A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.

Features relating to a cartridge for use with a vaporizer body are provided. The cartridge mates with the vaporizer body in a cartridge receptacle. The cartridge may include a cartridge body defining a reservoir configured to contain vaporizable material; a mouthpiece coupled to a proximal end region of the cartridge body; at least one proximal absorbent pad wedged within an internal volume of the mouthpiece; a mouthpiece seal with sealing ribs; a cannula defining a vaporization chamber extending through the cartridge body; a resistive heating element; a porous wick configured to draw the vaporizable material in the reservoir towards the vaporization chamber; an internal sealing gasket positioned in a distal end region of the cartridge body; a lower support structure positioned in the distal end region of the cartridge body; and at least one distal absorbent pad configured to wedge within a recess located in the lower support structure.

Exemplary backpressure monitoring apparatuses may include a fluid supply source having a fluid port. The backpressure monitoring apparatuses may include a flow control mechanism fluidly coupled with the fluid port. The backpressure monitoring apparatuses may include a delivery tube fluidly coupled with the flow control mechanism and the fluid port. The backpressure monitoring apparatuses may include a pressure differential gauge fluidly coupled with the delivery tube. The pressure differential gauge may include an interface mechanism that is engageable with an outlet of a fluid flow device.

Exemplary backpressure monitoring apparatuses may include a fluid supply source having a fluid port. The backpressure monitoring apparatuses may include a flow control mechanism fluidly coupled with the fluid port. The backpressure monitoring apparatuses may include a delivery tube fluidly coupled with the flow control mechanism and the fluid port. The backpressure monitoring apparatuses may include a pressure differential gauge fluidly coupled with the delivery tube. The pressure differential gauge may include an interface mechanism that is engageable with an outlet of a fluid flow device.

A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

A cockpit pressurization and oxygen warning system includes a cabin pressure input and an aircraft pressure input. A pilot interface includes a first visual indicator having a first recognizable characteristic disposed in a first position that is made visually perceptible when a first signal is asserted and a second visual indicator having a second recognizable characteristic esthetically different from the first recognizable characteristic and disposed in a second position different from the first position that is made visually perceptible when a second signal is asserted. A control circuit that is responsive to the cabin pressure input and the aircraft pressure input determines an acceptable range for the cabin altitude that corresponds to the aircraft altitude. The control circuit asserts the first signal when the cabin altitude is within the acceptable range and asserts the second signal when the cabin altitude is not within the acceptable range.

A pressure sensor for measuring a pressure of a fluid medium in a measuring chamber is provided. The pressure sensor includes a sensor housing, a first pressure-sensor module for measuring at least one first pressure of the medium in a first measuring chamber, and a second pressure-sensor module for measuring at least one second pressure of the medium in a second measuring chamber. The first pressure-sensor module and the second pressure-sensor module are situated inside the sensor housing. In addition, the pressure sensor has at least one first pressure connection, which is designed for the connection to the first measuring chamber. Moreover, the pressure sensor has at least one second pressure connection, which is developed for the connection to the second measuring chamber. The first pressure connection differs from the second pressure connection.

The present invention specifically relates to the pneumatic and electronic application of a pneumatic leak meter based on absolute pressure drop measurement having the peculiarity of compensating for ambient variations such as ambient temperature and temperature of the measured part, as well as mechanical deformations of the component being tested caused by the pressure being applied.

The present invention specifically relates to the pneumatic and electronic application of a pneumatic leak meter based on absolute pressure drop measurement having the peculiarity of compensating for ambient variations such as ambient temperature and temperature of the measured part, as well as mechanical deformations of the component being tested caused by the pressure being applied.

A hydraulic measuring mechanism for registering pressure differences, comprising a measuring mechanism platform having a process connection surface and two pressure input openings, in which, in each case, a pressure tube is arranged, which protrudes from a rear side of the measuring mechanism platform to support a pressure difference measuring cell, wherein the pressure tubes are connected pressure-tightly with the measuring mechanism platform from the process connection surface.