USA As Represented by Secretary of the Navy

University of California

Marcello Romano

Paul Oppenheimer

James Hansen Newman

William Mike Crane

Oscar Biblarz

Sergio R Restaino

Joseph Helmboldt

Simone Chesi

Josep Virgili-Llop

Richard Salvatore Zappulla, Ii

A method of simulating 3-degrees of freedom spacecraft rotational dynamics is provided that includes attaching a payload, using a spherical air bearing, to an inner gimbal of a 3-axis gimbal, where the 3-axis gimbal includes an outer gimbal, a mid-gimbal and the inner gimbal, using a motion controller to control motion of each the gimbal of the 3-axis gimbal, where the motion controller includes an appropriately programmed computer and a motion control motor, sensing limits of free travel of the spherical air bearing, using a position sensor, and changing a position of the 3-axis gimbal away from the limit of free travel of the spherical air bearing when the spherical air bearing approaches the limit of free travel, wherein the position change effects travel of the spherical bearing to be unbounded by the limit of free travel, wherein 4&#x3c0; steradians spacecraft dynamics of the payload are simulated.

Angularly unbounded three-axis spacecraft simulator

Systems, methods, and apparatuses for determining the distance between two positions are disclosed. The system includes a correlator, a first receiver, and a second receiver. The first and second receivers each include: an antenna, a steering mechanism, and a processor. The steering mechanism steers the antenna in an azimuthal direction and an elevation direction. The processor is configured to (i) control the steering mechanism, (ii) receive data recorded by the antenna from a plurality of sources, (iii) time-stamp the data recorded by the antenna, and (iv) control the transmission of the time-stamped data to the correlator. The correlator is configured to receive the time-stamped recorded data from the first receiver and the second receiver, and calculate a distance between the first receiver and the second receiver based thereon.

Systems, methods, and apparatuses for determining the distance between two positions

An agile attitude control system (AACS) that is a three axis attitude control device for small spacecraft based on miniature single gimbal control moment gyroscopes (SGCMGs) actuators. The AACS enables agile attitude slewing and accurate pointing/tracking for spacecraft made of multiple CubeSat units, or, more generally, for nanosatellites.

Agile attitude control system for small spacecraft

Disclosed is a planar test bed comprising a planar surface and further comprising mechanical couplings in mechanical communication with the planar table and the supporting legs. The mechanical couplings are translatable to provide three degrees of freedom for orientation of the planar surface. A processor receives position and velocity information describing an object on the planar surface, and calculates a relative acceleration typically using a function a=f(t,x,v,&#x3bc;). The processor communicates with the mechanical couplings to establish an orientation where a local gravity vector projects onto the planar surface and generates acceleration with magnitude and direction substantially equal to the desired acceleration aThe operations occur in cyclic fashion so the desired accelerations and planar orientations are updated as an object transits over the planar surface.

Dynamically tilting flat table to impart a time-varying gravity-induced acceleration on a floating spacecraft simulator

A field-ionization based electrical ion thruster utilizes a single propellant that can be used in either a high specific-impulse mode, i.e., ion-thruster mode, or a low-specific-impulse mode, i.e., a cold-gas thruster mode. In one embodiment, the high specific impulse mode (ion thruster mode) utilizes a miniaturized positive-ion field-ionization chamber including a permeable substrate infused with properly oriented carbon nanotubes (CNTs), which is fed propellant from a porous injection plug made from permeable carbon or equivalent material. In one embodiment, field-electron emission from a neutralizer, such as a carbon nanotube array neutralizer, positioned after one or more accelerator grids is used for ion neutralization. In one embodiment, the low specific-impulse (cold-gas mode) uses a conventional supersonic nozzle-expansion to generate thrust. In one embodiment, both the high specific-impulse mode and the low specific-impulse mode thruster embodiments share the same gas propellant, storage propellant tank, and delivery equipment.

Field-ionization based electrical space ion thruster using a permeable substrate

A micro-coupling active release mechanism including a shape memory alloy (SMA) cylindrical ring that is fit into a bushing or other mating attachment creating an interference joint held in place by frictional forces. The interference joint can be released upon actuation in which the SMA cylindrical ring is heated causing it to shrink in size, relieving the frictional forces of the interference joint thereby releasing the SMA cylindrical ring from the bushing or other mating attachment.

Micro-coupling active release mechanism

A demountable docking interface mechanism and method for docking and undocking two spacecraft utilizing the demountable docking interface mechanism.

Growing community of inventors

Monterey, CA, United States of America

Marcello Romano