35results about How to "Slow down the landing speed" patented technology

A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radial cutouts. The cutouts are positioned one above the other, one being located above the engine axis, the other one below the engine axis. At least two shells close the fixed structure cutouts and are pivotally mounted on the fixed structure to form a portion of the exhaust nozzle of the engine. A sealing means ensures fluid tightness between the shells and the fixed structure for any angular position of said shells. Actuator means are provided for pivoting the shells either to a symmetrical configuration for changing of the value of the exhaust area of the nozzle or to an unsymmetrical configuration for changing the angle of the thrust vector of the exhaust nozzle. In operation, the value of the exhaust area and the thrust vector angle of the exhaust nozzle are varied during flight to optimize performance of the aircraft.

A riser release system controllably lands a descending flight vehicle having a parafoil or canopy. The system has control lines and riser lines attached to the parafoil or canopy. The other end of the riser lines are attached to an upper portion of a release structure; a lower portion of the release structure is connected to the payload; and a coupling mechanisms releasably couples the upper and lower portions. When the upper and lower portions are decoupled, a distance control device controls and limits the distance of separation between the two portions, and a rate control device controls the rate of separation. Separation causes the riser lines to increase the distance between the payload and canopy, further causing the canopy to flare and decrease the rate of descent of the flight vehicle.

In a hydraulic actuator comprising a hydraulic piston, a hydraulic cylinder and a hydraulic pressure source wherein said hydraulic piston has a larger area exposed to pressure on the side of the control chamber than on the side of oil supply chamber of said hydraulic cylinder, wherein said hydraulic piston has, in its outer peripheral part, a slot connecting said oil supply chamber side with the control chamber side in the direction of shaft and the cross sectional area of the slot in the direction of said shaft changes according to the displacement of the hydraulic piston in the direction of its shaft, and the control chamber has a pilot valve, the suction and exhaust valve in a variable valve system of the internal combustion engine are opened and closed by said hydraulic actuator through a coupling and springs for the valve, for variably controlling the opening and closing timing, the opening and closing time, and the lift of the valve, whereby it is possible to provide a variable valve system for internal combustion engine that is a cam-less and sensor-less, and a hydraulic actuator that enable to reduce power consumption and to improve response speed, and to control landing speed so that a smooth landing may be realized.

The invention relates to a power-forced parachute opening device of a rocket, which comprises a rocket (1) and a traction belt (3), wherein the rocket (1) is arranged outside a parachute pack (2) and connected with a parachute (4) in the parachute pack (2) by the traction belt (3). Compared with the prior art, the invention has the advantages that the rocket can be used for rapidly pulling the parachute in the preset direction after the rocket is started, thereby greatly shortening the straightening time of the parachute, improving the parachute opening speed, greatly reducing height loss; and the parachute can be rapidly completely opened and work, a plurality of problems of abnormal parachute opening (such as parachute inside out, and the like) can be solved, and the aim of lifesaving is achieved finally, therefore, the reliability of parachute use is improved.

The invention provides a wheel shaft type wide-width precision seed distribution device, which includes a box body, an inner core, a seed discharge port and a seed distribution pipe, the inner core is cylindrical, the inner core is located inside the box body, and the Both ends of the inner core are connected to the box through bearings, the outer surface of the inner core is provided with evenly distributed concave and round dimples, and a row of brushes is arranged inside the box along the axial direction of the inner core, and the brushes and the The inner wall of the box is threaded, the seed discharge port is located at the bottom of the box, the seed distribution pipe is located below the seed meter, the seed distribution pipe includes a seeding trough, and the seeding trough is connected to the The seed discharge port is connected, and the seed distribution pipe is arc-shaped, and the arc angle is 40°≤θ≤50°. The seed distribution tube is arc-shaped and has a certain angle with the ground, which slows down the landing speed of the seeds, prevents the seeds from bouncing after landing and deviates from the sowing point, and improves the sowing accuracy. It can be seen from the above that the present invention solves the problem of seed bouncing in the background technology, and is simple and practical.

The invention relates to a control method for an aircraft carbon-ceramic wheel braking system with adjustable maximum braking pressure. The braking pressure of the carbon-ceramic wheel braking system is controlled through a drogue chute signal, wherein when the drogue chute signal is 1, the friction coefficient of a carbon-ceramic composite brake pad is normal, and an aircraft is braked and stopped with rated braking pressure through the carbon-ceramic wheel braking system; and when the drogue chute signal is 0, the friction coefficient of the carbon-ceramic composite brake pad becomes lower, the maximum braking pressure braking instruction of the carbon-ceramic wheel braking system is output by an anti-skid control box, and the carbon-ceramic wheel braking system multiplies the rated braking pressure according to a preset proportionality coefficient so that the braking pressure can be maximum. A method for increasing the braking pressure of the carbon-ceramic wheel braking system is used for eliminating the influences caused by decrease of the friction coefficient of the carbon-ceramic composite brake pad on braking torque and braking efficiency, and the problem that the braking efficiency of the carbon-ceramic wheel braking system is low when the landing speed of the aircraft is high or the drogue chute signal is 0 is solved. The braking efficiency and the reliability in the landing process of the aircraft are guaranteed.

The invention discloses a high-performance hybrid hullform for an amphibious aircraft. The high-performance hybrid hullform comprises a multi-bilge-line hull, two ground-effect wings and two force-bearing buoys, wherein the hull is tapering in front and rear; the ground-effect wings are symmetrically arranged at the two sides of the middle part of the hull, and the force-bearing buoys are fixed at the outer end. A non-step-fault design is adopted at the middle part of the hull, the hull is provided with three bilge lines, an upper hull between the upper bilge line and the middle bilge line and a middle hull between the middle bilge line and the lower bilge line are in the shape of a linear ramp with a bilge turn respectively, the bilge turns are arranged at the outer sides of the transverse sections, and the ramp angles of the upper hull and the middle hull range from 65 degrees to 75 degrees; and the transverse section of a lower hull is in the shape of a curve ramp. According to the high-performance hybrid hullform disclosed by the invention, the motion response of the amphibious aircraft in a wave is reduced through using the hull with the large ramp angle and multiple bilge lines; and meanwhile, an aerodynamic lift is remarkably increased and a water take-off and landing speed is reduced through using the ground-effect wings and a ground-effect lift-enhancing air cavity, and then the motion response of the amphibious aircraft in the wave is reduced and the pitching motion time of the amphibious aircraft during take-off and landing in the wave is reduced, and the anti-wave capacity of the amphibious aircraft is remarkably improved.

The invention provides a suction wheel type wide-width precision seed distribution device, comprising a seed storage box, a seed metering device and a seed metering tube. The seed metering device is a suction wheel type seed metering device, comprising a box body, a cover, an inner core And the seed metering port, the bottom of the seed metering device is fixed with a stopper, the inner core is cylindrical, the drive shaft passes through the inner core, the outer surface of the inner core is evenly distributed with concave and circular dimples, the The concave and round dimples are distributed in a row of five and a row of six at intervals, and the seeding tube is in the shape of an arc, and the arc angle is 40°≤θ≤50°. When working, the negative pressure is generated by the high-speed fan, and the concave circular socket absorbs the seeds under the action of the suction hole below, rotates with the inner core, and turns to the fixed stop below, the suction hole sucks the seeds. Descending or even disappearing, the seeds leave the concave circular socket under the action of the seed scraper and enter the seeding tube. The seeding tube is arc-shaped and forms a certain angle with the ground, which slows down the landing speed of the seeds and prevents the seeds from bouncing and deviating from the sowing after landing. point to improve seeding accuracy.

The invention discloses a portable single-person anti-spray type soft landing safety protection device and a using method thereof. Using the method of combining the parachute with the inflatable coat and the jet device, the parachute is opened at low altitude, and the jet is reversed when it is close to the ground, which reduces the landing speed to a large extent; at the same time, part of the gas is filled into the wear coat to reduce the impact of landing . The invention has high reliability, low operation difficulty, no need for professional training, and has strong popularization and realizability; it can obviously reduce the landing speed, and the controllable flight attitude can reduce the risk of skydiving; the future application prospect is broad, It can be popularized in a wide range, safe and environmentally friendly, and can be used in general aviation equipment, high-level rescue equipment, safety protection devices, etc.