13results about "Noise reduction installations" patented technology

A final approach and takeoff (FATO) surface for a VTOL aircraft redirects downwash as outwash and may capture outwash from the VTOL aircraft to generate electricity. The FATO surface system may include a central solid plateau configured to capture downwash from the VTOL aircraft to enhance a ground effect for optimal stabilization during takeoff and landing. A floor grate surrounding the plateau may allow outwash to pass through to a subsurface where the outwash is channeled to exhausts or at least one turbine for generating electricity from the outwash. Redirecting the downwash to outwash reduces undesirable effects such as noise and airspeed associated with the VTOL aircraft. The electricity may be used to recharge the VTOL, electric vehicles parked at a vertiport of the FATO surface system, may be used by a building at the vertiport, or may be delivered to a local power grid.

The invention discloses a portable tail flame airflow baffle device for an aero-engine. An airflow upper baffle comprises an airflow upper baffle mother plate and a telescopic daughter plate; the lower airflow baffle comprises a foldable support used for supporting the upper baffle and a support containing groove. The upper airflow baffle and the lower airflow baffle are connected through the heavy hinge, the universal wheels are used for moving the airflow baffle device, and the foldable supports are matched with the corresponding clamping grooves so that the opening and closing angle of the upper airflow baffle and the lower airflow baffle can be adjusted. A plurality of inverted spines are arranged on the outer wall face of the airflow lower baffle and can be unfolded to form an included angle with the outer wall face of the airflow lower baffle so as to be inserted into the ground to be fixed, and the unfolding direction of the inverted spines is consistent with the incoming flow direction after the airflow baffle device is unfolded. The airflow baffle device can block and distribute high-temperature and high-speed airflow, large-area sand and dust are prevented from being raised behind the aircraft, the sand and dust are effectively prevented from entering the aircraft, and smooth proceeding of a flight task is guaranteed.

A final approach and takeoff (FATO) surface for a VTOL aircraft redirects downwash as outwash and may capture outwash from the VTOL aircraft to generate electricity. The FATO surface system may include a central solid plateau configured to capture downwash from the VTOL aircraft to enhance a ground effect for optimal stabilization during takeoff and landing. A floor grate surrounding the plateau may allow outwash to pass through to a subsurface where the outwash is channeled to exhausts or at least one turbine for generating electricity from the outwash. Redirecting the downwash to outwash reduces undesirable effects such as noise and airspeed associated with the VTOL aircraft. The electricity may be used to recharge the VTOL, electric vehicles parked at a vertiport of the FATO surface system, may be used by a building at the vertiport, or may be delivered to a local power grid.

The utility model relates to the technical field of airport flow guiding screen, especially a modular detachable flow guiding screen, including support module, panel module and end compensation module, one or one and above support module cooperation splicing form triangular support main part, be equipped with the installation inclined plane on triangular support main part, the shape of panel module is matched with the shape of installation inclined plane, and panel module is detachably arranged on the installation inclined plane, end compensation module is detachably arranged on the top of support module. The utility model discloses according to the demand of different height and length of actual operation, can utilize one or one and above support module cooperation splicing form triangular support main part with installation inclined plane, triangular support main part can effectively improve the stability of overall structure, and adopts modular design to realize the quick dismounting of flow guiding screen.

A panel assembly is of a corrugated structure and comprises an upper corrugated panel and a lower corrugated panel, and a supporting structure comprises a front supporting frame, an upper supporting frame, a lower supporting frame, a locking rod, a connecting rod and a rear cross support. The upper corrugated panel and the lower corrugated panel are respectively arranged above the upper support frame and the lower support frame; a rotating hole in one end of the bevel edge of the front supporting frame is connected with a rotating hole in the upper supporting frame through a pin shaft, and rotating holes in the two sides of the short right-angle edge of the upper supporting frame are connected with rotating holes in the end of the lower supporting rod through rotating pins, so that overturning of the lower supporting frame is achieved; the lower supporting rods are connected through rear cross supports and connecting rods. A locking hole in one end of the locking rod is connected with a locking hole of the lower supporting rod through a locking pin, and a locking pin at the other end of the locking rod is connected with a locking hole of the front supporting frame and a locking hole of the upper supporting frame and used for locking the lower supporting rod, the front supporting frame and the upper supporting frame. A spiral anchoring hole is formed in the middle of the connecting rod, and the connecting rod is connected with a spiral anchoring structure through the spiral anchoring hole and used for fixing the guide plate.

The utility model provides a low negative pressure side wing diversion wall for airplane test run, which comprises a diversion structure surrounding an airplane, the diversion structure comprises a tail diversion wall corresponding to the tail of the airplane and side wing diversion walls corresponding to side wings of the airplane, and the side wing diversion walls are integrally parallel to or slightly inclined to the axial direction of an airplane body and are connected with the ground. The side wing flow guide wall comprises a windward side and a leeward side, the windward side is formed by continuously splicing a plurality of metal plates, the leeward side is connected with a supporting frame, and the bottom of the supporting frame is connected with a concrete ground anchor bolt; a plurality of silencing ducts are further arranged in the side wing flow guide walls, and the opening ends of the silencing ducts penetrate through the windward side and face the aircraft; the noise elimination ducts are arranged on the flow guide walls of the side wings, airflow can be introduced, the internal and external pressure difference of the flow guide walls is reduced, the test run environment of an airplane is facilitated, and meanwhile the influence of noise is greatly reduced through the cooperation of the perforated metal plates in the noise elimination ducts and the resistive sound absorption materials.

The utility model relates to the technical field of unmanned aerial vehicle parking equipment, in particular to an unmanned aerial vehicle parking apron deck with a noise reduction function. An unmanned aerial vehicle parking apron deck with a noise reduction function comprises a supporting seat, a noise reduction frame and a parking plate, the noise reduction frame is fixedly connected to the top of the supporting seat, the parking plate is slidably connected to the top of the noise reduction frame, the unmanned aerial vehicle parking apron deck further comprises dampers and buffer springs, the multiple dampers are arranged between the parking plate and the noise reduction frame, and each damper is sleeved with the corresponding buffer spring. The two ends of each connecting rod are fixedly connected between the parking plate and the noise reduction frame. By arranging a damper and buffer spring combined structure and combining the design of the sliding type parking plate, impact force generated when the unmanned aerial vehicle lands is effectively absorbed, and good damping and noise reduction effects are achieved.

The utility model relates to the technical field of flow guide screen, concretely provides a quick detachable strong support flow guide screen structure, including upper flow guide screen module, lower flow guide screen module and support frame assembly, the upper flow guide screen module is connected with lower flow guide screen module through hinged structure, and the upper flow guide screen module can rotate around the hinge point to adjust the flow guide screen height, the support frame assembly includes at least a group of detachable support unit and bracing bar of connection, the support unit is detachably connected with lower flow guide screen module, and the bracing bar is detachably connected with upper flow guide screen module, the utility model provides a flow guide screen structure for assembly type structure, and the dismounting is convenient, satisfies the demand of quick response, and can be repeatedly used many times, reduces the cost, and the upper flow guide screen module rotates folding type design, can realize the adjustment of flow guide screen height, satisfies the use demand of different working conditions, improves the applicability.

The invention provides a mounting method of an integrated folding guide wall, comprising more than two fixing seats, guide wall units arranged on the fixing seats and balancing weights arranged on the guide wall units, limiting supports are arranged on the fixing seats, and limiting spaces for accommodating the guide wall units are formed in the limiting supports; each flow guide wall unit comprises a supporting frame, a first flow guide assembly arranged on one side of the supporting frame, a second flow guide assembly hinged to the joint of the first flow guide assembly and the supporting frame and a folding assembly hinged to the second flow guide assembly and the supporting frame. Different guide wall units can be accurately spliced and mounted, and different test run working conditions of different models can be met by adjusting the angles of part of the guide surfaces of the guide wall units.

The invention provides a vertical take-off and landing platform capable of inhibiting downwash airflow and ground vortex, which structurally comprises a hollow take-off and landing platform surface, a large-volume sunken cavity, an exhaust runner, an exhaust fan and a one-way valve, and can exhaust downwash airflow generated by propellers and ducted fans from the lower part when an aircraft takes off and lands vertically; the air flow is scattered by the hollow surface of the take-off and landing platform surface and cannot rebound to form vortex, so that corresponding interference during take-off and landing and low-altitude hovering of the aircraft is effectively eliminated, and the take-off and landing efficiency and safety are remarkably improved. The vertical take-off and landing platform is high in universality and relatively low in manufacturing cost, and therefore the vertical take-off and landing platform has high popularization and application value.

The application provides a mounting method of an integrated folding guide wall, which comprises two or more fixing bases, guide wall units arranged on the fixing bases and counterweights arranged on the guide wall units, the fixing base is provided with a limiting support, a limiting space for accommodating the guide wall unit is formed in the limiting support, the guide wall unit comprises a support frame, a first guide assembly arranged on one side of the support frame, a second guide assembly hinged to the connecting position of the first guide assembly and the support frame and folding assemblies hinged to the second guide assembly and the support frame respectively; the method can realize accurate splicing and mounting of different guide wall units, and the angle of part of the guide surface of the guide wall unit can be adjusted to meet different test driving conditions of different models.