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US 9,957,068 B2Granted
Multiple space vehicle launch system
AssigneeThe Boeing Company
InventorsRichard W. Aston, Anna M. Tomzynska, Glenn N. Caplin
Life of this patent
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Abstract
A space vehicle system, a method of manufacturing the space vehicle system, and a method of launching the space vehicle system are disclosed. The method of manufacturing the space vehicle system may include disposing a first space vehicle with an upper core structure upon a second space vehicle with a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle.
Claims26
A method of manufacturing a space vehicle system, the method comprising:
- disposing a first space vehicle having an upper core structure upon a second space vehicle having a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle;
- mounting a first shear load panel on the upper core structure and a second shear load panel on the lower core structure;
- and
- supporting a first solar array by the first shear load panel and a second solar array by the second shear load panel, wherein the first solar array defines a lower edge and the second solar array defines an upper edge, and wherein the lower core structure of the second space vehicle extends upwardly above the upper edge of the second solar array to engage the upper core structure of the first space vehicle, and the upper core structure does not extend past the lower edge of the first solar array.
1 more element
A method of assembling a space vehicle system, the method comprising:
- disposing a first space vehicle having an upper core structure upon a second space vehicle having a lower core structure such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle;
- disposing the first space vehicle and the second space vehicle into a payload region of a launch vehicle;
- mounting a first shear load panel on the upper core structure and a second shear load panel on the lower core structure;
- and
- supporting a first solar array by the first shear load panel and a second solar array by the second shear load panel, wherein the first solar array defines a lower edge and the second solar array defines an upper edge, and wherein the lower core structure of the second space vehicle extends upwardly above the upper edge of the second solar array to engage the upper core structure of the first space vehicle, and the upper core structure does not extend past the lower edge of the first solar array.
2 more elements
A space vehicle system, comprising:
- a first space vehicle having an upper core structure, a first solar array, and a first shear load panel, wherein the first shear load panel is mounted on the upper core structure, the first shear load panel supports the first solar array, and the first solar array defines a lower edge;
- and
- a second space vehicle having a lower core structure, a second solar array, and a second shear load panel, wherein the second shear load panel is mounted on the lower core structure, the second shear load panel supports the second solar array, and the second solar array defines an upper edge, and wherein the first space vehicle is disposed upon the second space vehicle such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle, and wherein the lower core structure of the second space vehicle extends upwardly above the upper edge of the second solar array to engage the upper core structure of the first space vehicle, and the upper core structure does not extend past the lower edge of the first solar array.
A method of launching a space vehicle system including a first space vehicle having an upper core structure disposed upon a second space vehicle having a lower core structure, the method comprising:
- mounting a first shear load panel on the upper core structure and a second shear load panel on the lower core structure;
- supporting a first solar array by the first shear load panel and a second solar array by the second shear load panel, wherein the first solar array defines an upper edge and the second solar array defines a lower edge;
- extending the lower core structure upwardly above the upper edge of the second solar array to engage the upper core structure of the first space vehicle, wherein the upper core structure does not extend past the lower edge of the first solar array;
- causing loads associated with the first space vehicle to be transmitted to and borne by the lower core structure of the second space vehicle;
- and
- launching the first space vehicle and the second space vehicle.
3 more elements
A space vehicle system, comprising:
- a first space vehicle having an upper core structure, a first solar array, and a first shear load panel, wherein the first shear load panel is mounted on the upper core structure, the first shear load panel supports the first solar array, and the first solar array defines a lower edge;
- and
- a second space vehicle having a lower core structure, a second solar array, and a second shear load panel, wherein the second shear load panel is mounted on the lower core structure, the second shear load panel supports the second solar array, and the second solar array defines an upper edge, and wherein the first space vehicle is disposed upon the second space vehicle prior to deployment of the space vehicle system such that loads of the first space vehicle are transmitted to the lower core structure of the second space vehicle, and the first space vehicle and the second space vehicle are separated from one another during the deployment of the space vehicle system, and wherein the lower core structure of the second space vehicle extends upwardly above the upper edge of the second solar array to engage the upper core structure of the first space vehicle, and the upper core structure does not extend past the lower edge of the first solar array.
Dependencies are inferred from the claim text.