303 results about "Aircraft flight control system" patented technology

A VTOL UAV comprising a chassis, a propulsion system mounted on the chassis, electronics including a flight control system, and a 3D LIDAR sensor mounted on the chassis. The 3D LIDAR sensor has a laser beam 360° rotation axis (R) and an azimuthal scanning angle (α) in a range of 70° to 110°. The propulsion system comprises a plurality of propellers with motors configured for flight without wings, including static hovering flight, the VTOL UAV comprising a yaw axis (Z) about which it can rotate upon itself. The 3D LIDAR sensor is statically mounted on the chassis such that the LIDAR laser beam 360° rotation axis (R) is inclined at a LIDAR inclination angle (β) with respect to the yaw axis (Z) in a range of 35° to 50°.

The invention discloses an unmanned aerial vehicle load engine state identification method based on deep learning, and the method comprises the following steps: S1, collecting the multi-mode operation data of an unmanned aerial vehicle load engine, and completing the standardization preprocessing; s2, inputting the spatial data into a spatial pyramid pooling network, and extracting a multi-scale spatial feature matrix; s3, inputting the spatial features into a masking auto-encoder, performing feature masking, encoding and reconstruction, and generating reconstruction features and error information; s4, fusing the original features, the reconstructed features and the non-spatial data, inputting a discrimination network, and outputting a health label and a risk score; and S5, according to an identification result, a flight control system or a maintenance platform is linked to realize alarm and scheduling. According to the method, intelligent identification and abnormal risk early warning of the state of the load engine of the unmanned aerial vehicle are realized by fusing multi-scale spatial feature extraction and a covering self-encoding reconstruction mechanism.

The invention provides a civil aircraft flight control system dynamic reconstruction method fusing uncertainty quantification and toughness decision, and belongs to the field of aviation electromechanical product reliability engineering, and the method comprises the steps: S1, multi-source uncertainty modeling and optimization; s2, running state monitoring and risk prediction; s3, evaluating the toughness margin of the flight control system; S4, generating a candidate toughness response strategy; s5, multi-attribute utility evaluation based on online model prediction; s6, selecting an optimal robust toughness decision; s7, executing an optimal robust toughness decision; and S8, empirical learning and model adaptive optimization are carried out. The invention provides a novel operation safety guarantee theory and method which deeply integrates uncertainty quantification, a toughness engineering principle and a multi-criterion robust decision-making aiming at severe uncertainty faced by a dynamic reconfigurable civil aircraft flight control system in a complex operation environment and challenge on flight safety. And the safety decision quality and the overall operation toughness of the system under uncertainty can be obviously improved.

The invention relates to the technical field of intelligent flight control, in particular to a multi-source sensing data fused low-altitude flight track offset intelligent repair method, which comprises the following steps of: performing jitter correction on a visual image stream through a motion compensation module, performing resampling on an ADS-B positioning signal by adopting a Lagrange interpolation method, and performing multi-source sensing data fusion on the ADS-B positioning signal; the radar point cloud is mapped to an image coordinate system, and a fusion track representation vector with time-space synchronization is generated; extracting a curvature abrupt change point set, an environment shielding factor and an airspace visibility gradient based on the vector, and constructing a multi-dimensional offset feature tensor in combination with aircraft dynamics constraints; inputting the tensor into a pre-trained space-time diagram neural network, and outputting a risk grading restoration decision comprising a restoration angle, a climbing rate and a speed compensation amount; injecting the repair decision into a flight control simulator for verification, and outputting a final repair instruction when the trajectory deviation value is smaller than a safety threshold value; the method has high precision and closed-loop execution flight path repairing capability, and is suitable for a flight control system in a complex low-altitude environment.

The invention discloses an unmanned aerial vehicle and robot dog intelligent cooperation system. The system comprises an unmanned aerial vehicle, a robot dog and a ground control system; the unmanned aerial vehicle comprises an unmanned aerial vehicle sensor, an unmanned aerial vehicle communication module and a flight control system, the unmanned aerial vehicle communication module is used for performing data communication with the robot dog and the ground control system, and the flight control system is used for controlling flight of the unmanned aerial vehicle; the robot dog comprises a parking apron, a robot dog sensor, a robot dog communication module and a semantic recognition module, the parking apron is used for carrying the unmanned aerial vehicle, the robot dog communication module is used for performing data communication with the unmanned aerial vehicle and the ground control system, and the semantic recognition module is used for performing semantic analysis on the first environment data and the second environment data; generating a dynamic semantic map; the ground control system comprises a ground communication module used for performing data communication with the robot dog and the unmanned aerial vehicle; according to the invention, efficient and intelligent docking of the unmanned aerial vehicle and the ground equipment can be realized, and autonomy, reliability and task execution efficiency of collaborative operation are improved.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine a flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated one or more loads by predicting a distribution of loads associated with the aircraft, generate one or more effector commands based on the flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.

The invention discloses an air-drop and air-delivery large unmanned aerial vehicle ultra-low-altitude flight control system and method, and belongs to the field of flight control systems, and the system comprises a flight control module, a drop control module, an environment sensing module, a gravity center balance adjustment module and a data storage and interaction module. The flight control module is used for controlling the unmanned aerial vehicle to fly at an ultra-low altitude and ensuring that the flight attitude is stable, so that the position error is less than or equal to 10m, the height error is less than or equal to 2m and the flight path deviation is less than or equal to 10m when the unmanned aerial vehicle flies at the ultra-low altitude; the delivery control module is used for supporting a single delivery mode and a rapid continuous delivery mode, the maximum delivery of 1.2 tons of goods can be achieved, at most four pieces of goods can be delivered in a single flight, the delivery control module is compatible with parachute air delivery and non-parachute air delivery, and the delivery precision of the parachute air delivery at the high altitude of 300 meters is smaller than 100 meters. According to the invention, the unmanned aerial vehicle delivery precision can be improved, the stability is high, and material waste or incapability of accurately delivering to a target area is avoided.

An aircraft includes a flight plan and contingency data including a plurality of contingency landing sites. An aircraft communication system communicates with a ground control station via a communication link and detects a lost communication scenario in response to degradation in the communication link. An aircraft flight control system controls the aircraft en route according to the flight plan. In response to detecting the lost communication scenario, the flight control system routes the aircraft back to a last known location in which the communication link was not degraded. In response to failure to re-establish the communication link, the flight control system selects a landing site based on a current aircraft location relative to a plurality of potential landing sites including an origin airport, a destination airport, and a first continency landing site. The flight control system controls the aircraft to approach and land at the selected landing site.

The invention discloses a digital twin platform of an aircraft flight control system, a data processing method of the digital twin platform and a medium, and relates to the technical field of aircraft simulation training, and the platform comprises a parameter setting unit which is used for setting aircraft basic information and current flight state parameters; the control signal acquisition unit is used for acquiring an electric signal generated when a user operates the control device; the calculation unit is used for calculating the initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating the control surface deflection angle according to the control surface aerodynamic-control device force transmission model, and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model; and the force sensing feedback unit is used for calculating joystick feedback force in the current aircraft flight state and the current control state according to the control surface aerodynamic force-control device force transmission model, and feeding back generated corresponding control resistance to the control device. The platform not only saves the economic cost and occupied area for establishing an entity iron bird test bench, but also can test the performance of a flight control system of an airplane in different flight states.

The invention discloses an unmanned aerial vehicle natural language multi-modal navigation method and system based on a multi-dimensional thinking chain. The method mainly comprises the following steps: constructing a software-in-the-loop simulation environment deeply integrated with task planning software, and collecting a live-action image with a time-space stamp; secondly, the natural language task instruction is analyzed, and key landmarks and position coordinates of the key landmarks are recognized in combination with a real scene image; then the recognition result and the structured task sequence are input into a multi-dimensional thinking chain reasoning engine in parallel to be processed; and finally, integrating the output of the multi-dimensional thinking chain inference engine, generating a flight action sequence, and issuing the flight action sequence to a flight control system to complete a navigation task. According to the method, the explicit thinking chain reasoning process is embedded into each step of navigation decision and is deeply integrated with the existing task planning ecology, so that the autonomy, adaptability and task success rate of the unmanned aerial vehicle in an unknown or dynamic environment can be remarkably improved.

An aircraft having a plurality of independent yaw control mechanisms includes an airframe having a central fuselage sized to hold at least one operator or payload and a wing extending from the fuselage. The aircraft includes a distributed thrust array coupled to the airframe, the thrust array having at least a first, second, and third pair of propulsion assemblies. Each propulsion assembly includes a rotor and is operable for at least single-axis thrust vectoring. The aircraft further includes a flight control system operable to independently control and combine each yaw mechanism of the propulsion assemblies. The yaw mechanisms for inducing a yaw moment include: canting at least one pair of propulsion assemblies away from the fuselage, selectively tilting at least one pair of propulsion assemblies forwards and backwards, varying an aerodynamic control surface of at least one propulsion assembly, and varying a rotational speed of at least one propulsion assembly.

A system and method for flight control of an aircraft, the flight control system including a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.

The present disclosure is generally directed to a flight control system and method of flight control for an electric aircraft. The system includes a pilot input communicatively connected to an electric aircraft, wherein the pilot input is configured to receive an input datum, and plurality of flight components communicatively connected to the electric aircraft, wherein the plurality of flight components includes a plurality of control surfaces. The system also includes a flight controller, wherein the flight controller is configured to determine a phase of flight, determine a command datum to control a position of the plurality of control surfaces as a function of the input datum, and command, when the phase of flight is determined to be hover, the plurality of control surfaces using the command datum.

An unmanned quadcopter aircraft system integrated with a pneumatic paintball projectile launching mechanism for recreational and training applications. The system includes a compressed gas powered single-shot paintball launcher with gravity-fed ammunition hopper, mechanical counterweight recoil compensation, and multiple electronic safety systems. GPS-based geofencing prevents firing in restricted zones, while altitude sensors prevent firing above predetermined heights. The flight control system automatically reduces aircraft speed and altitude limits when the projectile system is armed. A ground control system integrates standard flight controls with firing controls, safety indicators, and emergency stop capability. An alternative embodiment allows a used to adjust the elevation of the firing system while maintaining the orientation of the drone in space and also allowing recoil compensation. The system enables aerial paintball gaming and training scenarios while maintaining safety through redundant control systems and automatic parameter limiting.

The invention discloses a self-coupling PID (proportion integration differentiation) flight control method of a rudder-controlled transverse-row type rotor unmanned aerial vehicle based on dynamic multi-dimensional heterogeneous fuzzy logic, and belongs to the technical field of flight control of rudder-controlled transverse-row type rotor unmanned aerial vehicles. A flight control system architecture of the self-coupling PID flight control method is composed of three core modules: (1) a dynamic multi-dimensional fuzzy logic coupling PID controller (DMHFL-SCPID); (2) control instruction distribution; and (3) a six-degree-of-freedom dynamical model of the rudder-controlled transverse rotorcraft. According to the control algorithm, input and output dynamic parameters of a system are analyzed in real time, and four-dimensional flight control quantities (roll, pitch, yaw and height instructions) are generated. A control distribution strategy based on the aerodynamic characteristics of the rotor converts the instructions into actuating quantity of an actuating mechanism, and flight attitude adjustment is realized by changing aerodynamic load distribution of a rotor system, so that the unmanned aerial vehicle is guided to realize accurate tracking along a predetermined flight path.

An inceptor apparatus for an aircraft having a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

An inceptor apparatus for an aircraft comprises a primary inceptor member provided in the form of a stick member having a grip portion, at which the stick member can be gripped by a pilot's hand, and a secondary inceptor member provided at an upper portion of the primary inceptor member and having an actuating portion, at which the secondary inceptor member can be manually actuated by a pilot's thumb. Both inceptor members have associated a respective sensor assembly which is provided to generate electronic flight control signals or commands in response to at least one of i) pivoting movements of the respective inceptor member around each of two independent maneuvering axes associated to the inceptor member, ii) forces acting on or via the respective inceptor member in pivoting directions with respect to each of the maneuvering axes, and iii) lateral flexing or bending of the respective inceptor member.

The invention discloses an actuator control electronic unit, a fly-by-wire control system and a control method. An actuator control electronics (ACE) architecture may include a normal mode partition and a direct mode partition. The normal mode partition of the ACE processes a normal mode / auxiliary mode control surface control instruction transmitted by the FCM and transmits the normal mode / auxiliary mode control surface control instruction to the ACE direct mode partition, and the ACE direct mode partition verifies the normal mode / auxiliary mode control surface control instruction; and an effective normal mode / auxiliary mode control surface control instruction or an effective direct mode control surface control instruction is transmitted to a remote control unit (REU), so that the ACE common mode fault problem in a flight control system can be avoided as far as possible.

A system and method are disclosed and may be used for controlling (e.g., stabilizing) a suspended load. The system may include a hoist, an imaging sensor configured to capture images of a swinging of a load suspended from the hoist, and a controller. The controller may include one or more processors configured to execute a set of program instructions stored in a memory. The program instructions may be configured to cause the one or more processors to receive the images, determine positions of the load over time based on the images, calculate swing data of the swinging of the load based on the positions, determine flight control commands based on the swing data, and direct a flight control system configured to adjust a flight of an aircraft based on the flight control commands.

A flight control system for an aircraft including a first set of primary flight control computers and a second set of secondary flight control computers, where each primary flight control computer implements a first autopilot functionality. The secondary flight control computers jointly take control of control surface actuators when the primary flight control computers fail. The flight control system further includes another computer, to which the secondary flight control computers are connected, which implements a simplified second autopilot functionality, the second autopilot functionality being able to be activated only when the second set of flight control computers has control of the control surface actuators. Thus, an autopilot functionality is widely available, while at the same time ensuring the robustness sought by the installation of the secondary flight control computers.

The invention belongs to the technical field of intelligent management, and discloses an unmanned aerial vehicle intelligent flight control system for low-altitude traffic management. The data acquisition module is used for acquiring gyroscope data, gravity gradient data and atomic clock time; the reference construction module is used for analyzing and obtaining initial positioning coordinates through a gravity matching positioning algorithm based on the gravity gradient data and the dynamic gravity anomaly graph; the coupling positioning module is used for analyzing according to the initial positioning coordinate, the gravity gradient data and the environment data to obtain a positioning error vector; the communication disaster recovery module is used for analyzing according to the initial positioning coordinate and the positioning error vector to obtain a gravity positioning result; the path re-planning module is used for analyzing according to a pre-stored gravity anomaly graph and a gravity positioning result to obtain an optimized flight path; according to the method, the problem of positioning failure caused by GPS signal loss in a strong interference environment is effectively solved, and high-precision positioning independent of GPS, real-time error correction and optimal path planning adaptive to a gravity field are realized.

The invention discloses a flight control system and method for a heavy-load manned eVTOL aircraft, and relates to the technical field of intelligent control of electric vertical take-off and landing aircrafts, and the method comprises the following steps: S100, obtaining the parameter information of cargoes carried by the aircraft, constructing a reflection risk distribution map covering the sensing range of the aircraft, and obtaining a reflection risk distribution map; the marker is used for marking a high-reflection interference risk space area; and S200, based on the reflection risk distribution diagram, carrying out angular domain shielding processing on laser radar and millimeter wave radar beams, shielding echo signals in corresponding directions, and obtaining an effective echo region. According to the invention, by constructing the reflection risk distribution diagram and a multi-mode fusion perception compensation mechanism, the identification and avoidance capability of the aircraft on high reflection interference in a manned freight task is improved, closed-loop control of perception correction and flight control parameter dynamic adjustment is realized, and the flight safety and stability are guaranteed.

The application belongs to the field of electromechanical control, and relates to electric pump working control technology, and discloses an electric pump working comprehensive control method and system.The working comprehensive control method comprises the following steps: collecting machine state signals, flight control system state signals and hydraulic pressure of each sub-hydraulic system in a hydraulic system in real time; controlling the opening and closing of the electric pump connected to the sub-hydraulic system according to the machine state signals through a first electric pump control logic and an error prevention working mechanism; and automatically controlling the electric pump connected to each sub-hydraulic system according to the flight control system state signals, the hydraulic pressure and the rest of the electric pump control instructions through a second electric pump control logic, the error prevention working mechanism and a staggered working mechanism.The application can ensure the accuracy of the electric pump working, avoid system damage caused by simultaneous starting of the electric pump, and improve system safety.

The application discloses a kind of based on hybrid power eVTOL unmanned aerial vehicle control method and related device, its method includes: flight control computer is based on flight control instruction obtains the flight phase that eVTOL unmanned aerial vehicle currently is in, the flight phase includes vertical take-off and landing phase, overdrive mode phase, cruise phase and emergency mode phase;The flight control computer indexes to the flight control strategy corresponding to the flight phase that eVTOL unmanned aerial vehicle currently is in;The flight control computer controls the turbine power generation system and / or the power battery pack based on the flight control strategy to N cruise electric drive unit and M vertical take-off electric drive unit on the eVTOL unmanned aerial vehicle Power supply processing.In the embodiment of the application, turbine power generation system and power battery pack are connected in parallel to supply power for eVTOL unmanned aerial vehicle, while combining redundancy flight control system, so as to achieve optimization in voyage expansion and safety performance improvement.

A flight control system may include active sidesticks with active sidestick computers which may execute flight control functions to determine control surface commands for remote electronic units. The active sidesticks may also include remote data concentrators which concentrate digital data for processing by the active sidestick computers. The flight control system may also include additional remote data concentrators and flight control computers which are located outside of the active sidesticks. The flight control computers may also generate the control surface commands for the remote electronic units.

System and method for intercepting intruding stratospheric balloons. The method comprises: receive (102, 104) a high-altitude wind profile (6) and a position (P0) of an intruding stratospheric balloon (2); Determine (106, 108), using the high-altitude wind profile (6), a future trajectory (10) of the intruding stratospheric balloon (2) and ascending trajectories (11a, 11b) of an intercepting stratospheric balloon (5) that intercept the future trajectory (10) at different positions (PF1, PF2); select (110) an upward path (11a); to perform a launch (112) of the intercepting stratospheric balloon (5) at a launch location (Li) and time (tL1) associated with the selected upward trajectory (11a); detect (114) deviations of the trajectory followed by the interceptor stratospheric balloon (5) during ascent with respect to the selected ascending trajectory (11a) and correct such deviations by activating a flight control system (12) of the interceptor stratospheric balloon (5); and activate (116) an interception apparatus (13) of the intercepting stratospheric balloon (5) once the interception (15) of the intruding stratospheric balloon (2) occurs.

The present invention provides a method and device for inhibiting the trim mechanism of a fly-by-wire flight control system. The method comprises: determining the current operating state of the flight control system; determining whether the cockpit control system is in a non-disengaged state based on a redundancy signal output by a displacement sensor; determining whether the lateral trim position and the longitudinal trim position are at zero; the flight control module issuing a trim inhibition enable signal to cut off power to the lateral and longitudinal trim mechanisms, thereby successfully activating trim inhibition; and after trim inhibition is successfully activated, toggling the aileron trim switch and the elevator trim switch disables the corresponding lateral and longitudinal trim mechanisms. The present invention is intended to address the problem of the normal function of a fly-by-wire flight control system being affected by erroneous operation of the cockpit manual trim system.

The present invention relates to an electric flight control system (5) for controlling an aircraft (1).The flight control system (5) comprises a plurality of functional subsets (95), each having at least one dissimilar primary computer (35) and at least one dissimilar secondary computer (36), at least one functional subset (95) being a simplex / duplex subset (96) comprising at least three identical simplex primary computers (41, 42, 43) and at least one duplex secondary computer (44, 45), each duplex secondary computer (44, 45) of a simplex / duplex subset (96) comprising an independent and synchronized control computing channel (46) and a monitoring computing channel (47), each simplex primary computer (41, 42, 43) of a simplex / duplex subset (96) having a single computing channel, and in that, barring failure, the three primary computers (41, 42, 43) of a subset simplex / duplex (96) form two virtual pseudo-duplex computers. Abbreviation figure: figure 1.

1. Name of the product in this design: Helicopter Flight Control Module (NEXUS-X). 2. Purpose of this design: This design is used in the flight control system of a model helicopter. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.