15 results about "Side-stick" patented technology

A side lever manipulating device and a manipulating method thereof, the side lever manipulating device for controlling pitching motion and rolling motion of an aircraft, comprising: a manipulating handle which is a main body part of the side lever manipulating device and is held by a pilot; a pitch control unit which is provided to the control handle, and which controls the pitch movement of the aircraft by means of the pitch control unit; and a rolling control unit which is provided on the control handle and controls the rolling motion of the aircraft by means of the rolling control unit, the pitch control unit and the rolling control unit being independent from each other and not interfering with each other during operation. The side rod control method is used for controlling the side rod control device. By means of the side rod control device and the control method thereof, pitching and rolling control can be decoupled, independent pitching and rolling control is achieved, and therefore the control problem of cross coupling of the side rod is solved.

The present application relates to the technical field of aircraft operating mechanism, in particular to a drive-control integrated aircraft side stick operating mechanism, which comprises a box body, a controller and a driver, a roll transmission shaft is rotatably supported in the box body, a U-shaped decoupling mounting seat is fixedly connected to one end of the roll transmission shaft, a pitch shaft is horizontally supported in the U-shaped decoupling mounting seat, a base is fixedly sleeved on the pitch shaft, a handle connecting rod and a handle assembly are sequentially connected to the upper end of the base, a roll motor drives a rocker arm I through a rocker arm II and a transmission connecting rod I, the rocker arm I is hinged to the roll transmission shaft, a pitch motor drives a fixed head through a rocker arm III and a transmission connecting rod II, and the fixed head is fixedly arranged at the end of the pitch shaft. The present application provides a drive-control integrated aircraft side stick operating mechanism with high integration, ultra-small volume, double-channel synchronous force sensing, microsecond-level real-time bus communication and plug-and-play, which is particularly suitable for the demand of high-fidelity, high-reliability and small-sized operating device of high-level flight simulator.

The present application belongs to the technical field of aircraft dual-sidestick control design, and specifically relates to an aircraft dual-sidestick control system and method thereof, wherein the aircraft dual-sidestick control system is respectively provided with a main sidestick and a secondary sidestick at the pilot position and the co-pilot position of the aircraft, and the main sidestick and the secondary sidestick are respectively equipped with a longitudinal command sensor, a lateral command sensor, an authority switch and an autopilot disconnect button. Based on whether the aircraft autopilot is connected and whether the longitudinal command sensors and lateral command sensors of the main sidestick and the secondary sidestick are in normal state, the aircraft dual-sidestick control mode is switched between the dual-side control mode, the main side locked control mode, the main side temporary control mode, the secondary side locked control mode, and the secondary side temporary control mode through the authority switch of the main sidestick and the secondary sidestick and the autopilot disconnect button, and the aircraft autopilot can be disconnected by control, which can greatly facilitate the pilot and co-pilot to control the aircraft.

The invention discloses a method, a device and equipment for monitoring a self-triggering instruction fault of an aircraft side lever. The method comprises the following steps: acquiring original flight data of a to-be-monitored aircraft at a preset acquisition frequency; identifying a self-triggering flight control instruction of a side rod of the to-be-monitored aircraft according to the original flight data; monitoring and counting appearance characteristics of the self-triggering flight control instruction; and analyzing appearance characteristics of the self-triggering flight control instruction to obtain a self-triggering instruction fault state of the side rod. According to the technical scheme, when the fault phenomenon that the actual position of the flight control surface is inconsistent with the position corresponding to the flight control instruction occurs, the fault range can be accurately limited to the aircraft side lever, the fault state of the aircraft side lever self-triggering instruction can be monitored in advance, the fault state can be predicted in time, and the service life of the aircraft side lever can be prolonged. And the occurrence of warning or unsafe phenomena caused by fault deterioration is avoided.

The invention belongs to the technical field of aircraft cockpit side lever devices, and discloses an aircraft miniaturized four-shaft side lever which comprises a handle, a yawing rotating shaft, a pitching rotating shaft and a rolling rotating shaft, the handle is provided with a shifting wheel, and control input of a vertical shaft can be achieved. The transverse rolling rotating shaft comprises a pitching rotating shaft assembly and a pair of deep groove ball bearings and can rotate around the transverse rolling bearing installed on the shell. The pitching rotating shaft comprises a yaw rotating shaft assembly and a pair of deep groove ball bearings and can rotate around a pitching bearing installed on the universal joint frame. The yaw rotating shaft comprises a handle assembly, a pair of angular contact ball bearings and a needle bearing and can rotate around the center line of a bearing chamber on a shell of the yaw shaft. The problems that an existing aircraft side rod is difficult to miniaturize and cannot be integrated with other aircraft attitude control equipment such as pedals are solved, and light weight and miniaturization are considered on the basis of increasing the degree of freedom.

This application relates to a scheme for visualizing sidestick input references, comprising: receiving data required for calculating reference stick values ​​from various data sources; calculating corresponding sidestick input reference values ​​by a sidestick input processor based on a programmed sidestick operation flow according to the received data; outputting the sidestick input reference values ​​calculated by the sidestick input processor to a display processor; generating corresponding sidestick visualization indicators based on the sidestick input reference values; and overlaying the sidestick visualization indicators from the display processor onto the main flight display screen (PFD).

According to an exemplary embodiment, an alignment structure includes a connecting body, a head stick including a first head stick extending from the connecting body and a second head stick that is provided to be able to be supported from the ground by extending in a direction of the ground while being separated from the first head stick at a first angle, and a side stick configured to enable three-point support from the ground along with the second head stick.

The application provides an aircraft control method for a side stick with a front wheel turning function, wherein the aircraft control method comprises: the side stick is in a side stick mode from an initial state, and a function of a front wheel turning mode is locked, then the aircraft starts running, when it is detected that the aircraft is on the ground and a wheel speed of the aircraft is less than a first threshold, the front wheel turning mode of the side stick is activated, and the function of the side stick mode is locked, then whether the mode of the side stick is switched is detected; and when the aircraft runs, if it is detected that the aircraft is on the ground and the wheel speed of the aircraft is greater than the first threshold, or if it is detected that the aircraft is not on the ground, the side stick mode of the side stick is activated, and the function of the front wheel turning mode is locked, then whether the mode of the side stick is maintained is detected.

The present application relates to the technical field of cockpit integration, and provides an active side stick control device and method with an emergency torque control mode, the device sequentially comprises a control stick, a torque sensor, a locking mechanism, a clutch, a driving rod, an active side stick driving unit and a device shell from top to bottom: the bottom of the control stick is connected with the torque sensor, the torque sensor is fixedly connected with the top of the locking mechanism, the bottom of the locking mechanism is detachably connected with the clutch, the clutch is connected with the driving rod, the driving rod is connected with the active side stick driving unit, and the active side stick driving unit is fixed on the device shell; when the clutch is separated from the locking mechanism, the locking mechanism is locked on the device shell. The method comprises a normal mode and an emergency torque control mode. The control device can meet the control requirements of the aircraft in different states, provides an emergency mode while providing the active ability of the side stick, avoids the loss of control of the aircraft due to jamming and failure, and improves flight safety.

The application provides an aircraft control method for a side stick with a front wheel turning function based on a side stick authority switch, wherein the aircraft control method comprises: the side stick is in a side stick mode from an initial state, and a function of a front wheel turning mode is locked, and then the aircraft runs, when it is detected that the aircraft is on the ground and that a wheel speed of the aircraft is less than a first threshold, the method comprises: the front wheel turning mode of the side stick is activated, and the function of the side stick mode is locked, and then a pressing state of an authority switch of the side stick is detected; and when the aircraft runs, after it is detected that the aircraft is on the ground and that the wheel speed of the aircraft is greater than the first threshold, or when it is detected that the aircraft is not on the ground, the method comprises: the side stick mode of the side stick is activated, and the function of the front wheel turning mode is locked, and then the pressing state of the authority switch of the side stick is detected.

The invention provides a cross shaft type integrated aircraft side lever based on torsional spring-electromagnetic damping, and belongs to the technical field of aircraft cockpit control devices. A handle; a dust cover; the cross shaft assembly is used for realizing manipulation decoupling; the two four-redundancy angular displacement sensors are used for converting the control signals received by the cross shaft assembly into electric signals and feeding back the electric signals to the flight control computer; the force sensor assembly is used for transmitting operating force; and the longitudinal rod force assembly and the transverse rod force assembly are used for converting the operating force transmitted by the force sensor assembly. According to the aircraft side lever, modular integrated design is adopted, a torsional spring is used for providing artificial sense force, electromagnetic damping is integrated into a longitudinal and transverse lever force assembly through two-stage straight tooth transmission, longitudinal and transverse decoupling control is conducted through a cross shaft assembly, and meanwhile a four-redundancy angular displacement sensor is integrated for collecting control signals. The scheme has the advantages of small size, fast dynamic response, good force sense linearity, high reliability and the like.

The utility model relates to an airplane side rod device and an airplane. The aircraft side rod device comprises a side rod body, a sliding structure and a locking structure, wherein the side rod body is provided with an operating handle; the sliding structure comprises a first sliding part and a second sliding part which are in sliding fit, the first sliding part is arranged on the side rod body, the second sliding part is used for being arranged on an instrument desk of an airplane, and in the relative sliding process of the first sliding part and the second sliding part, the side rod body can move in the first direction so that the side of a pilot can get close to or get away from the pilot; the locking structure is used for unlocking or locking the first sliding piece and the second sliding piece. The aircraft side lever device can provide comfortable control experience for pilots with different heights, and the problem of hand fatigue of short or high pilots in the driving process is effectively relieved.