Abstract: Technology for orbit raising of multiple spacecraft launched with a single launch vehicle. Two or more spacecraft are configured in a stacked launch configuration in which a lower spacecraft is mechanically coupled with a payload adapter of a launch vehicle with one or more upper spacecraft above the lower spacecraft. Propellant that is stored in the lower spacecraft during launch is transferred to an upper spacecraft in the stack after launch. The propellent may be used by the upper spacecraft for an orbit raising maneuver that raises the orbit of at least the upper spacecraft from a first orbit to a second orbit. Storing the propellant in the lower spacecraft lowers the center of mass of the stack during launch. Lowering the center of mass reduces the structural bending moment of the stack during launch, which allows a greater total launch mass.

Abstract: An example apparatus includes a first 3D printer head configured to form a spiral structure around a hub and a second 3D printer head configured to form a boom extending between the second 3D printer head and the hub. The apparatus further includes one or more actuators coupled to the first 3D printer head and the second 3D printer head to control a distance between the first 3D printer head and the second 3D printer head.

Abstract: An attitude control system for a satellite is presented that can determine on time values for attitude control thrusters without use of attitude rate sensors, such as those based on gyros. The attitude control systems uses the attitude values from a star tracker to determine both attitude adjustment values and attitude adjustment rate values directly from the star tracker values, where the processing is performed using quaternions. From the attitude adjustment values and attitude adjustment rate values, a set of thruster on time values are determined.

Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.

Abstract: An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.

Abstract: Various embodiments of the present technology relate to satellite tasking systems and methods. More specifically, embodiments include an operations center configured to receive a tasking order from a client and to generate satellite instructions for the satellite based on the tasking order. In some examples, a security tag is generated and associated with the tasking order. The security tag is correlated with the client on a remote server.

Abstract: Various embodiments of the present technology relate to synthetic aperture radar image capturing and scene reconstruction using a cluster of multi-static satellite receivers. More specifically, in some embodiments, the cluster of receivers retrieves a flight path over a communication network. Flying in-formation, a lead or main satellite sends radio or wave pulses to a target area and additional satellites capture an echo of the wave pulses after the waves bounce off the target area to capture SAR radar data. The radar data can be transmitted from the cluster of satellites to a radar stations or to the main satellite. The radar stations or the main satellite receive the SAR radar data and mapping to reconstruct the data as SAR image data that can be reconstructed as 2D or 3D landscapes and scenes using the SAR image data.

Abstract: A satellite includes a first radiator panel with first heat-generating components attached to its surface and a second radiator panel with second heat-generating components attached to its surface. One or more actuators are configured to deploy the first and second radiator panels from a compact configuration in which the first and second radiator panels are overlapping to a deployed configuration in which the first and second radiator panels are non-overlapping.

Abstract: Technology is disclosed herein for preventing or at least significantly reducing shock to spacecraft such as satellites when releasing a hold-down rod assembly that clamps the spacecraft to, for example, a launch vehicle adaptor. The hold-down rod assembly has tension rods that may be pre-loaded at considerable tension in order to hold down a stack of spacecraft in a launch configuration. In an embodiment, pneumatic actuators are used to slowly release the tension in the tension rods. Therefore, shock to the spacecraft is prevented or at least significantly reduced.

Abstract: Technology is disclosed herein for a payload dispensing hinge assembly. The payload dispensing hinge assembly has a first hinge-half and a second hinge-half that are joined by a hinge pin. The first hinge-half may be connected to a payload that is to be dispensed at a target angle. The second hinge-half may be connected to a payload base. The first hinge-half may have a first mounting bracket and a rotatable arm that are shaped to form interlocks that serve to dis-engageably link these two components. A biasing mechanism rotates the rotatable arm and hence the first mounting bracket and payload about a hinge line. The second hinge-half has a hinge stop that stops the rotation of the rotatable arm at a target angle, whereby the first bracket dis-engages from the rotatable arm to dispense the payload at the target angle.

Abstract: Technology is disclosed herein for dispensing stacked spacecraft. A stack of spacecraft may be joined together in an accordion configuration by dis-engageable links. A dis-engageable link may join two adjacent spacecraft at one edge of the spacecraft. Some of the links are on one side of the stack with other links on an opposite side of the stack to provide the accordion configuration. After the tie-down mechanism releases the stack of spacecraft from a launch adaptor the stack unfolds. Initially, the dis-engageable links continue to hold the spacecraft together in the accordion configuration with the angle between each pair of adjacent spacecraft increasing. After a pair of adjacent spacecraft have unfolded a sufficient amount to prevent collision, the dis-engageable links release one of the spacecraft to thereby dispense the spacecraft.

Abstract: Technology is disclosed herein for a payload dispensing hinge assembly. The payload dispensing hinge assembly has a first hinge-half and a second hinge-half that are joined by a hinge pin. The first hinge-half may be connected to a payload that is to be dispensed at a target angle. The second hinge-half may be connected to a payload base. The first hinge-half may have a first mounting bracket and a rotatable arm that are shaped to form interlocks that serve to dis-engageably link these two components. A biasing mechanism rotates the rotatable arm and hence the first mounting bracket and payload about a hinge line. The second hinge-half has a hinge stop that stops the rotation of the rotatable arm at a target angle, whereby the first bracket dis-engages from the rotatable arm to dispense the payload at the target angle.

Abstract: An artificial gravity heating system includes a cylindrical compartment formed of a hollow cylinder having a bottom base and an open top end. An electric motor rotates the cylindrical compartment to provide centripetal motion of materials inside the cylindrical compartment. While rotating, the materials move towards an inner wall of the cylindrical compartment. A heating element is conductively coupled along an outer wall of the cylindrical compartment for heating the materials against the inner wall via conduction. A temperature sensor is operatively coupled to the cylindrical compartment for monitoring a temperature of the cylindrical compartment. A controller is configured to control operation of the heating element based on the temperature monitored via the temperature sensor. An artificial gravity heating method is used to process materials including heating ingredients to cook food. The artificial gravity heating system may also be configured as a vapor generator dehydrator or a thermal gas generator.

Abstract: A passively damped mechanical system is disclosed, for example for use in aerospace applications where vibration can adversely affect navigational and operational instruments. In one example, the passively damped mechanical system includes an end fitting of a strut used to connect a structural element to a payload. The end fitting may include outer and inner cylindrical hubs, with a space between the outer and inner cylindrical hub at least partially filled with a viscoelastic material. In a further example, the passively damped mechanical system includes legs used to connect a structural element to a bracket configured to support a payload. Each leg may include a hollow interior having a lattice structure to add strength and a viscoelastic material to provide passive damping.

Abstract: The invention involves an method, which includes providing a plurality of game cards, each having a grid of tiles formed in a plurality of rows and a plurality of columns. Each tile corresponds to a defined result chosen from a plurality of defined results. The method includes selecting a tile from each of the plurality of game cards, and comparing the defined result of the selected tile to a selected one of the plurality of defined results. The selected one of the plurality of defined results is selected in response to an occurrence.

Abstract: The present disclosure presents lighting control systems and related methods. One such system comprises a light emitting device comprising a plurality of channels, each channel of the plurality of channels including one or more light emitting diodes configured to emit light at a respective predominant wavelength, and a plurality of direct current drivers, each direct current driver of the plurality of direct current drivers supplying power to a respective channel of the plurality of channels. The system further includes a router module that is configured to communicate with the light emitting device; and a graphical user interface configured to specify and control a plurality of parameters of each channel of the plurality of channels, wherein the plurality of parameters enable adjustment of a spectral content, intensity, and schedule of illumination, in addition to enabling a DC mode of operation or a pulse width modulation (PWM) mode of operation.

Abstract: A satellite propellant tank includes a tank body and a dome attached to the tank body to enclose an interior volume for propellant storage. One or more cavities are formed in the dome. One or more propellant control components are located in the one or more cavities formed in the dome.

Abstract: An example of an apparatus includes a spacecraft body and a solar array that is attached to the spacecraft body. In addition, a solar array spring element is configured to provide a force between the solar array and one or more components of a neighboring spacecraft in a stack of spacecraft.

Abstract: An example of an apparatus includes an inlet to connect to a propellant source a pressure regulator connected to the inlet to reduce propellant pressure from a first pressure at the inlet to a second pressure. The apparatus includes a manifold connected to the pressure regulator to receive propellant from the pressure regulator at the second pressure and includes a plurality of manifold outlets. The apparatus further includes a plurality of gas lines, each gas line extending from a corresponding manifold outlet for connection to a corresponding satellite propellant tank.