Air refueling umbrella cone active control device based on ducted vector air vane

Abstract

This application belongs to the field of aircraft refueling control and relates to an active control device for aerial refueling parachute cones based on a ducted vector air rudder. A duct (1) is provided at the end of the refueling hose (2) near the parachute cone (3). The duct (1) includes: a duct body (11), the inner wall of which is connected to the refueling hose (2) via a support mechanism (12). The support mechanism (12) includes multiple support rods (121), each of which is a telescopic rod driven to extend and retract by an automatic parachute cone controller (13); a power supply device for supplying power to the support rods (121) and the automatic parachute cone controller (13); the automatic parachute cone controller (13) is configured to control the extension and retraction of each support rod (121) so that the duct (1) deflects relative to the refueling hose (2), and the deflection direction is consistent with the direction of the parachute cone (3) deviating from the refueling port. This application can quickly dock with the refueling port of the receiving aircraft, improving the docking success rate.

Description

Technical Field

[0001] This application belongs to the field of aircraft refueling control, and specifically relates to an active control device for an aerial refueling parachute cone based on a ducted vector air rudder. Background Technology

[0002] Aerial refueling is a technology that replenishes fuel to other aircraft or helicopters during flight using a tanker aircraft. It can significantly improve the endurance of aircraft and plays an extremely important support role. In the existing technology, the tanker aircraft releases or retrieves the refueling hose through a winch controller, which drives the parachute cone located at the end of the refueling hose to align with the refueling connector of the receiving aircraft. The parachute cone is usually equipped with a position detection sensor, which can sense its positional relationship with the refueling connector of the receiving aircraft in real time. Then, the position signal is sent to the host computer. After spatial position calculation, the host computer controls the tanker aircraft to make relative position changes and controls the winch controller to control the length of the refueling hose. The two work together to complete the alignment and connection of the refueling connector.

[0003] The head wave and turbulence of the receiver aircraft cause disturbances to the refueling cone, which greatly affects the docking success rate. The traditional control method that relies on the refueling aircraft to adjust the relative position with the receiver aircraft has a long response time and poor control effect on the disturbances of the receiver aircraft head wave and turbulence on the refueling cone. Summary of the Invention

[0004] To address the aforementioned issues, this application provides an active control device and apparatus for aerial refueling parachute cones based on ducted vector air rudders. The active control scheme controls the parachute cones to deflect or move in a specified direction, thereby achieving rapid and precise docking with the refueling port of the receiving aircraft.

[0005] The in-flight refueling parachute cone active control device based on a ducted vector air rudder provided in this application has a duct at the end of the refueling hose near the parachute cone, and the duct includes:

[0006] The duct body has an inner wall connected to a refueling hose via a support mechanism. The support mechanism includes multiple support rods, each of which is a telescopic rod and is driven to extend and retract by an automatic umbrella cone controller.

[0007] Power supply unit, used to supply power to the support rod and the automatic controller of the umbrella cone;

[0008] The automatic controller for the parachute cone is configured to control the extension and retraction of each support rod so that the duct deflects relative to the refueling hose, the deflection direction being consistent with the direction of the parachute cone deviating from the refueling port, for controlling the movement of the parachute cone in a horizontal plane perpendicular to the axial direction of the refueling hose.

[0009] Preferably, the support mechanism comprises at least two sets, distributed axially at both ends of the culvert body.

[0010] Preferably, each support mechanism includes three support rods, which are distributed at 120° to each other in the circumferential direction on the inner wall of the duct.

[0011] Preferably, each support mechanism includes four support rods, which are distributed at 90° to each other in the circumferential direction on the inner wall of the duct.

[0012] Preferably, the power supply device includes a fan rotatably mounted on the refueling hose and a generator connected to the fan, the fan being located inside the duct.

[0013] Preferably, the automatic parachute cone controller is connected to the winch controller via wireless transmission, and is used to send the parachute cone forward and backward distance control signal to the winch controller, which then controls the release or retrieval of the refueling hose.

[0014] This application enables rapid docking with the receiving aircraft's refueling port, improving the docking success rate. Attached Figure Description

[0015] Figure 1 This is a structural perspective view of a preferred embodiment of the active control device for aerial refueling parachute cones based on a ducted vector air rudder, as described in this application.

[0016] Figure 2 for Figure 1 Right view of the illustrated embodiment.

[0017] Figure 3 for Figure 1 Left view of the embodiment shown.

[0018] Among them, 1-culvert, 11-culvert body, 12-support mechanism, 121-support rod, 13-umbrella cone automatic controller, 14-fan, 15-generator, 2-oiling hose, 3-umbrella cone. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0020] This application provides an active control device for an aerial refueling parachute cone based on a ducted vector air rudder, such as Figures 1-3 As shown, a duct 1 is provided at the end of the refueling hose 2 near the umbrella cone 3, and the duct 1 includes:

[0021] The duct body 11 has an inner wall connected to a refueling hose 2 via a support mechanism 12. The support mechanism 12 includes multiple support rods 121, each of which is a telescopic rod and is driven to extend and retract by an automatic umbrella cone controller 13.

[0022] Power supply device for supplying power to support rod 121 and umbrella cone automatic controller 13;

[0023] The automatic controller 13 of the parachute cone is configured to control the extension and retraction of each support rod 121 so that the duct 1 deflects relative to the refueling hose 2, and the deflection direction is consistent with the direction of the parachute cone 3 deviating from the refueling port, so as to control the parachute cone 3 to move in a horizontal plane perpendicular to the axis of the refueling hose 2.

[0024] In this embodiment, the automatic controller 13 of the umbrella cone is used to drive the extension and retraction of each support rod 121. The extension and retraction structure of each support rod 121 is, for example, a lead screw motion. The two ends of the support rod 121 are respectively hinged to the inner wall of the duct cylinder 11 and the annular outer sleeve of the refueling hose 2. The automatic controller 13 of the umbrella cone usually has a built-in control algorithm. The control algorithm generally includes two aspects: one is to output the corresponding deflection angle of the duct cylinder based on the deflection angle of the refueling connector fed back by the umbrella cone; the second is to calculate the movement of each extension rod based on the deflection angle and make each extension rod move in conjunction to prevent mutual interference. For example, when there are four support rods distributed at 90°, such as Figure 1 As shown, when the receiver probe is detected to be tilted upwards, the upper support rod extends and the lower support rod shortens, causing the airflow to move upwards, the control force to move downwards, and the parachute cone to move downwards; the reverse is also true. For example, when the receiver probe is detected to be tilted to the left, the left electric actuator rod extends and the right electric actuator rod extends and shortens, causing the airflow to move to the left, the control force to move to the right, and the parachute cone to move to the right; the reverse is also true.

[0025] In some alternative embodiments, the support mechanism 12 comprises at least two sets, axially distributed at both ends of the duct body 11. Figure 1 From the perspective of the viewpoint, there is a support mechanism at three points away from the umbrella cone. Figure 3 From the perspective, there is another set of support mechanisms near the umbrella cone 3. The extension and retraction lengths of the support rods in the two sets of support mechanisms can be the same or different. When they are the same, after the support rods extend and retract, the axis of the duct body 11 is parallel to the axis of the refueling hose 2. When they are different, after the support rods extend and retract, the axis of the duct body 11 and the axis of the refueling hose 2 form a certain angle.

[0026] In some alternative embodiments, each support mechanism 12 includes three support rods 121, which are distributed 120° apart from each other in the circumferential direction on the inner wall of the duct body 11.

[0027] In some alternative embodiments, each support mechanism 12 includes four support rods 121, which are distributed at 90° angles to each other in the circumferential direction on the inner wall of the duct body 11. This embodiment is shown in the accompanying drawings; it will be understood that each support mechanism 12 may also include more support rods 121.

[0028] In some alternative embodiments, the power supply device includes a fan 14 rotatably mounted on the refueling hose 2 and a generator 15 connected to the fan 14, the fan 14 being located inside the duct body 11.

[0029] Understandably, for safety reasons, electrical connection wires are usually not installed on the refueling hose 2, meaning it is inconvenient to introduce the machine's power into the duct 1 via wires. Therefore, in this embodiment, a rotating fan 14 is installed on the refueling hose 2 to generate electricity, thereby powering the support rod 121 and the umbrella cone automatic controller 13. In alternative embodiments, high-power lithium batteries or other power supply equipment can also be used, but regular maintenance is required.

[0030] In some alternative embodiments, the automatic parachute cone controller 13 is connected to the winch controller via wireless transmission, and is used to send the forward and backward distance control signal of the parachute cone 3 to the winch controller, which controls the release or retrieval of the refueling hose 2.

[0031] This embodiment is mainly used to control the parachute cone to move along the axial direction of the refueling hose 2, while the duct is used to control the parachute cone to move in a horizontal plane perpendicular to the axial direction of the refueling hose 2. The two work together to achieve omnidirectional movement control of the parachute cone.

[0032] Understandably, during aerial refueling, the receiver aircraft flies behind the tanker aircraft and maintains relatively stable flight. The tanker aircraft releases its parachute cones, which remain naturally extended to a position behind the tanker and remain essentially stationary, awaiting docking control. At this point, the parachute cones typically only experience angular displacement, which is transmitted wirelessly to the automatic parachute cone controller 13. The automatic parachute cone controller 13 then controls the deflection of the duct 1. However, there are also variations in the distance between the parachute cones and the receiver aircraft's refueling connector. Therefore, a distance signal also needs to be sent to the tanker aircraft's winch controller, which controls the winch to rotate, releasing or retrieving the refueling hose 2. Here, the automatic parachute cone controller 13 acts as a transition, forwarding the distance signal between the parachute cones and the receiver aircraft's connector to the winch controller. In an alternative embodiment, all monitoring signals for the parachute cones can be first sent to the winch controller, which then wirelessly transmits the control signals for the duct 1 to the automatic parachute cone controller 13.

[0033] This application is applied to aircraft that require autonomous aerial refueling. By making simple modifications to the parachute cone, the success rate of docking between the three cones and the refueling connector of the receiving aircraft is greatly improved.

[0034] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An active control device for an aerial refueling parachute cone based on a ducted vector air rudder, characterized in that, A duct (1) is provided at the end of the refueling hose (2) near the umbrella cone (3), the duct (1) comprising: The duct body (11) has an inner wall connected to a refueling hose (2) via a support mechanism (12). The support mechanism (12) includes multiple support rods (121), each of which is a telescopic rod and is driven to extend and retract by an automatic umbrella cone controller (13). A power supply device is provided for supplying power to the support rod (121) and the umbrella cone automatic controller (13); The automatic controller (13) of the parachute cone is configured to control the extension and retraction of each support rod (121) so that the duct (1) deflects relative to the refueling hose (2) in the same direction as the direction of the parachute cone (3) deviating from the refueling port, for controlling the parachute cone (3) to move in a horizontal plane perpendicular to the axis of the refueling hose (2).

2. The active control device for aerial refueling parachute cones based on ducted vector air rudders as described in claim 1, characterized in that, The support mechanism (12) includes at least two sets, which are distributed axially at both ends of the duct body (11).

3. The active control device for aerial refueling parachute cones based on ducted vector air rudders as described in claim 1, characterized in that, Each support mechanism (12) includes three support rods (121) that are distributed at 120° to each other in the circumferential direction on the inner wall of the duct body (11).

4. The active control device for aerial refueling parachute cones based on ducted vector air rudders as described in claim 1, characterized in that, Each support mechanism (12) includes four support rods (121) that are distributed at 90° to each other in the circumferential direction on the inner wall of the duct body (11).

5. The active control device for aerial refueling parachute cones based on ducted vector air rudders as described in claim 1, characterized in that, The power supply device includes a fan (14) rotatably mounted on the refueling hose (2) and a generator (15) connected to the fan (14), the fan (14) being located inside the duct body (11).

6. The active control device for aerial refueling parachute cones based on ducted vector air rudders as described in claim 1, characterized in that, The automatic parachute cone controller (13) is connected to the winch controller via wireless transmission. It sends the forward and backward distance control signal of the parachute cone (3) to the winch controller, which then controls the release or retrieval of the refueling hose (2).

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