7444results about "Attitude control" patented technology

Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters. When either the first or the second cockpit instrument panel fails, the remaining functional, first or second display, is adapted to provide all of the important flight information data, including airspeed, attitude, altitude, and detailed engine parameters.

The motion of the movable sections of the robot is taken for a periodic motion so that the attitude of the robot can be stably controlled in a broad sense of the word by regulating the transfer of the movable sections. More specifically, one or more than one phase generators are used for the robot system and one of the plurality of controllers is selected depending on the generated phase. Then, the controller controls the drive of the movable sections according to continuous phase information. Additionally, the actual phase is estimated from the physical system and the frequency and the phase of the phase generator are regulated by using the estimated value, while the physical phase and the phase generator of the robot system are subjected to mutual entrainment so that consequently, it is possible to control the motion of the robot by effectively using the dynamics of the robot.

Systems and methods are provided for integrated control, access, and presentation of flight information within the cockpit. Cockpit instrument systems and methods are provided which include a first cockpit instrument panel which has a first display proximately located to a first bezel. The first display is operable to present navigational data, communication data, and flight information data including airspeed, attitude, and altitude. The systems and methods further include a second cockpit instrument panel located adjacent to the first cockpit instrument panel. The second cockpit instrument panel has a second display proximately located to a second bezel. The second display is operable to present navigational data, communication data, and flight information data including detailed engine parameters. When either the first or the second cockpit instrument panel fails, the remaining functional, first or second display, is adapted to provide all of the important flight information data, including airspeed, attitude, altitude, and detailed engine parameters.

This invention is directed to a 3-dimensional imaging lidar, which utilizes modest power kHz rate lasers, array detectors, photon-counting multi-channel timing receivers, and dual wedge optical scanners with transmitter point-ahead correction to provide contiguous high spatial resolution mapping of surface features including ground, water, man-made objects, vegetation and submerged surfaces from an aircraft or a spacecraft.

A method for policing and managing the operation of a flying, unmanned aircraft in the event of usurpation of control of, malfunction of, or ill-intentioned use of, this aircraft includes the steps of (a) detecting inappropriate operation of the aircraft; (b) transmitting a takeover command to the aircraft to interrupt control of the operation of this aircraft by a first pilot and relinquish control of the aircraft to a second pilot; and (c) transmitting control commands to the aircraft to control its operation by the second pilot, until the need for alternate pilot control of the aircraft has ended or until the aircraft has landed safely.

The invention discloses a transformer station inspection tour robot positioning navigation system and a method. Confidence obtained by a laser range finding module and a dead reckoning module is outputted to a map creation module and a pose resolving module; the map creation module creates a laser road sign map and a laser grid map which show a robot operation environment and are inputted into a map storage module for storage; the posture resolving module utilizes map data in the map storage module and output data of the dead reckoning module to perform real-time calculation on the current position and the posture of the robot and accesses the obtained posture data into a path planning module and a motion control module; the path planning module generates robot operation path data which is outputted to the motion control module; the motion control module generates motion control quantity according to the current position and posture data of the robot and the path planning data, and then is driven to execute by a motor. The transformer station inspection tour robot positioning navigation system realizes the accuracy positioning of the inspection tour robot in the transformer station.

A closed-loop LRF pointing technology to measure the range of a target satellite from a chaser satellite for rendezvous is provided that includes several component technologies: LOS angle measurements of the target satellite on a visible sensor focal plane and the angles' relationships with the relative position of the target in inertial or LVLH frame, a relative navigation Kalman filter, attitude determination of the visible sensor with gyros, star trackers and a Kalman filter, pointing and rate commands for tracking the target, and an attitude controller. An analytical, steady-state, three-axis, six-state Kalman filter is provided for attitude determination. The system and its component technologies provide improved functionality and precision for relative navigation, attitude determination, pointing, and tracking for rendezvous. Kalman filters are designed specifically for the architecture of the closed-loop system to allow for pointing the laser rangefinder to a target even if a visible sensor, a laser rangefinder, gyros and a star tracker are misaligned and the LOS angle measurements from the visible sensor are interrupted.

A method and system which allow a user to define and edit workflow applications for a mobile device, screens associated with the applications, and workflow process is described. The states or schemas for these applications may be stored as records in databases.

A multiple rotors aircraft and a control method thereof are provided. The control method comprises the following steps. First, current motion information of the multiple rotors aircraft is obtained. Then, at least one control gain is adjusted through a gain adjustment function according to the current motion information. The gain adjustment function conforms to a non-Lipschitzian characteristic, and at least one rotor of the multiple rotors aircraft is controlled according to the control gain. Therefore, the multiple rotors aircraft would be ensured that its flight attitude is toward a target position, and the expected result would be conformed rapidly.

The invention discloses an unmanned aerial vehicle course generation method which includes the following steps: conducting view finding and flying in advance, recording flight waypoints which include location data and flight height information of an unmanned aerial vehicle; receiving and recording the flight waypoints of the unmanned aerial vehicle; generating a flight track according to the flight waypoints of the view finding and flying; compiling the flight track to obtain a new flight track; transmitting the complied flight track to the unmanned aerial vehicle to enable the unmanned aerial vehicle to fly according to the new flight track. An unmanned aerial vehicle course generation system is further provided.

The lumbar part of a robot as a controlled-object point where the mass is moved to the largest extent is set as the origin of a local coordinate, an acceleration sensor is disposed at the controlled-object point to directly measure the attitude and acceleration at that position to control the robot to take a stable posture on the basis of a ZMP. Further, at each foot which touches the walking surface, there are provided a floor reaction force sensor and acceleration sensor to directly measure a ZMP and force, and a ZMP equation is formulated directly at the foot nearest to a ZMP position. Thus there can be implemented a stricter and quick control of the robot for a stable posture.

A vertical situation display system for use in a vehicle such as, for example, an aircraft, is provided. A side view of an intended route of flight may be shown with altitude restrictions, airspace and instrument approach information, a projected flight path and range to airspeed symbol. The system may show terrain, weather, and traffic information along the intended route of flight. The system may be used in conjunction with a navigational display to enhance situational awareness. The system includes a computer, an electronic display device, an electronic entry device, a memory and a database. The database may contain terrain, airspace and flight planning data and may be updatable.

A system of self-organizing mobile robotic agents (MRAs) in a multi-robotic system (MRS) is disclosed. MRAs cooperate, learn and interact with the environment. The system uses various AI technologies including genetic algorithms, genetic programming and evolving artificial neural networks to develop emergent dynamic behaviors. The collective behaviors of autonomous intelligent robotic agents are applied to numerous applications. The system uses hybrid control architectures. The system also develops dynamic coalitions of groups of autonomous MRAs for formation and reformation in order to perform complex tasks.

A method and apparatus for managing separation between vehicles. A closest point of approach between a first vehicle traveling along a first path and a second vehicle traveling along a second path is predicted. A number of compensation commands for altering the first path of the first vehicle are generated using the closest point of approach and a desired level of separation between the first vehicle and the second vehicle. The number of compensation commands is integrated with a number of control commands for the first vehicle to form a final number of control commands configured to maneuver the first vehicle to substantially maintain the desired level of separation between the first vehicle and the second vehicle. A response of the first vehicle to the final number of control commands is a desired response.

A control method of a two-wheeled self-balance vehicle comprises the steps as follows: (1), performing initialization: (2), reading values of a gyroscope, an accelerometer and a rotation angle sensor as well as the pulse number of an encoder respectively; (3), obtaining a vehicle body inclination, a handlebar turning angle, motor speeds and a vehicle speed; (4), then calculating PWM (pulse width modulation) values of vertical control, direction control and speed control respectively through a PID (proportion integration differentiation) control algorithm; (5), superposing the three PWM values together and outputting the three PWM values to left and right motors; (6), then sending data of the gyroscope, the accelerometer, the vehicle body inclination, a battery voltage, motor currents and the vehicle speed to an upper computer so as to monitor the operating status of the whole vehicle; (7), when the battery voltage is monitored to be smaller than a preset value, and the motor currents or the vehicle speed is monitored to be larger than the preset value through monitoring, turning on corresponding LED warning lights; and (8), when the vehicle body inclination is larger than a preset angle through monitoring when the vehicle body inclination is monitored to be larger than a preset angle, determining that the vehicle body falls down, stopping the operation and returning to an initializer. According to the control method, a more accurate operational method is adopted.

A remotely controlled flying apparatus (200) utilized for crop-spraying and crop monitoring purposes is disclosed. The present indention comprises a microcontroller (110) electronically coupled to an inertia measuring means (120). A controller (140) is connected to a computer (130) to allow a user to control movements of the flying apparatus (200). The computer (130) interprets control motions of the controller (140) and translates the motions to control signals. Upon translation, control signals are sent to the microcontroller (110) wirelessly and the control signals are modulated by a pulse modulation generator (150) before they are sent to a plurality of speed controllers (160a-160d) which are coupled to a plurality of motors (170a-! 70d). The controller (140) allows the user to control the motions of the flying apparatus remote! }, by changing respective rotational speeds of the plurality of motors (170a-170d). The controller (140) also allows the user to wirelessly control a pump (180) or a camera (190) or both through the computer (130) for spraying a pesticide or fertilizer fluid—when necessary or for crop monitoring purposes.

An un-manned airborne vehicle (UAV), for acquiring aeromagnetic data for geophysical surveying at low altitude on land or over water, comprising an extended fuselage that is adapted to hold and maintain magnetometer and a magnetic compensation magnetometer at a minimum distance from the avionics and propulsion systems of the UAV. The magnetometer measures magnetic anomalies and the magnetic compensation magnetometer measures magnetic responses corresponding to the pitch, yaw and roll of the UAV. A data acquisition system stores and removes the magnetic response measurements from the magnetic anomaly measurements. The data acquisition system also stores a survey flight plan and transmits the same to the avionics system. The generator of the UAV is shielded and the propulsion system is stabilized to reduce magnetic and vibrational noises that can interfere with the operation of the magnetometer.

A method of stabilizing a jet-powered tri-mode aircraft as the aircraft travels in a helicopter mode, a compound mode, and a fixed-wing mode is disclosed. The method includes receiving a plurality of velocity vector component values and velocity vector commands derived from either (1) a number of pilot operated controllers or (2) a commanded array of waypoints, which are used for fully automated flights, and a rotor speed reference value, which is decreased with increasing forward speed to unload the rotor, thereby permitting conditions for stopping the rotor in flight. Stabilization of the commanded velocity vector is achieved in all modes of flight using blended combinations of rotor swashplate controls and aerodynamic controls such as elevons, canards, rudders, and a horizontal tail. Stabilization to the commanded velocity vector includes a plurality of control constraints applied to the pilot stick controllers that prevent penetration of envelope limits.

Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.

In order to measure the movement of a vehicle, especially an aircraft, an imaging optical system 2 which is to be positioned on the vehicle is used to detect an image of the environment 4, and an optoelectronic shift sensor 3 chip of the type comprising an inherent evaluation unit is used to measure any shift of the image from structures thereof. The shift sensor is equal or similar to the sensor used on an optical mouse. The sensor is positioned in such a way that infinite objects are focused. The measuring signal is evaluated to indicate movements and/or the position of the aircraft. The inventive system can also be used to measure distances e.g. in order to control the flight altitude. The invention further relates to methods for automatically controlling particularly a hovering flight by means of a control loop using optical flow measurement.

The invention relates to a miniature unmanned helicopter auto flight control system which comprises an on-board control system, wherein, an on-board computer gets signals from sensors through a serial port, and exchanges data with a ground-based computer through on-board and ground wireless Ethernet access points; the on-board computer carries out serial communication with a digital signal processor to control a steering engine set of the unmanned helicopter; a remote control signal receiver outputs to the digital signal processor and then is connected with the on-board computer through a serial port, and an auto control signal and a ground remote control signal are accumulated to get a current steering engine control signal. And the auto flight control system also comprises a ground control system, wherein, the ground-based computer transmits flight control instructions to the on-board computer and receives and records flight data; through operating a ground helicopter remote controller, manual control instructions can be transmitted to the on-board remote control signal receiver via wireless radio frequency signals. The invention can improve the auto flight ability of the miniature unmanned helicopter, strengthen system reliability, expand the application range of the unmanned helicopter and enable the helicopter to complete given missions beyond the visual range.

The present invention models dynamic behavior of flight vehicles for simulation, analysis, and design. The present invention allows a user to define the complexity of a flight vehicle model, and such models may be simple rigid body models, models of medium complexity, or very complex models including high order dynamics comprising hundreds of structural flexibility modes and variables related to aero-elasticity, fuel sloshing, various types of effectors, tail-wags-dog dynamics, complex actuator models, load-torque feedback, wind gusts, and other parameters impacting flight vehicles. The present invention accommodates and analyzes multiple vehicle and actuator concepts and configurations as defined in flight vehicle input data, which specifies flight vehicle parameters at a steady-state condition for modeling flight vehicle response to dynamic forces and flight control commands with respect to steady state operation.