This work presents a radiation-hardened reconfigurable hardware based platform to be used in deep-space cubesat missions. The platform has been designed for the in-orbit validation of two new technologies: a new radiation-hardened Field-Programmable Gate Array (FPGA) developed in France; and a CCSDS/ECSS IP Core for telemetry (TM) and telecommand (TC) designed at UFSC, Brazil. The printed circuit board (PCB) was designed following the European Space Agency (ESA) space product standards. It has a layered structure that mitigates the effects of radiation and electromag- netic interference on the components signals. All signal layers lie between power and ground planes, avoiding tracks on the outer layers. In addition, all components were selected to tolerate wide tem- perature variation and some even tolerate radiation – as the microcontroller (MCU) (MSP430FR6989) with ferroelectric program memory and the rad-hard FPGA (NX1H35S-BG625PR). An important ar- chitecture feature is to allow changing the hardware configuration of the FPGA through remote uplink of its Bitstream. The MCU is responsible for updating the configuration bitstream stored in a flash non- volatile memory. An aditional bitstream is also stored in the memory, as a fail-safe technique. There are three bitstream copies stored, and a voting scheme is used to ensure the data integrity, as the flash mem- ory is susceptible to Single Event Effects (SEE). The MCU module is responsible for the housekeeping and update management of the rad-hard FPGA. The implementation stored in the FPGA includes not only the TC/TM IP core, but also an abstract execution graph, in the form of a state machine, emulating the basic functionalities of an on-board computer (OBC). The communications module handles TC and TM data and it is an interface between the radio transceiver and the emulated OBC. The emulated OBC is based on the ECSS Telemetry & Telecommand Packet Utilization Standard (PUS), and it performs the validation of the routed telecommand received, and the packaging of the telemetry data acquired by the available sensors. The proposed architecture allows testing all the implementations, exercising its functionalities, and also the module’s integration as a payload of the FloripaSat mission.