A microfabricated valve with no moving parts. In one embodiment, the valve includes a reservoir of a liquid that is in fluid communication with an outlet channel having a throat that is less than 100 microns wide. Preferably, the channel is an elongated slit. The configuration of channel is adapted and configured such that surface tension of the liquid prevents flow out of the channel. A heater increases the temperature of the meniscus of the fluid, until a portion of the fluid is ejected from the channel. The ejection of the fluid creates both a thrusting effect and a cooling effect.

A microfabricated valve with no moving parts. In one embodiment, the valve includes a reservoir of a liquid that is in fluid communication with an outlet channel having a throat that is less than 100 microns wide. Preferably, the channel is an elongated slit. The configuration of channel is adapted and configured such that surface tension of the liquid prevents flow out of the channel. A heater increases the temperature of the meniscus of the fluid, until a portion of the fluid is ejected from the channel. The ejection of the fluid creates both a thrusting effect and a cooling effect.

A system for vibration control of a cryocooler that cools an imager. The system includes a vibration sensor that is physically affixed to the cryocooler. The vibration sensor senses a physical vibration of the cryocooler and to generates a vibration signal therefrom. The system also includes cryocooler drive electronics operatively coupled to the vibration sensor and the cryocooler. The cryocooler drive electronics output a drive waveform that drives the cryocooler so as to reduce the vibration impact of the cryocooler. The harmonic content of the cryocooler drive waveform is controlled by the cryocooler drive electronics based on the vibration signal.

A self-adjusting passive radiative cooling panel for spacecraft including a dielectric (e.g., HfO.sub.2) layer sandwiched between a mirror layer and spaced-apart thin-film phase-change (e.g., thermochromic) material islands disposed in a grating pattern having a lattice constant in the 2 to 10 μm range, depending on expected spacecraft operating temperatures. At low temperatures the phase-change material islands enter dielectric state phases that prevent generation of guided modes in the dielectric layer resulting in zero or low mid-IR emission. At high temperatures the phase-change material islands enter a metal state phase that couples mid-IR (thermal) radiation to guided mode resonances resulting in high mid-IR emission. The thermal emission can be tuned by the lattice constant of the grating pattern to peak at a target mid-IR wavelength (e.g., 8 μm), thereby significantly increasing the thermal emission contrast between the low and high temperature states resulting in the minimization of system-wide thermal transients.

A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

A radiative fin for a spacecraft is disclosed having an end fitting of heat conductive material, configured to be mounted on the spacecraft, a flexible radiative laminate, connected to the end fitting at one end and having an opposite free end, at least one pyrolytic graphite sheet, and at least one heat emission layer in contact with the pyrolythic graphite sheet on at least part of the surface of the pyrolythic graphite sheet, and a flexible rod, extending from the end fitting along at least part of a side of the flexible radiative laminate and being affixed to the latter. The flexible rod is adapted to occupy a folded position and a deployed position and to exert, while in the folded position, a deployment torque adapted to bring the flexible rod back to the deployed position.

Integrated power module device, systems, and methods are provided in accordance with various embodiments. For example, some embodiments include a system that may include one or more integrated power modules. Each integrated power module may include: one or more solar cells; one or more rechargeable energy storage cells; and/or one or more circuits coupling the one or more solar cells with the one or more rechargeable energy storage cells. In some embodiments, each integrated power module is configured such that the one or more rechargeable energy storage cells of the respective integrated power module are coupled with one or more back sides of the one or more solar cells. In some embodiments, at least two of the one or more integrated power modules are coupled with each other at least in parallel or in series.

Described herein is a heater for space equipment that includes a heat pipe. The heater also includes a first layer applied to the heat pipe. The first layer may be made from an electrically non-conductive material. The heater additionally includes a resistance heater printed onto the first layer after the first layer is applied to the heat pipe. The heater includes a second layer adjacent the resistance heater. The resistance heater may be positioned between the first layer and the second layer, and the second layer may be made from an electrically non-conductive material.

Described herein is a heater for space equipment that includes a heat pipe. The heater also includes a first layer applied to the heat pipe. The first layer may be made from an electrically non-conductive material. The heater additionally includes a resistance heater printed onto the first layer after the first layer is applied to the heat pipe. The heater includes a second layer adjacent the resistance heater. The resistance heater may be positioned between the first layer and the second layer, and the second layer may be made from an electrically non-conductive material.

Clean condensate production may be produced from humidity in unfiltered air for an extended period of time using a membrane microgravity air conditioner which comprises an air box, comprising an inlet air flow path from a side face through an open top, and a filtering system disposed within the air box. The filtering system comprises one or more trash screens disposed in the inlet air flow path, one or more latent heat exchangers (LHX) disposed in the inlet air flow path, one or more particulate filters disposed in the inlet air flow path intermediate the trash screen and the LHX, one or more thermal control system (TCS) medium temperature loops, and one or more sensible heat exchangers (SHX) disposed in the inlet air flow path intermediate the particulate filter and the LHX.