Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.

Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.

Abstract: The recovery device comprises a floating cradle configured to receive and support the vehicle, the cradle having an entrance for the vehicle situated at a rear end of the cradle and delimited between two lateral portions, the cradle being configured or capable of being configured with a rear lateral extension extending toward the rear from one of the two lateral portions, the other lateral portion having no rear lateral extension.

Abstract: Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Abstract: The recovery device comprises a floating cradle configured to receive and support the vehicle, the cradle having an entrance for the vehicle situated at a rear end of the cradle and delimited between two lateral portions, the cradle being configured or capable of being configured with a rear lateral extension extending toward the rear from one of the two lateral portions, the other lateral portion having no rear lateral extension.

Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for passively engaging with and securing the target vehicle.

Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints.

Abstract: Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

Abstract: An electret condenser microphone is provided. The electret condenser microphone comprises a diaphragm, a backplate with a metal layer on the side facing the diaphragm and an amplifier on the other side, the input of the amplifier electrically connecting the metal layer, a spacer separating the diaphragm and the backplate PWB; and a metal sleeve accommodating the diaphragm, the backplate and the spacer.

Abstract: Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Abstract: Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Abstract: The present disclosure provides a microphone including a main body, where an audio signal is generated in the main body based on the sound level and some other properties received, and an amplifier disposed in the main body, where the amplifier is adapted to amplify the audio signal, with the amplifier able to be configured with multiple gain levels. The present disclosure further provides a method for processing audio signals including: acquiring an audio signal; selecting a gain from multiple gain levels of an amplifier based on a property of the acquired audio signal, where the amplifier is built in a main body of a microphone; and modifying the digital representation after analog to digital conversion of the acquired audio signal according to the selected gain.

Abstract: An electret condenser microphone is provided. The electret condenser microphone comprises a diaphragm, a backplate with a metal layer on the side facing the diaphragm and an amplifier on the other side, the input of the amplifier electrically connecting the metal layer, a spacer separating the diaphragm and the backplate PWB; and a metal sleeve accommodating the diaphragm, the backplate and the spacer.

Abstract: The present disclosure provides a microphone including a main body, where an audio signal is generated in the main body based on the sound level and some other properties received, and an amplifier disposed in the main body, where the amplifier is adapted to amplify the audio signal, with the amplifier able to be configured with multiple gain levels. The present disclosure further provides a method for processing audio signals including: acquiring an audio signal; selecting a gain from multiple gain levels of an amplifier based on a property of the acquired audio signal, where the amplifier is built in a main body of a microphone; and modifying the digital representation after analog to digital conversion of the acquired audio signal according to the selected gain.

Abstract: Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Abstract: Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

Abstract: A method for packaging a plurality of microphones is provided. The method includes: obtaining a first parameter value, a second parameter value, and position information for each of the plurality of microphones and sorting the plurality of microphones by both the first parameter and the second parameter to obtain a sorted list which contains position information of the plurality of microphones. The method further includes packaging the plurality of microphones according to the sorted list.

Abstract: A system and method for RF immunity of an electret condenser microphone. In one embodiment, the microphone comprises a printed wire board, an amplifier, a capacitor. The amplifier and the capacitor are mounted on the printed wire board such that longitudinal axis, i.e., the axis defined by the line between the output pin and the ground pin, of the capacitor is perpendicular to the longitudinal axis of the amplifier. According to one embodiment of the method of the present invention, an electret condenser microphone according to the present invention is provided, and current is provided to the capacitor to result in the creation of a magnetic field about the longitudinal axis of the capacitor. The magnetic field created is positioned such that it does not significantly contribute to the generation of RF current in the amplifier.

Abstract: A bellows, spool, and collar system for dispensing projectiles and submunitions with a predictable and uniform pattern is disclosed. The system utilizes projectiles densely packed in a spool. A plurality of spools is packaged in a missile, bomb, or similar tubular device with an energetic bellows actuator between each spool. The energetic bellows actuator expands rapidly to push a spool of projectiles out of the tubular housing. Timing means is provided for each bellows to provide proper axial spacing between spools prior to subsequently timed release of the projectiles.