Abstract: A strut-and-node truss design that is applicable to space frame structure designs can be assembled with using robotic (semi-autonomous and/or fully autonomous) or telerobotic assembly/joining. The assembly system can include a storage module that includes the components for assembly and an assembly module that can retrieve and assembly the components. The resulting truss structure can be connected to an antenna (e.g., carried by the storage module) for deployment. The assembly module can be operated repeatedly in conjunction with additional resupply systems that provide additional components for assembly.

Abstract: A strut-and-node truss design that is applicable to all space frame structure designs can be made with using robotic (semi-autonomous and/or fully autonomous) or telerobotic assembly/joining. Nodes can include a 2-dimensional weld path in an effort to reduce the complexity of having to weld in 3-dimensions. Furthermore, each strut to node connection can be concentrated in a small area where each weld can be performed robotically from a fixed position that only requires the robotic weld head to swivel in a small operating window to reach each joint.

Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer.

Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N) for generating propulsive thrust along a thrust vector 8. One or more hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain produces exhaust gas only when oxidizer is provided. The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. The fuel grain can thus react quickly to a substantial flow of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle to disrupt the flow of propulsion fluid and modify the thrust vector.

Abstract: A rocket engine (10) generates a flow of hot propulsion fluid through a nozzle (14N). Hybrid exhaust gas generators (36,38) have their exhausts (44,54) through the side of the nozzle. Each gas generator includes a fuel grain (46,56) and a source of oxidizer (16,40,50). The fuel grain is kept hot by either or both (a) direct radiation or conduction from the hot propulsion fluid, or (b) by a trickle of oxidizer. When the thrust vector is to be modified, the appropriate one of the hybrid gas generators receives a flow of oxidizer, and the resulting exhaust gas is injected through the side of the nozzle.