Space Systems/loral, LLC

Marvell International Limited

Marvellworld Trade Ltd.

Yat Fai Leung

John Scott Higham

Scott W Tilley

Keith J Reckdahl

Tung Y Liu

Fatima Kazimi

Wallace S Boz, Ii

Embodiments include a testing arrangement for testing a first package, the testing arrangement comprising a frame having a top section and a bottom section, wherein the bottom section of the frame comprises a pickup section, and wherein the pickup section has a first air pathway; a second package mounted on a top surface of the bottom section of the frame such that a second air pathway is defined between (i) the second package and (ii) the top surface of the bottom section of the frame; and a vacuum path defined by (i) the first air pathway and (ii) the second air pathway, wherein during testing of the first package, a vacuum in the vacuum path is generated such that the pickup section of the bottom section of the frame holds the first package.

Method and apparatus for testing a semiconductor package having a package on package (PoP) design

Some of the embodiments of the present disclosure provide a method for operating a testing system to test a device, wherein the testing system comprises a pressing module, the method comprising attaching the device to the pressing module of the testing system; while the testing system operates in a first mode of testing, pressing the pressing module to a first position such that (i) the device is electrically coupled to a first component via a first pin, and (ii) the device is electrically isolated from a second component via a second pin; and while the testing system operates in a second mode of testing, pressing the pressing module to a second position such that (i) the device is electrically isolated from first component via the first pin, and (ii) the device is electrically coupled to the second component via the second pin.

Pressure activated high density switch array

A space vehicle includes an attachment system for attaching the vehicle to another space vehicle, a memory for storing data concerning the status of the other space vehicle and threats experienced by the other space vehicle, and a transmission system for transmitting data stored in the memory to a planet or a different space vehicle. An ejection system enables the secondary vehicle to be ejected from the primary vehicle when predetermined criteria concerning the status data or the threat data are met. A spin system causes the secondary vehicle to be spin stabilized when ejected from the primary vehicle. When the secondary vehicle is ejected, the nature of the threat or status of the primary vehicle can be determined.

Spacecraft attack and distress ejectable recorder

A spacecraft having a body, one or more appendages coupled thereto, and a controller that implements methods that rotate the one or more flexible appendages to point it (them) towards the Sun to reduce spacecraft attitude pointing disturbances and improves spacecraft attitude pointing. The steps of the one or more appendages are timed to deadbeat the disturbance imparted to the spacecraft body. Timing of the appendage steps may be such that the periodic disturbances are phased to substantially cancel each other, or phased to decrease the magnitude of the net disturbance. The present invention also cancels solar array slew disturbances. The present invention cancels predictable disturbance torques before they produce a pointing error, improving the spacecraft pointing performance. The present invention predicts a disturbance torque exerted on the body due to the controller moving the one or more appendages, calculates a feedforward torque necessary for the controller to cancel the disturbance torque and includes the feedforward torque in the calculation of the total control torque applied to the body.

Spacecraft and appendage stepping methods that improve spacecraft attitude pointing and cancel solar array slew disturbances

A system and method for RF autotracking multiple antennas to compensate for disturbances experienced by the antennas. The system and method uses two control algorithms implemented in fast and slow controllers and sums the result for each antenna that is tracked. One (fast) control algorithm corrects for rapid, common mode disturbances such as spacecraft motion disturbances, while the other (slow) control algorithm corrects for slower disturbances, such as thermal distortion, that do not affect all antennas in the same manner.

Dual RF autotrack control

A spacecraft orientation procedure, in accordance with a first embodiment of the invention, is practiced with a sun sensor to bring the x (roll) axis of the spacecraft parallel to a ray of the sun, and with a gyro sensor and an earth sensor of the spacecraft in conjunction with one instruction provided either autonomously or by a ground tracking station regarding an orientation of a spacecraft reference plane to enable locating the earth by the earth sensor. Furthermore, in accordance with a second embodiment of the invention, the orientation is established without aid from the ground tracking station by use of at least one telemetry and command antenna having a continuous field of view, as measured in one plane, which is greater than a semicircle. In the second embodiment, the orientation procedure provides for rotation of the spacecraft about the x axis for a scanning of the antenna to intercept command signals broadcast from the earth, thereby to locate the earth in a first reference plane. Rotation about the y (pitch) axis enables measurement of command signal strength for location of the earth in a second reference plane perpendicular to the first reference plane. Gyrocompassing establishes yaw in both embodiments of the invention.

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Granite Bay, CA, United States of America

Yat Fai Leung