An aero-engine test bench with adjustable attitude angle

Abstract

This invention provides an attitude-adjustable aero-engine test bench, relating to the technical field of aero-engine test benches. The test bench includes: a mounting plate; two support frames symmetrically arranged on the mounting plate, the tops of which are rotatably connected to the main mounting joints on both sides of the aero-engine; and at least one first telescopic assembly disposed between the two support frames, one end of which is hinged to the mounting plate, and the other end of which is rotatably connected to a secondary mounting joint above the aero-engine's exhaust nozzle. When it is necessary to adjust the angle of attack or attitude angle of the aero-engine, the length of the first telescopic assembly is adjusted to allow the aero-engine to rotate around the main mounting joint, changing the engine's tilt angle and simulating the engine's state during UAV flight to meet experimental requirements.

Description

Technical Field

[0001] This invention belongs to the technical field of aero-engine test benches, and more specifically, relates to an attitude angle adjustable aero-engine test bench. Background Technology

[0002] Before installing an aero-engine in the power system of a certain type of UAV, it is necessary to conduct relevant engine performance tests, such as aero-engine durability tests and propeller-engine matching tests, to ensure that its performance meets the relevant technical requirements of the power system. At the same time, engine testing is an indispensable means of evaluating the engine's power, economy, operational reliability, and wear resistance, and it is also an essential and important step in the research, design, and manufacture of new engines.

[0003] Currently, traditional test benches have relatively fixed structures, and the engine's angle of attack and attitude angle cannot be adjusted. They cannot simulate the changes in angle of attack and attitude angle during UAV flight and cannot meet the experimental requirements of aero engines. Summary of the Invention

[0004] The purpose of this invention is to provide an attitude-adjustable aero-engine test bench to address the shortcomings of existing technologies. This solves the problem mentioned in the background art that traditional test benches have relatively fixed structures, and the engine's angle of attack and attitude angle cannot be adjusted, making it impossible to simulate the changes in angle of attack and attitude angle during UAV flight and failing to meet the experimental requirements of aero-engines.

[0005] To achieve the above objectives, the present invention provides an attitude angle adjustable aero-engine test bench, the test bench comprising:

[0006] Mounting plate;

[0007] Two support frames are symmetrically arranged on the mounting plate, and the tops of the two support frames are respectively used to rotatably connect with the main mounting structures on both sides of the aero-engine;

[0008] At least one first telescopic component is disposed between the two support frames, one end of the first telescopic component is hinged to the mounting plate, and the other end of the first telescopic component is rotatably connected to the auxiliary mounting structure above the exhaust nozzle of the aircraft engine.

[0009] Preferably, the support frame includes a connecting rod and a second telescopic assembly, one end of the connecting rod and one end of the second telescopic assembly are away from each other and both are hinged to the mounting plate, and the other end of the connecting rod and the other end of the second telescopic assembly are hinged to each other.

[0010] Preferably, the other end of the connecting rod is provided with a circular hole, and a second shock absorber is installed inside the circular hole. The center hole of the second shock absorber is used to insert the corresponding main mounting joint.

[0011] Preferably, the first telescopic component includes:

[0012] The first sleeve has a first left-hand internal thread and a first right-hand internal thread on the inner sides of its two ends, respectively;

[0013] A first left-hand pull rod and a first right-hand pull rod, wherein the first left-hand pull rod passes through one end of the first sleeve and is threadedly connected to the first left-hand internal thread, and the first right-hand pull rod passes through the other end of the first sleeve and is threadedly connected to the first right-hand internal thread.

[0014] Preferably, the second telescopic component includes:

[0015] The second sleeve has a second left-hand internal thread and a second right-hand internal thread on the inner sides of its two ends, respectively.

[0016] The second left-hand pull rod and the second right-hand pull rod are connected. The second left-hand pull rod passes through one end of the second sleeve and is threadedly connected to the second left-hand internal thread. The second right-hand pull rod passes through the other end of the second sleeve and is threadedly connected to the second right-hand internal thread.

[0017] Preferably, the test bench further includes a double-hole hinge and two third telescopic components. The double-hole hinge is disposed between the two support frames, one end of the two third telescopic components is hinged to the double-hole hinge, and the other end of the two third telescopic components is respectively hinged to the side wall of the two connecting rods.

[0018] Preferably, the third telescopic component includes:

[0019] The third sleeve has a third left-hand internal thread and a third right-hand internal thread on the inner sides of its two ends, respectively;

[0020] The third left-hand pull rod and the third right-hand pull rod are respectively connected. The third left-hand pull rod passes through one end of the third sleeve and is threadedly connected to the third left-hand internal thread. The third right-hand pull rod passes through the other end of the third sleeve and is threadedly connected to the third right-hand internal thread.

[0021] Preferably, the support frame further includes a single-hole hinge and a main hinge support. The single-hole hinge and the hinge support are far apart from each other and are both fixed to the mounting plate. One end of the connecting rod and one end of the second telescopic component are respectively hinged to the single-hole hinge and the hinge support. The center line of the hinge hole of the single-hole hinge is perpendicular to the center line of the hinge hole of the hinge support.

[0022] Preferably, the test bench further includes at least one pad and at least one secondary hinge support. The pad is disposed between the two support frames, and the secondary hinge support is fixed to the pad. A first shock absorber is installed at one end of the first telescopic assembly, and the first shock absorber is hinged to the secondary hinge support.

[0023] Preferably, there are two first telescopic components, and the other end of each first telescopic component is used for rotatable connection with the two sub-mounting joints.

[0024] This invention provides an attitude angle adjustable aero-engine test bench, the advantages of which are:

[0025] The tops of the two support frames of the test bench are respectively used to rotatably connect with the main mounting joints on both sides of the aero-engine. One end of the first telescopic component is hinged to the mounting plate, and the other end of the first telescopic component is used to rotatably connect with the auxiliary mounting joint above the tail nozzle of the aero-engine. When it is necessary to adjust the angle of attack or attitude angle of the aero-engine, the length of the first telescopic component is adjusted to make the aero-engine rotate around the main mounting joint as the center, thereby changing the tilt angle of the aero-engine and simulating the state of the engine during the flight of the UAV to meet the experimental requirements.

[0026] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0027] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0028] Figure 1 A three-dimensional structural schematic diagram of an attitude angle adjustable aero-engine test bench according to an embodiment of the present invention is shown;

[0029] Figure 2 A top view of an attitude angle adjustable aero-engine test bench according to an embodiment of the present invention is shown.

[0030] Figure 3 A schematic diagram of the structure of the first telescopic component of an attitude angle adjustable aero-engine test bench according to an embodiment of the present invention is shown;

[0031] Figure 4 A schematic diagram of the structure of the second telescopic component of an attitude angle adjustable aero-engine test bench according to an embodiment of the present invention is shown;

[0032] Figure 5A schematic diagram of the structure of the third telescopic component of an attitude angle adjustable aero-engine test bench according to an embodiment of the present invention is shown.

[0033] Explanation of reference numerals in the attached figures:

[0034] 1. Mounting plate; 2. Connecting rod; 3. Single-hole hinge; 4. Third telescopic assembly; 5. Double-hole hinge; 6. Pad; 7. Secondary hinge support; 8. First telescopic assembly; 9. Second telescopic assembly; 10. Second shock absorber; 11. Lifting eyelet bolt; 12. Hinge support; 13. Lifting threaded hole; 14. Second left-hand pull rod; 15. Second sleeve; 16. Second right-hand pull rod; 17. Second lock nut; 18. First left-hand pull rod; 19. First sleeve; 20. First lock nut; 21. First right-hand pull rod; 22. First shock absorber; 23. Third left-hand pull rod; 24. Third sleeve; 25. Third right-hand pull rod; 26. Third lock nut. Detailed Implementation

[0035] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0036] like Figure 1 and Figure 2 As shown, the present invention provides an attitude angle adjustable aero-engine test bench, the test bench comprising:

[0037] Mounting plate 1;

[0038] Two support frames are symmetrically arranged on the mounting plate 1, and the tops of the two support frames are respectively used to rotatably connect with the main mounting structures on both sides of the aero-engine;

[0039] At least one first telescopic component 8 is disposed between two support frames. One end of the first telescopic component 8 is hinged to the mounting plate 1, and the other end of the first telescopic component 8 is used for rotatable connection with the auxiliary mounting structure above the tail nozzle of the aircraft engine.

[0040] Specifically, to address the problem that traditional test benches have relatively fixed structures, making it impossible to adjust the engine's angle of attack and attitude angle, thus failing to simulate changes in these angles during UAV flight and meet the experimental requirements of aero-engines, this invention provides an attitude-adjustable aero-engine test bench. The tops of the two support frames of this test bench are respectively used to rotatably connect to the main mounting joints on both sides of the aero-engine. One end of the first telescopic component 8 is hinged to the mounting plate 1, and the other end of the first telescopic component 8 is used to rotatably connect to the auxiliary mounting joint above the aero-engine's exhaust nozzle. When it is necessary to adjust the aero-engine's angle of attack or attitude angle, the length of the first telescopic component 8 is adjusted to allow the aero-engine to rotate around the main mounting joint, changing the aero-engine's tilt angle and simulating the engine's state during UAV flight to meet experimental requirements.

[0041] Preferably, the support frame includes a connecting rod 2 and a second telescopic component 9. One end of the connecting rod 2 and one end of the second telescopic component 9 are far apart from each other and are both hinged to the mounting plate 1. The other end of the connecting rod 2 and the other end of the second telescopic component 9 are hinged to each other.

[0042] Specifically, by replacing the connecting rod 2 with different lengths and adjusting the lengths of the second telescopic assembly 9 and the first telescopic assembly 8, it can adapt to the installation of aircraft engines of various specifications and installation sizes.

[0043] Preferably, the other end of the connecting rod 2 is provided with a circular hole, and a second shock absorber 10 is installed inside the circular hole. The center hole of the second shock absorber 10 is used to insert the corresponding main mounting joint.

[0044] Specifically, by designing a second shock absorber 10 inside the circular hole, the vibration of the aircraft engine itself can be reduced, thus protecting the aircraft engine.

[0045] like Figure 3 As shown, preferably, the first telescopic component 8 includes:

[0046] The first sleeve 19 has a first left-hand internal thread and a first right-hand internal thread on the inner sides of its two ends, respectively.

[0047] The first left-hand pull rod 18 and the first right-hand pull rod 21 are connected. The first left-hand pull rod 18 passes through one end of the first sleeve 19 and is threadedly connected to the first left-hand internal thread. The first right-hand pull rod 21 passes through the other end of the first sleeve 19 and is threadedly connected to the first right-hand internal thread.

[0048] Specifically, when it is necessary to adjust the length of the first telescopic component 8, since the inner sides of the two ends of the first sleeve 19 are respectively provided with the first left-hand internal thread and the first right-hand internal thread, when the first left-hand tie rod 18 and the first right-hand tie rod 21 are respectively hinged to the auxiliary mounting joint and the mounting plate 1 above the tail nozzle of the aero-engine, rotating the first sleeve 19 will change the length of the first telescopic component 8. The main mounting joints on both sides of the aero-engine will rotate in the two second shock absorbers and tilt around the main mounting joint as the center, thereby changing the angle of attack or attitude angle of the aero-engine.

[0049] Preferably, the first telescopic assembly 8 further includes two first locking nuts 20 threadedly connected to the first left-hand pull rod 18 and two first locking nuts 20 threadedly connected to the first right-hand pull rod 21.

[0050] Specifically, when the two first locking nuts 20 on the first left-hand pull rod 18 and the two first locking nuts 20 on the first right-hand pull rod 21 abut against the two ends of the first sleeve 19, they can restrict the movement of the first left-hand pull rod 18 and the first right-hand pull rod 21 and restrict the rotation of the first sleeve 19, thereby ensuring the stability of the first telescopic component 8.

[0051] like Figure 4 As shown, preferably, the second telescopic component 9 includes:

[0052] The second sleeve 15 has a second left-hand internal thread and a second right-hand internal thread on the inner sides of its two ends, respectively.

[0053] The second left-hand pull rod 14 and the second right-hand pull rod 16 are connected. The second left-hand pull rod 14 passes through one end of the second sleeve 15 and is threaded with the second left-hand internal thread. The second right-hand pull rod 16 passes through the other end of the second sleeve 15 and is threaded with the second right-hand internal thread.

[0054] Specifically, when it is necessary to adjust the length of the second telescopic component 9, since the inner sides of both ends of the second sleeve 15 are respectively provided with a second left-hand internal thread and a second right-hand internal thread, when the second left-hand pull rod 14 and the second right-hand pull rod 16 are respectively hinged to the other end of the connecting rod 2 and the mounting plate 1, rotating the second sleeve 15 will change the length of the second telescopic component 9. In this way, connecting rods 2 of different lengths can be replaced to adapt to the installation of aircraft engines of various specifications and different installation sizes.

[0055] Preferably, the second telescopic assembly 9 further includes two second locking nuts 17 threadedly connected to the second left-hand pull rod 14 and two second locking nuts 17 threadedly connected to the second right-hand pull rod 16.

[0056] Specifically, when the two second locking nuts 17 on the second left-hand pull rod 14 and the two second locking nuts 17 on the second right-hand pull rod 16 abut against the two ends of the second sleeve 15, they can restrict the movement of the second left-hand pull rod 18 and the second right-hand pull rod 16 and restrict the rotation of the second sleeve 15. Thus, in the natural state, the stability of the second telescopic component 9 can be guaranteed.

[0057] Preferably, the test bench also includes a double-hole hinge 5 and two third telescopic components 4. The double-hole hinge 5 is disposed between the two support frames, one end of the two third telescopic components 4 is hinged to the double-hole hinge 5, and the other end of the two third telescopic components 4 is respectively hinged to the side wall of the two connecting rods 2.

[0058] Specifically, by adjusting the length of the third telescopic component, the two second shock absorbers 10 can be appropriately moved away from or closer to each other. When the main mounting joints on both sides of the aircraft engine are inserted into the two second shock absorbers 10, the two second shock absorbers 10 can be better fixed to the main mounting joints on both sides, preventing the main mounting joints on both sides from falling off.

[0059] Preferably, the connecting rod 2 has a plurality of lifting threaded holes 13 arranged thereon, and the lifting threaded holes 13 are internally threaded with lifting eye bolts 11, and the other end of the third telescopic component 4 is rotatably connected to the lifting eye bolts 11.

[0060] like Figure 5 As shown, preferably, the third telescopic component 4 includes:

[0061] The third sleeve 24 has a third left-hand internal thread and a third right-hand internal thread on the inner sides of its two ends, respectively.

[0062] The third left-hand pull rod 23 and the third right-hand pull rod 25 are connected. The third left-hand pull rod 23 passes through one end of the third sleeve 24 and is threaded with the third left-hand internal thread. The third right-hand pull rod 25 passes through the other end of the third sleeve 24 and is threaded with the third right-hand internal thread.

[0063] Specifically, when it is necessary to adjust the length of the third telescopic component 4, since the inner sides of both ends of the third sleeve 24 are respectively provided with a third left-hand internal thread and a third right-hand internal thread, when the third left-hand tie rod 23 and the third right-hand tie rod 25 are respectively hinged to the side wall of the double-hole hinge 5 and the connecting rod 2, rotating the third sleeve 24 will change the length of the third telescopic component 4, which can make the two second shock absorbers 10 move away from or closer to each other appropriately.

[0064] Preferably, the third telescopic assembly 4 further includes two third locking nuts 26 threadedly connected to the third left-hand pull rod 23 and two third locking nuts 26 threadedly connected to the third right-hand pull rod 25.

[0065] Specifically, when the two third locking nuts 26 on the third left-hand pull rod 23 and the two third locking nuts 26 on the third right-hand pull rod 25 abut against the two ends of the third sleeve 24, they can restrict the movement of the third left-hand pull rod 23 and the third right-hand pull rod 25 and restrict the rotation of the third sleeve 24. Thus, in the natural state, the stability of the third telescopic component 4 can be guaranteed.

[0066] Preferably, the support frame further includes a single-hole hinge 3 and a main hinge support 12. The single-hole hinge 3 and the main hinge support 12 are far apart from each other and are both fixed to the mounting plate 1. One end of the connecting rod 2 and one end of the second telescopic component 9 are respectively hinged to the single-hole hinge 3 and the hinge support 12. The center line of the hinge hole of the single-hole hinge 3 is perpendicular to the center line of the hinge hole of the hinge support 12.

[0067] Specifically, the center line of the hinge hole of the single-hole hinge 3 is perpendicular to the center line of the hinge hole of the hinge support 12, which can prevent the connecting rod 2 and the second telescopic component 9 from tipping over.

[0068] Preferably, the test bench further includes at least one pad 6 and at least one secondary hinge support 7. The pad 6 is disposed between the two support frames, and the secondary hinge support 7 is fixedly connected to the pad 6. A first shock absorber 22 is installed at one end of the first telescopic component 8, and the first shock absorber 22 is hinged to the secondary hinge support 7.

[0069] Specifically, the first shock absorber 22 can reduce the vibration of the aircraft engine itself and play a protective role for the aircraft engine.

[0070] Preferably, there are two first telescopic components 8, and the other end of the two first telescopic components 8 is used for rotatable connection with two mounting joints.

[0071] Specifically, two first telescopic components 8 are set to improve stability when adjusting the aircraft engine.

[0072] Preferably, after the test bench is fully installed, the mounting plate 1, the connecting rod 2 and the second telescopic component 9 form a triangular shape, and the mounting plate 1, the connecting rod 2 and the third telescopic component 4 form a triangular shape.

[0073] Specifically, the triangular shape has good stability and a simple structure, which facilitates the disassembly and installation of aircraft engines.

[0074] In summary, when the attitude angle adjustable aero-engine test bench provided by the present invention is implemented, the aero-engine is placed on the attitude angle adjustable aero-engine test bench by means of a hoist or tooling. The main mounting joints on both sides of the aero-engine pass through the center holes of the two second shock absorbers 10 respectively. The auxiliary mounting joint above the tail nozzle of the aero-engine is connected by the first telescopic assembly 8 and has a rotating joint. Since the first shock absorber 22 is installed at one end of the first telescopic assembly 8 and the first shock absorber 22 is hinged on the auxiliary hinge support 7, the rigid impact between the aero-engine and the test bench can be reduced when the aero-engine starts by the cooperation of the second shock absorber 8 and the first shock absorber 22.

[0075] When it is necessary to adjust the angle of attack or attitude angle of the aero-engine, the first locking nut 20 is loosened. Since the inner sides of the two ends of the first sleeve 19 are respectively provided with the first left-hand internal thread and the first right-hand internal thread, when the first left-hand tie rod 18 and the first right-hand tie rod 21 are respectively hinged to the auxiliary mounting joint and the mounting plate 1 above the tail nozzle of the aero-engine, the first sleeve 19 is rotated, and the length of the first telescopic component 8 will change. The main mounting joints on both sides of the aero-engine will rotate in the two second shock absorbers 10 and tilt around the main mounting joint as the center, thereby changing the angle of attack or attitude angle of the aero-engine.

[0076] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. An attitude-angle adjustable aero-engine test bench, characterized in that, The test bench includes: Mounting plate; Two support frames are symmetrically arranged on the mounting plate, and the tops of the two support frames are respectively used to rotatably connect with the main mounting structures on both sides of the aero-engine; At least one first telescopic component is provided, the first telescopic component is disposed between the two support frames, one end of the first telescopic component is equipped with a first shock absorber, one end of the first telescopic component is hinged to the mounting plate, and the other end of the first telescopic component is used to rotatably connect with the auxiliary mounting structure above the tail nozzle of the aero-engine. The support frame includes a connecting rod and a second telescopic assembly. One end of the connecting rod and one end of the second telescopic assembly are away from each other and are both hinged to the mounting plate. The other end of the connecting rod and the other end of the second telescopic assembly are hinged to each other. The test bench also includes a double-hole hinge and two third telescopic components. The double-hole hinge is disposed between the two support frames. One end of the two third telescopic components is hinged to the double-hole hinge, and the other end of the two third telescopic components is respectively hinged to the side wall of the two connecting rods. The first telescopic component includes: The first sleeve has a first left-hand internal thread and a first right-hand internal thread on the inner sides of its two ends, respectively; A first left-hand pull rod and a first right-hand pull rod, wherein the first left-hand pull rod passes through one end of the first sleeve and is threadedly connected to the first left-hand internal thread, and the first right-hand pull rod passes through the other end of the first sleeve and is threadedly connected to the first right-hand internal thread; The other end of the connecting rod is provided with a circular hole, and a second shock absorber is installed inside the circular hole. The center hole of the second shock absorber is used to insert the corresponding main mounting joint.

2. The attitude angle adjustable aero-engine test bench according to claim 1, characterized in that, The second telescopic component includes: The second sleeve has a second left-hand internal thread and a second right-hand internal thread on the inner sides of its two ends, respectively. The second left-hand pull rod and the second right-hand pull rod are connected. The second left-hand pull rod passes through one end of the second sleeve and is threadedly connected to the second left-hand internal thread. The second right-hand pull rod passes through the other end of the second sleeve and is threadedly connected to the second right-hand internal thread.

3. The attitude angle adjustable aero-engine test bench according to claim 1, characterized in that, The third telescopic component includes: The third sleeve has a third left-hand internal thread and a third right-hand internal thread on the inner sides of its two ends, respectively; The third left-hand pull rod and the third right-hand pull rod are respectively connected. The third left-hand pull rod passes through one end of the third sleeve and is threadedly connected to the third left-hand internal thread. The third right-hand pull rod passes through the other end of the third sleeve and is threadedly connected to the third right-hand internal thread.

4. The attitude angle adjustable aero-engine test bench according to claim 1, characterized in that, The support frame also includes a single-hole hinge and a main hinge support. The single-hole hinge and the hinge support are far apart from each other and are both fixed to the mounting plate. One end of the connecting rod and one end of the second telescopic component are respectively hinged to the single-hole hinge and the hinge support. The center line of the hinge hole of the single-hole hinge is perpendicular to the center line of the hinge hole of the hinge support.

5. The attitude angle adjustable aero-engine test bench according to claim 1, characterized in that, The number of the first telescopic components is two, and the other end of the two first telescopic components is used for rotatable connection with the two sub-mounting joints.

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