Fly-launch performance matching verification test system
The integrated flight-engine performance matching verification test system realistically simulates the working state of the aircraft's intake and exhaust systems, solving the shortcomings of flight-engine matching performance verification in the design of aircraft intake and exhaust systems, and achieving more accurate and safer test results.
Patent Information
- Application Number
- CN202511995800.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-26
- Publication Date
- 2026-03-03
AI Technical Summary
In the existing technology, the design of the aircraft intake and exhaust system cannot effectively verify the matching performance between the aircraft and the engine, which may lead to a loss of engine thrust and strength. This is especially true for blended wing-body aircraft, where theoretical calculations cannot determine the rationality of the design.
An aircraft engine performance matching verification test system was designed, including a rigid platform, a power system, a load system, a remote control system, and a test system. Through integrated design, it realistically simulates the working state of the aircraft's intake and exhaust system and performs comprehensive control and monitoring.
It significantly enhances the capability and effectiveness of flight engine matching verification, provides strong technical support for the design and optimization of aircraft intake and exhaust systems, solves the problem that traditional test systems cannot cross-link verification, and improves the safety and accuracy of the test.
Smart Images
Figure CN121590769A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft intake and exhaust system testing technology, and specifically relates to an aircraft engine performance matching verification test system. Background Technology
[0002] In the design of an aircraft's engine intake and exhaust system, ground verification is required to ensure that the designed intake and exhaust pipes are compatible with engine performance. If the design results in significant losses or insufficient strength in engine thrust or stress, it would be extremely dangerous. Current traditional testing systems use the ground-based engine as the core testing component, without integrating the intake, exhaust pipes, and engine for verification.
[0003] In conventionally designed aircraft, engines are mounted on the wings or fuselage, making it easy to address both intake and exhaust issues without requiring complex intake and exhaust systems. However, in blended wing-body aircraft, the engines are embedded within the fuselage, increasing the size of the intake and exhaust systems. Theoretical calculations and design evaluations alone are insufficient to determine the feasibility of the design. Ground testing, on the other hand, can resolve early design issues, promptly identify flaws, and make necessary improvements.
[0004] Therefore, how to ensure the effective verification of the matching performance of the aircraft is a problem that needs to be solved. Summary of the Invention
[0005] To address the aforementioned issues, this application provides a flight engine performance matching verification test system to solve the problem of difficulty in effectively verifying flight engine matching performance in the prior art.
[0006] The technical solution of this application is: a flight engine performance matching verification test system, including a rigid platform, a power system, a load system, a remote control system, a test system, and a slide rail;
[0007] The hardware components of the power system, load system, remote control system, and testing system are mounted on a rigid platform. The load system, remote control system, and testing system are all electrically connected to the power system. The rigid platform is connected to the slide rail using a slider-type connection.
[0008] The power system can drive the slide rail to move, and the remote control system and test system can control the power system; the load system is used to perform load simulation and output simulation data.
[0009] Preferably, the power system includes a fuel supply system, a test piece, and a fixed release device. The fuel supply system is connected to the test piece via a pipeline, and the test piece is detachably connected to the fixed release device.
[0010] Preferably, the test piece includes a power unit, an air intake duct, and an exhaust pipe; the power unit is connected between the air intake duct and the exhaust pipe, and the air intake duct and the exhaust pipe are connected to the load system.
[0011] Preferably, the load system includes a hydraulic load simulation system, an engine load simulation system, and a bleed air load simulation system. The hydraulic load simulation system is used to simulate the hydraulic system, the engine load simulation system is used to simulate the engine, and the bleed air load simulation system is used to simulate bleed air.
[0012] Preferably, the load system is fixedly connected within the power system, and the load system is connected to the test specimen via pipelines and cables.
[0013] Preferably, the load system is connected to a remote control system via a data transmission and power supply cable, and the remote control system is capable of command control and data storage of the load system.
[0014] Preferably, the remote control system includes an on-board power supply and an emergency power supply, which can supply power to the power system, load system, and test system.
[0015] Preferably, the remote control system interacts with the test piece via a second data transmission cable, and the control system monitors and controls the operating status of the test piece.
[0016] Preferably, the remote control system interacts with the fixed release device via a third data transmission cable and controls its release state.
[0017] Preferably, the testing system is capable of collecting data on pressure, temperature, flow rate, vibration, strain, and noise of the test specimen, performing data preprocessing, and transmitting the preprocessed data to a remote control system via a first data transmission cable for further processing of the collected data. The system also controls the start and constraints of the test based on the collected pressure, temperature, flow rate, vibration, strain, and noise data.
[0018] The flight engine performance matching verification test system of this application has the following advantages:
[0019] Through technological innovations in integrated design, realistic simulation, comprehensive control and monitoring, and safety and stability assurance, the shortcomings of existing technologies have been effectively overcome, significantly enhancing the capability and effectiveness of flight-engine matching verification, and providing strong technical support and assurance for the design and optimization of aircraft intake and exhaust systems.
[0020] The power requirements of the test system are all provided by the remote control system. The test system is complete and compact, and can be flexibly configured in an appropriate area. It solves the problem of air intake flow that cannot be simulated by high-altitude test benches and ground test benches, and enhances the shortcomings of flight engine matching verification. Attached Figure Description
[0021] Figure 1 This is a schematic diagram of the overall structure of this application.
[0022] 1. Rigid platform; 2. Power system; 21. Fuel supply system; 22. Test specimen; 23. Fixed release device; 24. Flange; 3. Load system; 31. Hydraulic load simulation system; 32. Generator load simulation system; 33. Bleed air load simulation system; 4. Remote control system; 41. Second data transmission cable; 42. Data transmission cable; 5. Test system; 51. First data transmission cable; 6. Slide rail. Detailed Implementation
[0023] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0024] The first aspect of this application provides a test system for verifying the performance matching of aircraft engines, such as... Figure 1 As shown, it includes a rigid platform 1, a power system 2, a load system 3, a remote control system 4, a testing system 5, and a slide rail 6.
[0025] The hardware components of the power system 2, load system 3, remote control system 4 and test system 5 are located on the rigid platform 1. The load system 3, remote control system 4 and test system 5 are all electrically connected to the power system 2. The rigid platform 1 and the slide rail 6 are connected by a slider.
[0026] The power system 2 can drive the slide rail 6 to move, and the remote control system 4 and the test system 5 can control the power system 2; the load system 3 is used to perform load simulation and output simulation data.
[0027] Each system has one or more sub-users. The power system 2 is supplied with combustion energy by the fuel supply system 21, and then the set driving force is applied to the test specimen 22 to control the test specimen 22 to work according to the set parameters. Then, the test system 5 collects the data of the test specimen 22 and sends it to the remote control system 4 for data processing and performance matching verification.
[0028] The hardware of several key systems (power, load, remote control, and testing) required for the performance matching verification of the aircraft is concentrated on the rigid platform 1, making the entire test system more complete and compact, facilitating overall installation, commissioning, and transportation, and allowing for flexible configuration in appropriate areas.
[0029] The power system 2 provides thrust as the core, while the load system 3 can perform load simulation and output simulation data, which can realistically simulate the various load conditions that the power system 2 will bear during actual flight. The remote control system 4 and the test system 5 control and monitor the power system 2, ensuring the controllability of the test process and the accuracy of the data, which helps to fully verify the performance matching status of the aircraft and engine.
[0030] Preferably, the power system 2 includes a fuel supply system 21, a test piece 22, and a fixed release device 23. The fuel supply system 21 is connected to the test piece 22 via a pipeline, and the test piece 22 is detachably connected to the fixed release device 23, specifically by bolts or flanges 24.
[0031] The fuel supply system 21 is connected to the test piece 22 through a pipeline, which can stably provide combustion energy to the test piece 22 (power unit), ensure the normal operation of the power system 2, and provide a reliable power foundation for the performance verification of the aircraft.
[0032] The fixed release device 23 can disconnect from the test piece 22 under certain circumstances, which can ensure the safety of the test system when necessary and prevent more serious problems caused by abnormalities of the test piece 22.
[0033] Preferably, the test piece 22 includes a power unit, an air intake duct, and an exhaust pipe; the power unit is connected between the air intake duct and the exhaust pipe, and the air intake duct and the exhaust pipe are connected to the load system 3.
[0034] It realistically simulates the actual structure and working state of the aircraft engine's intake and exhaust system, and can more accurately verify the performance state of the aircraft-grade air intake, power plant and exhaust pipe after connection, solving the problem that traditional test systems do not verify the cross-linking of the three.
[0035] Preferably, the load system 3 includes a hydraulic load simulation system 31, an engine load simulation system, and a bleed air load simulation system 33. The hydraulic load simulation system 31 is used to simulate the hydraulic system, the engine load simulation system is used to simulate the engine, and the bleed air load simulation system 33 is used to simulate the bleed air.
[0036] By comprehensively simulating the various loads that the aircraft power system 2 experiences in actual operation through the load system 3, the performance status of the aircraft engine system is more realistically reflected, providing a more comprehensive basis for the performance matching verification of the aircraft engine.
[0037] The load system 3 is fixedly connected within the power system 2, and is connected to the test specimen 22 via pipes and cables. The load system 3 is connected to the remote control system 4 via data transmission and power supply cables, and the remote control system 4 is capable of command control and data storage for the load system 3.
[0038] The load system 3 is connected to the remote control system 4 via a data transmission and power supply cable, enabling the remote control system 4 to remotely control the load system 3. This allows operators to control and manage the test process from a safe distance, improving the safety and convenience of the test.
[0039] Preferably, the remote control system 4 includes an on-board power supply and an emergency power supply, which can supply power to the power system 2, the load system 3, and the test system 5.
[0040] The remote control system 4 interacts with the test piece 22 via the second data transmission cable, and monitors and controls the operating status of the test piece 22.
[0041] The remote control system 4 interacts with the fixed release device 23 via a third data transmission cable and controls its release status.
[0042] The remote control system 4 can acquire real-time operating status information of the test piece 22, such as temperature, pressure, and rotation speed, and accurately control the operating status of the test piece 22 based on this information, ensuring that the test process is carried out according to the predetermined plan, thereby improving the accuracy and safety of the test.
[0043] Preferably, the testing system 5 can collect data on pressure, temperature, flow rate, vibration, strain, and noise from the test specimen 22, perform data preprocessing, and transmit the preprocessed data to the remote control system 4 via the first data transmission cable 51. The system then processes the collected data and controls the start and constraints of the test based on the collected pressure, temperature, flow rate, vibration, strain, and noise data. Preprocessing the collected data removes noise and interference, improving data quality, and then transmitting the preprocessed data to the remote control system 4 via the data transmission cable improves the efficiency and accuracy of data transmission.
[0044] In summary, this application has the following advantages:
[0045] Through technological innovations in integrated design, realistic simulation, comprehensive control and monitoring, and safety and stability assurance, the shortcomings of existing technologies have been effectively overcome, significantly enhancing the capability and effectiveness of flight-engine matching verification, and providing strong technical support and assurance for the design and optimization of aircraft intake and exhaust systems.
[0046] The power requirements of the test system are all provided by the remote control system. The test system is complete and compact, and can be flexibly configured in an appropriate area. It solves the problem of air intake flow that cannot be simulated by high-altitude test benches and ground test benches, and enhances the shortcomings of flight engine matching verification.
[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A test system for verifying the performance matching of aircraft engines, characterized in that, It includes a rigid platform (1), a power system (2), a load system (3), a remote control system (4), a testing system (5), and a slide rail (6); The hardware components of the power system (2), load system (3), remote control system (4) and test system (5) are mounted on the rigid platform (1). The load system (3), remote control system (4) and test system (5) are all electrically connected to the power system (2). The rigid platform (1) and the slide rail (6) are connected by a slider. The power system (2) can drive the slide rail (6) to move, and the remote control system (4) and the test system (5) can control the power system (2); the load system (3) is used to perform load simulation and output simulation data.
2. The flight engine performance matching verification test system as described in claim 1, characterized in that, The power system (2) includes a fuel supply system (21), a test piece (22) and a fixed release device (23). The fuel supply system (21) and the test piece (22) are connected by a pipeline, and the test piece (22) and the fixed release device (23) are detachably connected.
3. The flight engine performance matching verification test system as described in claim 2, characterized in that, The test piece (22) includes a power unit, an air intake and an exhaust pipe; the power unit is connected between the air intake and the exhaust pipe, and the air intake and the exhaust pipe are connected to the load system (3).
4. The flight engine performance matching verification test system as described in claim 2, characterized in that, The load system (3) includes a hydraulic load simulation system (31), an engine load simulation system, and a bleed air load simulation system (33). The hydraulic load simulation system (31) is used to simulate the hydraulic system, the engine load simulation system is used to simulate the engine, and the bleed air load simulation system (33) is used to simulate bleed air.
5. The flight engine performance matching verification test system as described in claim 4, characterized in that, The load system (3) is fixedly connected to the power system (2), and the load system (3) is connected to the test piece (22) through pipelines and cables.
6. The flight engine performance matching verification test system as described in claim 4, characterized in that, The load system (3) is connected to the remote control system (4) via a data transmission and power supply cable. The remote control system (4) is capable of command control and data storage of the load system (3).
7. The flight engine performance matching verification test system as described in claim 2, characterized in that, The remote control system (4) includes an on-board power supply and an emergency power supply, which can supply power to the power system (2), the load system (3) and the test system (5).
8. The flight engine performance matching verification test system as described in claim 7, characterized in that, The remote control system (4) interacts with the test piece (22) via the second data transmission cable, and monitors and controls the operating status of the test piece (22).
9. The flight engine performance matching verification test system as described in claim 8, characterized in that, The remote control system (4) interacts with the fixed release device (23) via a third data transmission cable and controls its release status.
10. The flight engine performance matching verification test system as described in claim 2, characterized in that, The test system (5) can collect data on pressure, temperature, flow rate, vibration, strain and noise of the test piece (22), perform data preprocessing, and transmit the preprocessed data to the remote control system (4) through the first data transmission cable (51) for data processing, and control the start and constraints of the test based on the collected pressure, temperature, flow rate, vibration, strain and noise data.