109 results about "Telex" patented technology

A system providing mid-value selection (MVS) for control command output in a fly-by-wire system where the fly-by-wire systems includes a plurality of primary flight computers (PFCs) receiving data through integrated flight control buses from actuation control electronics (ACE) for flight crew and status sensor inputs, the PFCs providing data through the flight control buses to the ACE for control signal output, provides elements for receiving in an ACE data from each PFC and receiving a data valid signal with respect to each PFC. Fresh data for each PFC is selected as the data received or past MVS output responsive to the respective data valid signal. Based on a predetermined criterion the system chooses from the PFC fresh data a selected set of PFC fresh data as the MVS output and stores the MVS output for use.

An advertising/revenue generation system for use with telecommunication systems. A database can be organized or sorted on parameters relating to telecommunication, such as caller demographics, time and place of a call, and the services of the initially dialed number. Advertisers can submit advertisements to the advertising system. When a caller submits a communication request, for example by entering a telephone number into a communication device, the advertising system recognizes the request and accesses the database. The advertising system determines advertisements that are related to the caller's communication request and telecommunicates relevant advertising content to the caller. The content can be provided before, during, and/or after the caller establishes communication as initially requested. The advertising system can provide incentives to callers to select ads, can collect fees from advertisers for submitting their ads to callers, and can pay commissions to telecommunications carriers for supporting communication.

The invention relates to a hybrid redundancy configuration-based control architecture of a fly-by-wire flight control system. A control and sensing assembly, an actuator and a four-redundancy servo controller are connected with form a servo loop closed-loop control. The four-redundancy servo controller is connected with a three-redundancy flight control computer, and the two-way cross transmissionof data instructions is carried out. Therefore, the closed-loop control of a fly-by-wire inner loop and an automatic driving outer loop is realized. The flight control computer of each redundancy acquires the data of the four-redundancy servo controller at the same time and carries out monitoring and voting. The servo controller of each redundancy acquires the data of a three-redundancy flight control computer at the same time and carries out monitoring and voting. The three-redundancy flight control computer is connected with a comprehensive avionics management system, so that the data signal interaction of the flight control system is realized. A hybrid redundancy configuration is adopted by a control framework, so that the advantages of clear configuration, simple structure, complete functions, strong expandability, high safety and reliability, and good maintainability are realized.

The invention relates to an open platform for supporting design, verification and validation of a telex flight control system, which is composed of five function modules, namely 1) a demand analysis, verification and refinement environment module of the telex flight control system; 2) a design, verification and validation environment module of the telex flight control system; 3) a hardware design environment module of the telex flight control system; 4) a project development environment module of flight control software; and 5) a system-level entire digitization, entire duty simulation test and confirmation environment module of the telex flight control system. The open platform can assist flight control system engineers to carry out demand analysis and validation of the telex flight control system, system overall design, verification of a design proposal, system hardware design, system software project development, system-level entire digitization, entire duty simulation test and confirmation to solve the problems of long development cycle, high cost, large risk, and the like brought by development environment. The open platform has wide use value and application prospect in the technical field of system projects.

The invention discloses a configurational automatic flight control closed-loop test system and belongs to the technical field of aircraft testing. The configurational automatic flight control closed-loop test system includes a teletype control system, a high lifting force system, an automatic flight control system, an automatic flight control tester, a telex control tester and a flight simulator.The high lifting force system controls a slat movement mechanism to move and collects slat deflection signals; the high lifting force system sends the slat deflection signals to the teletype control system; slat signals are transmitted to the automatic flight control tester through the teletype control system and sent to the flight simulator through a reflection memory net; the flight simulator receives the slat signals and aircraft movement signals and then resolves flight attitude signals, and the flight attitude signals are transmitted to the telex control tester and the automatic flight control tester, to implement aircraft closed-loop control. Unnecessary testing devices are reduced, reliable stable high-precision configurational signals are provided for the flight simulator, and long-term high-strength test requirements are met.

The invention relates to a dynamic testing method of a digital telex main flight control system for an aircraft. The method comprises the following steps: sending an enable signal through a testing operating platform; responding to the enable signal through a flight control computer which communicates with the test operating platform; overlapping a preset standard signal to a command signal to dynamically test the tested system to obtain a responding signal; acquiring the command signal and the responding signal through the testing operating platform; receiving the command signal and the responding signal subjected to digital-analog conversion through a dynamic signal analyzing instrument; performing dynamic responding analysis for the command signal, the responding signal and a reference signal to obtain a first dynamic responding result and a second dynamic responding result; subtracting the first dynamic responding result and the second dynamic responding result under different frequency points to obtain the dynamic respond of the system under the different frequency points. According to the method, the delay caused by D/A conversion and data acquiring can be canceled out mutually during solving the difference, and thus the obtained system stability is avoided additional delay.

The invention discloses a processing method and apparatus used for high dynamic satellite navigation receiver baseband signal. The process of the satellite navigation receiver baseband signal is finished via the separated and parallel trapped engine and the tracing channel under the control of upper machine. When it comes to operation, the intermediate frequency signal enters the trapped engine and the tracing channel by mapping sample: the whole Doppler frequency domain parallel trapped algorithm is finished in the trapped engine, generates the local code sequence aligning with the phase of input signal sequence and transfer it to the tracing channel; in the tracing channel, the signal is accumulated timely and extracted, the bit quantity of the telex information, the monitoring quantity of the sheet deviation and the launching temporal information are provided to the upper machine; after the tracing channel losing lock, the trapped engine recaptures the signal. The invention adopts two-dimensional parallel search to accelerate the trapped speed; the trapped engine duplicates the FFT arithmetic unit, envelope arithmetic unit and detector and saves the resource; the module parameter design is fit for different system and scale.

Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes an asynchronous intermodule bus arrangement, a first vehicle control module, and a second vehicle control module. Each vehicle control module includes a respective interface arrangement to obtain and exchange data from different sensing arrangements with a first frequency, and a respective processing system to obtain the sensed data and determine actuator commands based on the sensed data with a lower frequency.

The invention relates to the field of steering control systems, in particular to a telex steering control system with feedback force. The telex steering control system is characterized by comprising a helm and a single-chip microcomputer. The helm is connected with a steering shaft, and the tail end of the steering shaft is meshed with a photoelectric encoder and a first brushless motor. The single-chip microcomputer receives pulses output by the photoelectric encoder and controls rotation speeds of the first brushless motor and a second brushless motor through a drive module. The second brushless motor is connected with a hydraulic steering gear which controls the oil inlet amount of an oil cylinder to achieve the rotation of a rudder blade, and the first brushless motor feeds the rotation angle of the rudder blade back to the helm. By means of the telex steering control system, the rotation of the rudder blade can be controlled accurately, drivers can actually sense the size of the rudder angle, and the failure rate of machinery is small.

The invention relates to a computer aided design system of a characteristic structure configuration flight control law. The system can be applied to a computer system and has a good man-machine interaction interface to be convenient for aided designers to finish the design operation of the characteristic structure configuration flight control law at high efficiency. The system provided by the invention can finish the design and simulation of the characteristic structure configuration flight control law and the design and simulation of horizontal and lateral control laws through the designers according to the parameters specified by the prompt input of a design subject operating window, and the design result is presented to the designers in the output forms such as graphs, data and the like, thus the optimization and selection of the multi-target control law control are carried out and the design and simulation of a telex control law are carried out.

A static brake pressure linear control method of a digital telex anti-skid brake system is disclosed. Through an anti-skid brake control box, the states of a brake command sensor and a static brake switch can be monitored in real time; through the states of the brake command sensor and the static brake switch, the states of an electric hydraulic pressure servo valve and an electromagnetic hydraulic lock can be determined; by adopting such control logic, the voltage-current gain of the electric hydraulic pressure servo valve controlled by an anti-skid brake control box 4 is realized; and the static brake pressure linear control is achieved. A dual wheel plane digital telex anti-skid brake system is taken as the base, the present structure, mechanical interfaces and electrical interfaces ofthe digital telex anti-skid brake system are maintained, by changing the static brake control logic, the linear control of plane static brake pressure and brake force moment is realized, the safe take-off is guaranteed, and the man-machine interaction of the brake system is excellent.

The invention relates to a system fault comprehensive declare processing method, in particular to a fault comprehensive declare processing method of a redundancy fly-by-wire flight control system. The redundancy fly-by-wire flight control system is composed of subsystems of a flight control computer, a servo actuator, a sensor, a control display, a built-in self detector and the like; in order to improve redundancy management information comprehensive capability of the subsystems, default information characteristic quantity of the subsystems are extracted and are composited by using a state matrix mode, fault levels are determined according to fault modes and number of faults, the system faults are comprehensively declared, and the fault modes and the fault levels are indicated through different modes and equipment, so that pilots can timely know flying state and security status of airplanes. The faults are comprehensively declared by the state matrix mode, the information of the faults is concentrated in one form document, the comprehensive declare information is acquired by searching the file, and accuracy in requirement description and execution efficiency of software are improved.

Belonging to the technical field of aircraft actuating system, the invention discloses an aircraft actuating system with mechanical aligning function. The system comprises an actuator controller (1), an actuator (2) with a mechanical aligning mechanism, a mechanical aligning rod (3) and a support (4). The actuator is mounted on a vertical tail back beam, one end of the mechanical aligning rod (3) is connected to the actuator, and the other end is connected to the support (4), and the support (4) is mounted on a rudder. Under a telex mode, the actuator controller (1) receives instruction from a flight control computer, converts the instruction into an output instruction and sends it to the actuator, the actuator responds to the instruction of the actuator controller (1) and makes movement to drive the rudder to deflect, at the moment a mechanical aligning mechanism on the actuator is in a suspension state, and does not respond to the instruction of the actuator. After conversion from a telex control mode to a mechanical aligning mode, the mechanical aligning mechanism on the actuator starts to work, through the feedback of the mechanical aligning rod to the rudder position, the rudder is driven to return to a neutral position.

The invention belongs to the technical field of steering systems of front wheels of airplanes, and particularly relates to a telex steering system of a carrier-based aircraft. The telex steering system is characterized by comprising a driver pedal steering sensor (1), a steering control unit (2), a steering control valve (3), a steering actuator (4) and a steering angle feedback sensor (5). According to the telex steering system disclosed by the invention, the condition that the mounting space of the system adapts to a space of a nose landing gear bin of the carrier-based aircraft can be ensured, and meanwhile, the requirement of 360-degree rotation of a nose landing gear of the carrier-based aircraft can be met.

The invention belongs to the redundancy management technology of a fly-by-wire control system and specifically relates to a mechanical two-redundancy and electrical four-redundancy attack angle sensor output monitoring and voting structure and a voting method thereof. The method is characterized by, to begin with, carrying out monitoring and voting on electrical four-redundancy signals of left and right attack angles to obtain attack angle electrical voting values respectively; and then, carrying out voting again on the electrical voting values of the left and right attack angles to obtain mechanical attack angle voting values respectively. Attack angle redundancy configuration is reasonable, and the monitoring and voting method is reliable; system closed loop control is allowed to be stable and reliable; and meanwhile, requirements for attack angle sensor output reliability and safety of the fly-by-wire control system are met.

The invention discloses a non-contact electricity-stealing prevention real-time monitoring device and method, and the device comprises a control unit, an electricity-stealing sensing unit, a zero electricity-stealing detection unit, a door magnetic detection unit, an automatic switching unit, a picture capturing unit, an APP data terminal unit and a power supply unit, wherein the electricity-stealing sensing unit, the zero electricity-stealing detection unit, the door magnetic detection unit, the automatic switching unit, the picture capturing unit, the APP data terminal unit and the power supply unit are connected with the control unit. The device and method can solve a technical problem that a conventional electricity-stealing prevention means cannot effectively prevent the non-contact electricity stealing, cannot locate an electricity theft and cannot upload the electricity-stealing information in real time.

The invention relates to a fly-by-wire system which comprises: three-stage piloting control (4), each stage including a control computer (16, 18, 20) suitable for determining the positions of the stick, and a monitoring computer (22, 24, 26) capable of verifying all the pre-determined positions of the stick; three-stage control-surface position calculation (6), each stage including a control computer (40, 42, 44) suitable for calculating the control-surface positions from encoded positions of the stick, and a monitoring computer (46, 48, 50) capable of verifying all the calculated control-surface positions; a single unidirectional communication link (88) connecting the control computer (16) of the first piloting control stage to the control computer (40) of the first control-surface position calculation stage; a single unidirectional communication link (132) connecting the control computer (18) of the second piloting control stage to the control computer (42) of the second control-surface position calculation stage; and a single unidirectional communication link (142) connecting the control computer (20) of the third piloting control stage to the control computer (44) of the third control-surface position calculation stage.

The embodiment of the invention provides a high-lift distributed teletype control system. The system comprises a control handle 1, a first high-lift control computer (HLCC) 3, a second high-lift control computer (HLCC) 4, a first flap motor control unit (FMCU) 6, a first slat motor control unit (SMCU) 5, a second flap motor control unit (FMCU) 7, a second slat motor control unit (SMCU) 8 and a mechanical transmission subsystem 9, wherein the first high-lift control computer (HLCC) 3 and the second high-lift control computer (HLCC) 4 are connected to the flap motor control unit (FMCU) 6, the first slat motor control unit (SMCU) 5, the second flap motor control unit (FMCU) 7 and the second slat motor control unit (SMCU) 8 in a bus mode and are both connected to the control handle 1, and thefirst flap motor control unit (FMCU) 6, the first slat motor control unit (SMCU) 5, the second flap motor control unit (FMCU) 7 and the second slat motor control unit (SMCU) 8 are connected to the mechanical transmission subsystem 9.

The invention belongs to the field of helicopter model identification, and provides a flight experiment data rapid frequency domain identification method suitable for a telex flight control helicopter, which comprises the following steps of: 1, eliminating and correcting a data outlier, performing low-pass filtering, correcting a sensor position, checking data compatibility and reconstructing data; 2, converting the flight experiment data into a frequency domain, constructing an identification model, and adopting a completely linearized state space model; 3, fast initial value estimation is carried out, and initial value estimation theta of the to-be-identified parameters is obtained; 4, model structure identification is carried out, and before the next step of identification is carried out, the parameters are selected and used; And 5, outputting an error in a fast frequency domain. According to the method, the accelerated optimization algorithm is designed according to the characteristic that the convergence rates of the parameters to be identified are different, so that the calculation efficiency is further improved, the relatively detailed description of the frequency spectrum is realized, and meanwhile, the calculation amount is ensured.

The invention discloses a dual-redundancy hydraulic machinery clutch mechanism for a mechanical backup actuator. The mechanism is characterized by comprising a hydraulic lock (1) and two sets of hydraulic machinery conversion control mechanisms; each set of hydraulic machinery conversion control mechanisms is matched with the hydraulic lock (1); and when a telex working mode of the actuator is failed, the intervention of a mechanical backup operation function is realized. Through design of the dual-redundancy hydraulic machinery clutch mechanism, the conversion of manual operation and other operation functions is realized, the clutch conversion reliability and safety are improved, and the mode conversion failure, the dysfunction or the hydraulic impact possibly caused by a traditional clutch mechanism is prevented.