초록 ▼

The invention relates to a piggyback satellite, a device for and a method of attaching piggyback satellites with multiple payloads, including a primary satellite and at least one secondary payload, such as a deployable micro satellite, affixed instrument package or the like, wherein the secondary pa

The invention relates to a piggyback satellite, a device for and a method of attaching piggyback satellites with multiple payloads, including a primary satellite and at least one secondary payload, such as a deployable micro satellite, affixed instrument package or the like, wherein the secondary payload is mounted on the nadir end of the primary satellite, preferably employing a universal adapter between the primary satellite and the at least one secondary payload that releases at least one secondary payload or the like in a certain orbit in space for allowing the secondary payload to continue its journey independently in space for transmitting and receiving data.

대표청구항 ▼

What is claimed is: 1. A method of assembling and deploying at least two satellites arranged in a piggyback configuration with a launch vehicle, the method comprising:providing a primary satellite having a nadir end and an apogee end, said satellite being equipped with deployable telecommunications

What is claimed is: 1. A method of assembling and deploying at least two satellites arranged in a piggyback configuration with a launch vehicle, the method comprising:providing a primary satellite having a nadir end and an apogee end, said satellite being equipped with deployable telecommunications antennae, deployable solar panels and a primary satellite propulsion system operative to lift the primary satellite into geostationary orbit after separation from the launch vehicle, and being further equipped with an adaptor to mate to a secondary micro-satellite;providing at least one secondary micro-satellite having a nadir end and an apogee end;affixing at least one secondary micro-satellite at its apogee end to the nadir end of the primary satellite using the adapter,wherein the adapter further comprises a first coupling structure and a second coupling structure, the first coupling structure being disposed on the nadir end of the primary satellite and positioned for support by the primary satellite support structure, and the second coupling structure is disposed on an apogee end portion of the secondary micro-satellite,securing the first coupling structure to the second coupling structure prior to launch to form a combined payload package comprising the primary satellite and the at least one secondary micro-satellite,launching the combined payload package with the launch vehicle,releasing the combined payload package from the launch vehicle along an orbit raising path for the primary satellite and operating the propulsion system to lift the primary satellite into geostationary orbit after separation from the launch vehicle; andcontrollably activating the adaptor for releasing the secondary micro-satellite along the parent's orbit-raising secondary micro-satellite along said primary satellite's orbit-raising path up to and including geostationary orbit (GEO) after launch, whereby the primary satellite serves as an upper stage for launch of said secondary micro-satellite and places the secondary micro-satellite into orbit without releasing any debris.