The Power Supply Unit onboard the HERMES nano-satellite constellation Paolo Nogaraa Giuseppe Sottilea Francesco Russoa Giovanni La Rosaa Fabio

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The Power Supply Unit onboard the HERMES nano-satellite

constellation

Paolo Nogaraa, Giuseppe Sottilea, Francesco Russoa, Giovanni La Rosaa, Fabio

Paolo Lo Gerfoa, Melania Del Santoa, Yuri Evangelistab, Riccardo Campanac, Fabio Fuschinoc,

and Fabrizio Fiored

aINAF/IASF-Palermo, Via Ugo la Malfa, 153, 90146 Palermo PA, Italy

bINAF/IAPS, Via del Fosso del Cavaliere, 100 - 00133 Roma, Italy

cINAF/OAS, Via Piero Gobetti, 93/3, 40129 Bologna BO, Italy

dINAF/OATS, via G.B. Tiepolo, 11, 34143 Trieste, Italy

ABSTRACT

HERMES Pathﬁnder (High Energy Rapid Modular Ensemble of Satellites Pathﬁnder) is a space mission based

on a constellation of nano-satellites in a low Earth Orbit, hosting new miniaturized detectors to probe the

X-ray temporal emission of bright high-energy transients such as Gamma-Ray Bursts and the electromagnetic

counterparts of Gravitational Waves. This ambitious goal will be achieved exploiting at most Commercial oﬀ-

the-shelf components. For HERMES-SP, a custom Power Supply Unit board has been designed to supply the

needed voltages to the payload and, at the same time, protecting it from Latch-Up events.

Keywords: NanoSAT, Gamma-Ray Bursts, GRB, Gamma Ray Detectors, Gravitational Wave Events, GWE,

Power Supply Unit, PSU, Latch-Up, LU, Commercial oﬀ-the-shelf, COTS

1. INTRODUCTION

HERMES (High Energy Rapid Modular Ensemble of Satellites)1is a mission based on a constellation of nano-

satellites (3U CubeSats) in low Earth orbit (LEO), hosting innovative X and γ-ray detectors to probe the high-

energy emission of bright transients.2–4HERMES is built upon a twin project: the HERMES Technological

Pathﬁnder (HERMES-TP), and the HERMES Scientiﬁc Pathﬁnder (HERMES-SP).

Both projects (HERMES-TP and HERMES-SP) provide three complete satellites (payload and service mod-

ule) to the constellation, with the aim of demonstrating that fast Gamma-Ray Burst (GRB) detection and

localization is feasible by disruptive technologies on-board miniaturized spacecrafts, mostly exploiting commer-

cial oﬀ-the shelf (COTS) components at a cost 1–2 orders of magnitude lower than space qualiﬁed ones (e.g.

ESA M-class missions and NASA Explorer missions) and with a development time of only a few years.

Being based on cost-eﬀective nano-satellites, HERMES is intrinsically a modular project. This allows to

avoid single or even multiple-point failures (if one or several units are lost, the constellation and the experiment

is guaranteed) and to test the in-ﬂight hardware and the on-board software since the ﬁrst launches. If needed,

both hardware and software can be improved with the following launches.

In this paper ﬁrst we will give a brief description of the payload, then we will describe the custom Power

Supply Unit (PSU) implemented and the design choices that we made. Finally, we will present the diﬀerent

components, with their peculiarities, that make up the PSU and a few results of our tests.

Further author information: (Send correspondence to Paolo Nogara and Giuseppe Sottile)

Paolo Nogara: E-mail: paolo.nogara@inaf.it, Telephone: +39 091 6869 567

Giuseppe Sottile: E-mail: giuseppe.sottile@inaf.it, Telephone: +39 091 6869 567

arXiv:2210.13875v1 [astro-ph.IM] 25 Oct 2022

2. THE PAYLOAD

The HERMES Payload (P/L4) is hosted in a single CubeSat Unit (1U) and it is composed by a number of

sub-systems, as represented in Figure 1and in the P/L product tree (Fig. 2). In particular:

•Detector assembly (DA)

– Detector support structure, mounted on the top of the detectors plane. This structure is split in

an upper and a lower part with the optical ﬁlter in-between. The lower detector support structure is

shaped in order to avoid touching the electrical components on the Front End Electronics (FEE);

– Optical ﬁlter, providing eﬀective ﬁltering of UV-VIS-IR bright emission from the Earth;

– FEE board, which includes:

∗Silicon Drift Detectors (SDDs) mounted on the printed circuit board (PCB) side opposite to

the detector support structure;

∗the ﬁrst analogue stage (LYRA-FE) of the electronics for each channels (pre-ampliﬁer, ﬁrst shaper

stage, line buﬀer);

∗the power distribution and ﬁltering for SDDs power;

∗the second (mixed signal) stage of the electronics (LYRA-BE).

–Scintillator crystals optically coupled to the SDD detectors which are contained in a light-tight crystal

box.

•Back End Electronic (BEE) board: is a PC/104 format board developed by INAF speciﬁcally for the

HERMES payload, using COTS components. Within the payload section, the BEE board is placed between

the Power Supply Unit (PSU), to which is directly plugged by two connectors, and the Detector Assembly.

The main component of the BEE is the Intel Cyclone V E FPGA, which is optimized for applications

that require low power consumption and low cost. The board hosts two identical quad-serial conﬁguration

(EPCQ) devices, that are an in-system programmable NOR ﬂash memory. The redundant devices and the

hardwired logic present on board guarantee the correct programming of the FPGA even if one of the two

EPCQs has the conﬁguration ﬁle corrupted. The BEE manages conﬁguration tables of the LYRA ASICs

through serial buses and monitors the trigger outputs to start the acquisition of the events by means of

four ADAQ7980 16 bits 1MSPS ADCs, one for each quadrant of the instrument. The time-tagging for

the scientiﬁc events is generated by the combination of a GPS synchronization signal provided by the

nanosatellite platform and the Microsemi SA.45s CSAC Chip Scale Atomic Clock (CSAC) hosted in the

BEE board. The BEE manages all the power switches for the FEE and the housekeeping 8 bits ADC

located on the PSU board. The Payload Data Handling Unit and BEE communicate by a reliable custom

protocol based on SPI serial bus;

•Power Supply Unit (PSU) board, like the BEE board, is developed by INAF speciﬁcally for the

HERMES payload using COTS components. PSU is connected to the satellite power bus, which is in

charge of the generation, ﬁltering and distribution of all the needed voltages to the payload.

FEE-BEE and FEE-PSU Harness connect the FEE to the BEE and PSU, respectively. More details

about the PSU board is described in the following sections.

•Payload Data Handling Unit (PDHU), which conﬁgures the FEE and BEE, receives digital data

from BEE and formats the event information (energy, address, time), generates the photon list, elaborates

the data with a burst search algorithm, produces TM data packets, receives and manages telecommands

(TLCs). The PDHU issues commands for the Power Supply Unit (PSU) to generate and distribute the

required voltages levels for the BEE, FEE and SDD, and procures a safe switch on/oﬀ procedure when

ramping up/down the relevant voltages.

•Mechanical structure.

Figure 1: Exploded view of the HERMES Payload (P/L).

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ThePowerSupplyUnitonboardtheHERMESnano-satelliteconstellationPaoloNogaraa,GiuseppeSottilea,FrancescoRussoa,GiovanniLaRosaa,FabioPaoloLoGerfoa,MelaniaDelSantoa,YuriEvangelistab,RiccardoCampanac,FabioFuschinoc,andFabrizioFioredaINAF/IASF-Palermo,ViaUgolaMalfa,153,90146PalermoPA,ItalybINAF/IAPS,ViadelF...

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The Power Supply Unit onboard the HERMES nano-satellite constellation Paolo Nogaraa Giuseppe Sottilea Francesco Russoa Giovanni La Rosaa Fabio

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