Abstract: A spacecraft trash disposal apparatus and method are disclosed. The spacecraft trash disposal apparatus includes an airlock, an inflatable trash enclosure holding trash, and a pressure regulating system. The spacecraft trash disposal apparatus permits wet and dry trash to be transported from the inside of a spacecraft via the inflatable trash enclosure holding the trash. The inflatable trash enclosure is ejected to the surrounding vacuum of space without causing trash or liquids to escape from the inflatable trash enclosure. The pressure regulating system permits reduction of pressure inside the inflatable trash enclosure from typically atmospheric to a lower pressure while the airlock is depressurizing without going to a full vacuum. This lower pressure is such that, at a given temperature, the liquid trash is prevented from boiling. The lower pressure permits a lightweight inflatable trash enclosure for low cost spacecraft trash disposal.

Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.

Abstract: An impact driver separation device for spacecraft and other vehicular separation mechanisms including a first element, second element, first connector, second connector, and impact actuator. The first element and the second element are joined by the first connector and the second connector. The impact actuator connects to the first connector or the second connector. In one example, the first connector is a bolt, and the second connector is a nut. In another example, the first connector is a nut, and the second connector is a bolt. When the impact actuator connects to the first connector, the impact actuator permits removal of the first connector from the second connector for separation of the first element and the second element. When the impact actuator connects to the second connector, the impact actuator permits removal of the second connector from the first connector for separation of the first element and the second element.

Abstract: A launch vehicle dispenser attach structure is disclosed. The launch vehicle dispenser attach structure includes a launch vehicle adapter, and a polygonal extruded cylinder comprising tapered side and an essentially closed end. The polygonal extruded cylinder connects to the launch vehicle adapter. The tapered sides and the closed end of the polygonal extruded cylinder provide mounting interfaces for connecting satellite dispensers. A mounting interface of the mounting interfaces includes a separation ring for transforming the launch vehicle dispenser attach structure into a free flying satellite. The launch vehicle dispenser attach structure is particularly useful for attaching multiple payload separation systems to launch vehicle.

Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.

Abstract: An impact driver separation device for spacecraft and other vehicular separation mechanisms including a first element, second element, first connector, second connector, and impact actuator. The first element and the second element are joined by the first connector and the second connector. The impact actuator connects to the first connector or the second connector. In one example, the first connector is a bolt, and the second connector is a nut. In another example, the first connector is a nut, and the second connector is a bolt. When the impact actuator connects to the first connector, the impact actuator permits removal of the first connector from the second connector for separation of the first element and the second element. When the impact actuator connects to the second connector, the impact actuator permits removal of the second connector from the first connector for separation of the first element and the second element.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

Abstract: Embodiments of the present disclosure describe seed, soil, or plant treatment compositions comprising a macronutrient source comprising or consisting of a mineral lactate. Embodiments also describe methods of synthesizing a mineral lactate comprising providing a solution of lactic acid in a first vessel; contacting the solution of lactic acid with a mineral precursor to form a reaction solution in which at least a portion of the mineral precursor is dissolved; allowing the reaction to proceed or optionally transferring the reaction solution to a second vessel where the reaction is allowed to proceed; and optionally reducing the solid mineral lactate to a select particle size to obtain a rapidly soluble solid mineral lactate. Embodiments also describe methods of applying a treatment composition to a seed, soil, or a plant, wherein the treatment composition comprises a macronutrient source comprising or consisting of a mineral lactate.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station. The spacecraft airlock system provides a defined volume of space payload to the international space station. The airlock further includes a means of attaching to a space station, a closed structure attached to said means, said means of attaching is capable of robotic manipulation, and a cooling system for cooling payload components within said closed structure.

Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module.

Abstract: A representative spacecraft system includes a launch vehicle elongated along a launch vehicle axis and having at least one stage carrying a corresponding rocket engine. The representative system further includes an annular support structure carried by the at least one stage and positioned to support a cargo spacecraft having a service module and a cargo module. The cargo module of the cargo spacecraft is positioned along the launch vehicle axis in a direction distal from the support structure, and at least a portion of the service module of the cargo spacecraft positioned within an annulus of the support structure.

Abstract: Various seed, soil, and plant treatment compositions, methods of applying such compositions, and the like are described herein. The treatment compositions can comprise one or more zinc compounds, one or more iron compounds, and/or one or more molybdenum compounds. Applications of the treatment compositions can include being placed in-furrow, side-dressed in fields, used as foliar treatments, broadcast in soil, tilled in soil, or otherwise applied to seeds, soils, or plants.

Abstract: The invention discloses a modular satellite deployer system and method utilizing a novel geometric door configuration employing a novel geometry that permits any number or combination of satellites to deploy from a common sized satellite deployer. The satellite deployer system includes an enclosure. The satellite deployer system includes two or more satellites shaped to conform with the inside of the enclosure. The satellite deployer system includes multi segmented doors, door release mechanisms, and multi segmented ejector mechanisms. Each of multi segmented ejector mechanisms is capable of pushing a satellite of the two or more satellites out of the enclosure. Two or more satellites deploy from the enclosure in any desired sequence by selectively opening the multi segmented doors using the multi segmented door release mechanisms and the multi segmented ejector mechanisms.

Abstract: A structural system and a method for joining a launch vehicle and with satellites are disclosed. The method includes generating centerlines of objects requiring a connection for a structure, generating hemispheres about the centerlines, shelling of the hemispheres; performing a finite element analysis (FEA) for verifying the strength of the structure; and increasing or decreasing the thickness of the hemispheres for providing both optimal strength and minimum mass for the structure. The novel design and construction of interconnected hemispheres provide nearly the maximum physical strength for a given amount of material that could otherwise not be accomplished by utilization of a single spherical structure. In addition, the structure permits the construction of modular elements that are readily constructed using generally low-cost, simple, reliable and verifiable methods.

Abstract: A method and apparatus for deploying satellites is disclosed a satellite deployment mechanism includes an enclosure having at least one door, a lift table implemented therein, and a spring arranged to apply force to the lift table. A mounting system is arranged to allow for the satellite deployment mechanism to be mounted to a portion of a spacecraft. Responsive to opening the at least one door, the spring may cause the lift table to eject one or more satellites from the enclosure.

Abstract: A payload mounting system including a launch vehicle attach structure with radial ports, payloads, and a moment transmitting structure. The payloads attach to the radial ports. The moment transmitting structure attaches to the payloads surrounding said launch vehicle attach structure to minimize the moment transmitted to the radial ports thus maximizing the launch mass capability of the launch vehicle attach structure. The payload mounting system presents a novel evolved expendable launch vehicle (EELV) secondary payload adapter (ESPA) port small payload mounting system that permits maximum mass utilization of each ESPA ports without regard to center of gravity constraints. In one or more embodiments, the payload mounting system enables to connect, in the unused central volume of an ESPA ring, the adjacent faces of at least two payloads on opposing sides of an ESPA ring with a cross-reaching moment transmitting structure that reduces moments transmitted to the ESPA ring.

Abstract: The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

Abstract: An impact driver separation device for spacecraft and other vehicular separation mechanisms including a first element, second element, first connector, second connector, and impact actuator. The first element and the second element are joined by the first connector and the second connector. The impact actuator connects to the first connector or the second connector. In one example, the first connector is a bolt and the second connector is a nut. In another example, the first connector is a nut and the second connector is a bolt. When the impact actuator connects to the first connector, the impact actuator permits removal of the first connector from the second connector for separation of the first element and the second element. When the impact actuator connects to the second connector, the impact actuator permits removal of the second connector from the first connector for separation of the first element and the second element.