7 results about "Cabin pressurization" patented technology

The utility model discloses an intelligent micro -pressure hydrogen oxygen sleep -aiding cabin, including sealed cabin body, hatch, pressure increasing module, hydrogen supply module, oxygen supply module, sleep -aiding module, intelligent control module, the sealed cabin body realizes the support and gas seal of cabin equipment, the hatch realizes personnel access and the sealing after hatch closing, the pressure increasing module is for the cabin pressurization, the hydrogen supply module provides hydrogen for the cabin, the oxygen supply module provides oxygen for the cabin, the sleep -aiding module provides sleep -aiding environment, the intelligent control module realizes touch control, voice control, human physiological parameter remote real -time monitoring, cabin gas parameter remote real -time monitoring and control to and the above parameter are uploaded to the background server or cloud server. The utility model can increase user experience.

The invention relates to the field of marine equipment pressure adjusting devices, in particular to a water tank internal and external pressure balancing device which comprises a tank body, a valve body is fixedly installed in the tank body, a closed valve cavity is formed in the valve body, an in-tank pressurization air inlet and an in-tank pressurization air outlet which are communicated with the valve cavity are formed in the outer wall of the valve body, and the in-tank pressurization air inlet is connected with a high-pressure air source; an in-cabin pressure relief air inlet hole and an in-cabin pressure relief air outlet hole which are communicated with the valve cavity are further formed in the outer wall of the valve body, and the in-cabin pressure relief air outlet hole is connected with an air storage device; a valve element is vertically installed in the valve body in a sliding mode, the upper end of the valve element is connected with an out-cabin pressure-bearing component extending out of the cabin body, and the lower end of the valve element is connected with an in-cabin pressure-bearing component extending into the cabin body. When the internal pressure and the external pressure of the cabin are balanced, the in-cabin pressurization air inlet and the in-cabin pressure relief air inlet are blocked by the valve element; when the pressure in the cabin body is higher than the pressure outside the cabin body, the valve element moves upwards, the in-cabin pressure relief air inlet hole and the in-cabin pressure relief air outlet hole are communicated through the valve cavity, and high-pressure air in the cabin body is exhausted to the air storage device.

This application belongs to the technical field of aircraft pressurized cabin pressurization prevention mechanism design, specifically relating to an aircraft pressurized cabin pressurization prevention mechanism. The mechanism is designed such that the transmission roller and the elongated hole on the pressure relief door lug have a certain fit margin after the cabin door is closed and the locking mechanism is engaged. The elastic force of the first and second torsion springs allows the pressure relief door to open to a certain angle, gradually closing as the pressurized cabin pressurizes. This design addresses the requirements for machining and assembly precision, avoids interference caused by machining and assembly errors, ensures the locking mechanism can complete locking, and is easy to install and debug with good manufacturability.

In some examples, a system includes a compressor configured to provide a compressed air flow to pressurize a compartment of a vehicle, such as an aircraft. The compressor is configured to provide the compressed air flow using an electrical power provided by an electrical distribution system of the vehicle or a mechanical power provided by a turbine assembly of the vehicle. The system is configured to cause the compressor to transition from using the electrical power to using the mechanical power when the electrical power is below a threshold.

In some examples, a system includes a compressor configured to provide a compressed air flow to pressurize a compartment of a vehicle, such as an aircraft. The compressor is configured to provide the compressed air flow using a primary mechanical power provided by a motor assembly or a secondary mechanical power provided by a turbine assembly. The system is configured to cause the compressor to transition from using the primary mechanical power to using the secondary mechanical power when an input electrical power to the motor assembly is below a threshold. The system includes a generator assembly configured to provide an output electrical power using the secondary mechanical power.

The utility model discloses a hyperbaric oxygen chamber pressurization system with a pressure relief type starting protection device, which comprises an air pretreatment unit, a compressor and a one-way valve which are sequentially connected through a pipeline, and a pressure relief assembly used for releasing residual air pressure in an air outlet end pipeline of the compressor before the compressor is started is arranged on the pipeline between the compressor and the one-way valve. The utility model aims to provide the pressure relief device which actively releases residual air pressure in a pipeline through the pressure relief assembly before the compressor is started, so that the reverse pressure needing to be overcome by the compressor during starting is reduced, and the starting current is ensured not to be too large; the hyperbaric oxygen chamber pressurization system with the pressure relief type starting protection device can prevent the compressor from being overloaded or / and being not started due to electrical impact. The pressure relief function is independent of the main pressurization process, so that the efficiency and stability of the pressurization system are not affected, and the overall reliability and safety of the pressurization system equipment of the hyperbaric oxygen chamber are greatly improved.

This invention discloses a testing method and testing equipment for functional testing of an aircraft cockpit pressurization control system, comprising steps S1 to S7. When testing the aircraft cockpit, this invention eliminates the need for repeated pressurization and depressurization of the cockpit, and avoids physical isolation measures such as disassembly or sealing of non-test valves. The testing pressure can be precisely controlled, and the testing process can be seamlessly integrated with the cockpit structural sealing test without requiring additional preparatory steps. This method effectively simplifies the testing process, shortens the overall testing cycle, and avoids damage to the original aircraft structure and onboard equipment caused by physical isolation and component disassembly. While ensuring accurate and reliable test results, it effectively improves the safety of the testing operation and the overall testing efficiency.