45results about How to "Improve landing safety" patented technology

The invention relates to a flight equipment landing method and a flight equipment landing device, and belongs to the field of internet. The flight equipment landing method comprises the steps of receiving the battery remaining capacity and location information of flight equipment, wherein the location information of the flight equipment is acquired under a safe landing mode which is activated after the flight equipment determines that the battery remaining capacity is less than a set threshold; judging whether the flight equipment can safely land at a position where a control terminal is currently located or not based on the battery remaining capacity and the location information of the flight equipment; determining a target falling site of the flight equipment based on the location information of the flight equipment when the flight equipment cannot safely land the position where the control terminal is currently located; and sending the target falling site to the flight equipment, and enabling the flight equipment to land. The embodiment of the invention prevents a circumstance that the flight equipment is damaged by falling caused by low electric quantity, and the landing safety of the flight equipment in a circumstance of low electric quantity is improved.

The small unmanned aerial vehicle landing gear buffer relates to the field of aviation aircraft, and solves the problems that the existing flat spring type buffer has low buffering efficiency, is easy to rebound, and cannot meet the high reliability requirements of the unmanned aerial vehicle. Including the outer cylinder, the first spring on the outer cylinder, the inner cylinder with a damping hole, the air bag between the outer cylinder and the inner cylinder, the upper joint, the lower joint, the piston rod extending into the inner cylinder, and the piston rod which is set on the piston rod in turn. Piston, damping plate, pressure limiting valve, one-way valve, guide sleeve and locking cover which are set on the piston rod and located inside the outer cylinder in turn; between the inner cylinder and the outer cylinder is the inner and outer cylinder ring-shaped oil storage chamber, and the damping plate along the piston The rod moves axially, and the pressure limiting valve limits the maximum damping force in the compression stroke to not exceed the preset value. After tightening the locking cap, the guide sleeve, one-way valve, and inner cylinder are axially compressed to the lower joint, and the one-way valve controls the inner and outer Whether the annular oil storage chamber of the barrel communicates with the right cavity of the inner barrel or not, the two ends of the first spring bear against the lower and upper joints respectively. The invention has high buffering efficiency, is not easy to rebound, has stable performance and high reliability.

The invention discloses a two-engine carrier-based aircraft with one engine off safety carrier landing control method, belonging to the flight control technology field. Through researching a flight characteristic of a carrier-based aircraft with asymmetric thrust force, the invention provides a flight state simulation method of the two-engine carrier-based aircraft with one engine off. Based on anormal two-engine aircraft flight state, different constant interference is added on a flight state variable of a flight speed, a pitch angle speed, a roll angle speed and a yaw angle speed respectively, thus a flight state of the two-engine carrier-based aircraft with one engine off is obtained. Based on a simulated flight state, vertical and lateral control law are subjected to reconstruction respectively, thus the two-engine carrier-based aircraft with one engine off safety carrier landing control method is obtained. Compared with the prior art, the method in the invention has the advantages of simple structure, reliable performance, high security of carrier landing and the like.

The invention discloses unmanned aerial vehicle airport-entering landing gliding channel design and a gliding path adjustment method, and belongs to the technical field of flying control. A gliding channel satisfying landing conditions is planned according to pneumatic characteristics of an aerial vehicle and engine characteristics of the aerial vehicle; then reasonable horizontal flying height and reasonable airport-entering gliding distance of the aerial vehicle are confirmed according to field conditions of an airport and actual requirements of the airport, wherein flight path inclined angles of an airport-entering landing balanced gliding segment of the aerial vehicle are changed so as to adjust the gliding distance and flight path inclined angles and effectively avoid effect of barriers on airport-entering landing of the aerial vehicle; and finally, changing curves of parameters along the path such as dynamic pressure, velocities, angles of attack and elevator drift angles of the aerial vehicle are acquired through a path continuation mode so as to achieve safety landing of the aerial vehicle. The adjustment method is suitable for an adjustment method of general five-side navigation path horizontal flying height and gliding distance, is more suitable for situations that landing is affected by the barriers, and improves landing safety. The unmanned aerial vehicle airport-entering landing gliding channel design and the gliding path adjustment method are simple in design and adjustment process and convenient to use.

The invention discloses an aircraft automatic landing control method based on direct force control. The method comprises the steps that 1, a nonlinear model of an aircraft is trimmed and linearized, and a transverse channel and a longitudinal channel are decoupled; 2, a glide angle is determined, and an aircraft guidance law of the transverse channel and the longitudinal channel is designed, wherein the aircraft landing process of the longitudinal channel is divided into three sections, namely a level flight section, a transition section and a guide section; 3, a longitudinal control law and atransverse control law are respectively designed, wherein the longitudinal control law design comprises the design of an elevator channel, an accelerator channel and a flap channel and the moment decoupling of direct force control on the elevator; the transverse control law design comprises the design of an aileron channel and a rudder channel. According to the invention, aircraft landing controlcan be carried out under the condition of deck movement, so that the aircraft can safely land according to a preset flight path.

The invention is applicable to the field of manned aircraft, and provides a low-altitude composite aircraft, including: an unpowered rotor mechanism, a four-rotor mechanism, a tilting mechanism and a frame for fixing the above mechanisms. The unpowered rotor mechanism provides lift for the low-altitude compound aircraft, and the four-rotor mechanism includes a left front rotor, a right front rotor, a left rear rotor and a right rear rotor whose rotation axes are arranged in parallel and have the same rotational speed. Arranged and turned oppositely, the left rear rotor and the right rear rotor turn oppositely, and the tilting mechanism is used to simultaneously drive the left front rotor, the right front rotor, the left rear rotor and the right rear rotor to Tilt forward or backward. The invention provides low-altitude composite aircraft to realize vertical lift and is conducive to improving the landing safety of the low-altitude composite aircraft and reducing energy consumption. Simultaneously, the simplified design reduces manufacturing costs and reduces the difficulty of control.