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654results about "Aircraft ejection means" patented technology

Application and design for embedding bionic honeycomb-shaped active safety escape capsule into aircraft

The invention provides the application and design for embedding a bionic honeycomb-shaped active safety escape capsule into an aircraft. The application and design comprise the following related technologies including redesign of a main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, internal space layout design of the main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, design of an escape capsule embedded type shell and the shape, analysis of influences of the embedded escape capsule on the overall load of the aircraft, integral analysis and determination of flight aerodynamic load data, selection of an escape capsule material, escape capsule ejection mode analysis and ejection device design, logic design of launch motion of the escape capsule, internal space structure analysis of the escape capsule; active safety design of space landing of the escape capsule, description of flight dynamics influences of the escape capsule on the aircraft during and after separation, and design of an active help seeking system of the escape capsule. In this way, the application and design for researching and manufacturing the bionic honeycomb-shaped active safety escape capsule embedded into the aircraft are achieved.
Owner:王晨

Modular miniature unmanned aircraft with vectored-thrust control

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T / V”) module and a second T / V module, and an electronics module. The electronics module provides commands to the two T / V modules. The two T / V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T / V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.
Owner:AURORA FLIGHT SCI CORP

Securing emergency and safety equipment on aircraft

An emergency equipment system comprising an elongate member, an emergency equipment package, and a cutter. The elongate member may have a first end and an angled end. The emergency equipment package may have a sleeve on one side capable of receiving the elongate member from the angled end. The cutter may be attached to a side of the elongate member and may be capable of cutting the sleeve.
Owner:THE BOEING CO

Protection device and protection method for tumbling out of control of rotor type unmanned aerial vehicle

The invention discloses a protection device for tumbling out of control of a rotor type unmanned aerial vehicle (UAV), and the technical scheme thereof is characterized in comprising ejection cylinders, a high-pressure gas cylinder, ejection opening and closing doors, a posture sensor and a control module, wherein top plates are mounted inside the ejection cylinders; each top plate divides the corresponding ejection cylinder into a high-pressure chamber and an ejection chamber; each ejection chamber is provided with a self-throwing parachute and the bottom of each high-pressure chamber is provided with an air inlet; the high-pressure gas cylinder is respectively connected with the air inlets of the two ejection cylinders through air duct pipes, and electromagnetic valves are respectively mounted near the two air inlets; the ejection opening and closing doors are hinged to the opening of the ejection cylinders; hinge shafts are provided with torsion springs; fixed parts for closing the ejection opening and closing doors at the opening of the ejection cylinders are mounted on the ejection cylinders; the posture sensor is arranged in a UAV body to periodically detect posture change data of the UAV body; and the control module receives the posture change data and outputs a corresponding control signal to the corresponding solenoid valve and the corresponding fixed part according to an angle of inclination to control the self-throwing parachute in the corresponding ejector cylinder to be forced out of the corresponding ejection chamber under the high pressure gas.
Owner:温岭鸿方智能科技有限公司
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