RU104124U1 - AMPHIBIAN DEVICE ON A DYNAMIC AIR PILLOW - Google Patents

Abstract

 A device based on a dynamic air cushion having a center of gravity position behind the center of pressure of the lifting aerodynamic force comprises a tail unit, a power unit with horizontal thrust propellers, a center section consisting of a system of tandemly located one or more wings with flaps and aft wing, and side washers-floats, characterized in that it is equipped with a support element located in the rear of the apparatus behind the trailing edge of the aft wing at a distance of not less than half Oplan by side washers-floats and contacting the shielding surface, superchargers static air cushion flexible enclosure beneath the front edge of the front wing, the trailing edge adjacent to the front edges of the subsequent wing to overlap the flap gap and the trailing edge aft wing declined downward.

Description

The technical field to which the utility model belongs.

The utility model relates to vehicles with aerodynamic unloading, in particular, to devices on a dynamic air cushion.

State of the art

Known ekranoplan патент patent No. DE 4405152 (A1), publ. 01/09/1994 containing a center section with side washers, front, middle retractable flaps, a horizontal thrust propeller with a device for taking part of the air flow and supplying it under the center section to create a two-chamber static air cushion in order to ensure longitudinal balance.

The disadvantages of ekranoplan are:

- low maneuverability when moving on a static air cushion due to the presence of a constantly acting thrust forward;

- the inability to use a reversing screw propeller to reduce landing speed and improve safety;

- low safety when driving at low altitude due to low longitudinal stability and the peculiarities of the oscillatory movement along the pitch angle and height with a high probability of impact on the underlying surface with a negative reference.

Known vehicle № patent No. RU 2173644, publ. September 20, 2001, has a body, a wing with flaps, a knob for controlling their rotation, air balloons installed in the lower part of the skegs, a air ball mounted on the lower surface of the wing and the body, propellers on the rotary pylon in front of the front edge of the wing, a handle for controlling the rotation of the pylon, plumage with rudder, stabilizer. The flap rotation control handle and the pylon rotation control handle with screws are kinematically connected to each other for easier balancing and control.

The disadvantages of the vehicle are:

- low maneuverability when driving in a mode with blowing due to the presence of a constantly acting thrust forward;

- low seaworthiness and reliability due to the possibility of damage to the propeller propellers on the water;

- low safety when driving at low altitude due to low longitudinal stability and the features of the oscillatory movement along the pitch angle and height with a high probability of impact on the underlying surface with a negative reference.

A known patent is № DE 102009004239 (No. WO 2010076776), publ. 08/07/2010, which has a body, tandem-mounted wings with washers, a removable front flap and flaps, propellers in front of the front edge of one or more wings with the ability to direct the jet under the wings, stabilizers and flaps kinematically connected to each other to ensure automatic stabilization and longitudinal stability.

The disadvantages of the vehicle are:

- low maneuverability when moving on a static air cushion due to the presence of a constantly acting thrust forward;

- the inability to use a reversing screw propeller in the blow mode to reduce landing speed and improve safety;

- low safety due to the lack of its own aerodynamic longitudinal stability of the layout and low reliability of the automatic stabilization system, which has complex kinematics and design;

- the presence of impacts on the flap aileron of irregularities of the shielding surface (waves, snow and ice growths, floating bodies, etc.), causing structural damage, complicating the pilot's work.

A device based on a dynamic air cushion (patent No. RU 2188137 publ. 08/27/2002) containing a displacement body with a tail, two side floats, a front and a main wing with a controllable flap, a power plant with propellers above the front wing, was selected as a prototype , the rear wing-float with a V-shaped lower surface, mounted with the possibility of contact of the tail with the shielding surface, and the center of gravity of the apparatus is located behind the center of aerodynamic pressure.

The disadvantages of the vehicle are:

- low maneuverability when driving in start-up mode with blowing due to the presence of a constantly acting thrust forward, the inability to use the reverse of the screw;

- low seaworthiness and reliability due to the possibility of damage to the propeller propellers on the water.

These shortcomings reduce the safety and operational capabilities of the device.

Utility Model Disclosure

In developing the proposed utility model, the task was to increase the safety of the amphibious vehicle on a dynamic air cushion and to improve its operational characteristics during maneuvering and in cruising driving modes.

The technical result consists in creating a controlled supporting force of the apparatus in the speed range from zero to cruising, including at large glancing angles, as well as in increasing the lifting aerodynamic force and enhancing its dependence on the height above the screening surface.

This problem is solved due to the fact that the device is on a dynamic air cushion, the center of gravity of which is located behind the center of pressure of the lifting aerodynamic force, comprising a tail unit, a power plant with horizontal thrust propellers, a center wing in the form of a system of tandem-mounted wings with flaps, aft wing and side washers-floats, equipped with a support element located in the rear of the apparatus behind the trailing edge of the aft wing at a distance of at least half of the center lan from the side washers-floats and contacting the shielding surface, superchargers static air cushion flexible enclosure beneath the front edge of the front wing, the trailing edge adjacent to the front edges of the subsequent wing to overlap the flap gap and the trailing edge aft wing declined downward.

The proposed apparatus is characterized by the presence of a support element located in the rear of the apparatus behind the trailing edge of the aft wing at a distance of not less than half the span of the center section from the side washers and is in contact with the shielding surface. The use of such a supporting element allows you to create part of the supporting force of the apparatus due to the reaction force from contact with the shielding surface, therefore, in case of contact loss, the value of the supporting force decreases, which prevents the apparatus from moving upward from the screen and ensures stability in height. The location of the support element and, accordingly, the contact point in the rear part allows balancing. The location of the support element at a specified distance provides such a change in aerodynamic force along the pitch angle at which the resulting change in lift creates a restoring moment. As a result, its own static and dynamic longitudinal stability of the apparatus is ensured.

In addition, the proposed device is characterized by the presence of a static air cushion blower, a flexible fence under the front edge of the front wing, and the rear edge of the aft wing deflected down. The combination of these elements, their shape and relative position together with the side washers-floats provides the formation of a closed chamber of the air cushion under the lower surface of the center section and the possibility of creating a static air cushion, as well as increasing the pressure of the dynamic air cushion.

Also characteristic is the relative positioning of the elements of the wing system, namely, the adjoining of the leading edges of the wings to the trailing edge of the previous wing with the possibility of overlapping the flap gap. As a result, by turning the flap, the airbag chamber is sealed and the full aerodynamic force can be controlled. This eliminates the possibility of contact between the flaps and the shielding surface and the impact of irregularities (waves, snow, ice and other ridges) on the flaps and control wiring.

The increase in pressure under the lower surface of the center section due to the additional injection of an air cushion into the chamber and the suction of air from the upper surface makes it possible to increase the dependence of the change in the lifting force on the pitch angle and also to prevent the flow stall on the upper surface. This helps to increase the longitudinal stability of the apparatus in a wide range of pitch angles and, accordingly, increases the safety of the apparatus.

In addition, in order to increase patency on a solid shielding surface, as well as to provide the possibility of optimizing the gap between the washers - cylinders and aft wing, the support element can be equipped with a vertical position adjustment device. And to reduce shock loads and increase comfort by reducing vibration, the support element can be sprung.

Thus, the presence of elements: a stern wing of a certain shape, a supporting element in contact with the shielding surface, their relative position relative to other elements of the apparatus - the body, superchargers, wings with flaps, side washers-floats, as well as their interconnection, ensures the achievement of a technical result namely, the creation of a controlled supporting force of the vehicle in the speed range from zero to cruising, including at large glide and pitch angles, as well as an increase in lifting aerodynamic force and increasing its dependence on the height above the shielding surface. This favorably affects the increase in stability, controllability and maneuverability of the apparatus over the entire range of operating speeds, glide and pitch angles, as well as its seaworthiness.

The achievement of this technical result allows us to solve the problem of improving safety and improving the operational characteristics of the apparatus on a dynamic air cushion during maneuvering, braking, in the starting and cruising modes of movement.

Brief Description of the Drawings

The figure 1 shows a General view of the amphibious apparatus from the side.

The figure 2 shows a General view of the apparatus in front.

The figure 3 shows a General view of the apparatus from above.

The apparatus on a dynamic air cushion having a center of gravity position behind the center of pressure of the total aerodynamic force consists of a housing 1 with a tail unit 2, a power unit 3 with horizontal thrust propellers and a center section. The center wing is made in the form of a system of tandemly located wings 4 and 5 with flaps 6 and 7, and the aft wing 8 with a reverse sweep at the trailing edge 9. The wings of the center wing at the ends are rigidly connected by side washers-floats 10, while the rear edges of the wings are adjacent to the leading edges subsequent wing with the possibility of overlapping the gap with a flap, and the trailing edge 9 of the aft wing is tilted down. A flexible fence 11 is mounted under the front edge of the front wing, designed to close the contour of the static air bag fence between the side washers - floats. Flexible fencing can be made in the form of a fabric curtain or retractable shield.

In the rear part of the apparatus there is a support element 12 located behind the trailing edge of the aft wing 8 at a distance of at least half of the center-wing span from the side washers-floats 10. The support element is in contact with the shielding surface 13 and can be made in the form of a hydro-ski, an air cushion platform, It can also be equipped with wheel bearings. Superchargers of the airbag 14 in the form of axial fans are integrated in one of the wings of the center section. As air cushion blowers, diametrical fans or centrifugal compressors can be used. On the housing 1 and the side floats 10 there are redans 15 to reduce the hydrodynamic resistance. The device is equipped with a hydraulic steering wheel 16 and an air rudder 17.

Utility Model Implementation

In the initial state, the apparatus is on the shielding surface 13 (water, soil, snow, etc.). When the superchargers 14 are turned on, the air flow enters the enclosed space under the center section, into the chamber of the static air cushion. The gaps between wings 4, 5 and aft wing 8 in the start mode are blocked by the deflection of the flaps 6, 7. With increasing pressure in the chamber of the static air cushion, the device rises above the screen surface and can make maneuvers under the influence of a control force. Under the action of the traction force of the propellers of the propulsion system 3, the apparatus accelerates. With an increase in the speed of movement to cruising, the flexible fence 11 is compressed under the influence of the high-pressure head of the oncoming flow and the apparatus moves on a dynamic air cushion. If it is necessary to brake the device, the driver reduces the propeller thrust or turns on the reverse, while the supporting force of the air cushion is maintained regardless of the speed and direction of flow from the air traction propellers, since at a low level of pressure head the flexible guard 11 is deflected and prevents the pressure in the chamber from falling air cushion created by the superchargers 14. In the mode of operation on a static air cushion, it is possible to move at low speed, in reverse, with a large lateral sliding a apparatus, or with great excitement, which increases maneuverability and seaworthiness. In the operating mode on a dynamic air cushion, movement is made at cruising or maximum speed.

The balance of the apparatus is ensured by the choice of the position of the center of gravity behind the center of aerodynamic pressure at a distance of 0.5-10%. wing chords. The cabling moment is compensated by the hydrodynamic force arising at the contact point of the support element 9 with the screening surface. The removal of the cottact point and, accordingly, the center of rotation of the apparatus beyond the trailing edge of the root wing by a specified distance provides a negative dependence of the lifting force on the pitch angle. In this case, the pitch angle of the apparatus in the normal mode of movement always remains positive, and its changes are more easily controlled by the driver and measuring instruments than changes in height above the screening surface.

Due to the negative dependence of the lifting force on the pitch angle, the longitudinal static stability of the apparatus is secured, and due to the operation of the superchargers, the center-of-wing lifting coefficient increases and more significantly depends on the pitch angle. In addition, the suction of air from the upper surface of the center section delays the stall at high angles of attack, which increases the operational characteristics of the apparatus and safety.

When moving along an agitated water surface, uneven snow or dirt surface, shock loads are perceived by the redans of the hull, side washers-floats, the supporting element of the tail part and partially the trailing edge of the stern wing both in the launch mode and in the cruiser mode. The trailing edge of the wings of the center section is remote from the shielding surface and is isolated from contact with its irregularities, therefore the controls — the flaps are not subject to shock loads, which ensures reliable and safe operation. In order to increase patency, seaworthiness and reduce shock loads, the supporting element 12 can be made with a lifting device and sprung.

The control of the lifting force and the position of the apparatus by the pitch angle is carried out by deflecting the flaps. Heading control is performed using rudders.

Claims (1)

A device based on a dynamic air cushion having a center of gravity position behind the center of pressure of the lifting aerodynamic force comprises a tail unit, a power unit with horizontal thrust propellers, a center section consisting of a system of tandemly located one or more wings with flaps and aft wing, and side washers-floats, characterized in that it is equipped with a support element located in the rear of the apparatus behind the trailing edge of the aft wing at a distance of not less than half Oplan by side washers-floats and contacting the shielding surface, superchargers static air cushion flexible enclosure beneath the front edge of the front wing, the trailing edge adjacent to the front edges of the subsequent wing to overlap the flap gap and the trailing edge aft wing declined downward.