Boaz Shoor's research while affiliated with Rafael Advanced Defense Systems and other places

Venµs is a satellite launched in 2017, for super-spectral Earth imaging and Electric Propulsion System (EPS) demonstration. In this paper we overview EPS design and operation throughout all five mission phases, from open/closed-loop orbit control, through orbit descent (720→410 km), orbit maintenance under high drag environment, to orbit raising (410→560 km). The EPS consisted of two throttleable Hall thrusters, PPU, Propellant Management Assembly (PMA), and a 9 liter propellant tank carrying 16 kg of Xenon. Both thrusters operated in the 300–550 W power range, generated a combined total impulse of 158.1 kN-sec and consumed all propellant. Two methods are described to compute the remaining propellant mass – “Bookkeeping” and “PTV” methods. The advantages and disadvantages of each method are discussed in light of the Venµs mission. Thruster performance was measured on-orbit using the “Orbit Determination” method and compared to laboratory experiments conducted on the ground with identical thrusters. The measured performance on-orbit was found to be on average lower by up to 5% than the performance measured on the ground. Lastly, we present several repeating events in which the propulsion system suffered from sudden beam-outs or ignition difficulties. We present the methods used to construct a solution and implement it.

Rafael's first generation Power Processing Unit (R-400PPU) is operating successfully, for over two years, in a LEO mission on-board the VENµS Micro-satellite. Presently, Rafael develops the 2 nd generation PPU (R-400PPU MK2) aimed at serving as a common and generic solution for Rafael's Hall Thruster based Electric Propulsion Systems (EPS) in the system power range of 150 to 1000W. The R-400PPU MK2 consists of two major sub-units, the Power Supply Unit (PSU) and the Sequencing and Control Unit (SCU), and provides all power, telemetry and communication requirements for the EPS. It also contains a Thruster Selection Unit (TSU) that selects one of two thrusters for operation. PPU design consists of four development phases, one for each model: Bread Board (BB), Engineering Model (EM), Engineering Qualification Model (EQM) and Proto-Flight Model (PFM). In this paper we describe the main characteristics of the R-400PPU MK2, its stages of development and the initial integration test conducted with the Rafael thruster units and other subsystems and EPS.

For over a decade Rafael has been developing and qualifying Hall thruster based electric propulsion components and full systems, specially designed for the SmallSat category. The focus on the activities conducted at Rafael are the development of low power Hall thruster technologies covering a discharge power range from 100 W up to 900 W. In this paper we overview the electric propulsion technologies developed at Rafael and their current development status. We present a flight operation status of the R-400EPS aboard the VENμS satellite mission in LEO, operating in the 300-600 W power range. Subsequently, we overview the qualification status of the R-200 and R-800EPS, two low power Hall thruster based systems operating in the 150-350 W and 450-900 W power ranges, respectively. We then present the heaterless cathodes developed to couple with these thrusters. We survey the development and qualification status of the PPU developed to serve all Hall thrusters. We review the components of the Propellant Management Assembly (PMA) and present some of the activities conduced to qualify the PMA components. Finally, we briefly overview the infrastructure at Rafael and its capabilities.

Venμs is a satellite launched in 2017, for super-spectral Earth imaging and Electric Propulsion System (EPS) demonstration. The EPS includes a novel design, developed, qualified, manufactured, integrated and fueled by Rafael. The EPS demonstrates mission enhancement capabilities and its in-space performance is characterized. The system and satellite were carefully designed to comply with the mission goals and constraints. In addition to the EPS, a Technological Mission Center (TMC) was built for the command and analysis of the technological mission. The satellite is now in orbit and performs EPS operation and characterization. After successfully conclusion of In Orbit Test (IOT), Venus started the first mission phase. Every month a dedicated EPS experiment is performed; and thus far the EPS operated well and demonstrated excellent results. The Technological Mission Center already posted technical results and characteristics from the EPS operation in space. Mission is continuing with additional planned four years of in space activity.

Venµs is a recently launched satellite, for super-spectral earth imaging and Electric Propulsion System (EPS) demonstration. The EPS includes a novel design, developed, qualified, manufactured and integrated by Rafael. The EPS will demonstrate mission enhancement capabilities and its space performance will be characterized. The system and satellite were carefully designed to comply with the mission goals and constraints. In addition to the EPS, a Technological Mission Center (TMC) was built for the command and analysis of the technological mission. The satellite is now beginning its in-orbit tests for the EPS and the rest of its components. Venµs mission duration is approximately four years, during which the satellite will operate in two major orbits.

Micro-Satellite Electric Propulsion System (MEPS) is a development and qualification programme jointly supported by the European Space Agency (ESA) and the Israeli Space Agency (ISA) aiming at the full space qualification of a low power electric propulsion system specifically designed to be used onboard for small satellites (mini-and micro-class). The system is conceived to have maximum flexibility to be appealing for a wide variety of missions, ranging from drag-compensation to spacecraft de-orbiting. To date the system components were developed to bread-board and engineering models level and take part in system integration tests. Currently Rafael and Sitael, the two prime companies that are in charge for the system development, are approaching the thruster units endurance test campaign, in parallel to power processing unit and propellant management assembly development.