Engine thrust measuring and calibrating device

Abstract

The invention relates to an engine thrust measuring and calibrating device which comprises a movable frame, a connecting piece, a thrust frame, a pre-tightening force assembly, a thrust measuring assembly and a calibrating assembly. The movable frame is fixed to the lower portion of the thrust frame through the connecting piece, and the movable frame and the thrust frame share the same longitudinal center line. The lower part of the movable frame is used for fixing an engine, the upper part of the movable frame is provided with the pre-tightening assembly and the thrust measuring assembly, and the pre-tightening assembly provides upward pre-tightening force for the movable frame, so that the thrust measuring assembly measures the in-situ thrust F of the engine during test run; the bottom end of the calibration assembly is arranged at a thrust point of the engine, the top end of the calibration assembly sequentially extends out of the movable frame and the thrust frame, and the standard thrust F1 of the engine is measured by applying pulling force to the engine so as to calibrate the thrust F. The device has the effects of improving the device sensitivity and ensuring the measurement precision; the performance requirement of the high-thrust engine test is fully met, and the safety and stability of the test process are guaranteed.

Description

Technical Field

[0001] The invention relates to the technical field of thrust measurement for aerospace engine test runs, in particular to an engine thrust measurement and calibration device. Background Art

[0002] With the rapid development of aerospace technology, accurate measurement and calibration of the thrust of aerospace engines, as the key power device of spacecraft, is crucial to ensure flight safety and mission success. The thrust of aerospace engines not only affects the takeoff, orbit adjustment and return operation of spacecraft, but is also closely related to the efficiency of the entire flight mission. Therefore, extremely high requirements are placed on the high precision and high stability of thrust measurement and calibration devices.

[0003] At present, conventional thrust measurement devices are widely used in aerospace engine test benches, but these devices are easily affected by external factors such as temperature changes, vibration interference, and air pressure fluctuations in the test environment, which may lead to measurement errors. In addition, the traditional calibration method usually adopts static loading calibration. Although it can meet the basic requirements in some application scenarios of the test bench, due to the complex working conditions of the engine in actual operation, the thrust changes show dynamic characteristics. Static calibration is difficult to fully reflect the thrust conditions in the actual working conditions under the test bench environment. Therefore, the existing technology has limitations in accuracy, adaptability and reliability, and cannot fully meet the thrust measurement and calibration needs of aerospace engines on test benches. Summary of the invention

[0004] The present invention aims at solving the technical problems existing in the prior art and provides an engine thrust measurement and calibration device.

[0005] The technical solution of the present invention to solve the above technical problem is as follows: an engine thrust measurement and calibration device, including a moving frame, a connecting member, a thrust frame, a preload assembly, a thrust measurement assembly, and a calibration assembly; The movable frame is fixed to the lower part of the thrust frame through the connecting piece, and the movable frame and the thrust frame share a longitudinal centerline; the lower part of the movable frame is used to fix the engine, and the upper part is provided with the pre-tightening assembly and the thrust measuring assembly, and the pre-tightening assembly provides an upward pre-tightening force to the movable frame, so that the thrust measuring assembly measures the thrust F of the engine in situ during the test run; The bottom end of the calibration component is arranged at the thrust point of the engine, and the top end of the calibration component sequentially extends out of the moving frame and the thrust frame. The thrust F is calibrated by measuring the standard thrust F1 of the engine by applying a pulling force to the engine. As a further technical solution, the thrust frame comprises: two arched beams, at least two cross beams, and a bottom beam having a U-shaped longitudinal section, wherein the two arched beams are arranged in parallel and connected by the cross beam; The top end of the bottom beam is connected to the bottom end of the arched beam to form a space for accommodating the moving frame; the cross beam is located on a side of the arched beam away from the bottom beam.

[0006] As a further technical solution, the preload assembly includes a preload pull rod, a first lifting unit, a load-bearing plate, a guide sleeve, and an elastic member; The upper end of the preload rod passes through the top plate of the moving frame and extends to the first accommodating cavity of the arched beam. The first lifting unit is located in the first accommodating cavity and is sleeved on the preload rod to control the axial displacement of the preload rod. The lower end of the preload rod extends out of the bottom end surface of the top plate of the moving frame and is located on the upper part of the bottom plate of the moving frame. The lower end of the preload rod is fixedly connected to the load-bearing plate. The guide sleeve is located on the bearing plate, and is provided with two guide sleeves symmetrically arranged along the preload rod. The elastic member is sleeved outside the guide sleeve. The top end of the guide sleeve abuts against the upper end surface of the top plate in the movable frame, and the elastic deformation of the elastic member is controlled to provide a vertical preload force for the movable frame. The preload force components are provided with at least four and are evenly distributed along the circumference of the movable frame.

[0007] As a further technical solution, the preload assembly also includes a first motor connected to the first elevator.

[0008] As a further technical solution, the first lifting unit includes a worm gear lifting unit, a first flange, a coupling, a first reduction box, and a hand wheel; The worm gear elevator and the first flange are sequentially sleeved on the preload rod from bottom to top. The worm gear elevator is connected to the first reduction box through the coupling, and the first reduction box is connected to the hand wheel.

[0009] As a further technical solution, the thrust measurement assembly includes a second flange, a force sensor, and a flexible member; The second flange, the force sensor, and the flexible member are arranged in sequence from bottom to top, and the second flange is fixed to the top end surface of the top plate in the moving frame, the top end surface of the flexible member is fixedly connected to the bottom end surface of the upper arched beam; the force sensor abuts against the flexible member; The thrust measurement components are provided with at least four and are evenly distributed along the circumference of the moving frame.

[0010] As a further technical solution, the calibration assembly includes a calibration pull rod, a calibration connecting plate, a calibration connecting rod, a standard force cylinder, a standard force sensor, a calibration bearing plate, and a calibration base; The bottom end of the calibration rod passes through the thrust frame and the moving frame in sequence and is located at the thrust point of the engine. The upper part of the calibration rod is fixedly connected to the calibration connecting plate. The upper end surface of the calibration connecting plate is fixedly connected to the calibration connecting rod. The upper part of the calibration connecting rod is provided with the standard force cylinder, the standard force sensor and the calibration bearing plate in sequence from bottom to top. The bottom end surface of the standard oil cylinder abuts against the top end surface of the calibration base, and both ends of the calibration base are fixed on independent brackets of the main load-bearing beam.

[0011] As a further technical solution, the standard force cylinder, the standard force sensor, and the calibration bearing plate are coaxial.

[0012] As a further technical solution, it also includes an upper limit assembly and a lower limit assembly arranged on the upper end surface of the movable frame, which are used to limit the axial displacement of the movable frame.

[0013] As a further technical solution, the lower limit assembly includes a second lifting group, a limit plate, and a screw rod. The second lifting group and the limit plate are both mounted on the screw rod, and the platform plate on the second lifting group is fixed to the bottom of the arched beam. The bottom end of the limit plate is fixed to the upper end surface of the top plate in the movable frame to control the downward movement of the movable frame.

[0014] The beneficial effects of the present invention are as follows: compared with the traditional thrust measurement device, for large and heavy aerospace engines, the present invention can evenly share the thrust on the dynamic frame by setting the thrust measurement assembly, thereby improving the sensitivity of the measurement device and ensuring the measurement accuracy; the measurement error caused by the deformation of the engine test frame, the thrust frame, the dynamic frame and other force transmission structures can be eliminated by the calibration assembly; in addition, by reasonably controlling the initial compression amount and stiffness of the elastic member, not only the required preload force can be applied, but also the fluctuation of the measurement value caused by vibration during the test can be effectively reduced; The device can meet the measurement needs of thrusts up to 1200 kN, and the measurement accuracy is as high as ±0.2%, fully meeting the performance requirements of large thrust engine tests and ensuring the safety and stability of the test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a structural schematic diagram of an engine thrust measurement and calibration device of the present invention when it is connected to a main bearing beam; Figure 2 It is a partial structural schematic diagram of an engine thrust measurement and calibration device of the present invention, wherein a pipeline connected to the engine is provided; Figure 3 It is a structural schematic diagram of an engine thrust measurement and calibration device of the present invention after the calibration component is removed from one perspective, wherein a pipeline connected to the engine is provided; Figure 4 It is a schematic structural diagram from another perspective of an engine thrust measurement and calibration device of the present invention after the calibration component is removed; Figure 5 This is a schematic diagram of the structure of the present invention after the thrust frame and calibration assembly are removed; Figure 6 It is a structural schematic diagram of the preload assembly of the present invention; Figure 7 It is a schematic diagram of the structure of the lower limit assembly; Figure 8 It is a schematic diagram of the partial structure of the calibration component; Fig. 9 A partially enlarged schematic diagram of the calibration component.

[0016] In the accompanying drawings, the components represented by the reference numerals are listed as follows: Moving frame 1, top plate 11, bottom plate 12, connecting column 13, pipeline 14; Connector 2; Thrust frame 3, arched beam 31, first accommodating cavity 311, cross beam 32, bottom beam 33, side beam 34, flange plate 35; Preload assembly 4, preload rod 41, first lifting unit 42, worm gear lifting unit 421, first flange 422, coupling 423, first reduction box 424, hand wheel 425, load-bearing plate 43, guide sleeve 44, elastic member 45, first motor 46; Thrust measurement assembly 5, second flange 51, force sensor 52, flexible member 53; Calibration assembly 6, calibration rod 61, calibration connecting plate 62, calibration connecting rod 63, standard force cylinder 64, standard force sensor 65, calibration bearing plate 66, calibration base 67, connecting base 68; Main bearing beam 7, upper limit assembly 8; The lower limit assembly 9, the second lifting unit 91, the platform plate 911, the limit plate 92, and the screw rod 93. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of this application.

[0018] In the description of this application, the terms "first" and "second" 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. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0019] In the description of the present application, the term "for example" is used to mean "used as an example, illustration or description". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid unnecessary details to obscure the description of the present invention. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in the present application.

[0020] Example 1 This embodiment provides a technical solution that is adaptable to complex working conditions and has high precision and a wide measurement range in response to the needs of aerospace engine thrust measurement and calibration. Figure 1-Figure 4 , specifically, an engine thrust measurement and calibration device, comprising a moving frame 1, a connecting member 2, a thrust frame 3, a preload assembly 4, a thrust measurement assembly 5, and a calibration assembly 6; The moving frame 1 is fixed to the lower part of the thrust frame 3 through the connecting member 2, and the moving frame 1 and the thrust frame 3 share a longitudinal centerline; the lower part of the moving frame 1 is used to fix the engine, and the upper part is provided with the preload assembly 4 and the thrust measurement assembly 5, and the preload assembly 4 provides an upward preload force to the moving frame 1, so that the thrust measurement assembly 5 measures the thrust F of the engine in situ during the test run; The bottom end of the calibration component 6 is arranged at the thrust point of the engine, and the top end of the calibration component 6 extends out of the moving frame 1 and the thrust frame 3 in sequence. The standard thrust F1 of the engine is measured by applying a pulling force to the engine to calibrate the thrust F.

[0021] For example, the dynamic frame 1 includes a top plate 11, a bottom plate 12, and a connecting column 13 connecting the top plate 11 and the top plate 11. The top plate 11 and the bottom plate 12 are both annular structures, and the inner diameter and outer diameter of the top plate 11 are larger than the inner diameter and outer diameter of the top plate 11; the bottom plate 12 is used to connect the engine. It can be explained that, in order to facilitate the installation of the pipeline 14, adjacent connecting columns 13 have a gap to facilitate the passage of the pipeline 14, such as the gap between adjacent connecting columns 13 can be used for the passage of the pipeline 14 with a diameter of 500mm. For example, the outer diameter of the top plate 11 is 3400mm, and Q460D material can be selected. The inner diameter of the bottom plate 12 is 1400mm, which is used to be connected to the bracket of the tested product, for example, the tested product is an engine; The top plate 11 and the bottom plate 12 are both provided with the connecting member 2, so that one end of the connecting member 2 is fixedly connected to the moving frame 1 and the other end is fixedly connected to the thrust frame 3. For example, the connecting member 2, the thrust frame 3 and the moving frame 1 are all connected and fixed by screws, and the connecting member 2 can be divided into two groups, one group is located at the upper part, used to connect the top plate 11 and the side beam 34, and the other group is located at the lower part, used to connect the bottom plate 12 and the bottom beam 33. The number of the connecting members 2 in the two groups can be 8 pieces, each piece is 600mm long and 200mm wide, adopts a straight-line variable cross-section design, and has a thickness of 1.5mm. Two pieces in each group can be arranged side by side and spaced apart as a unit as a connection point, that is, the upper and lower groups each have four connection points. In this embodiment, the connecting member 2 may be a spring plate, and the spring plate is calculated based on bearing a lateral load of 240 kN (20% of the rated thrust of 120 t), with a stress safety factor of not less than 3 and a lateral deformation of not more than 2 mm; at the same time, the stiffness on the thrust axis is very low, and when the movable frame 1 is supported only by the spring plate, under an axial load of 1200 N (0.15% of the rated thrust of 80 t), the theoretical displacement of the movable frame 1 is not less than 2 mm.

[0022] A plurality of bosses are disposed on the upper end surface of the top plate 11 , and flange interfaces that are adapted to be connected to the thrust measurement assembly 5 are disposed on the bosses.

[0023] It can be explained that the preload assembly 4 and the thrust measurement assembly 5 are both arranged on the upper end surface of the top plate 11, and the lower part of the preload assembly 4 extends out of the lower end surface of the top plate 11 from the through hole of the top plate 11; therefore, the top plate 11 is provided with a through hole adapted to the preload assembly 4. In order to improve stability and measurement accuracy, the preload assembly 4 and the thrust measurement assembly 5 are both provided in several groups, for example, four groups, and a thrust measurement assembly 5 is provided next to each group of the preload assembly 4.

[0024] In the specific implementation process, see Figure 2-Figure 4The thrust frame 3 includes two arched beams 31, at least two cross beams 32, and a bottom beam 33 having a U-shaped longitudinal section. The two arched beams 31 are arranged in parallel and connected by the cross beam 32. The top end of the bottom beam 33 is connected to the bottom end of the arched beam 31 to form a space for accommodating the movable frame 1 ; the cross beam 32 is located on a side of the arched beam 31 away from the bottom beam 33 .

[0025] For example, in order to improve the stability of the moving frame 1, two side beams 34 are further provided on the thrust frame 3, that is, a side beam 34 is correspondingly provided on the lower part of one arched beam 31, and the side beam 34 is located between the arched beam 31 and the bottom beam 33 and is arranged in parallel, so that the top plate 11 is fixedly connected to the side beam 34 through the connecting member 2, and the bottom plate 12 is fixedly connected to the bottom beam 33 through other connecting members 2, so as to fix the moving frame 1 on the thrust frame 3; The top end surfaces on both sides of the arched beam 31 are fixedly connected to the main load-bearing beam 7 of the engine test frame through flange plates 35, for example, screw connection. In this embodiment, the structural design of the arched beam 31 not only reduces the height of the entire structure, but also improves the rigidity of the entire structure, and the lower part of the arched beam 31 can be used to accommodate the dynamic frame 1 and the thrust measurement assembly 5, with high integration.

[0026] For example, the two ends of the two arched beams 31 adopt a rectangular cross section of 0.98×0.8m, the thickness of the plate is 40mm, a 40mm thick longitudinal partition is provided in the middle, and a 10mm transverse partition is provided every 1m. The middle part is a rectangular cross section of 1.47×0.8m, and a 10mm transverse partition is provided every 1m inside to strengthen the rigidity of the arched beam 31, so as to reduce the deformation of the bearing surface.

[0027] In the specific implementation process, see Figure 4-Figure 6 The preload assembly 4 includes a preload rod 41, a first lifting unit 42, a load-bearing plate 43, a guide sleeve 44, and an elastic member 45; The upper end of the preload rod 41 passes through the top plate 11 of the moving frame 1 and extends to the first accommodating cavity 311 of the arched beam 31. The first lifting unit 42 is located in the first accommodating cavity 311 and is sleeved on the preload rod 41 to control the axial displacement of the preload rod 41. The lower end of the preload rod 41 extends out of the bottom end surface of the top plate 11 of the moving frame 1 and is located on the upper part of the bottom plate 12 of the moving frame 1. The lower end of the preload rod 41 is fixedly connected to the load-bearing plate 43. The guide sleeve 44 is located on the load-bearing plate 43, and two of them are provided and symmetrically arranged along the preload rod 41. The elastic member 45 is sleeved on the outside of the guide sleeve 44. At this time, the top and bottom ends of the elastic member 45 respectively abut against the upper bottom end surface of the guide sleeve 44 and the top end surface of the load-bearing plate 43 (that is, the guide sleeve 44 is a structure that is thin in the middle and thick at the top, and the spring 45 is sleeved on the thin part in the middle); the top end of the guide sleeve 44 abuts against the upper end surface of the top plate 11 in the movable frame 1, and the elastic deformation of the elastic member 45 is controlled to provide a vertical preload force for the movable frame 1; the preload force assembly 4 is provided with at least four and is evenly distributed along the circumference of the movable frame 1. It can be explained that the elastic member 45 can be a spring. For example, the stiffness of the elastic member 45 is 240 N / mm. Eight springs are connected in parallel to pre-tighten the movable frame 1. When the movable frame 1 is displaced by 0.5 mm, the change in the spring pre-tightening force is 960 N, which is only 0.12% of the thrust load of 80 t, and the force transmission coefficient can reach 99%.

[0028] It can be explained that the preload rod 41 and the first lifting unit 42 can form a worm gear lifting unit 421, so its working principle is not described in detail. When the first lifting unit 42 is working, it drives the preload rod 41 to move axially upward, that is, before the device is tested, the preload rod 41 is pulled upward by the first lifting unit 42, so that the elastic member 45 undergoes elastic deformation to provide a vertical upward preload force for the moving frame 1, which can overcome the reverse thrust generated by the connection of the pipeline 14 and the flow of liquid, as well as the gravity of the moving frame 1 and the engine. The accuracy of the preload provided in this way can be improved by one order of magnitude compared to the transmission mechanical type. The size of the preload force can be adjusted according to the first lifting unit 42; More specifically, the preload assembly 4 further includes a first motor 46 connected to the first lifting unit 42, that is, the first motor 46 can be used as a power source to drive the first lifting unit 42 to work; For example, the first lifting unit 42 includes a worm gear lift 421, a first flange 422, a coupling 423, a first reduction box 424, and a hand wheel 425; the worm gear lift 421 and the first flange 422 are sequentially sleeved on the preload rod 41 from bottom to top, the worm gear lift 421 is connected to the first reduction box 424 through the coupling 423, the first reduction box 424 is connected to the hand wheel 425, and the other end of the first reduction box 424 is connected to the first motor 46. Therefore, the operation of the first lifting unit 42 can be controlled by the first motor 46 or the hand wheel 425.

[0029] In the specific implementation process, see Figure 5The thrust measurement assembly 5 includes a second flange 51, a force sensor 52, and a flexible member 53; the second flange 51, the force sensor 52, and the flexible member 53 are arranged in sequence from bottom to top, and the second flange 51 is fixed to the top end surface of the top plate 11 in the moving frame 1, and the top end surface of the flexible member 53 is fixedly connected to the bottom end surface of the upper arched beam 31 thereof; the force sensor 52 is in contact with the flexible member 53; At least four thrust measurement assemblies 5 are provided and are evenly distributed along the circumference of the movable frame 1 .

[0030] The structural design of the preload assembly 4 eliminates the gap between the force sensor 52 and the flexible member 53, so that the force sensor 52 bears the same load direction before and after the test. For example, the flexible member 53 is an inverted cone structure, that is, the top of the flexible member 53 is fixedly connected to the arched beam 31 above it, such as a screw connection. Because the cross-sectional area of ​​the upper part of the flexible member 53 is larger than that of the lower part, the contact area with the arched beam 31 is increased while improving its strength. Therefore, the flexible member 53 is a support for bearing force. It can be explained that the force sensor 52 is used to measure the thrust F of the engine in situ during the test.

[0031] For example, the force sensor 52 is connected to the movable frame 1 by using the second flange 51, and is connected to the thrust frame 3 by using the flexible member 53, so as to improve the stress state of the force sensor 52, eliminate the interference of non-axial force on the measurement, and improve the force measurement accuracy; the force sensor 52 can use a 1232-450 kN sensor with a comprehensive accuracy of not less than 0.05% FS, has a compact size and a proprietary interface temperature compensation, can compensate for eccentric loads, and can select a variety of output modes such as 4-20mA, ±5 V, ±10 V, 0-5 V, 0-10 V, etc. as needed.

[0032] In the specific implementation process, Figure 1 , Figure 2 , Figure 8 , Fig. 9 The calibration assembly 6 includes a calibration rod 61, a calibration connecting plate 62, a calibration connecting rod 63, a standard force cylinder 64, a standard force sensor 65, a calibration bearing plate 66, and a calibration base 67; The bottom end of the calibration rod 61 passes through the thrust frame 3 and the moving frame 1 in sequence and is located at the thrust point of the engine. The upper part of the calibration rod 61 is fixedly connected to the calibration connecting plate 62. The upper end surface of the calibration connecting plate 62 is fixedly connected to the calibration connecting rod 63. The upper part of the calibration connecting rod 63 is provided with the standard force cylinder 64, the standard force sensor 65, and the calibration bearing plate 66 in sequence from bottom to top. The bottom end surface of the standard force cylinder 64 abuts against the top end surface of the calibration base 67, and the two ends of the calibration base 67 are fixed on independent brackets of the main load-bearing beam 7. Furthermore, in order to improve the service life, the two ends of the calibration base 67 are provided with connecting bases 68 to be fixedly connected to the main load-bearing beam 7.

[0033] In this embodiment, the calibration rod 61 and the calibration connecting plate 62 are used to apply tension to the thrust surface of the tested product, and the standard force oil cylinder 64 and the standard force sensor 65 are arranged in series at the top center axis position of the thrust frame 3, thereby improving the calibration accuracy. For example, the thrust surface of the standard force oil cylinder 64 is aligned through the thrust spherical bearing, thereby ensuring the consistency of the thrust direction of the standard force oil cylinder 64.

[0034] The loading force range of the standard force cylinder 64 is, for example, 10-145 t, and the standard force sensor 65 can be a 1243-1350 kN sensor with a comprehensive accuracy of 0.05% FS; and the standard force sensor 65 is installed above the standard force cylinder 64 and connected to the calibration rod 61 through structures such as the calibration connecting rod 63, which can improve the stress state of the standard force sensor 65, eliminate the interference of non-axial force on the measurement, and improve the force measurement accuracy.

[0035] In a specific implementation process, the standard force cylinder 64, the standard force sensor 65, and the calibration bearing plate 66 are coaxial.

[0036] In the specific implementation process, the device of the present invention also includes an upper limit assembly 8 and a lower limit assembly 9 arranged on the upper end surface of the movable frame 1, which are used to limit the axial displacement of the movable frame 1, that is, the axial upward displacement of the movable frame 1 is controlled by the upper limit assembly 8, and the axial downward displacement of the movable frame 1 is controlled by the lower limit assembly 9.

[0037] The upper limit assembly 8 and the lower limit assembly 9 are each provided with a plurality of groups, for example, four groups are provided respectively, and one group of the upper limit assembly 8 corresponds to one group of the lower limit assembly 9, one group of the preload assembly 4, and one group of the thrust measurement assembly 5; More specifically, the lower limit assembly 9 includes a second lifting unit 91, a limit plate 92, and a screw rod 93. The second lifting unit 91 and the limit plate 92 are both sleeved on the screw rod 93, and the platform plate 911 on the second lifting unit 91 is fixed to the bottom of the arched beam 31. The bottom end of the limit plate 92 is fixed to the upper end surface of the top plate 11 in the movable frame 1, and is used to control the downward movement of the movable frame 1. For example, when the movable frame 1 is in the process of descending, the limit plate 92 can provide an upward pulling force to the movable frame 1 to control the axial downward displacement of the movable frame 1.

[0038] It can be explained that the second lifting unit 91 has the same structure and working principle as the first lifting unit 42, so it will not be described in detail. The upper limit assembly 8 is different from the lower limit assembly 9 in that the upper limit assembly 8 does not have the limit plate 92.

[0039] It can be explained that the second lifting unit 91 can also be set to be electrically adjustable, that is, a motor can be installed as a power source.

[0040] This embodiment is achieved as follows: In the initial state of the device, the spring in the preload assembly 4 is in a compressed state to provide preload to the movable frame 1. At this time, the thrust F of the force sensor 52 is 0. The calibration component 6 simulates thrust, applies pulling force to the engine, and measures the standard thrust F1 of the engine, which is measured by the standard force sensor 65; When the device is used to perform a thrust test on an engine, multiple tests are first set up to obtain the relationship between the thrust F and the standard thrust F1, that is, the standard thrust F1 is used as the calibration of the thrust F, so that when a simulated thrust test is performed on the engine, the thrust F of the engine in situ can be accurately obtained.

[0041] It should be noted that in the above embodiments, the description of each embodiment has its own emphasis, and for parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0042] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0043] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. An engine thrust measurement and calibration device, characterized in that: It comprises a movable frame (1), a connecting piece (2), a thrust frame (3), a preload assembly (4), a thrust measurement assembly (5), and a calibration assembly (6); The movable frame (1) is fixed to the lower part of the thrust frame (3) through the connecting member (2), and the movable frame (1) and the thrust frame (3) share a common longitudinal centerline; the lower part of the movable frame (1) is used to fix the engine, and the upper part is provided with the preload assembly (4) and the thrust measurement assembly (5), and the preload assembly (4) provides an upward preload force to the movable frame (1), so that the thrust measurement assembly (5) measures the thrust F of the engine in situ during the test run; The bottom end of the calibration component (6) is arranged at the thrust point of the engine, and the top end of the calibration component (6) extends out of the moving frame (1) and the thrust frame (3) in sequence. By applying a pulling force to the engine, the standard thrust F1 of the engine is measured, so as to calibrate the thrust F.

2. An engine thrust measurement and calibration device according to claim 1, characterized in that: The thrust frame (3) comprises: two arched beams (31), at least two cross beams (32), and a bottom beam (33) having a U-shaped longitudinal cross section, wherein the two arched beams (31) are arranged in parallel and connected via the cross beam (32); The top end of the bottom beam (33) is connected to the bottom end of the arched beam (31) to form a space for accommodating the movable frame (1); and the cross beam (32) is located on a side of the arched beam (31) away from the bottom beam (33).

3. An engine thrust measurement and calibration device according to claim 2, characterized in that: The preload assembly (4) comprises a preload pull rod (41), a first lifting unit (42), a load-bearing plate (43), a guide sleeve (44), and an elastic member (45); The upper end of the preload rod (41) passes through the top plate (11) of the movable frame (1) and then extends into the first accommodating cavity (311) of the arched beam (31); the first lifting unit (42) is located in the first accommodating cavity (311) and is sleeved on the preload rod (41) to control the axial displacement of the preload rod (41); the lower end of the preload rod (41) extends out of the bottom end surface of the top plate (11) of the movable frame (1) and is located on the upper part of the bottom plate (12) of the movable frame (1); the lower end of the preload rod (41) is fixedly connected to the load-bearing plate (43); The guide sleeve (44) is located on the load-bearing plate (43) and is provided with two of them symmetrically arranged along the preload rod (41). The elastic member (45) is sleeved outside the guide sleeve (44). The top end of the guide sleeve (44) abuts against the upper end surface of the top plate (11) in the movable frame (1), and the elastic deformation of the elastic member (45) is controlled to provide a vertical preload force for the movable frame (1). The pre-tightening force components (4) are provided with at least four and are evenly distributed along the circumference of the movable frame (1).

4. The engine thrust measurement and calibration device according to claim 3, characterized in that: The pre-tightening force assembly (4) also includes a first motor (46) connected to the first lifting unit (42).

5. The engine thrust measurement and calibration device according to claim 4, characterized in that: The first lifting unit (42) comprises a worm gear lifting unit (421), a first flange (422), a coupling (423), a first reduction box (424), and a hand wheel (425); The worm gear elevator (421) and the first flange (422) are sequentially sleeved on the preload rod (41) from bottom to top; the worm gear elevator (421) is connected to the first reduction box (424) via the coupling (423); and the first reduction box (424) is connected to the hand wheel (425).

6. The engine thrust measurement and calibration device according to claim 2, characterized in that: The thrust measurement assembly (5) comprises a second flange (51), a force sensor (52), and a flexible member (53); The second flange (51), the force sensor (52), and the flexible member (53) are arranged in sequence from bottom to top, and the second flange (51) is fixed to the top end surface of the top plate (11) in the movable frame (1), and the top end surface of the flexible member (53) is fixedly connected to the bottom end surface of the upper arched beam (31) thereof; the force sensor (52) is in contact with the flexible member (53); The thrust measurement components (5) are provided with at least four and are evenly distributed along the circumference of the moving frame (1).

7. The engine thrust measurement and calibration device according to claim 2, characterized in that: The calibration assembly (6) comprises a calibration pull rod (61), a calibration connecting plate (62), a calibration connecting rod (63), a standard force cylinder (64), a standard force sensor (65), a calibration load-bearing plate (66), and a calibration base (67); The bottom end of the calibration rod (61) passes through the thrust frame (3) and the moving frame (1) in sequence and is located at the thrust point of the engine; the upper part of the calibration rod (61) is fixedly connected to the calibration connecting plate (62); the upper end surface of the calibration connecting plate (62) is fixedly connected to the calibration connecting rod (63); the upper part of the calibration connecting rod (63) is provided with the standard force cylinder (64), the standard force sensor (65), and the calibration bearing plate (66) in sequence from bottom to top; The bottom end surface of the standard force oil cylinder (64) abuts against the top end surface of the calibration base (67), and both ends of the calibration base (67) are fixed on independent brackets of the main load-bearing beam (7).

8. The engine thrust measurement and calibration device according to claim 7, characterized in that: The standard force oil cylinder (64), the standard force sensor (65), and the calibration load-bearing plate (66) are coaxial.

9. The engine thrust measurement and calibration device according to claim 2, characterized in that: It also includes an upper limit assembly (8) and a lower limit assembly (9) arranged on the upper end surface of the movable frame (1) and used to limit the axial displacement of the movable frame (1).

10. An engine thrust measurement and calibration device according to claim 9, characterized in that: The lower limit assembly (9) comprises a second lifting unit (91), a limit plate (92), and a screw rod (93); the second lifting unit (91) and the limit plate (92) are both sleeved on the screw rod (93); the platform plate (911) on the second lifting unit (91) is fixed to the bottom of the arched beam (31); the bottom end of the limit plate (92) is fixed to the upper end surface of the top plate (11) in the movable frame (1) for controlling the movable frame (1) to move downward.

Images