S. Xu, and D. Goebel, “, K. Kubota, The most simple spacecraft mode for New Horizons is the Passive Spin Hibernation in which any attitude control is precluded, minimizing the electrical power demand and spacecraft monitoring as well as fuel consumption. H. Sun, D. Kuwahara, S. Bhandari, and An acceleration grid unit contains internal and external grids used for extraction and acceleration, respectively. R. Schneider, “, O. Baranov, M. A. Cappelli, X. Liu, “, Numerical studies of wall–plasma interactions and ionization phenomena in an ablative pulsed plasma thruster, 100. P. Minelli, W. Gärtner, T. Matlock, Y. Ding, S. Bhandari, and H. Horita, “, S. Isayama, P. Chabert, The critical elements of the electric propulsion thrusters of interest here are mainly degraded and sputtered by the effect of plasma fluxes and very strong heat loads. Third, theoretical understanding of the interaction between the plasma flow and the interior cathode structure would allow for the development of novel cathode configurations. To effectively combat and halt these processes, novel materials should feature self-healing surfaces and, moreover, external processes should be organized in the thrusters to ensure restoration of surfaces damaged by plasma and ion fluxes. Overall, the spacecraft attitude control system can keep the spacecraft body rates to within 24 µrad when in three-axis modes (34 µrad during spin-stabilization). G. Saccoccia, P. Sarrailh, B. Tian, For longer missions, the delivery of greater specific impulse requires a greater amount of energy for ion acceleration and thus an increased capacity with respect to energy storage and other systems. Space Sciences, 106. Current efforts to design the miniaturized ion thrusters include, e.g., the article in. A critical command decoder on the uplink card is in charge of receiving and executing commands without action of the rest of the C&DH system such as processor re-starts, switching of C&DH controllers and other power-switching commands. G. Sun, A. Shashurin, G. Cai, R. D. Bengtson, S. D. Baalrud, S. Yan, I. Funaki, “, D. Pedrini, This configuration decreases the efficiency of the device, yet it opens wide prospects for miniaturization by providing a way to build a tiny acceleration channel with a very small diameter. L. Garrigues, and Y. Nakagawa, P. Li, F. R. Chang-Díaz, and M. Merino, and J. S. Yee, X. Wu, Owing to their very high intrinsic specific impulse and other advantages, gridded ion thrusters have been historically among the most intensely researched space thrust platforms. S. Rauf, N. J. Mason, J. Li, Finally, whatever is the type of the electric propulsion system being considered, the study of interactions between the plume and the satellites and the induced spacecraft charging is of considerable importance. D. M. Goebel, D. Estublier, Only one star tracker is active at any given time while the other provides redundancy in case of problems with the primary unit. A. Bourdon, and It first flew in 2000 and hosts 110,000 transistors. All rights reserved. Y. Ohkawa, and The location of the propellant tank has been chosen based on the consideration of the Center of Mass of the spacecraft, but also to shield the bulk of electronics from the radioisotope generator to keep their total dose as low as possible. H. Kimura, “, A. Sasoh, This eliminates the need for additional neutralizers (cathodes). D. Nicolini, “, Qualifciation test series of the indium needle FEEP micro-propulsion system for LISA Pathfinder, 217. B. S. Hurley, and Complex optical systems for ion thrusters. HHCs are suitable primarily for low-current hollow cathodes, since the heaterless ignition may induce a high thermal stress on the insert when reaching relatively high discharge current levels. Sun, W. Yan, The excess heat is radiated into space using cooling tubes that transport heat to outer fins that use a black coating and maximize the active radiating area to prevent the components of the RTG from overheating. The development of the Hall thruster configuration known as “magnetic shielding” has resulted in a drastic improvement in the thruster lifetime range by decreasing the radial ion kinetic energy in the acceleration region. The aforementioned examples provide but a brief snapshot of the current efforts by many research and engineering teams to miniaturize various space assets to meet the growing expectations of the space industry and, in doing so, respond to a number of global challenges. N. Gascon, There are a wide variety of collision phenomena that can be described by means of the DSMC method. S. Samukawa, Another potential way to improve the efficiency of small Hall thrusters is by using the so-called wall-less configuration where the plasma discharge is shifted outside the channel, therefore drastically reducing losses at the walls; it also makes the device very simple and hence more reliable. P. Li, and C. Dodson, Hybrid PIC-DSMC simulation of a Hall thruster plume on unstructured grids, 171. Trajectory Correction Maneuvers may be conducted in each of these modes, the choice driven by the magnitude of the maneuver. P. Grondein, H. Li, and Furthermore, kinetic approaches are of. J. P. Boeuf, Y.-L. Wu, F. R. Chang-Díaz, and L. Wei, M. Keidar, “, Ion velocities in a micro-cathode arc thruster, 213. N. Guo, A. I. Bugrova, A. Domínguez-Vázquez, New Horizons is a Deep Space Exploration Mission operated by NASA, launched to study the Dwarf Planet Pluto and other icy objects in the Kuiper Belt. O. Sutherland, J. Fang, “, Plasmonic platform based on nanoporous alumina membranes: Order control via self-assembly, World record flights of beam-riding rocket lightcraft—demonstration of “disruptive” propulsion technology, 226. R. Martorelli, P. Lascombes, and Ion thruster prototype breaks records in tests, could send humans to Mars in just 40 days. E. Chinchilla, D. Rafalskyi, 178. B. Jorns, and M. Cappelli, Y. Takao, “, Effects of neutral distribution and external magnetic field on plasma momentum in electrodeless plasma thrusters, 13. M. Bocoum, Phys. P. Sarrailh, M. K. Scharfe, The characterization of all thrusters and their specific performances and potential deviations from the norm was completed as part of spacecraft commission for accurate prediction of maneuvers that are required for attitude and spin rate changes. The first challenge concerns present capability to propose efficient numerical schemes able to capture the effect of nondiagonal terms in the tensor of transport coefficients to be able to model a large variety of magnetic field configurations. K. Bazaka, A. Niemira, Pressure transducers are mounted directly downstream of the tank and the orifice to deliver data needed for the calculation of the thruster output at the given inlet pressure which will go down as tank pressure drops over the course of the mission. L. Wei, A web-interface tutorial is available to assist new users. R. Martorelli, X. G. S. Oehrlein, P. Matthias, S. Schreiner, and E. Ahedo, “, Experimental characterization of a 1 kW helicon plasma thruster, 89. Y. Ishigami, S. Xu, “, Explore space using swarms of tiny satellites, 6. A. P. Sinitsin, “, P. Saevets, D. Pedrini, The Uplink Card also provides command decoding, ranging tone demodulation, X-Band carrier tracking and a regenerative ranging subsystem. M. Andrenucci, “, C. Drobny, T. J. Scanlon, J. Yan, J. Vaudolon, A. Jorns, N. Arce, Pluto’s reclassification as a Dwarf Planet will not lessen the scientific return from the New Horizons mission that will deliver the first-ever will resolved photos of Pluto and its largest moon Charon. J. P. Boeuf, and The Propulsion Diode Boxes, two for redundancy, build the power interface to the propulsion system components – actuating the thruster seat valves, catalyst bed heaters and propellant latch valves. It is possible that with the development of sophisticated miniaturized semiconductor systems in may e possible to sustain safe generation of high voltages on board of Cubesats. A. Gurciullo, New opportunities offered by these interconnected networks include the widest-possible coverage of survey and information pickup; and larger, of the constellation size, observation bases with the relevant resolution and ability to collect and coherently process the information inside the constellation. G. J. H. Hagelaar, W. Helgeson, and New Horizons features a number of thermal sensors installed across the entire spacecraft and on components with the tightest thermal margins to alert the vehicle to dropping temperatures in which case heaters would be activated to maintain a safe thermal environment for all systems. Printable cathode arc thrusters are propulsion devices that rely on a pulsed or DC discharge between the two electrodes. S. Ullrich, L. Grimaud, “, Rotating spoke instabilities in a wall-less Hall thruster: Simulations, 157. D. Semenenko, K. Matyash, B. New Horizons is equipped with directional antennas – a single High-Gain Antenna, and one Medium Gain Antenna, as well as two omni-directional Low Gain Antennas. P. Dietz, and R. Wakabayashi, “, Laser propulsion technology on KKS-1 microsatellite, 228. A. D. Gallimore, J. Appl. The forward antenna system is comprised of the High-Gain Antenna, the Medium Gain Antenna, and one of the Low Gain Antennas, all installed on the –Y panel of the spacecraft. In this case, one signal would be right-hand polarized while the other system delivers a left-hand polarized signal. A. D. Gallimore, and The low current cathodes find their principal use in nano- and microsatellites deployed for varied purposes: scientific research, Earth observation, astronomy, as well as technological, educational, and military applications. S. P. Tierno, K. Bazaka, “, 5. L. Dubois, R. R. Hofer, AIAA Paper 2014-3815, 2014. M. Kawachi, A. Jullien, K. Bazaka, J. Sinko, “, A. Aanesland, V. T. Gurovich, R. Wirz, “, An investigation of low frequency plasma instabilities in a cylindrical hollow cathode discharge, 117. For most of its journey, the spacecraft will be spin-stabilized and only operate in three-axis control modes during testing, the Jupiter flyby, the Pluto approach & flyby, and other science observations as they arise during the mission. Y. Hadas, “, Low current heaterless hollow cathode development overview, 35th International Electric Propulsion Conference (IEPC), 135. T. Matsuba, B. The propulsion system uses monopropellant hydrazine thrusters that are fed from a single spherical titanium tank that resides within the central thrust tube of the spacecraft. All-electric propulsion satellites—Sparking a revolution in space; Accessed March 2019. W. Bohn, I. G. Mikellides, E. Ahedo, “, Two-dimensional plasma-wave interaction in an helicon plasma thruster with magnetic nozzle, 88. M. Wijnen, T. Lefrou, R. Lucken, Satellites and spacecraft still widely use gas-based thrusters or chemical engines as their primary means of propulsion. M. Keidar, “, Optimization of discharge triggering in micro-cathode vacuum arc thruster for CubeSats, 102. The spacecraft bus voltage is set at 30.25V, slightly above the maximum power transfer level of the RTG to account for voltage drops when power is distributed to the individual loads. J. Chen, M. K. Borg, All in all, the RTG has a total output of 3,948 Watts of thermal energy (at launch), but only 250W of electrical power can be delivered by the system, requiring the rest to be radiated into space. S. Cheng, B. T. Zhuang, R. Lopez-Martens, S. Samukawa, C. Huang, “, D. F. Berisford, Y. Yue, S. Mazouffre, R. Martorelli, K. Ostrikov, “, M. Celik, A. Shabshelowits, H. Kuninaka, “, G. Cai, New Horizons is the 27th NASA mission to employ a Radioisotope Thermoelectric Generator given the depth of space it will travel, far away from the sun where solar power generation would require extremely large solar arrays.

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