181 results about "Flight instruments" patented technology

A flight instrument displays azimuth information in combination with horizon information and other optional information such as altitude and / or airspeed. Azimuth information is displayed using an elliptical pattern placed below a horizon line displaying horizon information. The horizon information may be based on gyro enhanced vertical speed and / or vertical axis information. The elliptical pattern may be representative of a horizontal circular heading indicator viewed from above and behind the circular indicator. In one embodiment, the elliptical azimuth pattern moves in response to movement of the horizon line to maintain position below the horizon line. Airspeed and / or altitude information may be displayed at the sides of the screen area using a circular arc display pattern

A device for providing flight condition information and a method of displaying such information. In one form, the device functions as a backup system to provide flight condition information in the event of partial or complete inoperability of a primary flight instrument system, or to complement such primary flight instrument system. Numerous sensors collect flight data, which can pass through devices to convert and manipulate the data to produce flight condition information that can be displayed in such a way as to reduce a pilot's cognitive workload. The information displayed includes at least flight path angle, lateral acceleration, and turn rate. Additional information that may be displayed includes heading information, as well as information relating to airspeed and altitude, among others. In another form, the device can be part of either a primary or backup system.

The device attracts the attention of an aircraft crew on approach or normal (alert) or abnormal (alarm) crossing, of a traffic zone of an airport infrastructure presenting risks of collision. Accordingly, it selects on the basis of the information provided by the flight instruments, a type of flight phase from among a limited and pre-established choice of predefined types of flight phase. Then considers one or more runway incursion scenarios that are predefined as a function of the selected type of flight phase whose likelihood it analyzes by comparing the position of the aircraft provided by an onboard locating device with a plan of the airport infrastructure derived from an airport database and determines, on the basis of the analyzed scenarios that appear to be likely, alerts and alarms to be emitted in the cockpit.

The present invention is directed to novel primary flight displays, moving map displays and engine parameter displays for aircraft cockpits. These displays process data gathered from various aircraft sensors and, using an various electronic databases, generate intuitive symbols that aid the pilot. The present invention also uses various novel algorithms that use data gathered from inexpensive sensors to derive parameters normally requiring far more expensive sensors.

An integrated flight instrument which provides unambiguous information regarding the motion of a hovering aircraft. The instrument accurately depicts motion in six degrees of freedom (roll, pitch, yaw, forward translation, lateral translation, and vertical translation), as well as aircraft power requirements and utilization.

Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.

Apparatus and methods are provided for flight instruments in an electronic format. The flight instruments may appear in a standard configuration, including both primary flight instruments and secondary flight instruments. The apparatus and methods may also provide some or all of the primary flight instruments in one visual representation.

The invention provides an aviation emergency instrument which comprises an atmospheric pressure measurement unit, an inertial measurement unit, a double-antenna GPS satellite receiver connected with a satellite signal receiving antenna, a graphic display unit, a secondary power supply circuit, and a comprehensive processing and calculation unit, wherein the comprehensive processing and calculation unit receives the information from the individual sensors, calculates the navigation parameters indicative of air speed, pressure altitude, posture, flight direction, longitude and latitude by use of a sensor information fusion algorithm, and sends the calculation result to the high-density liquid crystal graphic display unit. According to the invention, since the aviation emergency instrument can provide the navigation parameters indicative of air speed, pressure altitude, posture (pitch angle and roll angle), flight direction, longitude and latitude, the aviation emergency instrument can not only provide reference information to a pilot who operates the main flight instrument in the normal state but also serve as an emergency instrument in case that the main flight instrument is in the failure state. When the main flight instrument completely fails to work, the pilot can operate the aircraft to return safely by means of the navigation information provided by the emergency instrument.

A a flight instrument enabling a pilot to intercept and precisely follow a predefined GPS track. The instrument—known as a GPS steering indicator—provides a visual display which is similar in appearance to other aircraft instruments (and therefore instantly recognizable to nearly all pilots). However, the instrument is preferably differentiated somewhat in its visual appearance to convey to the pilot the fact that it displays steering commands rather than cross track error. An indicator needle deflects to instruct the pilot which way to turn and how much to turn in order to intercept and fly along a predefined GPS track. By centering the indicator needle, the pilot maintains the desired instantaneous track.

A flight instrument and associated method where vertical speed information is combined with gyro information to produce gyro enhanced vertical speed information that is displayed to a pilot. The gyro information may include a pitch rate gyro and may include an azimuth rate gyro. The pitch rate gyro and azimuth rate gyro may be combined to yield a corrected pitch rate in turns. In one embodiment, the display is an airplane symbol that moves relative to a horizon line responsive to the gyro enhanced vertical speed information. The horizon line may also tilt in response to the azimuth rate gyro.

Flight data recorder with web access in real time to be used for recording and transmitting via internet in real time all events on-board and control parameters and aircrafts' command, and includes a computer with audio and video inputs respectively referred to microphones and cameras and ARINC interface (Aeronautical Radio Inc.) connected to the aircraft net to obtain information on the flight instruments, so that the information obtained, processed in the flight device formed by the data acquisition unit and cabin interface, is transmitted via internet through an ISP satellite (internet service provider) to the on land data center that feeds a database and provides, through a WEB application service, a front-end of specific access for each client where it can view in real time the information of any of his aircrafts and check the historic information and the application programming interface (API) which enables personalized and direct access for private use.

A flexible, thermal bridge element, particularly for a space flight instrument, a satellite, a transportation device, or a machine component, includes a number of carbon fiber-reinforced plastic (CFK) layers stacked on top of one another. Each of the CFK layers is composed of a plurality of heat-conductive carbon fibers embedded in a matrix. In at least two segments, particularly opposing end segments, the CFK layers are freed of the material of the matrix so that the carbon fibers of a respective CFK layer are exposed in the at least two segments. The exposed segments of the carbon fibers are provided with an associated metallization, by way of which within the framework of a thermally assisted joining process, the bridge element is connected to a thermally conductive connector element.

The invention discloses a flight fault emergency processing method and system, and relates to the field of flight fault processing. The method comprises the steps: S1, monitoring and collecting flightstate parameters in real time; S2, analyzing the flight state parameters to confirm flight fault conditions; S3, judging the priority of the flight fault condition, forming an execution strategy, andissuing the execution strategy to an unmanned aerial vehicle; and S4, controlling flight according to the execution strategy. The device comprises a data acquisition module, a data analysis module, afault strategy module and a flight control module. According to the invention, priority ranking is carried out on all the fault types, and an execution strategy is formed to control flight of an unmanned aerial vehicle, so that the application value of single flight of the unmanned aerial vehicle is maximized; measures corresponding to all the fault types are refined, and judgment processing of fault recovery is added, so that flight safety of the unmanned aerial vehicle is more reliable, and personal and property safety can be better guaranteed; and a fault priority discrimination module isadditionally arranged to sort various fault types of the unmanned aerial vehicle and generate a corresponding execution strategy, so that the single flight application value of the unmanned aerial vehicle is maximized.

A device supports a motorized flying instrument in a wind tunnel. To carry out tests in a wind tunnel on a motorized flying instrument (10), with the motor on, under different attitudes hands off, the instrument is connected to the fixed structure (15) of the wind tunnel (11) by a mounting device (12) at least one of the supports (14, 16) of which is fitted with a length adjustment system, such as a hydraulic jack (28). This jack (28) is remote controlled, in real time, by a control system (42).

The invention discloses a rotary wing blade type flapping wing air vehicle belonging to the technical field of aviation. The rotary wing blade type flapping wing air vehicle mainly comprises an air vehicle body, a tail rotor, a left rotary flapping wing device, a right rotary flapping wing device and an undercarriage, wherein the air vehicle body is internally matched with an operation control system, a self-navigated autonomous flight instrument and a remote control system; the left rotary flapping wing device and the right rotary flapping wing device are same in structure, parameter and working principle and are symmetrically arranged at a left support and a right support extending at the left and right sides of the air vehicle body; the tail rotor is driven by a small motor; the right rotary flapping wing device comprises an engine, a main shaft, a rotary arm, a central fixed gear, a first near-center gear, a first remote-center gear, a first wing blade, a second near-center gear, a second remote-center gear and a second wing blade; the meshing transmission ratio of all gears is 1:1; and the first wing blade and the second wing blade alternately upwards and upwards rush to generate a forward thrust force and an upward thrust force. The rotary wing blade type flapping wing air vehicle is used for meeting the requirements of aerial photography, agriculture, forestry and animal husbandry works and military affairs.

An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and / or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component.

This disclosure describes a system and method of an instrument flight training system that provides student pilots with simulation of instrument flight conditions. This is accomplished by obscuring the outside world using two cross-polarizing filters, one on the windshield and one on the student pilot's glasses, while still providing a view of all of the flight instruments inside of the cockpit to the student pilot, while providing a view of the outside world to a second pilot who is not wearing the glasses.

The invention belongs to the technical field of power equipment maintenance, and discloses an ice melting device and method for an electric transmission and distribution circuit in winter. The ice smelting device adopted by the method comprises an ice smelting aircraft; the ice smelting aircraft is composed of a monitoring device 2, an ice smelting device and a flying device 1; one side of the lower part of the flying device 1 is provided with a monitoring device, and the other side of the lower part of the flying device 1 is provided with the ice smelting device; the monitoring device is composed of a detector 2 and an actuator 3; the ice smelting device is composed of an f fan 4, a heating device 5 and an air duct 6; an air outlet of the f fan 4 is communicated with an input end of the heating device 5; and an output end of the heating device 5 is communicated with the air duct 6. The ice melting device and the method for the electric transmission and distribution circuit in winter provided by the invention can monitor and clear ice covering of the electric transmission and distribution circuit in a running process, maintain power transmission and transformation, and guarantee the reliable operation of electric transmission and transformation equipment.

The invention discloses an unmanned aerial vehicle auxiliary flight device based on artificial intelligence and a flight control method. The method comprises the steps of: establishing a knowledge base and a reaction planning base; monitoring and judging early warning indexes; finding a similar strategy close to an existing knowledge base and a reaction planning base autonomously through an algorithm, and outputting a control quantity corresponding to the early warning state quantity; receiving the control quantity through an actuator, and executing the strategy; performing early warning and judging whether actual flight is safe or not; additionally arranging a new danger library, and storing the state quantity of unsafe early warning judgment and the executed control quantity in the danger library; and determining the state quantity of early warning judgment safety and the executed control quantity as a new safety strategy, storing the new safety strategy in a real flight state matrix, and expanding data of a knowledge base and a reaction planning base. According to the invention, the flight mode can be self-designed, two same decision errors cannot be caused in the same flight state, and through a large amount of actual flight and calculation, the flight strategy iterated by the artificial intelligence algorithm is safer.

The invention discloses a flight detection ship which comprises a ship body (1), a support (2) arranged above the ship body (1), a grabbing device (3) arranged in the support (2), an underwater robot(4) arranged in the grabbing device (3), a flight device (5) arranged on the support (2), a detection device (6) arranged on the flight device (5), and a control host (7) arranged in the support (2) and used for controlling the movement of the ship body (1), the movement of the grabbing device (3), the movement of the flight device (5) and the work of the detection device (6). According to the flight detection ship, potential safety hazards occurring in a water area are found in time in a flight patrol mode, and the detection efficiency and timeliness of an underwater robot are improved.

The invention discloses a decoying effect evaluation system of laser decoy jamming equipment based on unmanned aerial vehicle formation. The system comprises a first flight device, a first image acquisition unit, a first image tracking processing unit, a laser target indicator , a second flight device and a detector in the second flight device, wherein the first image acquisition unit, the first image tracking processing unit, and the laser target indicator are arranged in the first flight device. During flight, the second flight device is arranged at a set distance near the first flight device, the relative position of the second flight device and the first flight device is kept unchanged, and the posture is kept consistent with that of the first flight device; the first image tracking processing unit calculates the position of the target according to the image; and the laser target indicator emits laser to the target. Before and after a to-be-evaluated laser decoy jamming equipment arranged on the target is started, laser reflection signals detected by the detector are calculated respectively; and the decoying effect of the laser decoy jamming equipment is evaluated according tothe deviation of the positions calculated before and after. According to the system, the decoying effect of the laser decoy jamming equipment can be effectively evaluated.

The invention relates to the technical field of unmanned aerial vehicle surveying and mapping, and particularly discloses an unmanned aerial vehicle ground-imitating flight device based on a laser radar. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, a high-definition camera and a laser radar, a control module is arranged on the upper surface of the unmanned aerial vehiclebody, a landing frame is connected to the lower surface of the unmanned aerial vehicle body, an upper connecting plate is connected to the lower surface of the unmanned aerial vehicle body in the middle of the landing frame, multiple round holes are evenly formed in the upper surface of the upper connecting plate, and sliding rods are inserted into the round holes; according to the unmanned aerialvehicle ground-imitating flight device based on the laser radar, the flight height of the unmanned aerial vehicle can be detected in a high-precision mode at any time through the laser radar, and then the flight height of the unmanned aerial vehicle is adjusted in real time through the control module, so that the high-definition camera of the unmanned aerial vehicle keeps a stable height with theterrain surface during surveying and mapping; Therefore, the fixed overlapping degree of the photos is ensured, and the aerial photogrammetry precision is ensured; compared with an existing unmannedaerial vehicle surveying and mapping device, thethe unmanned aerial vehicle ground-imitating flight device is better in surveying and mapping effect.

The invention, which belongs to the technical field of flight simulation, discloses a display system for a flight simulator. The display system is composed of a control signal acquisition and state display module, an avionics calculation host connected to the control signal acquisition and state display module, a plurality of graphic calculation hosts connected to the avionics calculation host, and a plurality of display terminals connected to the graphic calculation hosts. The control signal acquisition and state display module is used for collecting control signals of a plurality of multi-functional display control units and an integrated backup flight instrument and displaying the states of the control signals. The avionics calculation host is used for carrying out logic solution of the control signals, receiving input data of an external system, and transmitting the data to the plurality of graphic calculation hosts. The graphic calculation hosts are used for transforming the received data into corresponding characters, symbols, and data objects, carrying out real-time drawing, and transmitting the data to the corresponding display terminals for real-time displaying. Therefore, the occupation rate of the program system is reduced effectively; the communication efficiency is improved; and the post maintenance is realized conveniently by the system.

Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution;an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.

A support device for a motorized flying instrument in a wind tunnel. To carry out tests in a wind tunnel on a motorized flying instrument (10), with the motor on, under different attitudes hands off, the instrument is connected to the fixed structure (15) of the wind tunnel (11) by a mounting device (12) at least one of the supports (14, 16) of which is fitted with a length adjustment system, such as a hydraulic jack (28). This jack (28) is remote controlled, in real time, by a control system (42).

A a flight instrument enabling a pilot to intercept and precisely follow a predefined GPS track. The instrument—known as a GPS steering indicator—provides a visual display which is similar in appearance to other aircraft instruments (and therefore instantly recognizable to nearly all pilots). However, the instrument is preferably differentiated somewhat in its visual appearance to convey to the pilot the fact that it displays steering commands rather than cross track error. An indicator needle deflects to instruct the pilot which way to turn and how much to turn in order to intercept and fly along a predefined GPS track. By centering the indicator needle, the pilot maintains the desired instantaneous track.

A flight instrument that displays the rotational speed of a main rotor of a rotary-wing aircraft, with the flight instrument including display means, a first indicator of a setpoint for the rotational speed of the main rotor, a second indicator of the first current value of the rotational speed of the main rotor, and third and fourth indicators of the limit values of the rotational speed. The setpoint for the rotational speed of the main rotor is variable and the first indicator is stationary on the display means, with the second, third and fourth indicators being movable in relation to the first indicator.

Provided are a land all-terrain duct cross-domain robot and a cross-domain method thereof. The robot comprises a control system, a power source, a flight device, an air guide mechanism and mechanicallegs, and the mechanical legs are evenly distributed on the periphery of the flight device. The control system controls the flight device, the air guide mechanism and the mechanical legs to act, and the power supply supplies power to the control system, the flight device, the air guide mechanism and the mechanical legs. The air guide mechanism guides output airflow of a ducted fan to achieve flight control over the robot. Land operation and simple obstacle crossing functions are achieved through movement of two steering engines on the mechanical legs. The flight device lifts off through the relative movement of two blades on the motor so as to achieve the obstacle crossing function on complex terrains. The method has the characteristics that cross-domain operation in land and air space domains can be achieved and the requirement for reciprocating crossing is met. The executable capacity is improved, and related tasks of medium-and-long-distance complex road surface reconnaissance and rapid goods and materials delivery or transportation are achieved.