Abstract: A control system for reducing disturbance torque of a spacecraft is disclosed. The spacecraft revolves around a celestial body surrounded by an atmosphere. The control system includes processors in electronic communication with one or more actuators and a memory. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the spacecraft to enter a safing mode. In response to entering the safing mode, the control system instructs the one or more actuators to align a principal axis of the spacecraft with a vector that is normal to the orbit around the celestial body. The control system also instructs the actuators to rotate the spacecraft about the principal axis, where a rotational orientation of the spacecraft relative to the celestial body is shifted by about one-half a rotation about the principal axis.

Abstract: A stretchable watch band can include braided strands that provide a comfortable fit around the wrist of the user. The watch band can stretch and conform to the user based on the elasticity within each strand and based on the ability of the strands to move relative to each other. End sections of the watch band can include attachment elements that securely connect the watch band to a housing of the watch. The end sections can be configured to releasable connect to the housing in a manner that is reliable and easy for a user. Additionally, the watch band can provide a smooth transition from the size and/or shape of the housing to a size and/or shape of a continuous section of the watch band. Additionally, the watch band can conceal portions thereof other than the braided strands when connected to the housing of the watch.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: A control system for reducing disturbance torque of a spacecraft is disclosed. The spacecraft revolves around a celestial body surrounded by an atmosphere. The control system includes processors in electronic communication with one or more actuators and a memory. The memory stores data into a database and program code that, when executed by the one or more processors, causes the control system to instruct the spacecraft to enter a safing mode. In response to entering the safing mode, the control system instructs the one or more actuators to align a principal axis of the spacecraft with a vector that is normal to the orbit around the celestial body. The control system also instructs the actuators to rotate the spacecraft about the principal axis, where a rotational orientation of the spacecraft relative to the celestial body is shifted by about one-half a rotation about the principal axis.

Abstract: A stretchable watch band can include braided strands that provide a comfortable fit around the wrist of the user. The watch band can stretch and conform to the user based on the elasticity within each strand and based on the ability of the strands to move relative to each other. End sections of the watch band can include attachment elements that securely connect the watch band to a housing of the watch. The end sections can be configured to releasable connect to the housing in a manner that is reliable and easy for a user. Additionally, the watch band can provide a smooth transition from the size and/or shape of the housing to a size and/or shape of a continuous section of the watch band. Additionally, the watch band can conceal portions thereof other than the braided strands when connected to the housing of the watch.

Abstract: A stretchable watch band can include braided strands that provide a comfortable fit around the wrist of the user. The watch band can stretch and conform to the user based on the elasticity within each strand and based on the ability of the strands to move relative to each other. End sections of the watch band can include attachment elements that securely connect the watch band to a housing of the watch. The end sections can be configured to releasable connect to the housing in a manner that is reliable and easy for a user. Additionally, the watch band can provide a smooth transition from the size and/or shape of the housing to a size and/or shape of a continuous section of the watch band. Additionally, the watch band can conceal portions thereof other than the braided strands when connected to the housing of the watch.

Abstract: This application relates to a portable electronic device that includes an integrated pressure sensor. The portable electronic device includes a housing that defines a cavity with a number of components disposed therein. The cavity is sealed to form a volume of air within the cavity that is vented to the external environment through a barometric vent fluidly coupled to a first opening in the housing. A sensor measures a characteristic of a second volume of air within an isolated chamber that is vented to the external environment through a second opening in the housing. The second volume of air is isolated from the first volume of air within the housing of the portable electronic device. In some embodiments, the portable electronic device is a mobile phone and the sensor is a pressure transducer.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Aspects of the subject technology relate to electronic devices having sensors such as pressure sensors. A pressure sensor may be integrated into an audio component of an electronic device such that the pressure sensor is fluidly coupled to an environment external to a device housing via at least a portion of an internal cavity of the audio component housing. The audio component housing may include an opening. The pressure sensor may be mounted adjacent to or within the opening. The opening may be sealed to prevent passage of gas or liquid through the opening. The pressure sensor may be integrally formed with an inner wall of the audio component housing. The audio component may be a speaker or a microphone.

Abstract: Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.

Abstract: Methods, apparatus, and articles of manufacture to minimize command dynamics of a satellite are disclosed. An example apparatus includes a steering law module to calculate a first set of vectors to maneuver a space vehicle, and calculate a second set of vectors based on projecting the first set of vectors onto a fixed plane. The apparatus further includes an attitude controller to generate an attitude command based on the first and the second sets of vectors to prevent an unplanned rotation by the space vehicle.

Abstract: An electronic device having several modifications designed to prevent liquid ingress into an opening (or openings) of the electronic device is disclosed. For example, the electronic device includes a SIM tray having a sealing element designed to provide a seal at an opening that receives the SIM tray. The sealing element may include a first section and a second section extending from the first section, with the first section designed to bend with respect to (and in some cases collapse onto) the second section. The electronic device may further include an audio module fitted with a sealing element. The sealing element may include extensions extending away from a main body of the sealing element, with some extension designed to engage the audio module, and other extensions designed to engage an audio module interface. The sealing element provides a seal against liquid ingress into the audio module.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

Abstract: An electronic device having liquid-resistant modifications that prevent liquid ingress into an opening (or openings) in an enclosure of the electronic device is disclosed. For example, the electronic device may include a coating formed from a liquid-resistant material that is applied internally to the enclosure. The electronic device may further include a frame that carries a protective transparent layer designed to cover a display assembly. In order to secure the frame with the enclosure, the electronic device may include an adhesive assembly disposed over an outer perimeter of the coating. The adhesive assembly may include several adhesive parts initially separate from one another. However, with the adhesive parts between the frame and the enclosure, the adhesive parts can be compressed by the frame and the enclosure, causing the adhesive parts to expand and engage each other. As a result, the coating and the adhesive parts provide a seal against liquid.

Abstract: An electronic device having several modifications designed to prevent liquid ingress into an opening (or openings) of the electronic device is disclosed. For example, the electronic device includes a SIM tray having a sealing element designed to provide a seal at an opening that receives the SIM tray. The sealing element may include a first section and a second section extending from the first section, with the first section designed to bend with respect to (and in some cases collapse onto) the second section. The electronic device may further include an audio module fitted with a sealing element. The sealing element may include extensions extending away from a main body of the sealing element, with some extension designed to engage the audio module, and other extensions designed to engage an audio module interface. The sealing element provides a seal against liquid ingress into the audio module.

Abstract: An electronic device having liquid-resistant modifications that prevent liquid ingress into an opening (or openings) in an enclosure of the electronic device is disclosed. For example, the electronic device may include a coating formed from a liquid-resistant material that is applied internally to the enclosure. The electronic device may further include a frame that carries a protective transparent layer designed to cover a display assembly. In order to secure the frame with the enclosure, the electronic device may include an adhesive assembly disposed over an outer perimeter of the coating. The adhesive assembly may include several adhesive parts initially separate from one another. However, with the adhesive parts between the frame and the enclosure, the adhesive parts can be compressed by the frame and the enclosure, causing the adhesive parts to expand and engage each other. As a result, the coating and the adhesive parts provide a seal against liquid.