7 results about "Ejection velocity" patented technology

The present invention relates to the field of automated testing technology and discloses an ejection seat test device and a test control system. The present invention, through the setting of the test control system, performs detection through static simulation testing and dynamic simulation testing respectively to obtain a fourth static pull-out force, a first static pull-out force, a second static pull-out force, a third static pull-out force, a second dynamic pull-out force, a third dynamic pull-out force, and a fourth dynamic pull-out force. Then, a pull-out force estimation module calculates a second predicted pull-out force, a third predicted pull-out force, and a fourth predicted pull-out force to determine whether a preset first pull-out threshold, a second pull-out threshold, and a third pull-out threshold are met under an actual target ejection speed. In addition, a simulation speed correction strategy is provided to determine whether a preset simulation speed meets the requirements. If not, an expanded simulation speed is generated, so that a curve simulation result is closer to reality and the test result is more accurate.

The utility model discloses a model airplane track ejection device which comprises a guide rail sectional material, a guide rail is installed on the surface of the guide rail sectional material, a guide block is connected into the guide rail in a sliding mode, a carrier base is welded to the top face of the guide block, a first installation ring is fixedly connected to the surface of the carrier base, and a second installation ring is welded to the side face of the guide rail sectional material. An elastic rope is tied between the second mounting ring and the first mounting ring, an extension spring is fixedly mounted on the inner wall of the guide rail, the other end of the extension spring is fixedly connected with the surface of one side of a guide block, and a traction rope is tied on the surface of the other side of the guide block. According to the model airplane ejection device, the elastic rope and the extension spring are arranged as two elastic elements, the elastic rope and the extension spring are used in cooperation, the dual-force-storage ejection effect can be achieved, the model airplane ejection speed is higher, the model airplane ejection distance is longer, when the elastic rope is tired, the elastic rope can be unfastened to be replaced, the maintenance difficulty is lower, practicability is high, and the model airplane ejection device is worthy of popularization.

This application belongs to the field of electromagnetic catapult technology, and relates to a method and system for controlling the launch speed of an electromagnetic catapult. The method includes: acquiring the separation moment and velocity of the aircraft during its acceleration from the catapult platform to its detachment; establishing the aircraft's dynamic equations and obtaining the real-time velocity equations; acquiring the electromagnetic catapult parameters and aircraft parameters; constructing the velocity state equations of the electromagnetic catapult and obtaining the velocity observation vector; obtaining the velocity fusion equation based on the velocity observation vectors and the velocity state equations of the electromagnetic catapult; constructing a Kalman filter; using the velocity observation vectors as the filtering observations; estimating the velocity error of the electromagnetic catapult; and providing velocity feedback based on the estimation results. This method can meet the needs of various aircraft with different launch speeds.

The present invention relates to the field of impact and ejection test equipment, and specifically discloses an ejection device. The ejection device includes an ejection cylinder, a gas storage tank, and a gas supply member. The gas supply member is communicated with the gas storage tank. An ejection chamber is provided in the ejection cylinder, and a piston is slidably sealed in the ejection chamber. A piston rod is fixed on the piston. An air intake chamber is also provided in the ejection cylinder, and the air intake chamber is communicated with the gas storage tank. A communication port for communicating the ejection chamber with the air intake chamber is provided in the ejection cylinder; an opening valve core is provided in the air intake chamber, and the opening valve core is opposite to the communication port and is used for closing the communication port. The opening valve core is connected with a pushing member for pushing the opening valve core to slide. The ejection device in the present invention can provide a greater ejection speed without using a valve, so as to extend the service life of the ejection device.

The application belongs to the technical field of electromagnetic launching aircraft, and relates to an online speed measurement feedback control method and system for an electromagnetic launching aircraft. The method comprises the following steps: acquiring electromagnetic launcher parameters and aircraft parameters, constructing an output speed equation of the electromagnetic launcher, constructing an output speed equation of the aircraft, and constructing a speed state equation of the electromagnetic launching aircraft; obtaining a speed observation vector according to the output speed equation of the electromagnetic launcher and the output speed equation of the aircraft; obtaining a speed fusion equation according to the speed observation vector and the speed state equation of the electromagnetic launching aircraft, constructing a Kalman filter, taking the speed observation vector as a filter observation, estimating a speed error of the electromagnetic launching aircraft, and performing speed feedback according to the estimation result. The method can meet the needs of different launching speeds of various aircrafts and improve the control precision.

The invention belongs to the technical field of aircraft protection and lifesaving, and provides an air bag type head and neck protection device inflation opportunity control method and system.The method comprises the following steps that the seat ejection channel cleaning mode, the ejection speed and the ejection number are obtained; an air bag inflation control mode is automatically matched according to the seat ejection channel cleaning mode and the ejection number; and after the inflation control mode is confirmed, the inflation time of the seat lateral air bag and the pillow rear air bag is adjusted according to the ejection speed obtained in real time. The problems of different ejection channel cleaning modes, ejection speeds and air inflation time control of the air bag head and neck protection device during ejection lifesaving of multiple passengers are solved, and the protection effect on the heads and the necks of pilots is improved.

The embodiment of the invention discloses a flight recorder impact safety distance determination method, which comprises the following steps: establishing a digital model according to flight recorder parameters, and performing flight recorder aerodynamic characteristic simulation by using the digital model to obtain an air resistance model corresponding to a flight recorder; acquiring the speed and attitude of the flight recorder under the condition that the flight recorder is not ejected; calculating the ejection speed increment of the flight recorder according to the ejection momentum and attitude of the flight recorder; calculating the initial ejection speed of the flight recorder according to the speed of the flight recorder under the non-ejection condition and the ejection speed increment; and according to the ejection initial speed and the air resistance model, calculating an impact safety distance required by the flight recorder to reach a preset speed after the flight recorder is ejected.