11 results about "Flight control modes" patented technology

The invention belongs to the technical field of amphibious aircraft flight control, and discloses an amphibious aircraft fly-by-wire flight control system and a working method, a cockpit control device is connected with and controls a normal instruction sensor and a backup instruction sensor, the normal instruction sensor transmits a signal to an actuator control electron, and the backup instruction sensor transmits a signal to the actuator control electron; the actuator control electronics and the flight control computer transmit signals mutually, the actuator control electronics and the actuator control module transmit signals mutually, and the actuator control electronics further receive signals of the external signal sensor, the direct angular rate sensor, the flap position sensor and the flight control mode switch; the backup command sensor transmits the signal to the backup flight control computer, and the backup flight control computer transmits the signal to the actuator control module; the actuator control module is connected with and controls the actuator, and the angular displacement sensor is arranged on the actuator and transmits collected signals to the actuator control module. The problem that a current fly-by-wire flight control system is not matched with amphibious aircraft cross-medium application is solved.

The present invention provides a design method for a two-step flight control mode switching command fader for fly-by-wire aircraft, comprising detecting a flight control mode trigger signal; calculating in real time the difference between the elevator control commands at the current moment and the previous moment; maintaining the difference DU of the two control commands during flight control mode switching; performing a first-level fade process to obtain a first-level fade command DU1; performing a second-level fade process to obtain a second-level fade command DU2; generating a single-step command fader start signal SW_FADER; and determining whether to activate the single-step command fader or the two-step fader: when the single-step command fader start signal SW_FADER = 1, the single-step command fader is activated; when SW_FADER = 0, indicating that the difference DU of the two control commands for flight control mode switching is greater than a threshold for activating the second-level fade, the two-step fader is activated. The command fader design method of the present invention significantly improves the performance of the flight control system by optimizing transition time and reducing transient response.

The invention discloses a split-flow thrust control coaxial double-propeller aircraft and a flight control mode, and relates to the technical field of aircrafts. The device comprises a coaxial double-propeller unit and a thrust control unit, the thrust control unit comprises a thrust chamber and a plurality of overflowing adjusting mechanisms, the thrust chamber is arranged below a lower rotor wing and connected with a mounting frame, a plurality of overflowing cavities penetrating in the axial direction of an upper rotor wing are formed in the circumferential direction of the thrust chamber at intervals, and the overflowing adjusting mechanisms are arranged in the overflowing cavities. The overflowing adjusting mechanisms are correspondingly mounted in the overflowing cavities, so that the thrust distribution in the thrust chamber is adjusted by changing the through-flow area of the corresponding overflowing cavities to adjust the resistance when airflow passes through each overflowing cavity, and the flight attitude of the aircraft is adjusted. The advantages of a coaxial double-propeller aircraft and a multi-rotor aircraft are combined, so that the aircraft can obtain larger blade radius and lift action area, and has good controllability, maneuverability and stability.

The application belongs to the technical field of aircraft flight control system design, and particularly relates to a large aircraft lateral and longitudinal asymmetric self-trimming method, an automatic trimming instruction storage module of a rudder and an automatic trimming instruction storage module of ailerons are respectively arranged; automatic trimming working condition rudder and aileron instruction values at multiple speed points in a speed range of the aircraft are obtained; a linear interpolation table is established according to the automatic trimming working condition rudder and aileron instruction values, linear interpolation calculation is performed, and the required rudder and aileron trimming instructions at the current indicated airspeed of the aircraft are obtained; the rudder and aileron trimming instructions are used to control the deflection of the rudder and aileron; the aircraft can be automatically trimmed in the lateral and longitudinal asymmetric state when the aircraft is in an artificial flight control mode, and the pilot's operation burden is reduced. The method does not need to modify any hardware part, and the lateral and longitudinal automatic trimming related function modules can be added on the basis of the existing flight control law architecture according to the method, so that the modification cost is saved.

The application belongs to the technical field of aircrafts, and discloses a kind of adjusting method, system and operating device of flight operating device.The method is applied to flight control module, flight control module is connected with the operating module in operating device, operating device includes: operating lever, rotating mechanism, operating module connected in turn, and damper connected with rotating mechanism;The method comprises: determining the corresponding operating torque according to the current flight control mode;According to operating torque, operating module is controlled, so that operating module is adjusted to the position of operating lever by rotating mechanism.The above-mentioned mode is used to determine the operating torque according to the flight control mode, and the operating lever force is provided for the operating lever by using the operating module, so that the operating lever can be flexibly adapted to different flight control modes.

The application discloses a kind of shunt thrust control coaxial double-paddle aircraft and flight control mode, it is related to aircraft technical field.The application includes: coaxial double-paddle unit and thrust control unit, thrust control unit, the thrust control unit includes thrust chamber and multiple groups of flow regulating mechanism, the thrust chamber is placed below the lower rotor and is connected with the mounting frame, it is circumferentially spaced apart and is provided with multiple through-flow cavities along the axial direction of the upper rotor, multiple groups of flow regulating mechanism are correspondingly installed in multiple the through-flow cavities, to adjust the flight attitude of aircraft by changing the flow area corresponding to the through-flow cavity to adjust the resistance size when airflow passes through each the through-flow cavity to adjust the thrust distribution in thrust chamber.The application combines the advantages of coaxial double-paddle aircraft and multicopter, so that the aircraft can obtain larger paddle radius and lift action area, and has good controllability, maneuverability and stability.

The application discloses a method and system for enabling flight control of a UAV and a computer storage medium, the method comprising: establishing a gas flow model of associated gas combustion; setting basic control parameters according to the gas flow model and releasing the UAV; collecting flow velocity and temperature information of the ascending gas flow through the UAV, monitoring a real-time state of the associated gas combustion; and calibrating the UAV attitude, predicting the ascending gas flow state and selecting a flight control mode according to the flow velocity and temperature information of the ascending gas flow. The application can adjust the flight state according to the real-time collected gas flow field data, and improve the hovering time. The combustion of the associated gas is directly monitored and the surrounding gas is collected to detect the combustion state.

This invention discloses a method for modeling and verifying mode conversion in civil aircraft automatic flight systems based on the SysML language. First, it analyzes in detail the key issues in formal modeling for this field, including high-level abstraction, hierarchical design, mode conversion logic, and priority characteristics, constructing a meta-model for flight control mode design and conversion. Second, based on the proposed meta-model, the formal modeling language SysML is extended and encoded into a domain-specific SysML profile file. Subsequently, the extended SysML profile is used in a mode conversion modeling project for an automatic flight system of a certain type of civil aircraft, and the safety and correctness of the model are verified using NUSMV. This invention provides a relatively complete and unified model building approach for the field of automatic flight systems, effectively ensuring system design quality and improving system development efficiency and safety.

The application discloses a method for detecting smooth switching of dual modes of an aircraft, which comprises the following steps: determining a stage of the aircraft based on a motion posture of the aircraft and position information of the aircraft relative to a cable; determining a current control state of the aircraft by combining the stage of the aircraft and a normal contact pressure of a roller inside the aircraft; and switching a dominant right of a free flight control mode or a cable-holding control mode of the aircraft by using the current control state. The method can provide a switching reference by monitoring the motion posture of the aircraft and the position information of the aircraft relative to the cable in real time, determine the stage of the aircraft, determine the current control state of the aircraft by combining the obtained stage information and the normal contact pressure of the roller inside the aircraft, switch the dominant right of the free flight control mode and the cable-holding control mode based on the current control state, eliminate instruction grabbing and conflict between the two sets of control systems, and realize smooth transition between the dual modes.

The invention relates to a blade variable pitch driving mechanism for a coaxial reverse propeller rotor. The control host independently controls the corresponding synchronous speed reduction motors of the positive and negative layers of variable pitch propeller groups to rotate forwards / backwards through a conductive slip ring and slip group contact connection type electrical loop to drive the corresponding worm gears / worms to drive the corresponding movable blades to synchronously adjust the pitch angle and lock the pitch angle; according to the coaxial reverse-pitch variable-pitch driving mechanism, in a fly-by-wire flight control mode that variable-pitch driving is carried out on movable blades by a worm gear / worm integrated in a propeller hub through a touch connection type electrical loop and a synchronous gear motor, the axial occupied size of the coaxial reverse-pitch variable-pitch driving mechanism is greatly reduced, meanwhile, the blade variable-pitch effect is achieved, and the coaxial reverse-pitch variable-pitch driving mechanism is simple in structure, compact in layout, high in reliability and low in maintenance cost; meanwhile, under the condition that mechanical performance strength redundancy is guaranteed, the shaft diameter of the overhanging type main shaft and related matched assemblies can be optimized and reduced, the weight of the whole driving unit assembly is further reduced, and the energy efficiency ratio of the aircraft is increased.