The invention provides a low-orbit load platform separated remote sensing microsatellite configuration including a platform metal frame plate structure, a load bracket integrated structure, a frame separation mechanism, a plate type solar wing deployment mechanism and various devices. In a frame plate type structure, similar to a conventional base plate, side plate and top plate type structure, all structural plates adopt a thin metal plate + rib + lightening design; the whole structure adopts the base plate as the design and assembly standard, and a main force transferring route is from the base plate, to the side plate, to the top plate and then to the load. The load bracket integrated structure is mounted on a satellite top plate. A bracket can be connected to the top plate, the bracketcan be provided with a partial air-oriented device and can also be connected to a solar wing, the solar wing includes a one-fold fixing and two-folding unfolding type solar wing, and the solar wing is connected to the satellite side plate and the top plate bracket mainly through a fixing type solar wing. The microsatellite configuration has high space utilization, compact structure and small size, the final assembly process is good in openness, the test is convenient, and the configuration is not adjusted under the conditions of replacing the load of the same magnitude.