A spatial force loading device for a multi-component force test bench of an aero-engine

Abstract

The present invention belongs to the field of aero-engines, and relates to the design technology of an engine multi-component force test bench calibration device, and discloses a spatial force loading device for an aero-engine multi-component force test bench, including a horizontal mounting frame, a mounting plate, a circumferential angle adjustment mechanism, a radial position adjustment mechanism, a loading steel cable, and a loading frame. The mounting plate is fixed on the horizontal mounting frame; the circumferential angle adjustment mechanism is rotatably arranged at the center of the mounting plate, and a radial position adjustment mechanism is fixed on the circumferential angle adjustment mechanism; one end of the loading steel cable is arranged at the center of the circumferential angle adjustment mechanism, and the other end is fixed on the loading frame after passing through the radial position adjustment mechanism. The spatial force loading device of the present invention can load a certain calibration spatial angle and preload force for the calibration of the multi-component force test bench, and when a flexible cable is used for force transmission, the loading accuracy of the spatial multi-component force is controlled to be less than 0.1° under the premise of ensuring the accuracy of the spatial position information of the calibration device, so as to improve the calibration accuracy of the multi-component force test bench.

Description

Technical Field

[0001] The invention belongs to the field of aero-engines, relates to a design technology of an engine multi-component force bench calibration device, and specifically relates to a spatial force loading device of an aero-engine multi-component force bench. Background Art

[0002] In order to accurately evaluate the performance of aircraft engine nozzles and determine the flight force of the engine, it is necessary to use ground equipment (such as test benches) to conduct engine calibration tests to establish a mathematical model of flight force and measurable physical quantities of the engine. Among them, the performance of the multi-component force test bench, as an important ground equipment, directly affects the accuracy of the flight force, and with the development of aircraft engine technology, the high-precision requirements of the multi-component force test bench are also facing new challenges.

[0003] The purpose of calibrating a multi-component force test bench is to remove or minimize the influence of the inherent characteristics of ground equipment, such as the coupling effect between force measuring components in ground equipment, the elastic force of flexible components, the drag of the engine casing, and the systematic error of the transmission characteristics of the measuring sensor, etc. Therefore, the calibration accuracy of the multi-component force test bench will directly affect the test accuracy of the aircraft engine. At present, multi-component force test benches are widely calibrated by in-situ loading and center loading. Center loading is a slower and less convenient calibration method than in-situ loading. It is mainly used to provide a center correction curve for in-situ loading calibration, or occasionally verify the accuracy of the in-situ loading calibration method on a special test bench, so it can accurately simulate the actual engine test situation.

[0004] At present, the existing central loading devices mostly use rigid connections. The problem caused by this structure is that the lateral bending moment of the force transmission device will cause secondary interference to the multi-component force test bench, which will increase the difficulty of decoupling the multi-component force test bench. It has been verified that even if the two ends of the force device are connected by spherical hinges, the nonlinear friction of the hinge caused by the axial load cannot be eliminated.

[0005] Therefore, there is an urgent need for a spatial force loading device suitable for an aircraft engine multi-component force test bench to ensure that the calibration accuracy of the multi-component force test bench is improved while accurately providing the spatial position information of the calibration device. Summary of the invention

[0006] In order to solve the technical problem that the existing spatial force loading device is difficult to provide accurate spatial position information for the multi-component force test bench, resulting in low calibration accuracy, the present invention provides a spatial force loading device for an aircraft engine multi-component force test bench, the spatial force loading device comprising a horizontal mounting frame, a mounting plate, a circumferential angle adjustment mechanism, a radial position adjustment mechanism, a loading steel cable and a loading frame.

[0007] Wherein, the mounting plate is fixed in the vertical direction of the horizontal mounting frame;

[0008] The circumferential angle adjustment mechanism is rotatably arranged at the center of the mounting plate, and a radial position adjustment mechanism is fixed on the circumferential angle adjustment mechanism;

[0009] One end of the loading cable is arranged at the center of the circumferential angle adjustment mechanism, and the other end passes through the radial position adjustment mechanism and is fixed on the loading frame;

[0010] The circumferential angle adjustment mechanism cooperates with the radial position adjustment mechanism to adjust the angle of the loading cable, thereby providing a calibration space angle for the multi-component force stand located below the loading frame.

[0011] In an optional embodiment of the circumferential angle adjustment mechanism, the circumferential angle adjustment mechanism comprises a rotating assembly, a driving assembly, an adapter plate and a fixing portion. The rotating assembly is arranged at the center of the mounting plate via a tapered bearing, the rotating assembly is connected to the driving assembly, the adapter plate is fixed on the rotating assembly, the fixing portion is arranged on the adapter plate, and the loading steel cable is arranged on the fixing portion.

[0012] In an optional embodiment of the rotating assembly and the driving assembly, the rotating assembly includes a first gear and an axial rotating flange, the axial rotating flange is arranged on the fixed flange of the mounting plate via a tapered bearing, and the first gear and the adapter plate are fixed to the axial rotating flange.

[0013] The driving assembly includes a second gear and a circumferential radial servo motor, wherein an output shaft of the circumferential radial servo motor is connected to the second gear, and the second gear is meshed with the first gear.

[0014] In an optional embodiment of the adapter plate, the adapter plate includes a first adapter plate and a second adapter plate, the first adapter plate and the second adapter plate are symmetrically arranged on the rotating assembly, the fixing portion is fixed to the back sides of the first adapter plate and the second adapter plate, and a channel for the loading steel cable to pass through is provided between the first adapter plate and the second adapter plate.

[0015] In an improved embodiment of the above-mentioned spatial force loading device, the spatial force loading device also includes a preload adjustment mechanism, which is arranged on a fixed portion on the back of the circumferential angle adjustment mechanism, one end of the loading steel cable is arranged on the preload adjustment mechanism, and the other end passes through the center of the circumferential angle adjustment mechanism and the radial position adjustment mechanism in sequence and then is connected to the loading frame, and the preload adjustment mechanism is used to adjust the force of the loading steel cable to provide a calibrated preload for the multi-component force stand located below the loading frame.

[0016] In an optional embodiment of the preload force adjustment mechanism, the preload force adjustment mechanism includes a first fixed bracket, a second fixed bracket, a wire winding wheel and a wire winding servo motor, the first fixed bracket and the second fixed bracket are fixed on the fixed part, the wire winding wheel is arranged between the first fixed bracket and the second fixed bracket via a rotating shaft, the loading steel cable is wound on the wire winding wheel, and the rotating shaft is connected to the output shaft of the wire winding servo motor.

[0017] In another improved embodiment of the above-mentioned spatial force loading device, the spatial force loading device further comprises a displacement sensor and a calibration force sensor. The displacement sensor is arranged on the mounting plate and is used to measure the displacement change of the loading steel cable to calculate the calibration spatial angle. One end of the calibration force sensor is connected to the loading steel cable and the other end is connected to the loading frame, and the calibration force sensor is used to measure the calibration preload force.

[0018] In an optional embodiment of the calibration force sensor, two ends of the calibration force sensor are respectively connected to the loading cable and the loading frame via a ball joint.

[0019] In an optional embodiment of the radial position adjustment mechanism, the radial position adjustment mechanism includes a first radial displacement mechanism and a second radial displacement mechanism which are symmetrically arranged on the circumferential angle adjustment mechanism and move synchronously, a guide cylinder is provided between the sliders of the first radial displacement mechanism and the second radial displacement mechanism, and the loading steel cable is in contact with the surface of the guide cylinder.

[0020] In an optional embodiment of the first radial displacement mechanism and the second radial displacement mechanism, the first radial displacement mechanism and the second radial displacement mechanism are the same, and both include a screw fixing part, a screw, a slider and a radial servo motor, the screw fixing part is fixed to the circumferential angle adjustment mechanism, the screw fixing part is provided with the screw, the slider is provided on the screw, and the output end of the radial servo motor is connected to the screw.

[0021] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: the spatial force loading device of the aircraft engine multi-component force test bench of the present invention, by designing a circumferential angle adjustment mechanism and a radial position adjustment mechanism, can load a certain calibration spatial angle for the calibration of the multi-component force test bench; at the same time, by adding a preload adjustment mechanism to the circumferential angle adjustment mechanism, a certain size of calibration preload can also be loaded for the calibration of the multi-component force test bench, so that when a flexible cable is used for force transmission, the loading accuracy of the spatial multi-component force is controlled to be less than 0.1° while ensuring the accuracy of the spatial position information of the calibration device, thereby improving the calibration accuracy of the multi-component force test bench. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 A three-dimensional diagram of a space force loading device for a multi-component force test bench for an aircraft engine provided by an embodiment of the present invention;

[0024] Figure 2 A schematic diagram of a circumferential angle adjustment mechanism and a preload adjustment mechanism in an embodiment of the present invention;

[0025] Figure 3 is a schematic diagram of a radial position adjustment mechanism in an embodiment of the present invention;

[0026] Figure 4 A schematic diagram of a loading frame in an embodiment of the present invention;

[0027] Among them, 1, horizontal mounting frame; 2, mounting plate; 201, fixing flange; 3, circumferential angle adjustment mechanism; 301, first gear; 302, axial rotation flange; 303, fixing part; 304, second gear; 305, circumferential radial servo motor; 306, first adapter plate; 307, second adapter plate; 308, channel; 4, radial position adjustment mechanism; 401, guide cylinder; 402, screw fixing part; 403, screw; 404, slider; 405, radial Servo motor; 5. Loading steel cable; 501. Ball joint; 6. Loading frame; 601. First column; 602. Second column; 603. Third column; 604. Fourth column; 605. Loading fixed plate; 606. First loading beam; 607. Second loading beam; 608. Third loading beam; 7. Preload force adjustment mechanism; 701. First fixed bracket; 702. Second fixed bracket; 703. Wire winding wheel; 704. Wire winding servo motor; 8. Calibration force sensor. DETAILED DESCRIPTION

[0028] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0029] The following describes the implementation methods of the present application through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0030] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the invention.

[0031] In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, features defined as "first", "second", etc. may explicitly or implicitly include one or more features. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more.

[0032] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present disclosure. The drawings only show components related to the present disclosure rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0033] The embodiment of the present invention discloses a spatial force loading device for an aircraft engine multi-component force test bench, see Figure 1 As shown, the spatial force loading device includes a horizontal mounting frame 1, a mounting plate 2, a circumferential angle adjustment mechanism 3, a radial position adjustment mechanism 4, a loading steel cable 5 and a loading frame 6.

[0034] Among them, see Figure 1As shown, the mounting plate 2 is fixed in the vertical direction of the horizontal mounting frame 1, the circumferential angle adjustment mechanism 3 is rotatably arranged at the center of the mounting plate 2, and a radial position adjustment mechanism 4 is fixed on the circumferential angle adjustment mechanism 3. One end of the loading cable 5 is arranged at the center of the circumferential angle adjustment mechanism 3, and the other end passes through the radial position adjustment mechanism 4 and is fixed on the loading frame 6.

[0035] When the spatial force loading device is used, the angle of the loading cable 5 is adjusted by the circumferential angle adjustment mechanism 3 and the radial position adjustment mechanism 4, so as to provide a calibration spatial angle for the multi-component force stand located below the loading frame 6. Specifically, a certain circumferential angle can be generated by rotating the circumferential angle adjustment mechanism 3, and a certain radial angle can be generated by moving the radial position adjustment mechanism 4 up and down. The superposition of the circumferential angle and the radial angle will form the required calibration spatial angle.

[0036] Alternatively, see Figure 1 As shown, the horizontal mounting frame 1 can be placed on a horizontal ground, and the mounting plate 2 is fixed in the vertical direction of the horizontal mounting frame 1. At the same time, in order to maintain the stability of the mounting plate 2, the horizontal mounting frame 1 can be composed of a bottom frame, a vertical frame and an oblique support, the vertical frame is welded to the bottom frame, one end of the oblique support is welded to the bottom frame, and the other end is welded to the upper part of the vertical frame, and the mounting plate 2 is fixed in the vertical frame.

[0037] See also Figure 1 As shown, the mounting plate 2 can be made of a square steel plate with a circular hole processed in the center. A fixing flange 201 is arranged on the circular hole, and a tapered bearing is arranged between the fixing flange 201 and the circumferential angle adjustment mechanism 3. The rotation of the circumferential angle adjustment mechanism 3 on the mounting plate 2 is realized by the tapered bearing.

[0038] In an optional embodiment of the circumferential angle adjustment mechanism 3, the circumferential angle adjustment mechanism 3 includes a rotating assembly, a driving assembly, an adapter plate and a fixing portion 303. The rotating assembly is arranged at the center of the mounting plate 2 via a tapered bearing, the rotating assembly is connected to the driving assembly, the adapter plate is fixed to the rotating assembly, the fixing portion 303 is arranged on the adapter plate, and the loading steel cable 5 is arranged on the fixing portion 303.

[0039] In the embodiment of the present invention, the purpose of the fixing part 303 is to fix the loading cable 5, and to ensure that the center of the loading cable 5 coincides with the center of the circumferential angle adjustment mechanism 3 when the device is in the initial position. The fixing part 303 in the present invention can be a fixing seat, a fixing ear, a fixing ring or a fixing hook, which can be set on the back side of the adapter plate or on the front side. In the specific embodiment of the present invention, in order to avoid the interference of the fixing part 303 on the radial position adjustment mechanism 4, see Figure 2 As shown, the present invention preferably uses a fixing seat as the fixing portion 303 and arranges it on the back side of the adapter plate (ie, the side of the adapter plate away from the loading frame 6).

[0040] In an alternative embodiment of the rotating assembly and the driving assembly, see Figure 2 As shown, the rotating assembly includes a first gear 301 and an axial rotating flange 302. The axial rotating flange 302 is arranged on the fixing flange 201 of the mounting plate 2 via a tapered bearing. The first gear 301 and the adapter plate are fixed on the axial rotating flange 302. Figure 2 As shown, the gear surface of the first gear 301 is located on the back side of the adapter plate.

[0041] The driving assembly includes a second gear 304 and a circumferential radial servo motor 305, the output shaft of the circumferential radial servo motor 305 is connected to the second gear 304, the second gear 304 is meshed with the first gear 301, and the second gear 304 and the circumferential radial servo motor 305 are also located on the back of the adapter plate. The rotational torque of the circumferential radial servo motor 305 can be transmitted to the first gear 301 through the second gear 304, thereby realizing the controllable rotation of the circumferential angle adjustment mechanism 3 on the mounting plate 2.

[0042] In the present invention, the adapter plate can be set as one plate or multiple plates, as long as the fixing portion 303 and the radial position adjustment mechanism 4 can be set. Figure 2 and Figure 3 As shown, the adapter plate includes a first adapter plate 306 and a second adapter plate 307, the first adapter plate 306 and the second adapter plate 307 are symmetrically arranged on the rotating assembly, the fixing portion 303 is fixed to the back of the first adapter plate 306 and the second adapter plate 307, and a channel 308 for the loading cable 5 to pass through is provided between the first adapter plate 306 and the second adapter plate 307, and the setting of the channel 308 can make the loading cable 5 change position in the radial direction. In a specific implementation, the first adapter plate 306 and the second adapter plate 307 can be arc plates, and the first adapter plate 306 and the second adapter plate 307 are mirror-symmetrically arranged along the diameter of the axial rotating flange 302.

[0043] In an optional embodiment of the radial position adjustment mechanism 4, see Figure 3As shown, the radial position adjustment mechanism 4 includes a first radial displacement mechanism and a second radial displacement mechanism symmetrically arranged on the circumferential angle adjustment mechanism 3 and moving synchronously, a guide cylinder 401 is provided between the sliders of the first radial displacement mechanism and the second radial displacement mechanism, and the loading steel cable 5 is in surface contact with the guide cylinder 401. In specific implementation, the position of the loading steel cable 5 passing through the radial position adjustment mechanism 4 in the radial direction can be changed by the synchronous movement of the first radial displacement mechanism and the second radial displacement mechanism, thereby generating radial displacement, and the function of the guide cylinder 401 is to guide the loading steel cable 5 through its rotation when the first radial displacement mechanism and the second radial displacement mechanism move.

[0044] In an optional embodiment of the first radial displacement mechanism and the second radial displacement mechanism, see Figure 3 As shown, the first radial displacement mechanism is the same as the second radial displacement mechanism, and both include a screw fixing portion 402, a screw 403, a slider 404 and a radial servo motor 405. The screw fixing portion 402 is fixed to the circumferential angle adjustment mechanism 3, the screw fixing portion 402 is provided with the screw 403, the screw 403 is provided with the slider 404, and the output end of the radial servo motor 405 is connected to the screw 403. Among them, the radial servo motor 405 is coaxially connected to the screw 403, and the rotational motion of the radial servo motor 405 is converted into the linear motion of the first / second radial displacement mechanism through the screw 403 and the slider 404; the guide cylinder 401 is fixed between the two sliders 404, and the positions of the two sliders 404 are changed synchronously through the synchronous movement of the two radial servo motors 405, so as to ensure that the guide cylinder 401 moves along the center line of the axial rotating flange 302, and at the same time, combined with the circular motion of the circumferential angle adjustment mechanism 3, the loading cable 5 is made to move in a conical shape around the loading point of the loading frame 6, thereby realizing loading of different calibrated space angles.

[0045] It should be noted that the radial position adjustment mechanism 4 can also be implemented using a radial displacement mechanism and a guide cylinder 401 , as long as it is ensured that the loading cable 5 can axially rotate along the center line of the flange 302 .

[0046] In an improved embodiment of the above-mentioned spatial force loading device, the spatial force loading device also includes a preload adjustment mechanism 7, which is arranged on the fixed portion 303 on the back of the circumferential angle adjustment mechanism 3, one end of the loading steel cable 5 is arranged on the preload adjustment mechanism 7, and the other end passes through the center of the circumferential angle adjustment mechanism 3 and the radial position adjustment mechanism 4 in sequence and then is connected to the loading frame 6, and the preload adjustment mechanism 7 is used to adjust the force of the loading steel cable 5 to provide a calibrated preload for the multi-component force stand located below the loading frame 6.

[0047] In an optional embodiment of the preload force adjustment mechanism 7, see Figure 2 The preload adjustment mechanism 7 includes a first fixed bracket 701, a second fixed bracket 702, a wire winding wheel 703 and a wire winding servo motor 704. The first fixed bracket 701 and the second fixed bracket 702 are fixed on the fixed part 303. The wire winding wheel 703 is arranged between the first fixed bracket 701 and the second fixed bracket 702 via a rotating shaft. The loading steel cable 5 is wound on the wire winding wheel 703. The rotating shaft is connected to the output shaft of the wire winding servo motor 704. The rotational torque of the wire winding servo motor 704 applies force to the loading steel cable 5, thereby loading the multi-component force gantry with a calibrated preload.

[0048] In another improved embodiment of the above-mentioned spatial force loading device, the spatial force loading device further comprises a displacement sensor and a calibration force sensor 8. The displacement sensor is arranged on the mounting plate 2, and is used to measure the displacement change of the loading steel cable 5 to calculate the calibration spatial angle. One end of the calibration force sensor 8 is connected to the loading steel cable 5, and the other end is connected to the loading frame 6, and the calibration force sensor 8 is used to measure the calibration preload force.

[0049] In an alternative embodiment of calibrating the force sensor 8, see Figure 1 and Figure 4 As shown, two ends of the calibration force sensor 8 are respectively connected to the loading cable 5 and the loading frame 6 via a ball joint 501 .

[0050] In an alternative embodiment of the loading frame 6, see Figure 4 As shown, the loading frame 6 includes a first column 601, a second column 602, a third column 603, a fourth column 604, a loading fixed plate 605, a first loading beam 606, a second loading beam 607, and a third loading beam 608. The first column 601, the second column 602, the third column 603, the fourth column 604, the loading fixed plate 605, the first loading beam 606, the second loading beam 607, and the third loading beam 608 form a loading load-bearing frame, and the loading steel cable 5 is fixed on the loading fixed plate 605 via a ball joint 501, and the calibration space angle of the set calibration preload force output by the loading steel cable 5 is transmitted to the multi-component force stand; during loading, the size and angle of the loaded spatial multi-component force are measured and fed back in real time through the displacement sensor and the calibration force sensor 8.

[0051] In an optional embodiment of the present invention that is not shown in the drawings, the spatial force loading device also includes an energy recovery device, which is connected to the second gear 304 of the circumferential angle adjustment mechanism 3, and is used to recover the energy when the circumferential radial servo motor 305 drives the second gear 304 to rotate. Specifically, the energy recovery device includes a drive motor, a meshing gear, and a reduction gear, the meshing gear is connected to the input shaft of the drive motor, and the reduction gear is respectively meshed with the second gear 304 and the meshing gear to recover the rotational energy of the reduction gear, and the reduction gear can rotate when the spatial force is loaded and unloaded. The output end of the energy recovery device is connected to a power generation unit or an energy storage unit to convert the rotational energy of the energy recovery device into electrical energy.

[0052] The spatial force loading device of the aero-engine multi-component force test bench of the present invention can load a certain calibration spatial angle for the calibration of the multi-component force test bench by designing a circumferential angle adjustment mechanism and a radial position adjustment mechanism. At the same time, by adding a preload adjustment mechanism to the circumferential angle adjustment mechanism, a certain size of calibration preload can also be loaded for the calibration of the multi-component force test bench. When a flexible cable is used for force transmission, the loading accuracy of the spatial multi-component force is controlled to be less than 0.1° under the premise of ensuring the accuracy of the spatial position information of the calibration device, thereby improving the calibration accuracy of the multi-component force test bench.

[0053] Obviously, those skilled in the art should understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

[0054] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.

Claims

1. A spatial force loading device for an aircraft engine multi-component force test bench, characterized in that: The space force loading device comprises: A mounting plate (2), wherein the mounting plate (2) is fixed in the vertical direction of the horizontal mounting frame (1); A circumferential angle adjustment mechanism (3), the circumferential angle adjustment mechanism (3) being rotatably arranged at the center of the mounting plate (2), and a radial position adjustment mechanism (4) being fixed on the circumferential angle adjustment mechanism (3); A loading steel cable (5), one end of the loading steel cable (5) being arranged at the center of the circumferential angle adjustment mechanism (3), and the other end of the loading steel cable (5) passing through the radial position adjustment mechanism (4) and then being fixed on the loading frame (6); The circumferential angle adjustment mechanism (3) cooperates with the radial position adjustment mechanism (4) to adjust the angle of the loading steel cable (5) to provide a calibration spatial angle for the multi-component force stand located below the loading frame (6); A preload adjustment mechanism (7), the preload adjustment mechanism (7) being arranged on a fixed portion (303) on the back side of the circumferential angle adjustment mechanism (3), comprising a first fixed bracket (701), a second fixed bracket (702), a wire winding wheel (703) and a wire winding servo motor (704), the first fixed bracket (701) and the second fixed bracket (702) being fixed on the fixed portion (303), and a rotating shaft is provided between the first fixed bracket (701) and the second fixed bracket (702). The shaft is provided with the wire winding wheel (703), the rotating shaft is connected to the output shaft of the wire winding servo motor (704), one end of the loading steel cable (5) is wound on the wire winding wheel (703), and the other end passes through the center of the circumferential angle adjustment mechanism (3) and the radial position adjustment mechanism (4) in sequence and is connected to the loading frame (6), and the preload adjustment mechanism (7) is used to adjust the force applied to the loading steel cable (5) to provide a calibrated preload for the multi-component force stand located below the loading frame (6); An energy recovery device, the energy recovery device is connected to the second gear (304) of the circumferential angle adjustment mechanism (3) and is used to recover energy when the circumferential radial servo motor (305) of the circumferential angle adjustment mechanism (3) drives the second gear (304) to rotate.

2. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 1 is characterized in that: The circumferential angle adjustment mechanism (3) comprises a rotating assembly, a driving assembly, an adapter plate and a fixing portion (303); the rotating assembly is arranged at the center of the mounting plate (2) via a tapered bearing; the rotating assembly is connected to the driving assembly; the adapter plate is fixed to the rotating assembly; the fixing portion (303) is provided on the adapter plate; and the loading steel cable (5) is provided on the fixing portion (303).

3. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 2 is characterized in that: The rotating assembly comprises a first gear (301) and an axial rotating flange (302); the axial rotating flange (302) is arranged on a fixed flange (201) of the mounting plate (2) via a tapered bearing; the first gear (301) and the adapter plate are fixed on the axial rotating flange (302); The driving assembly comprises a second gear (304) and a circumferential radial servo motor (305); an output shaft of the circumferential radial servo motor (305) is connected to the second gear (304); and the second gear (304) is meshed with the first gear (301).

4. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 2, characterized in that: The adapter plate comprises a first adapter plate (306) and a second adapter plate (307); the first adapter plate (306) and the second adapter plate (307) are symmetrically arranged on the rotating assembly; the fixing portion (303) is fixed to the back sides of the first adapter plate (306) and the second adapter plate (307); and a channel (308) through which the loading steel cable (5) passes is provided between the first adapter plate (306) and the second adapter plate (307).

5. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 1, characterized in that: The spatial force loading device further comprises a displacement sensor and a calibration force sensor (8); the displacement sensor is arranged on the mounting plate (2) and is used to measure the displacement change of the loading steel cable (5) to calculate the calibration spatial angle; one end of the calibration force sensor (8) is connected to the loading steel cable (5), and the other end is connected to the loading frame (6); the calibration force sensor (8) is used to measure the calibration preload force.

6. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 5, characterized in that: Two ends of the calibration force sensor (8) are respectively connected to the loading steel cable (5) and the loading frame (6) via a ball joint (501).

7. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 1, characterized in that: The radial position adjustment mechanism (4) comprises a first radial displacement mechanism and a second radial displacement mechanism which are symmetrically arranged on the circumferential angle adjustment mechanism (3) and move synchronously, a guide cylinder (401) is provided between the sliders of the first radial displacement mechanism and the second radial displacement mechanism, and the loading steel cable (5) is in surface contact with the guide cylinder (401).

8. The spatial force loading device of the aircraft engine multi-component force test bench according to claim 7, characterized in that: The first radial displacement mechanism and the second radial displacement mechanism are identical, and both comprise a lead screw fixing portion (402), a lead screw (403), a slider (404) and a radial servo motor (405); the lead screw fixing portion (402) is fixed to the circumferential angle adjustment mechanism (3); the lead screw (403) is provided on the lead screw fixing portion (402); the slider (404) is provided on the lead screw (403); and the output end of the radial servo motor (405) is connected to the lead screw (403).

Images