS or the primary mission objectives. To meet this requirement, payload developers must take part in a series of safety reviews with the SLS Program's Spacecraft Payload Integration & Evolution (SPIE) organization, which is responsible for the Block 1 upper stage, adapters and payload integration. In addition to working with payload developers to ensure mission safety, the SLS Program also provides a secondary payload deployment system in the OSA (Orion Space Adapter). The deployment window for the CubeSats will be from the time ICPS disposal maneuver is complete (currently estimated to require about four hours post-launch) to up to 10 days after launch. 14)
Deployment windows of secondary payloads: The smallsats manifested on EM-1 will undertake a diverse variety of experiments and technology demonstrations. Seven payloads will be deployed after the ICPS has cleared the first Van Allen Radiation Belt (bus stop 1, Figure 8).
• JAXA, the Japanese Space Agency, will have two smallsats deploy at the first stop: OMOTENASHI will land the smallest lander to date on the lunar surface to demonstrate the feasibility of the hardware for distributed cooperative exploration systems. If this mission is successful, Japan will be the fourth nation to successfully land a mission on the Earth's moon. The other JAXA payload, EQUULEUS, will fly to a libration orbit around the EML2 (Earth-Moon L2) point and demonstrate trajectory control techniques within the sun-Earth-moon region for the first time by a smallsat.
• Lunar Flashlight is a NASA/JPL ( Jet Propulsion Laboratory) mission that will look for ice deposits and identify locations where resources may be extracted from the lunar surface.
Figure 8: Providing smallsats with extraordinary access to deep space, SLS presented payload developers with several "bus stops," or deployment opportunities, for the first mission; similar opportunities are expected to be available on future missions (image credit: NASA)
• The NASA/ARC ( Ames Research Center) developed the BioSentinel mission is a yeast radiation biosensor that will measure effects of space radiation on DNA.
• ArgoMoon, sponsored by the Agenzia Spaziale Italiana (ASI), will perform proximity operations with the ICPS post-disposal and record imagery of engineering and historical significance — as well as of the Earth and moon — by testing an advanced software imaging recognition system using high-definition cameras.
• Cislunar Explorers, a team from Cornell University in Ithaca, New York, competing in NASA's Cube Quest Centennial Challenge competition, has designed a 6U CubeSat that will split into two smaller spacecraft that will orbit the moon using a novel propulsion system of inert water to carry out gravity assists with the moon, and then be captured into lunar orbit.
• Finally, Lunar Icecube, developed by Morehead State University in Kentucky, will search for water in ice, liquid and vapor forms as well as other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact infrared spectrometer.
• About 90 minutes after the ICPS clears the first Van Allen Belt, the NEA Scout (Near Earth Asteroid) Scout, a NASA/MSFC (Marshall Space Flight Center) mission equipped with a solar sail to rendezvous with an asteroid, will be deployed. NEA Scout will gather detailed imagery and observe the asteroid's position in space.
• After the ICPS has cleared both radiation belts, the LunaH-Map (Lunar-Polar Hydrogen Mapper) payload from Arizona State University will be released. LunaH-Map will help scientists understand the quantity of hydrogen-bearing materials in cold traps in permanently shaded lunar craters via low-altitude flybys of the moon's south pole.
• About one hour after clearing the radiation belts (bus stop 2, Figure 8), Lockheed Martin's LunIR spacecraft, a technology demonstration mission that will perform a lunar flyby, will be deployed. Using a miniature high-temperature MWIR (Mid-Wave Infrared) sensor to collect spectroscopy and thermography data, LunIR will provide data related to surface characterization, remote sensing and site selection for lunar future missions.
About 12 hours after the ICPS passes the moon (bus stop 5, Figure 8) and uses its gravity to enter heliocentric orbit, the final three smallsats will be released.
• The CuSP (CubeSat Mission to Study Solar Particles) mission of SwRI (Southwest Research Institute) in San Antonio, Texas, will study the sources and acceleration mechanisms of solar and interplanetary particles in near-Earth orbit, support space weather research by determining proton radiation levels during ESP (Solar Energetic Particle) events and identifying suprathermal properties that could help predict geomagnetic storms.
• Team Miles, of Miles Space, LLC, of Tampa, Florida, another Cube Quest competitor, has a mission that will fly autonomously using a sophisticated onboard computer system. The spacecraft will be propelled by evolutionary plasma thrusters.
• The final Cube Quest entrant, the University of Colorado CU-E3 (Earth Escape Explorer), is a CubeSat from the University of Colorado in Boulder, Colorado, that will use solar radiation pressure rather than an onboard propulsion system.
Sensor complement: (BioSensor, LET Spectrometer, TID Dosimeter)
The primary objective of BioSentinel is to develop a biosensor using a simple model organism to detect, measure, and correlate the impact of space radiation to living organisms over long durations beyond LEO (Low Earth Orbit). While progress identifying and characterizing biological radiation effects using Earth-based facilities has been significant, no terrestrial source duplicates the unique space radiation environment. 15)
The BioSentinel biosensor uses the budding yeast S. cerevisiae to detect and measure DSBs (Double Strand Breaks) that occur in response to ambient space radiation. DSBs are deleterious DNS lesions that are generated by exposure to highly energetic particles in the deep-space radiation without errors by the cell. The biosensor consists of genetically engineered yeast strains and nutrient selection strategies that ensure that only cells that have repaired DSBs will grow in specialized media. Therefore, culture growth and metabolic activity of yeast cells directly indicate a successful DSB-and-repair event.
BioSentinel Science Concept: 16)
• Quantify DNA damage from space radiation environment
- Space environment cannot be reproduced on Earth
- Omnidirectional, continuous, low flux with varying particle types
- Health risk for humans spending long durations beyond LEO
- Radiation flux can spike 1000 x during a SPE (Solar Particle Event).
• Correlate biologic response with TID and LET data
- BioSensor payload uses engineered S. cerevisiae
- Measures rate of DSBs (Double Strand Breaks) in DNA
- LET spectrometer measures particle energy and count
- TID dosimeter measures integrated deposited energy
• Yeast assay uses microfluidic arrays to monitor for DSBs
- Three strains of S. cerevisiae, two controls and an engineered strain
- Wet and activate multiple sets of microwells over mission lifetime
- DSB and associated repair enable cell growth and division of the engineered "biosentinel" strain
- Activate reserve wells in event of an SPE.
Figure 9: Overview of the BioSentinel mission (image credit: NASA/ARC)
The NASA NEN (Near Earth Network) is comprised of stations distributed throughout the world in locations including Svalbard, Norway; Fairbanks, Alaska; Santiago, Chile; McMurdo, Antarctica; and Wallops Island, Virginia. Figure 1 is an overview of the NEN. The NEN supports spacecraft trajectories from near Earth to two million kilometers (Ref. 6).
Figure 10: Overview of the NASA NEN (image credit: NASA)
The NASA TDRS (Tracking and Data Relay Satellite) System provides continuous global communications and tracking services to low earth orbiting satellites including the International Space Station, earth observing satellite, aircraft, scientific balloons, expendable launch vehicles, and terrestrial systems. The global TDRS fleet currently consists of four first-generation, three second-generation and two third generation satellite supported by three tracking stations, two at White Sands, New Mexico, and a third on the Pacific island of Guam. The third third-generation satellites will be deployed in early of 2018. This combination of nine relay satellites and three ground stations comprise NASA's Space Network (SN). Figure 11 provides a representative overview of the NASA SN.
CubeSats and SmallSats provide a cost-effective, high return on investment for conducting science missions by using miniaturized scientific instruments and bus components. Higher data rate CubeSats are transitioning away from Amateur Radio bands to S- and X-bands in the near and mid-term and Ka-band in the long term, now requiring CubeSat communication hardware standardization and compatibility with NEN and SN. Based on a high-level communication architecture for future space-to-ground CubeSat communication proposed within NASA/GSFC,
Results of the CubeSat NEN (Near Earth Network) and SN (Space Network) support analysis are provided. CubeSat constellation concept and ISL (Intersatellite Link) CDMA (Coded Division Multiple Access) signal model and trades study are discussed. A simulation model with power and bandwidth efficient signal schemes to study CubeSat maximum achievable data rate for NEN space science X-band downlink 10 MHz channel is presented and the results are discussed. Results of NEN CubeSat Ka-band end-to-end communication analysis using portable antenna system are summarized.
The proposed NASA future CubeSat/SmallSat communication configurations are depicted in Figure 12: CubeSat to NEN direct-to-ground communication, CubeSat to TDRSS MA array communication, CubeSat constellation with mother ship communication through NEN direct-to-ground communication, and CubeSat Constellation with mother ship communication through TDRSS MA array or KSA/SSA (K-band Single Access)/S-band Single Access).
Legend to Table 2: 11.3 m at AS1, CubeSat PA = 1 W, 0 dBi Antenna Gain (S-band), Antenna Gain = 5 dBi (X-band). S/C at 745 km altitude.
The required Cubesat EIRP can be met with practical spacecraft (S/C) power amplifier (PA) 1 W/2 W and patch antenna zero dBi gain (S-band) Earth coverage antenna 6 dBi gain (X-band) with plenty of link margin. Table 2 is summary of the link analysis for representative date rate, required EIRP, modulation and coding schemes, ground station parameters and link margin.
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The information compiled and edited in this article was provided by Herbert J. Kramer from his documentation of: "Observation of the Earth and Its Environment: Survey of Missions and Sensors" (Springer Verlag) as well as many other sources after the publication of the 4th edition in 2002. - Comments and corrections to this article are always welcome for further updates (email@example.com).