Unmanned aerial vehicle-mounted rotating tower for inhibiting boundary layer effect of high-speed flow field
By designing a low-drag saucer-shaped structure and an active rectification mechanism for the UAV-borne turret, the problem of flow field influence on the airborne optoelectronic system during high-speed flight was solved, thereby improving the stable imaging and target recognition capabilities of the optoelectronic equipment.
Patent Information
- Application Number
- CN202511581700.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-31
- Publication Date
- 2026-01-23
AI Technical Summary
In high-speed flight environments, the high-speed flow field causes phase distortion of light waves in airborne optoelectronic systems, affecting the target image of the imaging system by causing offset, blurring, and jitter, thus reducing the ability to detect, identify, and track targets.
Design a UAV-borne turret with a low-drag saucer-shaped structure, combining a passive flow guide structure and an active flow rectification mechanism. The angle of the guide plate is adjusted by a servo motor to suppress the boundary layer effect of the high-speed flow field and reduce aero-optical effects.
It effectively suppresses the boundary layer effect in high-speed flow fields, reduces irregular vibrations of optoelectronic devices, improves the ability to detect, identify and track targets, and reduces aero-optical effects.
Smart Images
Figure CN121376244A_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of UAV-borne optoelectronic system technology, specifically to a UAV-borne turret structure design for suppressing boundary layer effects in high-speed flow fields. Background Technology
[0002] With the continuous advancement of laser-related technologies, optoelectronic systems are developing rapidly. The functions and shapes of optoelectronic devices vary depending on the application scenario. Optoelectronic systems deployed on large platforms such as the ground or ships have no strict requirements regarding weight, volume, or shape; however, optoelectronic systems deployed on aircraft platforms require lightweight and miniaturized designs due to limitations such as platform space, energy supply, and high-speed flight. Furthermore, the high-speed motion of optoelectronic systems in airborne environments generates complex aerodynamic flow fields. Drastic changes in flow field density alter the refractive index of the surrounding gas, causing additional phase distortion in the transmitted light waves. This affects beam transmission characteristics, leading to target image shifts, blurring, and jitter in the imaging system, thus impacting the optoelectronic system's ability to detect, identify, and track targets.
[0003] In view of this, it is necessary to design an unmanned aerial vehicle (UAV) turret to suppress the boundary layer effect in high-speed flow fields in order to solve the above problems. Summary of the Invention
[0004] In view of the technical problems existing in the background art, this application provides a UAV carrier turret for suppressing the boundary layer effect of high-speed flow fields. The main structure of the UAV carrier turret adopts a low-drag saucer-shaped structure (saucer-shaped photoelectric turret). The saucer-shaped photoelectric turret includes a saucer-shaped photoelectric turret azimuth frame and a photoelectric turret pitch frame designed conformally to the azimuth frame. The UAV carrier turret also includes a passive flow guiding structure disposed at the mounting surface of the photoelectric turret azimuth frame and the carrier platform, and an active flow rectification mechanism (aerodynamic compensation mechanism) installed below the saucer-shaped photoelectric turret. The shape of the aerodynamic compensation mechanism can be adjusted by a servo motor to change the windward angle of the flow guiding mechanism plate according to the different flight speeds of the carrier aircraft, thereby changing the airflow field state below the photoelectric turret, suppressing the high-speed complex flow field formed below the saucer-shaped photoelectric turret, achieving the function of suppressing the boundary layer effect of high-speed flow fields, and reducing the aero-optical effects of photoelectric equipment.
[0005] This application achieves the function of suppressing the boundary layer effect in high-speed flow fields through the combined action of the aforementioned saucer-shaped photoelectric turret, auxiliary flow guiding structure, and aerodynamic compensation mechanism.
[0006] This application provides an embodiment of an unmanned aerial vehicle (UAV) turret for suppressing boundary layer effects in high-speed flow fields, including a saucer-shaped photoelectric turret. The saucer-shaped photoelectric turret includes a saucer-shaped photoelectric turret azimuth frame, a turret azimuth rotation axis system for mounting the photoelectric turret azimuth frame, and a photoelectric turret pitch axis system for mounting the photoelectric turret pitch frame at the circumference of the photoelectric turret azimuth frame. The photoelectric turret pitch frame is conformally designed with the photoelectric turret azimuth frame. The UAV turret also includes an incident light beam channel protruding upward from the upper surface of the photoelectric turret azimuth frame, an auxiliary flow guiding structure extending from the upper surface of the photoelectric turret azimuth frame toward the outer wall of the incident light beam channel, and an aerodynamic compensation mechanism disposed at the bottom of the photoelectric turret azimuth frame.
[0007] In some embodiments, the pneumatic compensation mechanism includes a set of symmetrically installed flow guide plates, a set of servo motors, and a wind speed sensor for collecting real-time wind speed data of the environment where the photoelectric turret is located. Based on the real-time wind speed data, the pneumatic compensation mechanism controls the servo motors to rotate, thereby driving the flow guide plates to rotate and changing the opening and closing angle of the two flow guide plates, thus achieving active suppression of airflow.
[0008] In some embodiments, a clearance space is provided at the circumference of the azimuth frame of the photoelectric turret for accommodating the pitch frame of the photoelectric turret; the pitch frame of the photoelectric turret has a columnar circumferential symmetrical structure that is thicker in the middle and thinner at both sides, and its diameter gradually decreases from the center line to both sides.
[0009] In some embodiments, pitch bearings are provided at both ends of the pitch frame of the photovoltaic turret; the pitch frame of the photovoltaic turret rotates around the pitch axis of the photovoltaic turret; during the pitch rotation, the outer envelope dimension of the saucer-shaped photovoltaic turret does not change with the pitch angle. Therefore, when the working direction of the photovoltaic turret is forward, lateral, or backward, the windward area and wind load moment do not change.
[0010] In some embodiments, the auxiliary flow guiding structure is provided with a smooth curved surface. The projection of the auxiliary flow guiding structure on the surface where the light beam channel is located completely blocks the light beam channel, so as to completely block the cylindrical azimuth rotation axis system, reduce the concave and sharp corners and other protruding structures on the surface of the UFO-shaped photoelectric turret, and guide the air flow field between the photoelectric turret and the aircraft platform.
[0011] In some embodiments, the auxiliary flow guiding structure is disposed on the incoming flow surface of the UAV-borne turret.
[0012] The auxiliary flow guiding structure does not rotate with the photoelectric turret around the azimuth rotation axis. Its installation direction is consistent with the direction of the aircraft nose. The smooth curved surface always faces the direction of the incoming flow, which is used to suppress the irregular and rapidly changing vortex field generated at the connection area.
[0013] In some embodiments, a curved optical window is provided on the pitch frame of the photoelectric turret, and the curved optical window is conformally designed with the pitch frame of the photoelectric turret.
[0014] In some embodiments, the curved optical window is embedded in the pitch frame of the photoelectric turret, and the connection between the two is smoothly transitioned.
[0015] The curved optical window is installed on the pitch frame of the photoelectric turret by embedding. The curved optical window is fixed by pressure ring and sealing ring to achieve airtightness. After the curved optical window is installed, the outer envelope dimension of the pitch frame of the photoelectric turret remains unchanged.
[0016] In some embodiments, the incident light beam channel is arranged in a cylindrical shape.
[0017] The beneficial effects of this invention are: The main structure of the UAV-borne turret of this invention adopts a low-drag saucer-shaped structure (saucer-shaped photoelectric turret). The saucer-shaped photoelectric turret includes a saucer-shaped azimuth frame and a conformally designed pitch frame. The entire UAV-borne turret of this invention adopts an arc-shaped, curved surface design, reducing aerodynamic irregularities and turbulent structures formed by concave corners and other irregularities on the outer surface, reducing the windward area of the photoelectric turret, lowering aerodynamic drag, suppressing the boundary layer effect of high-speed flow fields, and reducing the aero-optical effects of the airborne photoelectric system. The wind load torque remains unchanged when the saucer-shaped photoelectric turret rotates to any azimuth, the turbulent structure is stable, effectively reducing irregular vibrations of the photoelectric turret and improving the ability of photoelectric equipment to detect, identify, and track targets.
[0018] This application also includes a passive flow guiding structure located at the azimuth frame of the photoelectric turret and the mounting surface of the aircraft platform, and an active flow rectification mechanism (aerodynamic compensation mechanism) installed below the saucer-shaped photoelectric turret. This auxiliary flow guiding structure does not rotate with the photoelectric turret around its azimuth axis; its installation direction is consistent with the nose direction of the aircraft, and its smooth curved surface always faces the incoming flow direction, used to suppress irregular and rapidly changing vortex fields generated at the connection area. The shape of this aerodynamic compensation mechanism can be adjusted by a servo motor to change the windward angle of the flow guiding mechanism plate according to different flight speeds of the aircraft, thereby altering the airflow field state below the photoelectric turret, suppressing the high-speed complex flow field formed below the saucer-shaped photoelectric turret, achieving the function of suppressing the boundary layer effect of the high-speed flow field, and reducing the aero-optical effects of the photoelectric equipment.
[0019] This application achieves the function of suppressing the boundary layer effect in high-speed flow fields through the combined action of a saucer-shaped photoelectric turret, an auxiliary flow guiding structure, and an aerodynamic compensation mechanism.
[0020] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description
[0021] To more clearly illustrate the technical solution of this application, the accompanying drawings used in this application will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without any creative effort.
[0022] Figure 1 This is a schematic diagram of the structure of the UAV turret for suppressing the boundary layer effect in a high-speed flow field, as described in this application embodiment. Figure 2 This is a schematic diagram of the front structure of the UAV turret in the embodiments of this application; Figure 3 This is a side view of the UAV turret structure in an embodiment of this application; Figure 4 This is a schematic diagram of the bottom structure of the UAV turret in the embodiments of this application; Figure 5 To remove Figure 1 A schematic diagram of the structure behind the pitching frame of the Zhongguang Optoelectronics turret; Figure 6 This is a schematic diagram of the pitching frame of the photoelectric turret. Detailed Implementation
[0023] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.
[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.
[0025] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly specifying the number, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly defined.
[0026] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.
[0027] In the description of the embodiments in this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this document generally indicates that the preceding and following related objects have an "or" relationship.
[0028] In the description of the embodiments of this application, the term "multiple" refers to two or more (including two), similarly, "multiple sets" refers to two or more (including two sets), and "multiple pieces" refers to two or more (including two pieces).
[0029] In the description of the embodiments of this application, the technical terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.
[0030] In the description of the embodiments of this application, unless otherwise expressly specified and limited, technical terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.
[0031] Due to limitations imposed by platform space, energy supply, and high-speed flight, airborne optoelectronic systems deployed on aircraft platforms require lightweight and miniaturized designs. Secondly, the high-speed motion of the optoelectronic system in an airborne environment generates complex aerodynamic flow fields. Drastic changes in flow field density alter the refractive index of the surrounding gas, causing additional phase distortion in the transmitted light waves. This affects beam transmission characteristics, leading to target image shifts, blurring, and jitter in the imaging system, ultimately impacting the optoelectronic system's ability to detect, identify, and track targets.
[0032] Please see Figures 1 to 6 As shown, to address the technical problem of aerodynamic flow affecting imaging performance, this application provides a UAV-borne turret for suppressing boundary layer effects in high-speed flow fields, comprising a saucer-shaped photoelectric turret. The saucer-shaped photoelectric turret includes a saucer-shaped photoelectric turret azimuth frame 5, a turret azimuth rotation axis system 8 for mounting the photoelectric turret azimuth frame 5, and a photoelectric turret pitch axis system 7 for mounting the photoelectric turret pitch frame 2 at the circumference of the photoelectric turret azimuth frame 5. In the embodiments of this application, the saucer-shaped photoelectric turret has a diameter of 800 mm, a height of 400 mm, and a weight of approximately 70 kg, meeting the weight and size requirements of UAVs for photoelectric turrets.
[0033] The photoelectric turret pitch frame 2 and the photoelectric turret azimuth frame 5 are designed to conform to each other.
[0034] The UAV-borne turret of this invention adopts an arc-shaped, curved surface design, reducing aerodynamic irregularities and turbulent structures caused by concave corners and other irregularities on the outer surface. This reduces the windward area of the photoelectric turret, lowers aerodynamic drag, suppresses the boundary layer effect in high-speed flow fields, and reduces the aero-optical effects of the airborne photoelectric system. The wind load torque remains constant when the saucer-shaped photoelectric turret rotates to any position, ensuring stable turbulent structures and effectively reducing irregular vibrations of the turret, thereby improving the ability of photoelectric equipment to detect, identify, and track targets.
[0035] The photoelectric turret pitch axis system 7 is used to change the detection field of view of the pitch direction of the UFO-shaped photoelectric turret.
[0036] The turret orientation rotation axis system 8 is set at the connection between the saucer-shaped photoelectric turret and the carrier aircraft, and is used to change the detection field of view of the saucer-shaped photoelectric turret in the horizontal direction (photoelectric turret orientation rotation).
[0037] The azimuth frame 5 of the photoelectric turret has a clearance space around its circumference to accommodate the pitch frame 2. The pitch frame 2 is a cylindrical, symmetrical structure, thicker in the middle and thinner at both ends. Hollow shaft systems are installed at both ends of the circumference, with the hollow area serving as the beam channel. When the photoelectric turret pitches, the light channel in the hollow area does not undergo any changes in the optical path, similar to the principle of the azimuth rotation shaft system. Therefore, the light channels of the photoelectric turret can pass through the shaft system without optical path deflection. The diameter of the pitch frame 2 gradually decreases from the centerline towards both ends, such as... Figure 6 As shown.
[0038] In the embodiments of this application, the dimensions of the photoelectric turret pitch frame 2 are: 350mm in length, and the circumferential dimension is conformally designed with the photoelectric turret orientation frame 5, with a maximum circumferential dimension of 280mm.
[0039] The photovoltaic turret's pitch frame 2 is equipped with pitch bearings 9 at both ends. The photovoltaic turret's pitch frame 2 rotates around the photovoltaic turret's pitch axis 7. During the pitch rotation, the outer envelope dimension of the saucer-shaped photovoltaic turret does not change with the pitch angle. With this configuration, the windward area and wind load moment remain unchanged when the photovoltaic turret's working direction is forward, lateral, or backward.
[0040] A curved optical window 3 is provided on the pitch frame 2 of the photoelectric turret, and the curved optical window 3 is conformally designed with the pitch frame 2. The curvature of the curved optical window 3 is consistent with the curvature of the pitch frame 2. There are no pits or protrusions at the lens mounting point of the curved optical window 3, and the lens transitions smoothly with the photoelectric turret. In this embodiment, the curved optical window 3 is made of microcrystalline glass, with dimensions of 200mm in length, 160mm in width, and 10mm in thickness. These dimensions meet the requirements of general UAV-borne photoelectric turrets for light transmission aperture. The curved optical window 3 is installed on the pitch frame 2 of the photoelectric turret by embedding, and is fixed and airtight by pressure rings and sealing rings. After the curved optical window 3 is installed, the outer envelope dimension of the pitch frame 2 of the photoelectric turret remains unchanged.
[0041] The UAV-borne turret also includes an incident light beam channel 6 that protrudes upward from the upper surface of the photoelectric turret azimuth frame 5, an auxiliary flow guiding structure 1 that extends from the upper surface of the photoelectric turret azimuth frame 5 toward the outer wall of the incident light beam channel 6, and an aerodynamic compensation mechanism 4 located at the bottom of the photoelectric turret azimuth frame 5.
[0042] In some embodiments, the pneumatic compensation mechanism 4 includes a set of symmetrically installed airflow guide plates 4, a set of servo motors 10, and a wind speed sensor for collecting real-time wind speed data of the environment where the photoelectric turret is located. The wind speed sensor obtains the current wind speed data (real-time wind speed data) of the environment where the photoelectric turret is located. The pneumatic compensation mechanism controls the rotation of the servo motors to drive the airflow guide plates to rotate, thereby changing the opening and closing angle of the two airflow guide plates and achieving active suppression of airflow.
[0043] The shape of the aerodynamic compensation mechanism 4 can be adjusted according to the different flight speeds of the carrier aircraft. The angle of attack of the guide mechanism plate can be adjusted by the servo motor 10 to change the airflow field state under the photoelectric turret, suppress the high-speed complex flow field formed under the saucer-shaped photoelectric turret, and achieve the function of suppressing the boundary layer effect of the high-speed flow field, thereby reducing the aero-optical effect of the photoelectric equipment.
[0044] In some embodiments, the incident light beam channel 6 is cylindrical, and the auxiliary flow guiding structure 1 is a smooth curved surface. The projection of the auxiliary flow guiding structure 1 on the surface where the incident light beam channel 6 is located completely blocks the incident light beam channel 6, thereby completely blocking the azimuth rotation axis of the cylindrical turret, reducing the concave and sharp corners and other protruding structures on the surface of the saucer-shaped photoelectric turret, and guiding the airflow field between the photoelectric turret and the aircraft platform.
[0045] In some embodiments, the auxiliary flow guiding structure 1 is disposed on the incoming flow surface of the UAV-borne turret.
[0046] The auxiliary flow guiding structure 1 does not rotate with the photoelectric turret around the azimuth rotation axis 8. Its installation direction is consistent with the direction of the aircraft head. Its smooth curved surface always faces the direction of the incoming flow, which is used to suppress the irregular and rapidly changing vortex field generated at the connection area.
[0047] With this configuration, the auxiliary flow guiding structure 1 further suppresses the boundary layer effect for the saucer-shaped photoelectric turret.
[0048] This optoelectronic turret can suppress the turbulent flow field formed at the outer envelope of the turret in high-speed airflow environments, thereby reducing the aero-optical effects of optoelectronic products.
[0049] It should be noted that this application is not limited to the above-described embodiments. The above embodiments are merely examples, and any embodiments with the same structure and effect as the technical concept within the scope of this application are included in the technical scope of this application. Furthermore, various modifications that can be conceived by those skilled in the art to the embodiments, and other ways of constructing by combining some of the constituent elements of the embodiments, without departing from the spirit of this application, are also included in the scope of this application.
Claims
1. A UAV turret for suppressing boundary layer effects in high-speed flow fields, characterized in that, The system includes a saucer-shaped photoelectric turret; the saucer-shaped photoelectric turret includes a saucer-shaped photoelectric turret azimuth frame, a turret azimuth rotation axis system for mounting the photoelectric turret azimuth frame, and a photoelectric turret pitch axis system for mounting the photoelectric turret pitch frame at the circumference of the photoelectric turret azimuth frame; the photoelectric turret pitch frame and the photoelectric turret azimuth frame are conformally designed; the UAV-borne turret also includes an incident light beam channel protruding upward from the upper surface of the photoelectric turret azimuth frame, an auxiliary flow guiding structure extending from the upper surface of the photoelectric turret azimuth frame towards the outer wall of the incident light beam channel, and an aerodynamic compensation mechanism disposed at the bottom of the photoelectric turret azimuth frame.
2. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The pneumatic compensation mechanism includes a set of symmetrically installed flow guide plates, a set of servo motors, and a wind speed sensor for collecting real-time wind speed data of the environment where the photoelectric turret is located. Based on the real-time wind speed data, the pneumatic compensation mechanism controls the rotation of the servo motors to drive the flow guide plates to rotate, thereby changing the opening and closing angle of the two flow guide plates and achieving active suppression of airflow.
3. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The circumference of the azimuth frame of the photoelectric turret is provided with a clearance space for accommodating the pitch frame of the photoelectric turret; the pitch frame of the photoelectric turret has a columnar circumferential symmetrical structure that is thick in the middle and thin at both sides, and its diameter gradually decreases from the center line to both sides.
4. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 3, characterized in that, The two ends of the photoelectric turret pitch frame are provided with pitch rotation bearings; the photoelectric turret pitch frame rotates around the photoelectric turret pitch axis; during the pitch rotation, the pitch angle changes, but the outer envelope dimension of the saucer-shaped photoelectric turret remains unchanged.
5. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The auxiliary flow guiding structure is designed with a smooth curved surface, and the projection of the auxiliary flow guiding structure on the surface where the incident light beam channel is located completely blocks the incident light beam channel.
6. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The auxiliary flow guiding structure is located on the incoming flow surface of the UAV-borne turret.
7. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The photoelectric turret pitch frame is provided with a curved optical window, which is conformally designed with the photoelectric turret pitch frame.
8. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 7, characterized in that, The curved optical window is embedded in the pitch frame of the photoelectric turret, and the connection between the two is smooth.
9. The UAV turret for suppressing boundary layer effects in high-speed flow fields according to claim 1, characterized in that, The incident light beam channel is cylindrical in shape.