Abstract: A flow splitting device for gas reverse circulation drilling, including: an upper joint for connecting with a double-wall drill pipe; an inner tube which is arranged in the upper joint and defines a first passageway in communication with an inner chamber of the double-wall drill pipe, a second passageway in communication with an annular space in the double-wall drill pipe formed between the inner tube and the upper joint; a lower joint, having an upper end fixedly connected with the upper joint and a lower end for connecting with a drill tool; and a flow guiding member provided between the upper joint and the lower joint. A flexible sealing mechanism is provided outside the upper joint. The flexible sealing mechanism extends radially outward relative to the upper joint and the lower joint to form a sealing contact with a wellbore wall.

Abstract: According to various embodiments, the present invention relates to a platform and method for testing aircraft message trigger logics are disclosed. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (a Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.

Abstract: The present invention relates to a test apparatus that includes a simulation signal generation portion and a test portion. Embodiments of the simulation signal generation portion include an input interface, a simulation signal generation module, and an output interface. Embodiments of the test portion include wiring extension apparatus, a Digital Flight Data Acquisition Unit and a comparison module.

Abstract: The present invention relates to a platform and method for testing aircraft message trigger logics. Apparatus for testing message trigger logics of aircraft comprises: DFDAU (Digital Flight Data Acquisition Unit), which is adapted to receive message trigger logics to be tested; an input interface, which is adapted to receive data of aircraft condition; and a simulation signal generator, which is adapted to generate simulation signals according to the data of aircraft condition; wherein, the DFDAU is adapted to receive the simulation signals, and generate messages according to the message trigger logics to be tested.

Abstract: The present invention relates to a test apparatus based on DFDAU (Digital Flight Data Acquisition Unit), comprising: a simulation signal generation portion; and a test portion; wherein, the simulation signal generation portion comprises: an input interface, which receives test data; a simulation signal generation module, which generates simulation signal according to the test data; and an output interface, which is adaptive to be connected to one end of one or more signal transmission device to be tested and output the simulation signal; wherein, the test portion comprises: wiring extension apparatus, which is used to form a gating wiring apparatus and is adaptive to be connected to the other end of the one or more signal transmission devices to be tested, and receive the simulation signal passing through the one or more signal transmission devices to be tested; DFDAU, which is adaptive to receive simulation signal from the wiring extension device, and obtain the transmitted test data; a comparison module, wh