The Multi Mission Platform (MMP) represents a modern concept of satellite architecture, with the purpose of bringing together in a single platform all the equipment that perform functions necessary for satellite operations, regardless of orbit characteristics: pointing, power generation, thermal control, data management and telecommunication services. That means, it can meet the requirements of different missions and payloads.
The Multi Mission Platform (MMP) is a generic platform (Service Module) for satellites in the 500 kg class. With a mass of 250 kg, it provides all the necessary resources to support the operation, in orbit, for different payloads around 280 kg.
The main advantages of a multi-mission platform are the reduction of costs and development time of new missions that use it as a base, since, after the development and qualification of the first platform, its reproduction will not require the long and expensive stages of development and qualification of space projects. Another important point to note is reliability aspects, as future missions benefit from project maturity.
The Multi Mission Platform is composed by subsystems, each of them in charge of performing a specific function to ensure the operationality of the satellite in orbit. The MMP subsystems are: Mechanical Structure of the Service Module; Attitude and Orbit Control and Onboard Supervision; Propulsion; Telemetry and Telecommand; Thermal Control; Power Supply, which includes the Solar Generator (electrical part and panel structure).
Is the set of structural components and their connections that support the installation of equipment and closing panels or walls.
The PMM Structure is responsible to encapsulate the equipment that provides vital control, power and telecommunications functions, protecting them from both, the aggressive launch environment (in which the equipment experiences extreme accelerations) and the space environment, when in orbit. In addition, these equipment, sensors, antennas, balancing masses are also packaged in the structure, which includes adapters for the solar panels and for the launch vehicle.
This subsystem was completely developed and manufactured in Brazil.
Responsible for attitude and orbit control and on-board data processing and storage. The ACDH is divided into two parts: one for attitude and orbit control (AOCS) and the other for onboard data processing and satellite supervision (OBDH - "On Board Data Handling").
The ACDH subsystem is one of the most complex subsystems of the satellite, because in addition to the large number of equipment that compose it (sensors, actuators and computers), there is a highly complex embedded software needed for satellite management and on-board decision actions.
This subsystem includes: OBDH computer, AOCS computer, propulsion control electronics, magnetometers, solar sensors, star sensors, gyros, reaction wheels, magnetic bars, GPS receivers and onboard supervision systems software and control, embedded on their computers.
This subsystem was developed in cooperation with Argentina.
It is responsible for changing the satellite velocity and for the acquisition and maintenance of its nominal orbit. In the case of Amazonia satellites, the fuel used is hydrazine. The propulsion subsystem has no autonomy for operation, being supervised and controlled by the ACDH subsystem.
Propulsion subsystem includes thrusters, valves, filters, propellant tank, pressure transducer and set of tubes.
This subsystem was fully designed and manufactured in Brazil.
Responsible for converting solar energy incident on solar panels into electrical energy. Two solar panels are used, positioned on opposite sides of the satellite structure.
This subsystem includes the structure of the solar generator (SAG), the electrical parts of the solar generator (EPSA) and the mechanisms required to open and close the panels (HDRD).
Like the propulsion subsystem, the solar generator subsystem is controlled by the subsystem ACDH via subsystem energy supply (PSS).
This subsystem was fully developed and manufactured in Brazil
The Power Supply subsystem is composed by a set of equipment responsible for the storage, conditioning and distribution of all the electrical energy necessary for the satellite. The subsystem receives the power from the Solar Generator subsystem, packs in batteries, provides power control and distribution to the various equipment in both the Service Module and the Payload Module, using an unregulated power supply architecture. The general supervision of the PSS subsystem is performed by the ACDH subsystem.
This subsystem includes the solar generator set (SADE and SADA), batteries and the power conditioning and distribution unit (PCDU).
This subsystem was designed in Brazil, by using "off the shelf" equipment available in the international market.
Provides heat distribution to the satellite so that all equipment operates within its projected temperature range. Satellite temperature control is maintained in all modes of operation of the satellite and during all phases of the mission.
This subsystem includes thermistors, heaters, blankets, radiators and internal and external insulation. The control for the heaters operations is managed by the ACDH subsystem.
This subsystem was designed and manufactured in Brazil, using some materials and parts available in the international market.
The telemetry and Telecommand (TT&C) subsystem provides communication between the platform and the TT&C earth station in order to ensure the monitoring and control of the satellite in all its modes of operation and during all phases of the mission.
This subsystem includes TT&C transponders, S-band antennas, diplexer, hybrid, waveguides and interconnection cables.
This subsystem was purchased in the international market.
