Abstract: A satellite is disclosed, including a body and a communication device attached to the body. The body has an additively manufactured external wall structure at least partially forming an enclosed compartment, and the communication device is configured to receive and transmit data while in space.

Abstract: A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.

Abstract: A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.

Abstract: A spacecraft panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members, and each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure.

Abstract: A satellite is disclosed, including a body having an additively manufactured wall panel and a communication device connected to the body. The wall panel includes a facesheet and a stiffening structure extending from a first side of the facesheet. The communication device is configured to send and receive data while in space.

Abstract: A satellite is disclosed, including a body having an additively manufactured wall panel and a communication device connected to the body. The wall panel includes a facesheet and a stiffening structure extending from a first side of the facesheet. The communication device is configured to send and receive data while in space.

Abstract: A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.

Abstract: A satellite is disclosed, including a body and a communication device attached to the body. The body has an additively manufactured external wall structure at least partially forming an enclosed compartment, and the communication device is configured to receive and transmit data while in space.

Abstract: A method of additively manufacturing a spacecraft panel includes printing a first skin and a second skin, spaced apart from the first skin. The method further includes printing a first truss structure connecting the first skin to the second skin.