RU2797452C1 - In-flight refueling cone stabilization device - Google Patents

Abstract

FIELD: aviation, namely in-flight refueling.

SUBSTANCE: in-flight refueling unit is comprised of a supply hose (1), a rigid bushing (2), a stabilizing aerodynamic body (3), a receiving ball joint (4), a dynamically balanced gyro bushing (5), ball bearings (7), a protective cover (8) , mounting posts (9) of the protective cover, feedback bushing (12). On the bushing (5) there are screw protrusions (6). The bushing (2) contains a compensating bushing (10). On the bushing (10) there are screw protrusions (11). Shutters (13) are made on the bushing (12). The helical protrusions of the compensating bushing are made in the opposite direction of the helical protrusions of the gyro bushing.

EFFECT: automatic stabilization of the aerodynamic cone of the refueling unit is achieved.

1 cl, 2 dwg

Description

The invention relates to the field of aviation, namely in-flight refueling.

A device for a cone sensor of an in-flight refueling unit is known (RU 2490179 C1, 20.08.2013). The known device contains a housing, a ball joint, stabilizing the aerodynamic cone, and a special casing is installed on the cone body, which allows aerodynamic compensation of spontaneous oscillations of the filling device due to turbulent fluctuations in the air flow, due to the presence of electronic devices for measuring acceleration (accelerometers) on the casing with damper control systems that create an aerodynamic effect to compensate for spontaneous vibrations.

A disadvantage of the known device is the insufficient provision of stabilization of the aerodynamic cone of the refueling unit.

The technical result of the proposal is to automatically ensure the stabilization of the aerodynamic cone of the refueling unit by creating a gyroscopic effect on the cone.

The technical result is achieved by the fact that the in-flight refueling unit contains a flexible supply hose, at the end of which, on the flexible part of the supply hose, there is a feedback bushing with projections opposite the projections of the compensating bushing, and at the other end, a rigid bushing is installed, with a compensating bushing placed in series on it. with screw protrusions, a gyroscopic dynamically balanced bushing with axisymmetric protrusions, mounted on a rigid bushing through bearings, and with a protective casing covering the gyroscopic bushing, mounted on a rigid bushing with uprights, and a stabilizing aerodynamic cone with a ball joint for the fuel receiver, while the screw protrusions of the compensating bushings are made in the opposite direction of the helical protrusions of the gyroscopic bushing.

In FIG. 1 is a sectional diagram of an in-flight refueling unit.

In FIG. 2 shows the appearance of the unit without a protective cover.

The circuit contains a supply hose 1, a rigid bushing 2, a stabilizing aerodynamic body 3, a receiving ball joint 4, a gyroscopic dynamically balanced bushing 5, screw protrusions 6 on the bushing 5, ball bearings 7, a protective cover 8, mounting posts 9 of the protective cover, a compensating sleeve 10 on bushing 2, screw protrusions 11 on bushing 10, feedback bushing 12, shutters 13 on bushing 12, fuel filling direction 14, air flow direction 15 during flight.

When the tanker aircraft releases the supply hose 1 in flight in the direction of the aircraft being refueled, under the influence of the oncoming flow acting on the screw projections 6 of the sleeve 5, which act as a screw turbine, the sleeve 5 begins to rotate, creating a gyroscopic effect, holding the end of the supply hose 1 together with the body 3 and receiving hinge 4 in the direction of the refueling aircraft. At the same time, the protective cover 8 protects the protrusions 6 and improves the rotation characteristics of the sleeve 5. Since, when the sleeve 5 rotates, the friction in the rotation bearings 7 can cause a torque to occur on the rigid sleeve 2, therefore, in order to compensate for this torque, which can cause unwanted rotation of the supply hose 1 , a compensating sleeve 10 is used with a reverse rotation of the protrusions 11, which causes a reverse rotation of the supply hose 1. To adjust this rotation, a direct-acting regulator in the form of dampers 13 is used on the sleeve 12, mounted on the supply hose 1. In the neutral state, the dampers 13 maximally close the access of the oncoming air flow to the protrusions 11, and since the sleeve 12 is located on the flexible part of the supply hose 1, the rotation of the hose causes the rotation of the sleeve 12 and the movement of the dampers 13, opening the access of the oncoming air flow to the protrusions 11 of the sleeve 10, causing an increased reverse rotation of the supply hose.

Claims (1)

In-flight refueling unit, characterized in that it contains a flexible supply hose, at the end of which, on the flexible part of the supply hose, there is a feedback bushing with projections opposite the projections of the compensating bushing, and at the other end, a rigid bushing is installed, with a compensating bushing placed in series on it with screw protrusions, a gyroscopic dynamically balanced sleeve with axisymmetric protrusions, mounted on a rigid sleeve through bearings, and with a protective casing covering the gyroscopic sleeve, mounted on a rigid sleeve with uprights, and a stabilizing aerodynamic cone with a ball joint for the fuel receiver, while the screw protrusions of the compensating sleeve made in the opposite direction of the screw protrusions of the gyroscopic sleeve.

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