Device for testing center of gravity of fixed wing target aircraft

Abstract

The invention relates to a fixed wing target aircraft gravity center test device, which comprises a lower support member and an upper support member rotatably arranged on the lower support member, and is characterized in that the upper support member is used for fixedly connecting a complete machine to be tested and recording rotation angle information at any time relative to the lower support member; the base part is fixed to a test site and connected with the lower supporting piece through a plurality of horizontally-arranged movable pieces, and the movable pieces at least can feed back bearing capacity information. The whole machine can be rotated through running fit of the upper supporting piece on the lower supporting piece and bearing data feedback among the multiple movable pieces, and whether the gravity center of the whole machine coincides with a lifting force acting point or not can be judged conveniently according to the bearing force difference fed back by the movable pieces and rotation angle information of the upper supporting piece.

Description

Technical Field

[0001] This invention relates to the testing of aerodynamic characteristics of flight devices, specifically to a fixed-wing target drone center of gravity testing device. Background Technology

[0002] As experimental equipment or training targets, target drones also need to meet certain requirements for flight performance, and therefore also need to have certain aerodynamic characteristics. Generally speaking, the center of gravity of the whole aircraft needs to be at the same level as the point of lift or be sufficiently close in the horizontal direction. When the two cannot be fully overlapped in the horizontal direction, it will lead to insufficient flight stability of the whole aircraft. At this time, the center of gravity must be adjusted, such as by adjusting the counterweight. For fixed-wing aircraft, once the planar shape of the wing is determined, the horizontal position of the lift point can be determined directly through calculation. However, the determination of the aircraft's center of gravity is affected by various design and manufacturing factors. For example, the different positions and layouts of power components and structural components inside the fuselage will result in different overall center of gravity positions. Therefore, it can only be obtained through actual testing. Summary of the Invention

[0003] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0004] To address the technical problem of the lack of a convenient device in current technology, which makes it inconvenient to conduct simple testing of the center of gravity of the entire machine, the present invention provides the following technical solution: A fixed-wing target drone center of gravity testing device includes: The support part can be specifically divided into a lower support member and an upper support member that can be rotatably mounted on the lower support member. The upper support member is used to fix the whole machine under test and records the rotation angle information relative to the lower support member at all times. The base is fixed to the test site and connected to the lower support through multiple horizontally arranged movable parts, which can at least provide feedback on the load-bearing capacity.

[0005] In the above scheme, the upper support can drive the whole machine to rotate. When the center of gravity deviates, it will wobble, so that the force on multiple moving parts is different. This can determine whether the center of gravity has shifted. With the captured rotation information, the direction of the center of gravity deviation can be determined. When the entire support is a whole, it can still be used to realize the aerodynamic characteristics test of the whole machine.

[0006] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the lower support member and the upper support member are configured with a driving force for relative rotation.

[0007] In the above scheme, the rotation of the upper support on the lower support can be easily achieved through the driving force between the two.

[0008] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the lower support and the upper support are respectively provided with a motor stator assembly and a motor rotor assembly.

[0009] In the above scheme, the upper support and the lower support are equivalent to forming a motor structure. Compared with setting an external drive motor, this can reduce the overall number and volume of structures, and the force applied to the upper support by this drive will be more stable.

[0010] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, it also includes an angle detection element. The upper support has an initial rotation angle relative to the lower support, and the angle detection element records the deflection angle of the upper support relative to the lower support.

[0011] In the above scheme, when there is a difference in load-bearing capacity among multiple moving parts, the current rotation angle is recorded, and combined with the angle difference between the current angle and the initial angle, it can be determined on which side the center of gravity shift occurs.

[0012] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the plurality of movable parts include a first group and a second group. The first group of movable parts and the second group of movable parts are connected to different horizontal sides of the lower support. The bearing capacity deviation of the first group of movable parts and the second group of movable parts, as well as the rotation angle of the upper support, are obtained synchronously.

[0013] In the above scheme, the first group and the second group are both conceptual understandings. For example, when the entire support part tilts due to swaying, one side of the entire support part will inevitably be higher, and the opposite side will inevitably be lower. Among the multiple moving parts connected to different horizontal positions on the entire support part, they can be divided into the first group and the second group according to the positions of these two sides. Due to the height difference, the moving parts in the first group and the second group are compressed to different degrees, that is, the bearing capacity is different, resulting in a difference in force. Therefore, it can be determined that the center of gravity of the whole machine has shifted.

[0014] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the angle detection element includes a rotation sensor disposed between the lower support and the upper support.

[0015] In the above solution, the rotation angle of the upper support can be quickly and easily captured using an angle sensor.

[0016] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, it also includes a locking component, wherein the lower support and the upper support are kept in relative motion restriction by the locking component.

[0017] In the above scheme, the locking component keeps the upper support and the lower support relatively fixed, making the entire support part a whole structure.

[0018] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the locking component includes a pin head movably disposed on the lower support member, and the upper support member is provided with a pin hole corresponding to the pin head.

[0019] In the above scheme, the fit between the pin head and the pin hole provides a specific way to lock the upper support and the lower support.

[0020] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the lower support is provided with a pushing end, and the pin head is slidably disposed on the lower support and maintains an elastic connection with the pushing end.

[0021] In the above-mentioned solution, the push end is used to drive the movement of the pin head. For example, the push end can be a component such as an electric push rod. The elastic connection allows the pin head to elastically abut against the upper support before the pin hole is aligned with the pin head. As the upper support rotates, the pin head automatically engages with the pin head when the pin hole comes over.

[0022] As a preferred technical solution for a fixed-wing target drone center of gravity testing device, the upper support is provided with an angle scale, and the lower support is provided with an indicator end that indicates the angle scale.

[0023] In the above scheme, the scale is easy for testers to observe with their naked eyes, so that they can find the corresponding scale based on the angle data, in order to determine which side of the body the center of gravity shifts to.

[0024] The fixed-wing target drone center of gravity testing equipment provided by this invention has the following beneficial effects: 1. This invention utilizes the rotational cooperation of the upper support member on the lower support member, and through the load-bearing data feedback between multiple moving parts, the entire machine can be rotated. By using the load-bearing force difference fed back by the moving parts and simultaneously capturing the rotation angle information of the upper support member, it is easy to determine whether the center of gravity of the entire machine coincides with the point of application of the lift force.

[0025] 2. In this invention, the motor is integrated into the entire support by cooperating with the motor stator assembly and the rotor assembly, thereby reducing the number of components on the entire support and thus reducing its weight and volume.

[0026] 3. The present invention uses locking components to keep the upper support and lower support relatively fixed, thereby cooperating with the action of multiple moving parts, so that the entire device can be used to perform aerodynamic characteristic testing of the whole machine. Attached Figure Description

[0027] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. Wherein: Figure 1 and Figure 2 These are schematic diagrams of the three-dimensional structure from different perspectives of embodiments of the present invention.

[0028] Figure 3 for Figure 2 A magnified view of a specific area within the image.

[0029] Figure 4 and Figure 5 This is a schematic diagram showing the support portion from different perspectives in an embodiment of the present invention.

[0030] Figure 6 This is a three-dimensional cross-sectional view of the support portion described in an embodiment of the present invention.

[0031] Figure 7 This is a schematic diagram of the pin head and corresponding driving part described in an embodiment of the present invention.

[0032] Figure 8 for Figure 1 , 2 The illustrated embodiment is shown in the following diagram.

[0033] Figure 9 This is a schematic diagram of the arrangement of multiple pressure measuring chambers in the prior art.

[0034] Figure 10 This is a schematic diagram of the arrangement of multiple telescopic cylinders in the prior art.

[0035] Figure label: 100. Upper support component; 101. Lower support component; 200. Angle sensor; 300. Stator winding; 301. Rotor winding; 400. Ball bearing; 500. Electric telescopic rod; 501. Pin head; 502. Pin hole. Detailed Implementation

[0036] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0037] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0038] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0039] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth. Example

[0040] Reference Figures 1 to 6 This invention provides a fixed-wing target drone center of gravity testing device. Specifically, this device is a further improvement on the device disclosed in patent application No. 2025114756667, entitled "A Method and Apparatus for Detecting the Aerodynamic Characteristics of a Fixed-Wing Target Drone." The difference between this application and the original technical solution is that the support portion used for fixing and connecting the entire machine in the original technical solution has been replaced with a combination of an upper support member 100 and a lower support member 101. Furthermore, the detailed layout of the multiple pressure measuring chambers C1 to C4, multiple telescopic cylinders S1 to S6, and multiple pressure sensors Y1 and Y2 in this application is shown in "A Method and Apparatus for Detecting the Aerodynamic Characteristics of a Fixed-Wing Target Drone." The specific technical solution of this application is as follows: The lower support 101 is still used to maintain a universal connection with the piston rod in the telescopic cylinder. Both the lower support 101 and the upper support 100 are disc-shaped structures. The lower support 101 is equipped with ball bearings 400 on its periphery, and the upper support 100 is constructed with a groove to cooperate with the ball bearings 400, so that the upper support 100 can rotate smoothly on the lower support 101. A locking member is provided between the upper support 100 and the lower support 101, so that the upper support 100 and the lower support 101 can be locked when necessary, so that the two remain relatively fixed, thus acting as a whole. This allows the entire device to continue the aerodynamic characteristic testing process described in the original scheme. Furthermore, an angle sensor 200 is fixedly installed at the center of the lower support member 101. The input end of the angle sensor 200 is connected to the upper support member 100. The surface of the upper support member 100 is provided with a scale, and the lower support member 101 is equipped with a corresponding pointer to facilitate recording the rotation angle of the upper support member 100 according to the scale. Figure 1 As shown in the image, in this state, the rotation angle of the upper support 100 on the lower support 101 is zero degrees, and the data recorded by the rotation sensor 200 at this position is also zero degrees. Based on the above, such as Figure 8 As shown, during the overall center of gravity test, the entire machine remains fixed on the upper support 100. Specifically, the lift center of the entire machine must be horizontally aligned with the rotation axis of the upper support 100. In other words, under these conditions, when the upper support 100 rotates, if the center of gravity of the entire machine is not at the same horizontal level as the rotation center (i.e., the lift point), the entire machine, along with the entire support, will sway. During rotation, the support and the entire machine will swing towards the side where the center of gravity deviates from the rotation axis. This can be understood as: the greater the mass on one side, the more the machine will sway towards that side. When swaying occurs, the entire machine will tilt towards the side where the center of gravity has shifted, resulting in different load-bearing capacities on the multiple telescopic cylinders, i.e., a force difference. Whether a significant force difference can be detected indicates whether the machine's center of gravity has deviated from the lift point. Based on the above principles, such as Figure 9 as well as Figure 10 As shown, during the test, pressure chambers C1 and C2 are kept connected, and C3 and C4 are kept connected. During the rotation of the whole machine, when the side with the center of gravity shifts passes the front side of the equipment (i.e. the side where telescopic cylinders S3 and S4 are located), the force on S3 and S4 will be greater than the force on S1, S2, S5 and S6. That is, the pressure on C3 and C4 is greater than the pressure on C1 and C2, resulting in a significant data difference between pressure sensors Y1 and Y2. In other words, the detection result of Y2 is significantly greater than the result of Y1. Throughout the test, the detection data from the two pressure sensors and the detection data from the angle sensor 200 are recorded synchronously in real time, so that the pressure data corresponds to the angle data. After the whole machine has rotated one or several times, the angle information corresponding to when Y2 is greater than Y1 is found based on the acquired data. The initial angle minus this angle can determine which side the center of gravity shifts to. Since the initial angle of the angle sensor 200 is consistent with the initial angle of the upper support 100 on the lower support 101, the center of gravity can be visually determined to be on which side of the whole machine based on the scale. Based on the same principle, the same test process can be completed using other sides of the equipment. For example, keep C2, C3, and C4 connected. When the side with the shifted center of gravity rotates to the side where S1 and S2 are located, the force borne by S1 and S2 will inevitably be greater than the pressure borne by other telescopic cylinders. That is, the angle information can be obtained based on the pressure difference between Y1 and Y2. The process is the same as above. Through multiple tests in different directions, the accuracy of the test results can be better guaranteed. Furthermore, such as Figures 4 to 6 As shown, a stator winding 300 is arranged on the lower support member 101, and a rotor winding 301 is arranged on the upper support member 100, so that the lower support member 101 and the upper support member 100 form a motor structure to realize the rotational drive of the upper support member 100 on the lower support member 101. Furthermore, such as Figure 2 , Figure 3 as well as Figure 7 As shown, the locking component includes a pin 501 slidably mounted on the lower support 101. An electric telescopic rod is provided on the lower support 101, and its output end is elastically connected to the pin 501 via a spring plate. Thus, the movement of the pin 501 can be controlled by the electric telescopic rod 500. The upper support 100 is also equipped with a corresponding pin hole 502. When the pin 501 is inserted into the pin hole 502, the upper support 100 is locked. The end of the pin 501 has a roller structure, thereby preventing contact with the upper support. The dry friction between 100, when it is necessary to lock the upper support 100, while the upper support 100 is still rotating, the electric telescopic rod 500 can push the pin head 501 in advance. Through elastic connection, the pin head 501 abuts against the edge of the upper support 100, and the setting of the roller structure does not affect the rotation of the upper support 100. When the pin hole 502 rotates to the position of the pin head 501, the pin head 501 is inserted into the pin hole 502 under the action of elastic force to complete the locking of the upper support 100. Furthermore, when the whole machine is connected to the upper support 100, several support rods are reserved on the machine body. The bottom of the support rods is fixedly connected (by means of clamping, bonding or bolting) to the surface of the upper support 100. The reserved position of the support rod on the machine body is located in the horizontal direction close to the lifting point of the machine body. To ensure lightweight, the support rods are made of carbon fiber, so as to ensure a small diameter while providing sufficient strength to stably support the whole machine.

[0041] This invention combines existing equipment, enabling the entire device to perform both aerodynamic characteristic testing and center of gravity deflection testing without excessive structural increase, thus achieving versatility in device functionality.

[0042] It should be understood that numerous specific implementation decisions can be made during the development of any practical implementation, such as in any engineering or design project. Such development efforts may be complex and time-consuming, but for those skilled in the art who benefit from this disclosure, the development effort will be a routine work of design, manufacturing, and production without requiring much experimentation.

[0043] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A fixed-wing target drone center of gravity testing device, characterized in that: include: The lower support and the upper support rotatably mounted on the lower support, the upper support being used to fix the whole machine under test and to record the rotation angle information relative to the lower support at all times; The base is fixed to the test site and connected to the lower support through multiple horizontally arranged movable parts, which can at least provide feedback on the load-bearing capacity.

2. The fixed-wing target drone center of gravity testing device according to claim 1, characterized in that: A driving force is provided between the lower support member and the upper support member to maintain relative rotation.

3. The fixed-wing target drone center of gravity testing device according to claim 2, characterized in that: The lower support member and the upper support member are respectively provided with a motor stator assembly and a motor rotor assembly.

4. The fixed-wing target drone center of gravity testing device according to claim 1, characterized in that: It also includes an angle detection element, wherein the upper support member has an initial rotation angle relative to the lower support member, and the angle detection element records the deflection angle of the upper support member relative to the lower support member.

5. The fixed-wing target drone center of gravity testing device according to claim 4, characterized in that: The plurality of movable components include a first group and a second group. The movable components of the first group and the movable components of the second group are connected to different sides of the lower support in the horizontal direction. The bearing capacity deviation of the movable components of the first group and the movable components of the second group, as well as the rotation angle of the upper support, are obtained synchronously.

6. The fixed-wing target drone center of gravity testing device according to claim 4, characterized in that: The angle detection element includes a rotation sensor disposed between the lower support and the upper support.

7. The fixed-wing target drone center of gravity testing device according to claim 1, characterized in that: It also includes a locking member, which restricts the relative movement between the lower support member and the upper support member.

8. The fixed-wing target drone center of gravity testing device according to claim 7, characterized in that: The locking member includes a pin head that is movably disposed on the lower support member, and the upper support member is provided with a pin hole corresponding to the pin head.

9. The fixed-wing target drone center of gravity testing device according to claim 8, characterized in that: The lower support member is provided with a pushing end, and the pin head is slidably disposed on the lower support member and maintains an elastic connection with the pushing end.

10. The fixed-wing target drone center of gravity testing device according to claim 1, characterized in that: The upper support member is provided with a corner scale, and the lower support member is provided with an indicator end that points to the corner scale.

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