Stability augmentation device of aerial refueling taper sleeve

Abstract

The invention belongs to the technical field of aerial refueling of airplanes, and particularly relates to a stability augmentation device of an aerial refueling taper sleeve. The stability augmentation device of the air refueling taper sleeve comprises an oil conveying hose (1), a taper sleeve (2), a fairing (3), a stable wing surface (4), a movable control surface (5) and a pneumatic rotor (6), the oil conveying hose (1) penetrates through the fairing (3), the fairing (3) is fixed to the front end of the taper sleeve (2), the stable wing surface (4) is arranged on the fairing (3) in the circumferential direction, the stable wing surface (4) is fixed to the fairing (3), and the movable control surface (5) is fixed to the movable control surface (5). The stable airfoil (4) is provided with a hinge (8) and a movable control surface (5), the movable control surface (5) can freely rotate around a hinge rotating shaft (7), a pneumatic rotor (6) is arranged in the movable control surface (5), and the pneumatic rotor (6) can freely rotate around a rotor rotating shaft (9).

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft aerial refueling, and in particular relates to a stabilization device for an aerial refueling drogue. Background Art

[0002] Aerial refueling can significantly increase the range and combat radius of an aircraft, increase the aircraft's mission load and improve mission effectiveness. Aerial refueling technology is a technological high ground that all military powers must compete for. Hose-type aerial refueling technology was developed earlier, is mature, and is widely used. However, hose-type aerial refueling is easily affected by atmospheric turbulence, causing the hose cone sleeve to swing with the wind, greatly increasing the difficulty of aerial docking and reducing the success rate of docking. At present, several methods have been found to increase the stability of the cone sleeve, such as: using actively controlled aerodynamic control surfaces, deformable drag parachutes, etc. These methods basically require power to power sensors and actuators. The oil hose is generally tens of meters long, and the technical difficulty and risk factor of powering the end of it are high. Summary of the invention

[0003] Purpose of the invention: To provide a stabilization device for an aerial refueling drogue, so as to solve the problem of low docking success rate caused by airflow disturbance during aerial refueling, and at the same time improve the safety of the refueling process.

[0004] The technical solution of the present invention is:

[0005] A stabilization device for an aerial refueling drogue comprises: an oil delivery hose 1, a drogue 2, a fairing 3, a stabilizing wing surface 4, a movable rudder surface 5, and an aerodynamic rotor 6, wherein the oil delivery hose 1 passes through the fairing 3, the fairing 3 is fixed to the front end of the drogue 2, the fairing 3 is provided with a stabilizing wing surface 4 along the circumferential direction, the stabilizing wing surface 4 is fixed to the fairing 3, the stabilizing wing surface 4 is provided with a hinge 8 and a movable rudder surface 5, the movable rudder surface 5 can rotate freely around a hinge shaft 7, the movable rudder surface 5 is provided with an aerodynamic rotor 6, and the aerodynamic rotor 6 can rotate freely around a rotor shaft 9.

[0006] Furthermore, the stabilizing airfoils 4 are evenly arranged in the circumferential direction of the fairing 3 .

[0007] Furthermore, the number of the stabilizing wing surfaces 4 is four.

[0008] Furthermore, the hinge shaft 7 is swept back along the span direction of the stabilizing wing surface 4 .

[0009] Furthermore, the sweep angle is typically 45°.

[0010] Furthermore, a sawtooth structure is provided on the outer periphery of the pneumatic rotor 6 .

[0011] Furthermore, at least one half of the pneumatic rotor 6 is buried inside the movable control surface 5 .

[0012] Furthermore, the airfoil of the entire airfoil including the movable control surface 5 and the stabilizing airfoil 4 is a symmetrical airfoil.

[0013] Beneficial effects of this application:

[0014] The stabilization device of the aerial refueling drogue of the present invention utilizes the precession law of the pneumatic rotor to generate precession torque, drives the movable control surface to deflect, and the deflection of the control surface generates aerodynamic force and torque to resist airflow interference. The hinge shaft is swept back, which can decompose the aerodynamic torque of the control surface into rolling, pitching and yaw directions, increase the damping of disturbed motion, and increase the flight stability of the drogue. The device is a purely mechanical structure and does not require power supply. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the overall structure of the stabilization device of the aerial refueling drogue of the present invention.

[0016] Figure 2 Schematic diagram of the stable wing surface and movable control surface.

[0017] Figure 3 This is the front view of the pneumatic rotor. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0019] In the description of the present invention, it is necessary to understand that the terms "center", "axial", "vertical", "up", "down", "upper end", "bottom end", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present invention.

[0020] The present invention provides a device for improving the flight stability of a drogue, so as to solve the problem of low docking success rate caused by airflow disturbance during aerial refueling. At the same time, the present invention does not use electronic components, does not require external power supply and autonomous power generation, thereby reducing the technical difficulty of implementation and the risk factor of use.

[0021] The stabilization device of the aerial refueling cone sleeve of the present invention is applied to hose-type aerial refueling, which can reduce the drogue of the cone sleeve and improve the stability of the cone sleeve. Its main feature is that it does not use electronic components and does not require power supply. The present invention is based on the conventional hose cone sleeve, and adds a stabilizing wing surface, including: an oil delivery hose 1, a cone sleeve 2, a fairing 3, a stabilizing wing surface 4, a movable control surface 5, and an aerodynamic rotor 6. Among them, the hinge shaft 7 of the movable control surface 5 is swept back along the span direction of the wing surface. After the hose cone sleeve is released in the air, the airflow blows the aerodynamic rotor 6 to rotate at a high speed. When the hose cone sleeve is disturbed and the attitude is shifted, the aerodynamic rotor 6 generates a precession torque to drive the movable control surface 5 to deflect, and the generated aerodynamic force and torque can resist the interference of the airflow and increase the stability of the hose cone sleeve.

[0022] The present application is described in further detail below in conjunction with the accompanying drawings, but the present invention can be implemented in many different ways as defined and covered by the claims.

[0023] A stabilization device for an aerial refueling drogue, such as Figure 1 As shown, it includes an oil delivery hose 1, a cone sleeve 2, a fairing 3, a stabilizing airfoil 4, a movable control surface 5 and an aerodynamic rotor 6, wherein the oil delivery hose 1 passes through the fairing 3, the fairing 3 is installed at the front of the cone sleeve 2, the fairing 3 is the base for installing the stabilizing airfoil 4, and the four groups of stabilizing airfoils 4 are evenly distributed along the circumference of the fairing 3.

[0024] Figure 2 The stabilizing wing 4 shown is provided with a movable rudder surface 5, which is connected to the stabilizing wing 4 through a hinge 8, and the hinge shaft 7 is swept 45 degrees along the span direction of the stabilizing wing 4. The airfoil of the stabilizing wing 4 is a symmetrical airfoil. The movable rudder surface 5 is provided with an aerodynamic rotor 6, which is half buried outside the movable rudder surface 5 and about 3 / 4 of the circumference of the aerodynamic rotor 6 is buried inside the movable rudder surface. The aerodynamic rotor 6 can rotate freely around the rotor shaft 9. Figure 2 As shown, the airflow flows through the wing tip of the stabilizing wing surface 4 at high speed, blowing the exposed part of the aerodynamic rotor 6, causing the aerodynamic rotor 6 to rotate clockwise at high speed.

[0025] Figure 3 The pneumatic rotor 6 is shown as a gear-like structure with an indefinite number of teeth. In this embodiment, the number of teeth is 16.

[0026] The working principle of this device is:

[0027] After the tanker releases the oil delivery hose in the air, the hose cone sleeve is affected by the high-speed airflow and enters a dragging state. The pneumatic rotor 6 rotates at high speed due to the high-speed airflow. When the airflow is stable, the movable control surface 5 is in a neutral position (it may tilt at a small angle under the action of gravity). When the airflow is unstable, the hose cone sleeve changes its attitude due to the disturbance of the airflow. According to the law of precession, the pneumatic rotor 6 generates a precession torque to the outside, thereby driving the movable control surface 5 to deflect and generate aerodynamic force and torque. The hinge shaft 7 is swept back 45° to decompose the aerodynamic torque into the cone sleeve roll axis and pitch / yaw axis, thereby resisting the attitude change of the hose cone sleeve.

[0028] The above is only a preferred embodiment of the device of the present invention and is not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0029] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A stabilization device for an aerial refueling drogue, characterized in that , comprising: an oil delivery hose (1), a cone sleeve (2), a fairing (3), a stabilizing wing surface (4), a movable rudder surface (5), and an aerodynamic rotor (6), wherein the oil delivery hose (1) passes through the fairing (3), the fairing (3) is fixed at the front end of the cone sleeve (2), the fairing (3) is provided with a stabilizing wing surface (4) along the circumferential direction, the stabilizing wing surface (4) is fixed to the fairing (3), the stabilizing wing surface (4) is provided with a hinge (8) and a movable rudder surface (5), the movable rudder surface (5) can rotate freely around a hinge shaft (7), the movable rudder surface (5) is provided with an aerodynamic rotor (6), and the aerodynamic rotor (6) can rotate freely around a rotor shaft (9).

2. The stabilization device for the aerial refueling drogue according to claim 1, characterized in that: The stabilizing wing surfaces (4) are evenly arranged in the circumferential direction of the fairing (3).

3. The stabilization device for the aerial refueling drogue according to claim 1, characterized in that: The number of the stabilizing wing surfaces (4) is four.

4. The stabilization device for the aerial refueling drogue according to claim 1 is characterized in that , the hinge shaft (7) is swept back along the span direction of the stabilizing wing surface (4).

5. The stabilization device for the aerial refueling drogue according to claim 1 is characterized in that ,The typical value of the sweep angle is 45°.

6. The stabilization device for the aerial refueling drogue according to claim 1, characterized in that A sawtooth structure is arranged on the outer periphery of the pneumatic rotor (6).

7. The stabilization device for the aerial refueling drogue according to claim 1 is characterized in that At least one half of the pneumatic rotor (6) is buried inside the movable rudder surface (5).

8. The stabilization device for the aerial refueling drogue according to claim 1, characterized in that The airfoil of the entire wing surface including the movable control surface (5) and the stabilizing wing surface (4) is a symmetrical airfoil.

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