Conical variable body aircraft toroidal servo loading device

Abstract

The application discloses a conical variable body aircraft annular servo loading device, and belongs to the technical field of flight wing surface ground simulation test loading in aerospace equipment. The application solves the problem that the existing loading device cannot continuously load corresponding loads with the deformation of a machine body. The application comprises a first support, a second support and a plurality of loading devices, wherein the first support comprises a first base and a cylindrical support fixed on the first base, a machine body to be measured is arranged in the cylindrical support, one end of the machine body to be measured is fixed on the second support, and the plurality of loading devices are distributed in the circumferential direction of the cylindrical support. Through the loading device with the force feedback control function, the time and the value of the load acting on the machine body to be measured are controlled, so that the load strength adjustment space is larger, the load is more stable and accurate, and the load environment simulation is more comprehensive.

Description

Technical Field

[0001] This invention relates to a ring-shaped dynamic loading device for a conical morphing aircraft, belonging to the field of loading technology for ground simulation tests of flight wing surfaces in aerospace equipment. Background Technology

[0002] A morphing aircraft is a novel concept of a multi-purpose, multi-form aircraft that can adaptively transform according to the needs of the flight environment, flight profile, and combat mission, making its flight path, altitude, and speed maneuverable and flexible, so as to give full play to the aircraft's optimal flight performance.

[0003] Throughout its service life, an aircraft must withstand various severe external loads. Ensuring good flight performance under these harsh loads is crucial. Since it is difficult to monitor the condition of the aircraft's external surface in real time during flight, it is necessary to conduct ground tests on the ground using the external loads during flight as a standard to test the aircraft's flight performance in the corresponding environment, especially for the structural components of morphing aircraft.

[0004] Most existing loading devices are test and verification devices for fixed-form aircraft, which can verify the static performance of the aircraft in various states. However, there is a lack of test devices that continuously load the aircraft as it deforms, making it impossible to effectively verify the deformation performance of morphing aircraft under external loads. Therefore, there is an urgent need for a dynamic loading test device suitable for morphing aircraft to better guide the structural design of morphing aircraft. Summary of the Invention

[0005] The present invention aims to solve the above-mentioned technical problems and provides a ring-shaped dynamic loading device for a conical morphing aircraft.

[0006] The technical solution adopted by the present invention to solve the above-mentioned technical problems is as follows:

[0007] A ring-shaped dynamic loading device for a conical morphing aircraft includes a first support, a second support, and several loading devices. The first support includes a first base and a cylindrical support fixed to the first base.

[0008] The device under test is installed inside a cylindrical support, and one end of the device under test is fixed to a second support.

[0009] Several loading devices are distributed circumferentially along the cylindrical support.

[0010] Each loading device includes a servo electric cylinder, a cylinder support frame, a guide connector, a push rod, a support rod, a main lever support, two secondary lever supports, and several ceramic bearings. The servo electric cylinder is fixedly mounted on the cylindrical support via the cylinder support frame. The guide connector is fixedly mounted on the movable end of the servo electric cylinder. The push rod is radially inserted into the side wall of the cylindrical support. One end of the push rod is coaxial and movably inserted into the guide connector. A pressure sensor is installed between one end of the push rod and the guide connector. One end of the support rod is coaxially inserted into the other end of the push rod. The main lever support is rotatably mounted on the other end of the support rod. The two secondary lever supports are parallel and rotatably mounted on the two ends of the main lever support. Several ceramic bearings are rotatably mounted on each secondary lever support along its length.

[0011] Furthermore, a second groove with an upward opening is provided on the push rod, and a buffer spring is provided between one end of the support rod and the bottom of the second groove.

[0012] Furthermore, a limiting cap is fixed to the other end of the push rod, and the support rod has a stepped rod structure, with its large diameter section located in the second groove and its small diameter section extending out of the push rod through the limiting cap.

[0013] Furthermore, the sidewall of the guide connector is provided with a through hole, and the through hole is arranged opposite to the pressure sensor.

[0014] Furthermore, the top of the first base is fixed with two opposing support seats, and the cylindrical bracket is horizontally arranged and fixed between the two support seats.

[0015] Furthermore, the cylindrical support has several first through holes machined along its circumference, and the top of the first base has several second through holes machined. The push rod is inserted into the first through holes, and the loading device located below the cylindrical support passes through the second through holes.

[0016] Furthermore, several first through holes are distributed in two groups along the axial direction of the cylindrical support, wherein several first through holes in each group are arranged along the circumference of the cylindrical support.

[0017] Furthermore, the first base includes a first frame and a horizontal support plate fixed on the first frame, and a second through hole is formed on the horizontal support plate.

[0018] Furthermore, the second support includes a second frame and a vertical support plate fixed on the second frame. The vertical support plate has a horizontally opened observation hole, and the observation hole is coaxially arranged with the machine body under test.

[0019] Furthermore, the test unit and the cylindrical support are arranged coaxially.

[0020] Compared with the prior art, the present invention has the following advantages:

[0021] By setting up several loading devices, the loading devices are modularly designed. Different loading layouts or different numbers of loading devices can be designed according to the deformation form of the morphing aircraft to adapt to the deformation direction of the test body. This makes it more adaptable, interchangeable, and easier to install.

[0022] The circular dynamic loading device for conical morphing aircraft of the present invention controls the time and magnitude of the load applied to the test body through a loading device with force feedback control function, so as to make the load intensity adjustment space larger, the application more stable and accurate, and the load environment simulation more comprehensive.

[0023] The annular follow-force loading device for conical morphing aircraft of the present invention uses a ceramic bearing as the part that contacts the test body. During the follow-force loading process, it can convert the sliding friction at contact into rolling friction, reduce the influence of friction during loading, and make the loading more reliable and accurate. Attached Figure Description

[0024] Figure 1 This is a three-dimensional structural schematic diagram of the annular follow-force loading device for the conical morphing aircraft of the present invention;

[0025] Figure 2 This is a three-dimensional structural diagram of the first support.

[0026] Figure 3 This is a schematic diagram of the three-dimensional structure of the second support.

[0027] Figure 4 This is a three-dimensional structural diagram of the loading device;

[0028] Figure 5 This is a cross-sectional schematic diagram of the loading device (servo cylinder and cylinder support frame are not shown).

[0029] In the picture:

[0030] 1. First bracket; 1-1. First base; 1-11. Second through hole; 1-12. First frame; 1-13. Horizontal bearing plate; 1-2. Cylindrical bracket; 1-21. First through hole; 1-3. Support seat; 2. Second bracket; 2-1. Second frame; 2-2. Vertical bearing plate; 2-21. Observation hole; 3. Loading device; 3-1. Servo electric cylinder; 3-2. Electric cylinder support frame; 3-3. Guide connector; 3-31. Through hole; 3-4. Push rod; 3-5. Support rod; 3-6. Main lever bracket; 3-7. Secondary lever bracket; 3-8. Ceramic bearing; 3-9. Pressure sensor; 3-10. Buffer spring; 3-11. Limit cover. Detailed Implementation

[0031] Specific implementation method one: Combining Figures 1-5This description of embodiments provides a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0032] It should be noted that the descriptions of "front," "rear," "left," "right," "inner," "outer," "left side," "right side," "upper part," "lower part," "top," and "bottom" in this invention are defined based on the orientation or positional relationships shown in the accompanying drawings. They are merely for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the described structure must be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0033] In the description of this invention, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0034] A ring-shaped dynamic loading device for a conical morphing aircraft includes a first support 1, a second support 2, and several loading devices 3. The first support 1 includes a first base 1-1 and a cylindrical support 1-2 fixedly mounted on the first base 1-1.

[0035] The device under test 4 is inserted into the cylindrical bracket 1-2, and one end of the device under test 4 is fixed to the second bracket 2.

[0036] Several loading devices 3 are distributed circumferentially along the cylindrical support 1-2.

[0037] Each loading device 3 includes a servo electric cylinder 3-1, an electric cylinder support frame 3-2, a guide connector 3-3, a push rod 3-4, a support rod 3-5, a main lever support 3-6, two auxiliary lever supports 3-7, and several ceramic bearings 3-8. The servo electric cylinder 3-1 is fixedly mounted on the cylindrical support 1-2 via the electric cylinder support frame 3-2. The guide connector 3-3 is fixedly mounted on the movable end of the servo electric cylinder 3-1. The push rod 3-4 is radially inserted into the side wall of the cylindrical support 1-2. One end of the push rod 3-4 is coaxially and movably inserted into the guide connector 3-3. A pressure sensor 3-9 is installed between one end of the push rod 3-4 and the guide connector 3-3. One end of the support rod 3-5 is coaxially inserted into the other end of the push rod 3-4. The main lever bracket 3-6 is rotatably installed at the other end of the support rod 3-5. Two secondary lever brackets 3-7 are parallel and rotatably installed at both ends of the main lever bracket 3-6. Several ceramic bearings 3-8 are rotatably installed on each secondary lever bracket 3-7 along its length.

[0038] The first support 1 and the second support 2 together form a support frame, which is used to support the loading device 3 and the test body 4, respectively.

[0039] The end of the test unit 4 that is fixed on the second bracket 2 is the rear end.

[0040] The test body 4 is the nose cone portion of a morphing aircraft, which is a hollow rotating structure with several screw holes at the rear end for fixing to the second base. The accompanying drawings in this specification only illustrate the test body 4 using a variable-diameter rotating structure; the actual shape of the test body 4 is based on the nose cone structure of the morphing aircraft being tested.

[0041] By setting up several loading devices 3, the loading devices 3 are modularly designed. Different loading layouts or different numbers of loading devices 3 can be designed according to the deformation form of the variant aircraft to adapt to the deformation direction of the test body 4. This makes it more adaptable, interchangeable, and easier to install.

[0042] The guide connector 3-3 has a first groove with an upward opening, and the lower part of the push rod 3-4 and the pressure sensor 3-9 are both located in the first groove.

[0043] By incorporating pressure sensor 3-9, the loading device 3 acquires force feedback control functionality. Specifically, pressure sensor 3-9 is fixedly mounted between one end of push rod 3-4 and guide connector 3-3.

[0044] The annular dynamic loading device for conical morphing aircraft of the present invention controls the time and magnitude of the load acting on the test body 4 through the loading device 3 with force feedback control function, so that the load intensity adjustment space is larger, the application is more stable and accurate, and the load environment simulation is more comprehensive.

[0045] The annular follow-force loading device for conical morphing aircraft of the present invention uses ceramic bearings 3-8 as the parts that contact the test body 4. During the follow-force loading process, it can convert the sliding friction at contact into rolling friction, reduce the influence of friction during loading, and make the loading more reliable and accurate.

[0046] The ceramic bearings 3-8 are preferably eight in number, and are symmetrically mounted on two secondary lever supports 3-7 via shaft systems.

[0047] Two separate lever supports are connected to the bifurcated structure of the main lever support 3-6 by pins.

[0048] The servo electric cylinder 3-1 and the electric cylinder support frame 3-2 are fixedly connected by bolts.

[0049] The electric cylinder support frame 3-2 has a U-shaped structure, with its open end fixedly connected to the cylindrical support 1-2 and its closed end fixedly connected to the servo electric cylinder 3-1.

[0050] This invention enables the load acting on a conical morphing aircraft to remain constant as the aircraft deforms, and enables the loading device 3 to follow the deformation of the test body 4 with dynamic loading. This dynamic loading platform can be designed with different numbers of loading modules to perform dynamic loading on a ring-shaped morphing aircraft as needed.

[0051] A second groove with an upward opening is provided on the push rod 3-4, and a buffer spring 3-10 is installed between one end of the support rod 3-5 and the bottom of the second groove. This design, by including the buffer spring 3-10, provides a buffering effect when the loading device 3 contacts the test body 4, reducing the impact force during contact and thus protecting the test body 4 and the loading device 3. One end of the buffer spring 3-10 is fixed to the bottom of the second groove, and the other end contacts one end of the support rod 3-5.

[0052] The other end of the push rod 3-4 is fixed with a limiting cover 3-11. The support rod 3-5 has a stepped rod structure, with its large diameter section located in the second groove and its small diameter section extending out of the push rod 3-4 through the limiting cover 3-11.

[0053] The guide connector 3-3 has a through hole 3-31 on its side wall, and the through hole 3-31 is arranged opposite to the pressure sensor 3-9.

[0054] Two opposing support seats 1-3 are fixedly mounted on the top of the first base 1-1, and a cylindrical bracket 1-2 is horizontally arranged and fixed between the two support seats 1-3. This design, with the two opposing support seats 1-3, provides better support for the cylindrical bracket 1-2. The outer surface of the cylindrical bracket 1-2 can rest on the top surface of the support seats 1-3. Each support seat 1-3 is a right-angled triangle, and the cylindrical bracket 1-2 is fixed to the inclined surface of the support seat 1-3 with bolts. The right-angled surfaces of the support seats 1-3 are fixed to the first base 1-1 with bolts.

[0055] The cylindrical support 1-2 has several first through holes 1-21 machined along its circumference, and the top of the first base 1-1 has several second through holes 1-11 machined. The push rod 3-4 is inserted into the corresponding first through holes 1-21, and the loading device 3, located below the cylindrical support 1-2, passes through the second through holes 1-11. This design allows for easy displacement of the push rod 3-4 in the radial direction of the cylindrical support 1-2 by opening the first through holes 1-21. The second through holes 1-11 serve as clearance holes, facilitating the passage of the loading device 3 below the cylindrical support 1-2.

[0056] Several first through holes 1-21 are distributed in two groups along the axial direction of the cylindrical support 1-2, wherein several first through holes 1-21 in each group are arranged along the circumference of the cylindrical support 1-2. With this design, it is preferable that several first through holes 1-21 in each group are evenly distributed along the circumference of the cylindrical support 1-2.

[0057] The first base 1-1 includes a first frame 1-12 and a horizontal support plate 1-13 fixed on the first frame 1-12, and a second through hole 1-11 is formed on the horizontal support plate 1-13. With this design, the first frame 1-12 is a frame structure assembled from square tubes, which ensures structural stability while achieving lightweight.

[0058] The second support 2 includes a second frame 2-1 and a vertical support plate 2-2 fixedly mounted on the second frame 2-1. The vertical support plate 2-2 has a horizontally oriented observation hole 2-21, which is coaxially arranged with the device under test 4. With this design, the vertical support plate 2-2 has several screw holes machined on it for mounting the device under test 4. These screw holes are evenly distributed around the observation hole 2-21. By providing the observation hole 2-21, the interior of the device under test 4 can be observed from the back of the second support 2. The second frame 2-1 is a frame structure assembled from square tubing, ensuring structural stability while achieving lightweight design.

[0059] The test body 4 is arranged coaxially with the cylindrical support 1-2.

[0060] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. A ring-shaped dynamic loading device for a conical morphing aircraft, characterized in that: It includes a first support (1), a second support (2), and several loading devices (3), wherein the first support (1) includes a first base (1-1) and a cylindrical support (1-2) fixed on the first base (1-1). The test body (4) is inserted into the cylindrical bracket (1-2), and one end of the test body (4) is fixed on the second bracket (2). Several loading devices (3) are distributed circumferentially along the cylindrical support (1-2). Each loading device (3) includes a servo electric cylinder (3-1), an electric cylinder support frame (3-2), a guide connector (3-3), a push rod (3-4), a support rod (3-5), a main lever support (3-6), two secondary lever supports (3-7), and several ceramic bearings (3-8). The servo electric cylinder (3-1) is fixedly mounted on the cylindrical support (1-2) via the electric cylinder support frame (3-2). The guide connector (3-3) is fixedly mounted on the movable end of the servo electric cylinder (3-1). The push rod (3-4) is radially inserted into the side wall of the cylindrical support (1-2). One end of the push rod (3-4) is coaxially and movably inserted into the guide connector (3-3). A pressure sensor (3-9) is installed between one end of the push rod (3-4) and the guide connector (3-3). One end of the support rod (3-5) is coaxially inserted into the other end of the push rod (3-4). The main lever bracket (3-6) is rotatably installed at the other end of the support rod (3-5). Two secondary lever brackets (3-7) are parallel and rotatably installed at both ends of the main lever bracket (3-6). Each secondary lever bracket (3-7) is rotatably installed with several ceramic bearings (3-8) along its length.

2. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The push rod (3-4) has a second groove with the opening facing upwards, and a buffer spring (3-10) is provided between one end of the support rod (3-5) and the bottom of the second groove.

3. The annular follow-force loading device for a conical morphing aircraft according to claim 2, characterized in that: The other end of the push rod (3-4) is fixed with a limiting cover (3-11). The support rod (3-5) has a stepped rod structure, with its large diameter section located in the second groove and its small diameter section extending out of the push rod (3-4) through the limiting cover (3-11).

4. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The guide connector (3-3) has a through hole (3-31) on its side wall, and the through hole (3-31) is arranged opposite to the pressure sensor (3-9).

5. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The top of the first base (1-1) is fixed with two oppositely arranged support seats (1-3), and the cylindrical bracket (1-2) is horizontally arranged and fixed between the two support seats (1-3).

6. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The cylindrical support (1-2) has several first through holes (1-21) machined along its circumference, and the top of the first base (1-1) has several second through holes (1-11). The push rod (3-4) is inserted into the first through hole (1-21) respectively, and the loading device (3) located below the cylindrical support (1-2) is set through the second through hole (1-11).

7. The annular follow-force loading device for a conical morphing aircraft according to claim 6, characterized in that: Several first through holes (1-21) are distributed in two groups along the axial direction of the cylindrical support (1-2), wherein several first through holes (1-21) in each group are arranged circumferentially along the cylindrical support (1-2).

8. The annular follow-force loading device for a conical morphing aircraft according to claim 6, characterized in that: The first base (1-1) includes a first frame (1-12) and a horizontal support plate (1-13) fixed on the first frame (1-12), and a second through hole (1-11) is formed on the horizontal support plate (1-13).

9. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The second support (2) includes a second frame (2-1) and a vertical support plate (2-2) fixed on the second frame (2-1). The vertical support plate (2-2) has a horizontal observation hole (2-21) and the observation hole (2-21) is coaxially arranged with the body (4) to be tested.

10. The annular follow-force loading device for a conical morphing aircraft according to claim 1, characterized in that: The test body (4) and the cylindrical support (1-2) are arranged coaxially.

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