61 results about "Ground staff" patented technology

The invention provides a scene aerial patrol method and an aircraft. The method includes the steps of presetting a patrol range, receiving an aerial patrol control signal through the aircraft, determining a patrol mode according to the aerial patrol control signal, conducting aerial patrol on a pre-monitored scene in the patrol range according to the patrol mode, and sending a patrol result. According to the technical scheme, the real-time controllability of the aircraft is obviously improved by controlling the patrol mode of the aircraft. The function of timely feeding back the aerial patrol result is achieved through interaction between the aircraft and the outside world. Therefore, the ground staff can timely obtain scene information of the monitored scene, the comprehensive monitoring of the monitored scene is achieved, problems are timely found and solved, the work efficiency of the staff is greatly improved, property losses, especially heavy losses of public property, can be effectively avoided or reduced, and even casualties can be avoided or reduced.

A method for reducing the turnaround time of an aircraft having at least one self-propelled undercarriage wheel comprising the step of: moving the aircraft to a required location using at least one self-propelled undercarriage wheel; wherein thrust equipment, (e.g. turbines) are turned on only when needed for takeoff or prior to landing, and are turned off until takeoff or after landing; whereby departing equipment, arriving equipment, and turnaround equipment are not at risk from operating thrust equipment, (e.g. turbines). An apparatus for reducing the turnaround time of an aircraft is disclosed comprising a control unit for facilitating voice communication between a pilot and ground staff. Said control unit may further comprise a control arm for inputting the required direction of movement of said nosewheel; means for transmitting direction information to said self-propelled nosewheel; means for receiving direction information at said self-propelled nosewheel; and means for controlling the direction of said nosewheel. The control unit may also comprise means for turning on and off an APU, parking brakes, and other aircraft features.

The invention discloses a tower escaper apparatus which comprises a bearing fixing support, a rope winding device, a riding accommodation device and a descending control device. The coiling device comprises a shell and a winding roll, the winding roll is wound with a bearing rope, and the rope winding device is suspended on the bearing fixing support through a free end of the bearing rope; the riding accommodation device is fixedly connected below the shell; and the descending control device comprises a friction brake and a descending operation handle which are tightly clasped to the winding roll in a normal state, and the descending operation handle is in transmission fit with the friction brake. When in use, the bearing fixing support is arranged on a window or a balcony or other places, a person can control the friction braking force of the friction brake to the winding roll through the descending operation handle so as to control the descending speed of the riding accommodation device to be in a safety range, and meanwhile, ground staff can unlock the winding roll through a reset unlocking mechanism and remotely control a motor through a remote controller to drive the winding roll to rotate so as to ensure that the riding accommodation device returns to a high place and can be used by other people for escape. In addition, the invention is comfortable in use and suitable for various people.

An apparatus for controlling the movement of an aircraft having a self-propelled nosewheel, on the ground, is disclosed. The apparatus comprises a control arm; a control unit; means for transmitting information to said self-propelled nosewheel; means for receiving information at said self-propelled nosewheel; and means for controlling at least one of the speed and direction of said nosewheel; whereby airport ground staff can intuitively control the movements of said aircraft by holding said arm and moving it in the direction of required movement of said aircraft.

A system of assistance in the entry of flight data for an aircraft transmitted between a crew on board the aircraft and a ground staff including, a radiofrequency communications link to transmit flight data between the crew and the ground staff. At least one means of sending and one means of receiving data on board the aircraft, wherein the system includes a voice recognition means capable of detecting a piece of data of a predefined type emitted, during the communications call, by the crew or the ground staff and a means of analysis and transcription of this piece of data in digital or alphanumeric form.

The invention discloses a five-degree-of-freedom gyro case structure. The five-degree-of-freedom gyro case structure mainly consists of a motor shaft, a single radical magnetic bearing, a repeatable type locking mechanism, an axial magnetic bearing, a motor, an upper gyro case, a coded disc shaft, a lower gyro case, a radial electrical eddy current sensor probe, a rotor outer hub, a lower protective bearing cover, an axial electrical eddy current sensor probe and a rotor inner hub, wherein a magnetic suspension bearing adopts the single radical bearing, and is used for controlling radical translation and rotation of a rotor. The repeatable type locking mechanism adopts a fire work pin puller to realize unlocking of the rotor when a spacecraft is in in-orbit operation, and meanwhile, a movable threaded chuck structure capable of manually adjusting degree of tightness is adopted, so that ground staff carries out installation and debugging for many times conveniently. The axial flow electrical eddy current sensor probe and the radical electrical eddy current sensor probe are fixedly mounted on the inner part of the gyro case, are integrated and are used for detecting the axial displacement and the radical displacement of the high-speed rotor respectively. According to the five-degree-of-freedom gyro case structure, the gyro case sensor is integrally designed and the single radical magnetic bearing is adopted, so that the gyro structure is simplified in structure, reduced in size, reduced in weight and relatively high in reliability.

The invention discloses an automatic collecting and monitoring system and method of a flight service support node. The system comprises a flight service monitoring and collecting system, a convolutional neural network dividing system, a service state determining system, a storage module, and a flight service time schedule display module, wherein the convolutional neural network dividing system receives electronic data of the flight service monitoring and collecting system and divides the electronic data into an aircraft entry frame, a wheel box, a bridge frame and a fueling frame according toareas, the service state determining system comprises an airplane state determining module, a wheel state determining module, a bridge state determining module and a fueling state determining module,and the flight service time schedule display module displays service schedule and time. The system monitors the airplane, the fuel car and the bridge and collects data in real time and analyzes database image characteristics so as to determine the airplane state and the service support state, provides accurate data support for flight operating, and relieves working strength of ground staff in theairport.

The present invention relates to a circuit detection device, in particular to a portable electroscope, which comprises a contact electroscope. The portable electroscope is characterized in that the contact electroscope is connected with an insulating rope, the other end of the insulating rope is fixedly wound on a rolling wheel, and the rolling wheel is connected with a retractable device capable of driving the rolling wheel to rotate forwards or backwards. Since the insulating rope is used instead of an insulating rod in the technical scheme, the present invention has the following advantages that: 1, the weight in the detection process is greatly reduced; 2, no installation of pulleys or cooperation of ground staff is needed, and thus the detection time is shortened and the number of the detection personnel is reduced; and 3, since the existing power transmission line adopts an aluminum stranded wire with a steel wire in the middle, and the power detection head of the electroscope is provided with a high-performance magnet, the contact electroscope can be accurately contacted with the power transmission line to be connected with the power transmission line for measurement. Therefore, the device is easy to carry and measure, effectively improves the measurement efficiency, reduces the required personnel, and enhances the detection safety.

The invention relates to a lock catch device used in cooperation with a pedal. A sliding type lock catch device is installed on a fuselage skin structure and is used for limiting rotation of the pedaland controlling the pedal to be opened and closed; the lock catch device comprises a special bolt, a lock base, a nut, a lock catch and a spring; the special bolt is in the type of T, and comprises abolt head matched with the outer surface of the lock base and a vertically arranged bolt body; the end, close to the bolt head, of the bolt body is provided with a thread, and the remaining portion is an unthreaded rod; the bolt body penetrates a through hole formed in the top end of the lock base; the nut is matched with the thread of the special bolt, and is used for fixing the special bolt tothe lock base; the lock catch comprises an open hole containing the unthreaded rod and used for the unthreaded rod to pass through and a lock catch stretch-out part clamped to a pedal clamping groove;the lock catch moves up and down along the unthreaded rod; the spring is arranged on the unthreaded rod in a sleeving manner; one end of the spring abuts against the nut, and the other end of the spring abuts against the lock catch; and the end portion of the unthreaded rod is provided with a limiting part preventing the lock catch from disengaging. The lock catch device has the following beneficial effect that the device structure is simple, the lock catch is easy to replace, installing is convenient, and aviators or ground staff can manually start the airplane pedal conveniently to get on or off a plane.

The invention provides an innovative modern high-rise building fire emergency self-rescue system. A cantilever guide rail is designed at the top of a window facing side of a high-rise building, a group of hanging baskets are mounted on the guide rail and can run up and down to reach each window of the high-rise building while horizontally moving on the cantilever guide rail, a box system is usually mounted at a top hidden corner of the high-rise building, the appearance of the building is not affected, and the system mainly comprises a transverse movement body, the guide rail, a lifting hovering mechanism, automatic rescue baskets, an independent power supply system, a wireless remote control device and the like. When an accident or fire danger happens, ground staff can remotely control the high-rise building fire emergency self-rescue system to run, the system can reach any floors and any windows of the building, and trapped persons are timely rescued to rapidly reach the ground or a high-rise building emergency evacuation safety exit by the aid of the rescue baskets and facilities of the system. The functional design of the system gives full expression to 'people-oriented' design concept, and the system is innovative, high in practicability, fine in reliability and high in cost performance.

The invention discloses an aircraft hardpoint sealing mechanism driven by motors. The aircraft hardpoint sealing mechanism comprises a casing (1), wherein a hanging frame hole (12) is formed in the casing (1), and two sealing plates (9) matched with the casing (1) in a rotating manner are mounted on the bottom surface of the outer sides of the casing (1) respectively and positioned on two sides of the hanging frame hole (12) respectively; a step motor (2) driving the sealing plates (9) to rotate and two opposite-transmitting type infrared sensors (4) positioned on two sides of the hanging frame hole (12) respectively are mounted on the inner side surface of the casing (1). The aircraft hardpoint sealing mechanism disclosed by the invention is simple in structure and convenient to use, when a hanging frame is mounted, the sealing plates are opened through a switch by ground staff, then the sealing plates are held in an open state, and when the hanging frame is released, the sealing mechanism is automatically closed, so that the aircraft hardpoint sealing mechanism is relatively convenient to use; because space for the sealing plates does not need to be reserved in the inner part of the casing, and plan view sizes of the sealing mechanism and a corresponding skin opening are small and slightly greater than sizes of the hanging frame, so that influence on the structural strength of the aircraft is small.

The invention discloses an apparatus capable of flexibly changing a civil aviation aircraft position information broadcast frequency and a processing method thereof. A PDOD module and a PTIC module are included. A ground host sends an uplink trigger instruction. The PDOD module analyzes a control parameter of the uplink trigger instruction requesting aircraft instant position broadcast and broadcasts a current position state of an aircraft. A PTIC uplink trigger instruction possesses a variable used for changing an aircraft position broadcast time interval. An aircraft communication management component nonvolatile memory possesses a default timing variable. The PTIC module dynamically changes the timing variable through a PTIC variable so as to change a time interval of aircraft position broadcast under the condition that a current position state of the aircraft is acquired. In the invention, according to an actual condition and an actual demand, a fixed time interval of the aircraft position broadcast is changed so that a ground staff of an aviation company can actively acquire position information of the aircraft and simultaneously a purpose of economically, safely and effectively monitoring aircraft position information is realized.

The invention relates to an automatic truck quantitative piling and loading system. The system comprises a loading position and a lane; a feeding valve is arranged above the loading position; a smartcard is installed on a truck; the target cargo weight is transmitted to a controller through a card reader on the lane; two distance sensors are further arranged above the lane in a spaced mode, and can scan the distance from objects below at the same fixed frequency and transmit the distance to the controller; the controller can calculate the length of a truck head and the length of a truck bucket and distributes a plurality of pre-feeding positions on the truck bucket according to the length of the truck bucket and the target cargo weight; the side, away from the lane, of the loading position is provided with a third distance sensor which can scan the horizontal distance between the third distance sensor and the truck and transmits the distance to the controller; the controller can calculate the horizontal distance between the next pre-feeding position and the center of the feeding valve, and continuously feeds back the horizontal distance to the truck, so that the truck is driven tothe next pre-feeding position and aligned with the center of the feeding valve conveniently, and automatic quantitative piling and loading without ground staff instructions are achieved.

The invention discloses a safety lifting hook of a tower crane. The safety lifting hook comprises a lifting hook part and lifting rods; a counterweight block is arranged at the upper part of the lifting hook part; the mutually symmetrical lifting rods are arranged on the two sides of the counterweight block; a reel bracket is arranged on the counterweight block; a reel is arranged on the reel bracket, and is connected with a cross beam of the tower crane through a crane rope; lifting rod ropes are arranged on the lifting rods; and the lifting hook part is rotationally connected with a lifting hook baffle through a lifting hook rotating shaft. The safety lifting hook has the beneficial effects that the symmetrical lifting rods are arranged on the two sides of the counterweight block of the lifting hook of the tower crane, and when the lifting hook of the tower crane hooks and lifts tubular heavy objects or strip-type heavy objects and is unsafe, the objects can be bound and lifted through the two lifting rod ropes on the lifting rods. Through such mode, the incident safety problems of the lifting hook are solved, and the safety of ground staff is guaranteed.