Abstract: A method for deploying multiple spacecraft is disclosed. The method can be used in a situation where a first celestial body is being orbited by a second celestial body. The spacecraft are loaded onto a single spaceship that contains the multiple spacecraft and the spacecraft is launched from the second celestial body towards a third celestial body. The spacecraft are separated from each other while in route to the third celestial body. Each of the spacecraft is then subjected to the gravitational field of the third celestial body and each of the spacecraft assumes a different, independent orbit about the first celestial body. In those situations where the spacecraft are launched from Earth, the Sun can act as the first celestial body, the Earth can act as the second celestial body and the Moon can act as the third celestial body.

Abstract: A method and apparatus is disclosed for accurately determining the spatial orientation of planar and linear features expressed along the exterior surface of a core sample. The core sample is positioned in a plurality of sequentially generated orthogonal electromagnetic fields. The core sample is retained by a device which allows complete rotation of the core sample about a predetermined axis while positioned in the electromagnetic fields. A stylus containing an antenna for detecting the electromagnetic fields is used to trace surficial features along the core exterior while simultaneously detecting components of the generated electromagnetic fields. The stylus provides an output to an analyzing device which calculates the coordinates of points along the core features. The coordinates are passed to a computer which has also been monitoring the rotation angle of the core.