초록

A separation frame for mounting and separating satellites in a launch vehicle, includes two congruent frames (10, 12) are arranged one inside the other. The frames are connected to each other by means of a swivel joint.

대표청구항 ▼

1. A frame assembly for separably mounting satellites in a launch vehicle, said frame assembly comprising: first and second correspondingly shaped frames arranged one inside the other; a joint rotatably connecting said first and second frames; first releasable connectors for detachably mounting

1. A frame assembly for separably mounting satellites in a launch vehicle, said frame assembly comprising: first and second correspondingly shaped frames arranged one inside the other; a joint rotatably connecting said first and second frames; first releasable connectors for detachably mounting said satellite to said launch vehicle via said first frame; and second releasable connectors for detachably mounting said satellite to said second frame. 2. The frame assembly according to claim 1, wherein: said first frame is an outer frame; said second frame is an inner frame; and the inner frame is rotatable relative to the outer frame about an axis of rotation through the joint, such that a separation axis of a satellite attached to said second frame runs through a center of gravity of the satellite and of a remaining body of said launch vehicle. 3. The frame assembly according to claim 1, wherein the outer frame and the inner frame, respectively, have the form of satellite interfaces. 4. Apparatus for separably mounting a satellite to a launch vehicle, comprising: a first frame having releasable connectors for detachably mounting said satellite to said launch vehicle via said first frame; a second frame having releasable connectors for detachably mounting the satellite to the second frame, said second frame being coupled to said first frame via a rotation joint; wherein said second frame has a shape that corresponds to a shape of first frame; said second frame is rotatable about said joint between a first position in which said second frame is substantially coplanar with and nested within said first frame, and a second position in which a plane of said second frame is inclined at a preselected angle relative to a plane of said first frame. 5. The apparatus according to claim 4, further comprising: a driver for causing said second frame to rotate from said first position to said second position; and locking apparatus for fixing said second frame in said second position; wherein said preselected angle is such that a separation axis of a satellite detachably connected to said second frame passes through a center of gravity of the satellite and of a remaining mass of said launch-vehicle. 6. A method of separating a satellite from a launch vehicle, comprising: detachably mounting a first frame to said launch vehicle via releasable connectors that detachably mount said satellite to said launch vehicle via said first frame; detachably mounting said satellite to a second frame which has a shape corresponding to a shape of said first frame, is connected to said first frame via a rotation joint, and is rotatable about said joint between a first position in which said second frame is substantially coplanar with said first frame and nested inside said first frame, and a second position in which a plane of said second frame is inclined at a preselected angle relative to a plane of said outer frame; deploying said second frame initially in said first position, whereby a satellite detachably mounted thereto is detachably connected to said launch vehicle via said first frame during a launch of said satellite; and following a release of said releasable connectors, rotating said second frame from said first position to said second position; and detaching said satellite from said second frame. 7. The method according to claim 6, wherein said preselected angle is such that a separation axis of said satellite passes through a center of gravity of the satellite and of a remaining mass of said launch-vehicle.