350 results about "Airplane mode" patented technology

A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

An air vehicle, such as a manned or unmanned air vehicle, has a fuselage, a rotor / scissors wing, and a scissors wing. At helicopter mode, the rotor / scissors wing rotates to make the air vehicle fly like a helicopter to achieve vertical and / or short take-off and landing, hovering, and low speed flying. At airplane mode, the rotor / scissors wing and scissors wing form a scissors wings configuration to maximize the air vehicle's flying efficiency at a wide range of speed and flying conditions by adjusting the yaw angle of the rotor / scissors wing and scissors wing. During the conversion from helicopter mode to airplane mode, the scissors wing generates lift to offload the rotating rotor / scissors wing and eventually the offloaded rotor / scissors wing's rotating speed is slowed and stopped so that the rotor / scissors wing can be locked at a specific position and the conversion can be achieved. In a reverse order, the air vehicle can convert from airplane mode to helicopter mode. Either turbofan or turbojet engine, or turboshaft / turbofan convertible engine can be used to power the air vehicle.

An unmanned aerial vehicle apparatus (100) that includes an air vehicle assembly (150) that is at least partially enclosed within a protective enclosure assembly (120) The protective enclosure assembly (120) is typically at least partially elastic, to protect the air vehicle assembly (150) from bumps, collisions, and other similar occurrences. The enclosure assembly (120) can also facilitate the ability of the apparatus (100) to operate in a ground movement mode (114), such as a rolling mode (116), in addition to a flying mode (112).

A method, apparatus, and system for automatically changing the operating mode of a wireless device are provided. A determination is made whether at least one state of the wireless device has changed. This determination is performed using at least one integrated device of the wireless device. A determination is made whether the change in the state of the wireless device indicates that the first operating mode should be changed. The operating mode is changed to a second operating mode of the wireless device in response to a determination that the change in the state of the wireless device indicates that the first operating mode should be changed. Changing to the second operating mode includes altering at least one wireless communication operation of the wireless device. Examples of the second operating mode may include, but is not limited to, an airplane mode, a train mode, a vehicle mode, an environmental condition mode; or a device-access mode.

Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode.

Systems, computer program products, and methods for displaying navigation performance based flight path deviation information during the final approach segment to a runway and during landing of non-precision flight modes are provided. Improved graphical depictions of navigation performance based flight path deviation information provide pilots and flight crew members with clear, concise displays of the dynamic relationship between ANP and RNP, mode and aspect of flight and related procedures, intersecting flight paths, and current actual flight path deviation from a predefined flight path during the final approach segment to a runway and during landing. For example, an enhanced IAN display may include NPS-type deviation scales to show RNP / ANP relationships and predetermined RNP markers to alert the pilots and flight crew members that the FMC has transitioned from an NPS display for RNAV (LNAV / VNAV) flight procedures to an enhanced IAN display for a non-precision (non-xLS) approach and / or landing.

An aircraft is equipped with hingeless rotors on tilting nacelles, and the tilt angles of the nacelles are controlled using either or both of an actuator and a mast moment generated by a hingeless rotor. An aircraft with two or more rotors on tilting nacelles can achieve control of yaw orientation by differential tilt of its nacelles or masts. Hingeless rotors can be manipulated to control a tilt angle of a mast by changing the rotor blade pitch to produce a mast moment. The rotor and nacelle tilt of a tiltrotor rotorcraft can be controlled and effected in order to manipulate the yaw orientation and flight mode of a rotorcraft such as a tiltrotor. The use of mast moment to control nacelle tilt angle can reduce tilt actuator loads and allows for the control of nacelle tilt even in the event of an actuator failure.

The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

The application relates to a fitness monitoring device with an altimeter. The invention describes a biology metering monitoring device and includes various technologies which can be applied in the device. Besides, the technology for being employed by the altimeter in the biology metering monitoring device is provided. In some embodiments, the technologies are provided: re-calibrating the biology metering monitoring device based on position data; employing data of the altimeter as the aid of posture recognition; and / or employing the data of the altimeter to manage an airplane mode of the biology metering monitoring device.

A method of establishing a persistent emergency call and positional indication of the call is provided. Upon a call center receiving a call by a user equipment (UE) device initiated by activation of a smart button, the call center issues a request for a current location. If the call is inadvertently terminated by the user prior to the emergency being cleared, the UE device, attempts to reestablish the call automatically and continually. Prior to initiating the call, if the UE device is in airplane mode or standby mode, these modes are automatically switched off and location services are enabled.

The invention discloses an autonomous and cooperated type aircraft cluster system and a running method. The aircraft cluster system mainly comprises at least one node aircraft cluster, wherein the node aircraft cluster has an autonomous running capability and a network information connection function, the node aircraft cluster is provided with a resource sharing interface, node aircrafts in the node aircraft cluster are connected with each other by a space self-organizing network, the node aircrafts in the aircraft cluster fly in shared navigation and cluster flight modes, the commutation is realized by the space self-organizing network, and the fleet configuration is automatically adjusted according to the task existing condition. When the aircraft cluster receives a task instruction, the resource scheduling, the task planning, the task reconfiguration and the failure regrouping are autonomously carried out according to the task types, so as to further complete the tasks. The autonomous and cooperated type aircraft cluster system is suitable for quick or maneuvering launching of small carrier rockets, the quick response of the space system is greatly improved, and the risk of the in-orbit failure of the aircrafts is reduced.

A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.

A personal communications device includes a processor, a plurality of subsystems connected to the processor for exchanging signals therewith, at least one of the subsystems being configurable between a flight mode and a non-flight mode, an input device connected to the processor for inputting a flight mode selection thereto, and a flight mode module operable on the processor for causing the processor to monitor for input of a predetermined flight mode selection through the input device and configure the at least one subsystem into flight mode upon the input of the flight mode selection.

The invention discloses a self-help switching type air-and-ground dual-purpose aircraft and belongs to the field of aircrafts. The aircraft mainly comprises an aircraft body, a switching driving mechanism, a taking-off and landing supporting mechanism and the like, wherein wheel rotors of the aircraft body are fixed at two ends of rotor cross beams; the switching driving mechanism controls the rotor cross beams to rotate through gear meshing, so that the wheel rotors are switched horizontally and vertically; the taking-off and landing supporting mechanism comprises a third motor, a lifting screw and a landing gear, the third motor is fixed on the aircraft body, the landing gear is rotationally connected with the lifting screw, and the lifting screw is driven by the third motor to perform lifting movement relative to the aircraft body. The landing gear having a lifting function is arranged on the aircraft body, so that the aircraft can be switched automatically between a flying mode and a ground driving mode, has the high intelligent degree and is applicable to field investigation.

A method, apparatus, and system for automatically changing the operating mode of a wireless device are provided. A determination is made whether at least one state of the wireless device has changed. This determination is performed using at least one integrated device of the wireless device. A determination is made whether the change in the state of the wireless device indicates that the first operating mode should be changed. The operating mode is changed to a second operating mode of the wireless device in response to a determination that the change in the state of the wireless device indicates that the first operating mode should be changed. Changing to the second operating mode includes altering at least one wireless communication operation of the wireless device. Examples of the second operating mode may include, but is not limited to, an airplane mode, a train mode, a vehicle mode, an environmental condition mode; or a device-access mode.

An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash.

A flying vehicle having a pair of counter rotating propeller blades which provide lift for the vehicle when the vehicle is in a flight mode of operation. The counter rotating blades have in flight adjustable pitch and are connected to a control and steering system in the cockpit of the vehicle. A gas turbine engine located in the aft section of the vehicle is connected through a drive shaft and transmission to the counter rotating propeller blades When the vehicle transitions to the flight mode, the user has aircraft controls available in the cockpit to make the transitions from a driver to a pilot in a short time period. Yaw pedals located on the floor board of the cockpit as well as a pitch control handle and the steering wheel allow the user to steer and control the altitude of the vehicle when the vehicle is in the flight mode.

A wireless device configured to selectively enable and disable functionality when another wireless device that is paired to it is set to enable and disable functionality is provided. The wireless device can mirror the settings of a paired device such that when the paired device is set to airplane mode, the wireless device can automatically be set to airplane. Furthermore, when the airplane mode is disabled in the paired device, the wireless device can automatically disable its own airplane mode.

The invention relates to the field of spacecraft trajectory tracks, and provides a tool kit and method for optimizing a high-precision self-adaptation and modular spacecraft trajectory multi-constrained track. By means of the tool kit and method, the problems that in a traditional method, unfixed terminal time is hard to solve, boundary values of two points can not be solved due to low precision, initial value sensitiveness is low and the scale of nonlinearity is large are solved. The tool kit comprises a simulation platform main interface, multiple optimization algorithm selections, performance optimization indexes, multiple constraint conditions and trajectory simulation. The method comprises the following steps of (1) registering curve plug-in, (2) compiling exe files and then getting access to the simulation platform main interface, (3) allocating an airplane mode and setting parameters, (4) optimizing variable initial values, performance index parameters and multiple constraint parameters of multiple optimization algorithms respectively, (5) carrying out simulation setting in a trajectory simulation sub module, (6) processing an optimization and simulation result of the spacecraft trajectory multi-constrained track. The tool kit and method are applied to the field of the spacecraft trajectory multi-constrained tracks.

A wide area sensor system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a state detection sensor provided in the unmanned airplane, the state detection sensor being driven to detect a state of a detection target, and an external control apparatus that controls flight of the unmanned airplane and driving of the state detection sensor. The external control apparatus performs high speed sensing by driving the state detection sensor while performing the high speed flight of the unmanned airplane in the airplane mode. The control apparatus performs low speed sensing by driving the state detection sensor while performing the low speed flight of the unmanned airplane in the VTOL mode.

The invention discloses a method and a device for automatically control a flying mode, and a mobile device. The method comprises the following steps: obtaining the parameter information of the mobile device; and opening or closing the flying mode of the mobile device through judging whether the parameter information meets the pre-arranged conditions or not, in case of meeting, the flying mode is opened, otherwise, closed. According to the invention, a mobile terminal, as required, can automatically enter the flying mode, so that the radiation of the mobile phone on the users is reduced, and the user experience is improved.

A tiltrotor aircraft having a fixed wing and tilting rotors has a rotor blade with a shaped tip portion that provides improved hover performance. The shaped tip portion preferably has a terminal anhedral of at least 20° with respect to its stacking line, and the blade has an overall twist from root to tip of at least 20°, and a thickness ratio between 19% and 30% at a radial station of 10%. These features advantageously conspire to provide a hover figure of merit of at least 0.84 and a cruise propulsive efficiency of at least 0.85. A controller preferably limits the rotor speed in sustained airplane-mode forward flight cruise of at most 40% of a hover maximum rotor speed, and alternatively or additionally limits a rotor edgewise advance ratio to at most 0.20.

A method of enhancing public land mobile network (PLMN) search for a mobile device in a wireless communication system is disclosed. The method comprises deriving a mobile country code (MCC) for identifying a visited country when the mobile device is switched on, powered up, into flight mode off, or coming back from no service area, and performing the PLMN search excluding for at least a PLMN, whose MCC is not the same as the derived MCC, according to a PLMN search list stored in the mobile device.

The embodiment of the invention provides a data fusion and flight mode switching method and device for flight equipment. The data fusion method for flight equipment includes: acquiring the measured data of each sensor, determining the work state of each sensor, and performing data fusion according to the measured data and work state of each sensor, thus obtaining flight state variables of the flight equipment and effectiveness parameters thereof. According to the invention, when a disturbed sensor or broken-down sensor exists among the sensors, by determining the work state of each sensor andperforming data fusion according to the work status, measured data of normally operating sensors can be obtained, and through data fusion of the obtained measured data, the flight state variables of the flight equipment and effectiveness parameters thereof can be obtained, thus avoiding error of the data fusion result, realizing safe and autonomous flight of the flight equipment, and reducing theprobability of air crash.

The invention discloses a mobile phone for self-adapting communication environment and an energy saving method of the mobile phone. The mobile phone comprises a base band chip arranged in a mobile phone body, an acceleration sensor and a communication module, wherein a communication status indicating lamp for displaying the current communication signal connection status is arranged at the top of the mobile phone body; and the base band chip is connected with the acceleration sensor, the communication module and the communication status indicating lamp respectively. According to the mobile phone for self-adapting the communication environment and the energy saving method of the mobile phone of the invention, the fly mode status is automatically started when the mobile phone is in the region with bad signals, namely, all communication functions are closed so as to save power and monitor the displacement of the mobile phone; and the network is searched again after the mobile phone moves for a certain distance so as to acquire the communication signal again.

The invention relates to the technical field of an unmanned aerial vehicle, in particular to a mixed layout unmanned aerial vehicle, which comprises a vehicle body, fixed wings, an empennage and a propulsion motor, wherein the fixed wings are fixed at the two sides of the vehicle body; the empennage is arranged at the tail part of the vehicle body; the propulsion motor is arranged at the back part of the vehicle body; a paddle is arranged on an output shaft of the propulsion motor; the middle part of the vehicle body is provided with a strip-shaped installing hole; a four-rotor folding mechanism is arranged in the strip-shaped installing hole. Unique multi-rotor vehicle arms capable of realizing wireless one-key folding are used, so that the unmanned aerial vehicle can take off or land like a rotor aircraft; when the unmanned aerial vehicle is about to enter a fast cruise stage, the four vehicle arms can be collected back to the two sides of the vehicle body, so that the unmanned aerial vehicle can fly in a fixed wing airplane mode. The relative streamline type vehicle body conforms to the aerodynamic requirements better than the multi-rotor; higher speed and smaller wind resistance can be realized; the integral flight stability of the mixed layout unmanned aerial vehicle is improved.