11 results about "Autothrottle" patented technology

The invention discloses a testing device for automatic accelerator switch assemblies, and relates to the technical field of aviation equipment maintenance. Each automatic accelerator switch assembly comprises a plug and a plurality of micro switches; the testing device of the automatic accelerator switch assembly comprises an assembly socket module, a toggle switch group module, a resistance measuring module and a dynamic display module which are connected in sequence. The assembly socket module comprises sockets of which the number is the same as that of the plugs, and is used for connecting the plugs to obtain the output of the micro switch; the toggle switch group module comprises toggle switches of which the number is double of that of the micro switches, and each toggle switch is used for forming a measurement path between two contact pins of one micro switch; the resistance measurement module is used for measuring the resistance value of the measurement path; the dynamic display module is used for displaying the resistance value. By adopting the embodiment of the invention, the micro switch to be tested can be conveniently selected, and the test result can be automatically displayed, so that quick troubleshooting can be realized, and the efficiency of flight line maintenance work can be effectively improved.

A system including a engine having a low spool and a high spool, a first hybrid electric motor connected to the low spool and a second hybrid electric motor connected to the high spool. An auto-throttle controls an amount of power provided to the engine responsive to at least one aircraft parameter. A power splitting algorithm implemented between the auto-throttle and at least one of the first and second hybrid electric motors determines a power split dividing the total engine power into the power produced by burning fuel and electrical power provided to the at least one of the first and second hybrid electric motors responsive to control signals from the auto-throttle.

The invention discloses a flight-engine coupling-based propulsion system simulation architecture, relates to the technical field of aircraft simulation, and is used for solving the technical problem of dynamic response mismatch of a flight control system and an engine in an existing simulation platform. The flight-launch coupling-based propulsion system simulation architecture comprises a propulsion terminal module, a flight management computer module, an engine simulation computer and a pilot cockpit system, the propulsion terminal module is provided with a sequential logic and state management mechanism and is used for simulating an execution unit response process and a fly-by-wire accelerator process when the aircraft is started; the flight management computer module is used for carrying out automatic control and resolving functions and carrying out automatic accelerator resolving, accelerator mode switching and flight launching instruction management; the engine simulation computer is used for performing dynamic simulation tasks of an engine control system and engine performance; and the pilot cockpit system is used for receiving pilot operation input and displaying state feedback of the simulation architecture.

The invention discloses a control method for gliding parachute-opening landing of an unmanned aerial vehicle, belongs to the technical field of safe landing of the unmanned aerial vehicle, and utilizes the unmanned aerial vehicle to enter gliding and adjust various states and parameters of the unmanned aerial vehicle to enable the unmanned aerial vehicle to meet conditions of safe parachute landing. The method comprises the following steps that an aircraft follows a route in an approaching state, and an automatic accelerator is controlled by speed; in the lifting rate zeroing stage, transverse guidance is closed, longitudinal guidance is controlled by the lifting rate, and an automatic accelerator is closed; in the gliding stage, longitudinal guidance is controlled by speed, and airspeed is equal to recovery speed; in the recovery stage, the longitudinal guidance is closed, the pitch angle is equal to the sum of the increment of the climbing angle and the increment of the attack angle of the parachute opening action, and the recovery system is started and parachute opening is performed until the aircraft lands safely to complete landing.

The application discloses a kind of test device of automatic throttle electric door component, it is related to aviation equipment maintenance technical field, each automatic throttle electric door component includes plug and several microswitches, the test device of automatic throttle electric door component includes sequentially connected component socket module, dial switch group module, resistance measurement module and dynamic display module;Component socket module includes the same number of socket with the plug, for connecting the plug, obtain the output of the microswitch;Dial switch group module includes the double quantity of dial switch of microswitch, and each dial switch is used to form the measuring path between the two pins of a microswitch;Resistance measurement module is used to measure the resistance value of the measuring path;Dynamic display module is used to display resistance value.The microswitch of the present application embodiment can be conveniently selected for testing, and the test results are automatically displayed, to realize rapid troubleshooting, effectively improve the efficiency of line maintenance work.

The invention discloses a portable airplane automatic accelerator S switch in-situ test system, and relates to the technical field of test, and the technical scheme comprises the following steps: screening based on a test feature identification library to obtain target actual measurement data of a switch to be tested; obtaining an actual test index of the target actual measurement data, obtaining abnormal test data according to the actual test index and the standard test parameter, and obtaining a test deviation coefficient of the abnormal test data according to an actual parameter measurement value; obtaining a first environment test coefficient of the test environment according to the abnormal data parameter of the abnormal test data in the test environment and the test deviation coefficient; marking a switch corresponding to the abnormal test data as an abnormal switch, and obtaining a second environment test coefficient of the test environment according to abnormal equipment parameters of the abnormal switch in the test environment; the effect is that a clear basis is provided for maintenance or replacement of the electric switch.

The invention discloses an automatic accelerator control method and system based on a thrust prediction function. The method comprises the steps that thrust prediction items are calculated, and the thrust prediction items comprise a steady-state thrust prediction value needed for maintaining the current flight state of an aircraft and a total thrust prediction value including the dynamic acceleration and deceleration process; calculating a thrust prediction correction term, wherein the thrust prediction correction term is a difference value between the actual thrust of the aircraft and the total thrust prediction value; superposing the thrust prediction item and the thrust prediction correction item to generate an engine rotating speed instruction; and superposing the engine rotating speed instruction for compensating the speed error on the engine rotating speed instruction to generate a final engine rotating speed instruction to control a throttle lever to move so as to maintain the target speed.

A system including a engine having a low spool and a high spool, a first hybrid electric motor connected to the low spool and a second hybrid electric motor connected to the high spool. An auto-throttle controls an amount of power provided to the engine responsive to at least one aircraft parameter. A power splitting algorithm implemented between the auto-throttle and at least one of the first and second hybrid electric motors determines a power split dividing the total engine power into the power produced by burning fuel and electrical power provided to the at least one of the first and second hybrid electric motors responsive to control signals from the auto-throttle.

The invention belongs to the field of flight control, and relates to an automatic accelerator nonlinear control method and device for full-automatic landing of an aircraft, and the method comprises the steps: S1, obtaining an accelerator control input quantity; s2, feed-forward lead-lag correction is carried out; s3, negative feedback is superimposed on the correction value, and the accelerator control quantity is formed; s4, automatic accelerator control system transmission calculation is carried out, and the accelerator output quantity is obtained; s5, automatic accelerator execution system transmission calculation is conducted on the accelerator output quantity, and the actuator output quantity is obtained; s6, accelerator system model operation is carried out on the accelerator output quantity to form a first control quantity, and second time delay compensation operation is carried out on the first control quantity to form a second control quantity; and S7, subtracting the second control quantity from the controller output quantity, inputting the controller output quantity into the PD controller, and superposing the first control quantity on the output result to form negative feedback. According to the method, the aircraft approach power compensation effect is improved, and the flight path control precision is improved.

An automatic throttle control method and system for controlling aircraft takeoff / go-around are disclosed. The automatic throttle control method includes: when the aircraft's automatic throttle is pre-positioned, detecting the aircraft's engine speed in response to the activation of the aircraft's vertical flight guidance go-around mode; and engaging the aircraft's automatic throttle when the detected engine speed is greater than a first speed threshold. The automatic throttle control method further includes: when the aircraft is on the ground and the aircraft's main wheel contact time is greater than or equal to a first main wheel contact time threshold, detecting the aircraft's throttle lever movement rate in response to the activation of the aircraft's vertical flight guidance go-around mode; and engaging the aircraft's automatic throttle when the detected positive throttle lever movement rate duration is greater than a first positive throttle lever movement rate duration threshold or when the detected throttle lever movement rate is greater than a first throttle lever rate threshold.

The invention discloses an accelerator control method, device and equipment for flight equipment, and the method comprises the steps: determining an accelerator control state at the current moment according to the current accelerator position of an accelerator control part and a preset soft stop point position; and in the soft stop state, according to the collected and determined external applied force, the soft stop distance between the accelerator position and the soft stop point position at the next moment is calculated, and the accelerator control component is controlled to conduct precision according to the soft stop distance. And in the non-soft locking state, compensation force is generated according to the position of the control component, and a driver is assisted to control the accelerator. The interaction condition between an automatic accelerator control system and a driver in an active driving mode is fully considered, and the most appropriate auxiliary accelerator control is provided according to different control states. The driving experience of a driver is effectively improved, the flight quality of the flight equipment is also improved to a certain extent, and good life and health guarantee is provided for members in the flight equipment.