Propeller power assembly test board
By designing a propeller powertrain test bench, the problem of high testing costs during the improvement phase of piston aero engines was solved, achieving convenient acquisition of test parameters and cost reduction.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- MIANYANG EFOUNTEX INTELLIGENT EQUIP CO LTD
- Filing Date
- 2025-05-12
- Publication Date
- 2026-05-01
AI Technical Summary
In the existing technology, propeller testing during the improvement phase of piston aero engines is costly, and there is a lack of testing equipment that facilitates timely acquisition of relevant test parameters during the improvement process.
A propeller powertrain test bench was designed, including a bench, support frame, mounting bracket, drive shaft, torque sensor, force sensor, data acquisition box and fuel system, for conducting propeller-driven tests on piston aero engines in an open outdoor field, and for real-time acquisition and processing of parameters such as thrust, thrust and torque.
It enables convenient acquisition of test parameters during the improvement process, reduces testing costs, supports comprehensive testing within the enterprise, and improves testing efficiency.
Smart Images
Figure CN224189544U_ABST
Abstract
Description
A propeller powertrain test bench Technical Field
[0001] This utility model relates to the field of piston aero-engine testing technology, and in particular to a propeller powertrain test bench. Background Technology
[0002] Piston-type aircraft engine propeller testing typically involves endurance testing and propeller compatibility testing. This is a necessary process for aircraft (low-altitude aircraft) to obtain airworthiness certificates and undergo relevant performance tests. During the testing process, various operations such as acceleration, deceleration, and even shutdown of the engine are performed. Thrust, thrust, torque, generator voltage, generator current, temperature, and speed are obtained during the testing process to complete the propeller powertrain testing. This allows for a rapid assessment of important parameters such as climb power and cruise power of the propeller powertrain for aircraft compatibility, providing customers with necessary technical parameters to improve engine performance, propeller performance, and propeller-engine compatibility.
[0003] Currently, piston-type aero engines need to be sent to specialized wind turbine and propeller testing laboratories for testing. However, these tests are mainly suitable for obtaining test reports at the finished engine stage. Continuing to conduct tests during the improvement stage is costly. When testing is required during engine improvement, a test bench that facilitates comprehensive testing is needed to obtain relevant parameters in a timely manner. Summary of the Invention
[0004] (a) Technical issues
[0005] The purpose of this invention is to provide a propeller powertrain test bench, which is designed to perform propeller-driven tests on piston aircraft engines, facilitating timely access to relevant test parameters during the improvement process.
[0006] (II) Technical Solution
[0007] To achieve the above objectives, this utility model provides the following technical solution:
[0008] A propeller powertrain test bench includes a frame and a support frame fixed on the frame. A mounting bracket is fixed on the support frame for mounting a piston-type aircraft engine. A propeller is connected to the output shaft of the piston-type aircraft engine. A drive shaft is rotatably mounted on the support frame and connected to the output shaft of the piston-type aircraft engine. A torque sensor and a force sensor are connected to the drive shaft. The frame is equipped with a data acquisition box for the test parameters of the torque and force sensors, and an electrical control box for controlling the piston-type aircraft engine. A fuel system for supplying fuel to the piston-type aircraft engine is also provided on the frame.
[0009] Preferably, the mounting bracket comprises multiple rectangular steel pipes welded together to form a triangular frame structure, the frame structure having a mounting cavity for mounting a piston-type aircraft engine.
[0010] Preferably, a tie rod is provided between the support frame and the platform.
[0011] Preferably, a platform base is fixedly installed on the frame, and rotating seats are provided at intervals on the platform base, with the transmission spindle rotatably installed on the rotating seats.
[0012] Preferably, the support frame is equipped with a docking flange and a transition bracket connected to the docking flange, and the transition bracket is connected to the mounting bracket.
[0013] Preferably, a protective net is also installed on the top of the support frame.
[0014] Preferably, both sides of the support frame are fixed with anchoring lugs, which are used to bolt ground anchoring chains.
[0015] Preferably, the platform comprises multiple rectangular steel pipes, which are welded together to form a rectangular frame structure.
[0016] Preferably, the support frame is also equipped with a water tank radiator and an oil cooler for cooling the piston-type aircraft engine.
[0017] Preferably, the bottom of the platform is equipped with multiple casters at intervals, and the casters are integrated with a braking structure.
[0018] (III) Beneficial Effects
[0019] A stable support structure is formed by a test bench and a support frame. A mounting bracket is integrated on the support frame for mounting the piston engine. The output shaft of the piston engine is connected to a propeller, thus enabling propeller-driven testing. At the same time, a transmission main shaft and integrated torque and force sensors are set on the support frame to monitor parameters such as thrust, thrust, and torque during the test. These parameters are processed and transmitted through an integrated data acquisition box. Meanwhile, the operation of the piston aero engine is controlled by an integrated electronic control box, and the fuel system is used to deliver fuel to the piston aero engine.
[0020] This constitutes a small test bench, which can conveniently conduct integrated tests of piston aircraft engines with propellers in open outdoor spaces, and can conveniently provide various parameter tests during the improvement test process. It can also reduce costs for manufacturing companies to conduct various tests internally and can be carried out within the company. Attached Figure Description
[0021] Figure 1 is a three-dimensional structural schematic diagram of an embodiment of the present utility model;
[0022] Figure 2 is a top view of the structure of an embodiment of the present utility model;
[0023] Figure 3 is a front view structural schematic diagram of an embodiment of the present utility model;
[0024] Figure 4 is a schematic diagram of the left-side structure of an embodiment of the present invention;
[0025] Figure 5 is a schematic diagram of the right-side structure of an embodiment of the present utility model;
[0026] In Figures 1 to 5, the correspondence between component names or lines and the attached drawing numbers is as follows:
[0027] Piston-type aircraft engine 100, propeller 200, stand 1, support frame 2, mounting bracket 3, drive shaft 4, torque sensor 5, force sensor 6, data acquisition box 7, electrical control box 8, fuel system 9, tie rod 10, platform base 11, rotating seat 12, docking flange 13, transition bracket 14, protective net 15, anchoring lug 16, caster wheel 17. Detailed Implementation
[0028] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.
[0029] Referring to Figures 1-5, this embodiment of the invention proposes a propeller powertrain test bench, including a bench 1 and a support frame 2 fixed on the bench 1. A mounting bracket 3 is fixed on the support frame 2, which is used to mount a piston-type aircraft engine 100. A propeller 200 is connected to the output shaft of the piston-type aircraft engine 100. The bench 1 and support frame 2 form a stable support structure, reliably fixing the mounting bracket 3, facilitating the assembly and disassembly of the piston-type aircraft engine 100 on the mounting bracket 3. The propeller 200 is a finished product that will actually be assembled into the aircraft, thus testing the piston-type aircraft engine 100 under propeller-driven conditions. Specifically, during the testing process, parameters such as thrust / pull force, torque, generator voltage, generator current, temperature, and speed of the piston-type aircraft engine 100 need to be tested. This allows for rapid evaluation of important parameters such as the climb power and cruise power of the propeller 200 powertrain for aircraft compatibility, providing necessary technical parameters for improving the performance of the piston-type aircraft engine 100, the propeller 200, and propeller-engine compatibility.
[0030] Therefore, a drive shaft 4 is rotatably mounted on the support frame 2. The drive shaft 4 is connected to the output shaft of the piston-type aircraft engine 100. A torque sensor 5 and a force sensor 6 are connected to the drive shaft 4. During the test, the torque parameter can be obtained through the torque sensor 5, and the push / pull force parameter can be obtained through the force sensor 6. At the same time, a data acquisition box 7 for the test parameters of the torque sensor 5 and the force sensor 6 is installed on the test bench 1. The data acquisition box 7 adopts mature technology and is used to collect parameters such as push / pull force, torque, generator voltage, generator current, temperature, and speed. Therefore, it is also necessary to connect the detection terminals in the data acquisition box 7 to the signal terminal of the piston-type aircraft engine 100, so that various test data can be collected and transmitted externally through the data acquisition box 7.
[0031] It also includes an electrical control box 8 for controlling the piston-type aircraft engine 100. The test bench 1 is equipped with a fuel system 9 for supplying fuel to the piston-type aircraft engine 100. The electrical control box 8 is a PLC control box, which mainly controls the various components. The fuel system 9 has storage bottles and delivery pump pipelines, which can continuously supply fuel to the piston-type aircraft engine 100. The fuel includes one of gasoline, diesel, aviation kerosene or hydrogen.
[0032] Specifically, the parameter acquisition and processing for the specific testing process are directly applied from existing technologies. This embodiment does not protect the specific testing methods, but mainly proposes a test bench structure that can quickly disassemble and assemble the piston-type aero-engine 100 for testing.
[0033] The mounting bracket 3 needs to have a stable structure and be able to meet good load-bearing strength requirements. The mounting bracket 3 includes multiple rectangular steel pipes, which are welded to form a triangular frame structure. The frame structure has a mounting cavity for mounting the piston-type aircraft engine 100. The triangular frame structure can ensure the structural stability of the mounting bracket 3 and maintain a good load-bearing state after the piston-type aircraft engine 100 is installed, without the risk of collapse.
[0034] Meanwhile, in order to improve the load-bearing strength of the support frame 2, a diagonal tie rod 10 is provided between the support frame 2 and the platform 1. The diagonal tie rod 10 forms a reinforced connection, thereby improving the stability of the support frame 2 when it is installed on the platform 1.
[0035] In order to provide stable support for the transmission main shaft 4 and ensure that the transmission main shaft 4 can rotate synchronously with the output shaft of the piston aircraft engine 100, a platform base 11 is fixedly installed on the frame. Rotary seats 12 are provided at intervals on the platform base 11, and the transmission main shaft 4 is rotatably installed on the rotating seats 12.
[0036] Meanwhile, a docking flange 13 and a transition bracket 14 connected to the docking flange 13 are installed on the support frame 2. The transition bracket 14 is connected to the mounting bracket 3. The docking flange 13 is also used to fasten the connection end of the piston aircraft engine 100, while the transition bracket 14 can form a transition connection when the piston aircraft engine 100 is installed, so as to ensure the good load-bearing performance of the mounting bracket 3.
[0037] Meanwhile, a protective net 15 is also installed on the top of the support frame 2 to prevent the propeller 200 from blowing debris to the rear end and causing impact risks to various components.
[0038] Specifically, to prevent the entire test bench from moving during the test, anchoring lugs 16 are fixed on both sides of the support frame 2. The anchoring lugs 16 are used to connect to the ground anchoring chain. Before the test, the entire test bench is connected to the anchoring lugs 16 through the ground anchoring chain to form a relative limit, avoiding the risk of the test bench moving due to the force generated by the rotation of the propeller 200.
[0039] The test bench 1 needs to have strong stability to provide good support during the testing process. Specifically, the test bench 1 includes multiple rectangular steel pipes welded together to form a rectangular frame structure. This rectangular frame structure has a large footprint, resulting in higher overall stability of the test bench on the ground. Meanwhile, multiple casters 17 are installed at intervals at the bottom of the test bench 1. Each caster 17 integrates a braking mechanism. Movement is achieved through the casters 17, while during testing, the braking mechanism locks the casters in place. The casters 17 with braking mechanisms are mature products directly applied.
[0040] Meanwhile, the support frame 2 is also equipped with a water tank radiator and an oil cooler for cooling the piston aircraft engine 100. The commonly used water tank radiator and oil cooler are used to cool the piston aircraft engine 100, thereby improving the stability during the test.
[0041] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.
[0042] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.
[0043] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.
Claims
1. A propeller powertrain test bench, characterized in that: The device includes a test bench (1) and a support frame (2) fixed on the test bench (1). A mounting bracket (3) is fixed on the support frame (2). The mounting bracket (3) is used to install a piston-type aircraft engine (100). A propeller (200) is connected to the output shaft of the piston-type aircraft engine (100). A transmission main shaft (4) is rotatably mounted on the support frame (2). The transmission main shaft (4) is connected to the output shaft of the piston-type aircraft engine (100). A torque sensor (5) and a force sensor (6) are connected to the transmission main shaft (4). A data acquisition box (7) for the test parameters of the torque sensor (5) and the force sensor (6) is installed on the test bench (1). An electrical control box (8) for controlling the piston-type aircraft engine (100) is also installed on the test bench (1). A fuel system (9) for supplying fuel to the piston-type aircraft engine (100) is provided on the test bench (1).
2. The propeller powertrain test bench according to claim 1, characterized in that: The mounting bracket (3) includes multiple rectangular steel pipes, which are welded to form a triangular frame structure. The frame structure has a mounting cavity for mounting a piston-type aircraft engine (100).
3. The propeller powertrain test bench according to claim 2, characterized in that: A tie rod (10) is provided between the support frame (2) and the platform (1).
4. The propeller powertrain test bench according to claim 3, characterized in that: A platform base (11) is fixedly installed on the frame, and a rotating seat (12) is provided at intervals on the platform base (11). The transmission main shaft (4) is rotatably installed on the rotating seat (12).
5. A propeller powertrain test bench according to claim 4, characterized in that: The support frame (2) is equipped with a docking flange (13) and a transition bracket (14) connected to the docking flange (13), and the transition bracket (14) is connected to the mounting bracket (3).
6. A propeller powertrain test bench according to claim 5, characterized in that: The top of the support frame (2) is also equipped with a protective net (15).
7. A propeller powertrain test bench according to claim 6, characterized in that: Anchoring lugs (16) are fixed on both sides of the support frame (2), and the anchoring lugs (16) are used to bolt ground anchor chains.
8. A propeller powertrain test bench according to claim 7, characterized in that: The platform (1) includes multiple rectangular steel pipes, which are welded together to form a rectangular frame structure.
9. A propeller powertrain test bench according to claim 8, characterized in that: The support frame (2) is also equipped with a water tank radiator and an oil cooler for cooling the piston-type aircraft engine (100).
10. A propeller powertrain test bench according to claim 8, characterized in that: The bottom of the platform (1) is equipped with multiple casters (17) at intervals, and the casters (17) are equipped with brake structures.