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Enabling Future Constellation Missions Using Micro-Satellites for Space Weather

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Enabling Future Constellation Missions Using Micro-Satellites for Space Weather SSC07-IV-6 Space Technology 5 – Enabling Future Constellation Missions Using Micro-Satellites for Space Weather Guan Le NASA Goddard Space Flight Center Greenbelt, MD 20771; 1-301-286-1087 [email protected] Thomas E. Moore NASA Goddard Space Flight Center Greenbelt, MD 20771; 1-301-286-5236 [email protected] James A. Slavin NASA Goddard Space Flight Center Greenbelt, MD 20771; 1-301-286-5839 [email protected] ABSTRACT Space Technology 5 (ST5) is a three micro-satellite constellation deployed into a 300 x 4500 km, dawn – dusk, sun synchronous polar orbit on March 22, 2006. The spacecraft were maintained in a “pearls on a string” constellation with controlled spacing ranging from just over 5000 km down to under 50 km. Each spacecraft carried a miniature tri-axial fluxgate magnetometer (MAG). Although the short 90-day mission was designed to flight validate new technologies, the constellation mission returned high quality multi-point magnetic field data through the Earth’s dynamic ionospheric current systems. These data allow us to separate spatial versus temporal structures of auroral field-aligned currents over a wide range of spatial (~ 50-4000 km) and temporal (~ 5 s-10 min) scales. The ST5 mission was designed as a pathfinder for future Heliophysics constellation missions making particles and fields measurements over large volumes of Geospace. Based on the success of ST5, we are developing the concept of a new constellation mission, called Magnetospheric Convection Explorer (CONVEX), using ~ 10 small ST5-class spacecraft, distributed in local time around the Earth to complement the THEMIS mission’s radial deployment. The science approach is to generate the first global “images” of magnetospheric convection. This will allow definitive determinations of how major types of solar events drive specific space weather response modes in the near Earth environment. INTRODUCTION - Operate the 3 satellites as a single The ST5 Mission is the fifth mission in NASA’s New constellation rather than as individual Millennium Program (NMP) to flight validate new elements. technologies built for micro-satellite. It is NASA’s The official NMP technologies that have been pathfinder for future small spacecraft constellation successfully validated by ST5 are described in Carlisle missions. The ST5 mission consists of three micro- et al.1 and Carlisle and Webb2. satellites and has three top level technology validation objectives: The ST5 spacecraft were launched by a Pegasus XL launch vehicle into a sun-synchronized, dawn – dusk, - Design, develop, and operate three full service 300 x 4500 km, polar orbit (inclination 105.6 deg) on micro-spacecraft, each with a mass less than March 22, 2006 and operated successfully for its 25kg; nominal 90-day mission. As shown in Figure 1, the - Demonstrate the ability of these micro- satellites were maintained in a “pearls on a string” satellites to return research-grade magnetic constellation. The spacecraft were spin-stabilized with periods near 3 seconds. Spin axis orientation for each field measurements; Le 1 21st Annual AIAA/USU Conference on Small Satellites spacecraft was maintained to be within 0.5º of ecliptic Science measurements are required to support the normal with knowledge of ~ 0.1º. Inter-satellite spacing technology validation, especially to validate the ST5 was controlled using the micro-satellites’ cold gas spacecraft as a suitable platform for taking research propulsion system. This propulsion system was also quality measurements. The boom-mounted miniature used to raise perigee at the beginning of the mission and fluxgate magnetometers are the only scientific re-orient some of the spacecraft spin axes for eddy instrument onboard each of the three ST5 spacecraft. current assessments and magnetometer inter- Although the short 90-day mission is designed to flight calibration3. Figure 2 displays the history of the validate new technologies, the constellation mission spacecraft spacing, where the red is for the separation returned unprecedented data as they flied in formation between the lead (155) and middle (094) spacecraft and and made simultaneous multi-point measurements of the blue between the middle and trailing (224) the geomagnetic field in its low Earth orbit. In addition spacecraft. As shown, these spacings varied between to returning high quality magnetic field measurements from just over 5000 km down to under 50 km. of the auroral currents that flow into and out of the auroral zone, the measurements at perigee are also sensitive to horizontal currents flowing in the ionosphere and the Earth’s crustal magnetic anomalies. In this paper, we present results of ST5 science validation. We first provide some information about the magnetometer and its boom. Then, we present the science data returned from ST5 that demonstrate the capabilities of the spacecraft as a platform for research quality measurements and the high performance of the miniature magnetometers. Finally, we describe a new micro-satellite constellation mission concept, Magnetospheric Convection Explorer (CONVEX), which is being developed. Leveraged on the success of the ST5 mission, the CONVEX mission will deploy ~ 10 small ST5-class spacecraft to generate the first global “images” of magnetospheric convection. This Figure 1: Illustration of the ST-5 three satellite will allow definitive determinations of how major types constellation’s sun-synchronous polar orbit. of solar events drive specific space weather response modes in the near Earth environment. ST5 MAGNETOMETER (MAG) MAG Specifications The three ST5 magnetometers were developed by UCLA. Table 1 details the ST5 magnetometer specifications. These instruments function as “state vector machines” that deliver 16 vectors per second to the spacecraft command and data handling whenever it receives a clock signal and power. The magnetometer sensor is mounted at the end of a stiff, very low mass, self-deploying boom designed and built by GSFC. This arrangement places the magnetometer almost 110 cm from the center of the spacecraft, in order to reduce the effects of any stray magnetic fields from within the body of the spacecraft. The magnetometer boom stows Figure 2: The history of the spacecraft separations by folding around the spacecraft equator and was over the ST5 mission life. The red is the separation released on-orbit using a shape memory alloy pin between the leading (155) and the mid (094) puller. Strain energy in the hinges, from stowing, spacecraft, and the blue between the tailing (224) deploys the boom. It is constructed as an assembly of and the mid spacecraft. graphite composite tube sections with beryllium copper "carpenter tape" hinges. It is about 225 g in mass and 80 cm in length. It has been designed to minimize Le 2 21st Annual AIAA/USU Conference on Small Satellites magnetic interference with the magnetometer and data into the fixed spacecraft frame using the sun sensor provide thermal and dynamic stability. data; (4) calibrating the despun data with the Earth’s internal magnetic field model, and (5) transforming the The MAG sensors have dimensions of 5 cm x 5 cm x 3 calibrated data into geophysical coordinate systems cm and the total mass of each sensor plus its electronics using the spacecraft attitude data. Our results show that is approximately 570 gm. The MAG has two ranges: the ST5 magnetic field data are of very high quality. +/- 64,000 nT (Full-Field) and +/- 16,000 nT (Low- The observed magnetic field along the ST5 orbit agrees Field) that are controlled by each micro-satellite on the well with the prediction of the International basis of the measured ambient magnetic field strength. Geomagnetic Reference Field (IGRF) model. With The digital resolution of the MAG in its full and low preliminary calibrations, we have achieved the MAG magnetic field ranges is better than 1.25 nT and 0.30 data accuracies of 0.1º in pointing knowledge and better nT, respectively. The intrinsic noise for these miniature than 0.1% in field strength. Magnetic signatures of magnetometers was < 0.1 nT rms @ 1 Hz. science events as small as a few nT can be readily identified in the data with a background field up to ~ 50,000 nT. We do not see any effect of nutation or Table 1: Magnetometer Specifications coning of the spacecraft, or contamination due to Specifications unstable spacecraft magnetic field. These inflight MAG data have further validated that the ST5 spacecraft are Dynamic Range 0 - ±64,000 nT (Full-Field) magnetically clean and meet full success requirements. 0 - ±16,000 nT (Low-Field) Digital Resolution < 1.25 nT (Full-Field) < 0.30 nT (Low-Field) ST5 SCIENCE VALIDATION Intrinsic Noise < 0.1 nT rms @ 1 Hz The fundamental measurement strategy of all micro- Data Rate - 16 vectors per second satellite constellation missions is to synthesize higher - simultaneous 17 bit per axis data order physical quantities from the collective sample measurements made by the individual satellite Power 570 mW at 7.2 V (77.8 mA) elements. The ST5 mission provides validation for this Mass Sensor Head: 290 g measurement concept by using three micro-satellites Electronics Box: 570 g through the coordinated collection and analysis of Cable: 90 g magnetometer measurements over the Earth’s auroral Total: 910 g ovals in low Earth orbit. In addition to returning high Size Sensor Head: 5cm×5cm×3cm quality magnetic field measurements of the electric Electronics Box: 10cm×12cm×7.6cm currents that flow into and out of the auroral zone, the measurements at perigee are also sensitive to horizontal currents flowing in the ionosphere and the Earth’s MAG Performance crustal magnetic anomalies. In this section, we present examples of ST5 science measurements to demonstrate The ST5 spacecraft were developed with a magnetic the quality of the ST5 data and how the constellation cleanliness program, which screens parts to avoid using measurements enable new science.
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