344 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, 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.

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 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.

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 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.

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.

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.