Rotor nacelle ground comprehensive test device and method

Abstract

The present application belongs to the technical field of tilt rotor aircraft, and discloses a rotor nacelle ground comprehensive test device and method; wherein the rotor nacelle ground comprehensive test device comprises a tower base, a first transition piece, a second transition piece, a wing test piece, a fuselage test piece and a balance system; wherein the top end of the tower base is provided with a first connecting part, a second connecting part and a third connecting part; the top side of the tower base is provided with a fourth connecting part and a fifth connecting part; the balance system is used for measuring the functional performance characteristic parameters of the rotor nacelle system to be tested during simulation test. The present application can carry out rotor nacelle component level / system level test, can fully verify the functional reliability and performance characteristics of the rotor nacelle, the test link is reliable, and can effectively support the tilt rotor aircraft model development.

Description

Technical Field

[0001] This invention belongs to the field of tiltrotor aircraft technology, and specifically relates to a ground integrated test device and method for a rotor nacelle. Background Technology

[0002] Tiltrotor aircraft, combining the vertical takeoff and landing capabilities of helicopters with the high-speed cruise performance of fixed-wing aircraft, represent a key development direction for future aviation equipment and have garnered significant attention from major aerospace research institutions worldwide in recent years. The rotor nacelle is a crucial core component of tiltrotor aircraft and a key factor determining their successful development; furthermore, a high-performance and reliable rotor nacelle is essential for ensuring the successful development of tiltrotor aircraft.

[0003] Currently, the development and testing methods for rotor nacelles generally follow existing ground testing methods for traditional helicopter rotor systems. Specifically, this includes: first, component testing and verification on a rotor test bench, and then comprehensive ground testing and verification of the entire aircraft on a "ground-based integrated test bench." However, these existing ground testing methods do not consider the tilting dynamic characteristics of tiltrotor rotor nacelles, nor the aerodynamic interference characteristics between the rotor nacelle and the wing / fuselage / rotor. They lack component-level / system-level "modular" testing and verification, resulting in poor reliability of key single-aircraft system engineering testing and verification. Summary of the Invention

[0004] The purpose of this invention is to provide a ground-based integrated testing device and method for rotor nacelles to solve one or more of the aforementioned technical problems. The technical solution provided by this invention can conduct component-level / system-level testing of rotor nacelles, fully verifying the functional reliability and performance characteristics of the rotor nacelles. The testing process is reliable and can effectively support the development of tiltrotor aircraft models.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] In a first aspect, the present invention provides a ground-based integrated test apparatus for a rotor nacelle, comprising: a tower base, a first transition component, a second transition component, a wing test component, a fuselage test component, and a balance system; wherein,

[0007] The top of the tower base is provided with a first connecting part, a second connecting part, and a third connecting part. The first connecting part is used to install the first transition piece during simulation testing. The second connecting part is used to install the fuselage test piece during simulation testing. The third connecting part is used to install the rotor nacelle system to be tested during simulation testing. The top side of the tower base is provided with a fourth connecting part and a fifth connecting part. The fourth connecting part is used to install the second transition piece during simulation testing. The fifth connecting part is used to install the wing test piece during simulation testing. The balance system is used to measure the functional performance characteristics of the rotor nacelle system to be tested during simulation testing.

[0008] A further improvement of the present invention is that it also includes: a universal adjustment mechanism;

[0009] When simulating and testing the functional performance characteristics at different attitude angles, the lower end of the first transition piece is fixedly connected to the tower base through the first connecting part, and the upper end of the first transition piece is connected to the rotor nacelle system to be tested through the universal adjustment mechanism.

[0010] A further improvement of the present invention is that the universal adjustment mechanism adopts a cross universal joint or a ball cage universal joint.

[0011] A further improvement of the present invention is that it further includes: a tilt adjustment mechanism;

[0012] When simulating and testing the functional performance characteristics at different tilt angles, one end of the second transition piece is fixedly connected to the tower base through the fourth connecting part, and the other end of the second transition piece is connected to the rotor nacelle system to be tested through the tilt adjustment mechanism.

[0013] A further improvement of the present invention is that the tilt adjustment mechanism adopts a slider connecting rod or a ball screw.

[0014] A further improvement of the present invention is that the balance system includes a six-component balance and a torque balance.

[0015] A further improvement of the present invention is that the functional performance characteristic parameters are one or more of the following: thrust, drag, side force, pitching moment, rolling moment, yaw moment, and system torque of the rotor nacelle system under test.

[0016] In a second aspect, the present invention provides a ground-based integrated testing method for rotor nacelles, implemented based on the ground-based integrated testing apparatus for rotor nacelles described in the first aspect of the present invention. The ground-based integrated testing method for rotor nacelles includes the following steps:

[0017] Step 1: A rotor nacelle system to be tested is fixedly installed on the tower base through the third connecting part, driven by an electric drive system, and the aerodynamic performance parameters of the rotor nacelle system under different collective pitch and cyclic pitch are measured by a balance system.

[0018] Step 2: Fix the first transition piece to the tower base through the first connecting part, install a rotor nacelle system to be tested on the first transition piece, drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system to be tested at the set attitude angle through the balance system.

[0019] Step 3: Fix the second transition piece to the tower base through the fourth connecting part, install a rotor nacelle system to be tested on the second transition piece, drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system to be tested at the set tilt angle through the balance system.

[0020] Step 4: Fix one side of the wing test piece to the tower base through the fifth connecting part, install a rotor nacelle system to be tested on the wing test piece, drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system under the set single-sided wing test piece working condition through the balance system.

[0021] Step 5: Fix the fuselage test piece to the tower base via the second connecting part, and fix one side of the wing test piece to the tower base via the fifth connecting part; install a rotor nacelle system to be tested on the wing test piece, drive it via an electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system to be tested under the conditions of the fuselage test piece and the wing test piece on one side via a balance system;

[0022] Step 6: Fix the fuselage test piece to the tower base via the second connecting part, and fix the wing test piece to the tower base on both sides via the fifth connecting part; install the two rotor nacelle systems to be tested on the wing test pieces on both sides respectively, drive them via an electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle systems to be tested under the conditions of the fuselage test piece and the two wing test pieces via a balance system.

[0023] A further improvement of the present invention is that the rotor nacelle ground integrated test device further includes: a universal adjustment mechanism and a tilt adjustment mechanism;

[0024] Step 2 specifically includes: fixing the first transition piece to the tower base through the first connecting part, installing a rotor nacelle system to be tested on the first transition piece through the universal adjustment mechanism, driving it through the electric drive system, and measuring the aerodynamic performance parameters of the rotor nacelle system under different attitude angles through the balance system;

[0025] Step 3 specifically includes: fixing the second transition piece to the tower base through the fourth connecting part, installing a rotor nacelle system to be tested on the second transition piece through the tilt adjustment mechanism, driving it through the electric drive system, and measuring the aerodynamic performance parameters of the rotor nacelle system under different tilt angles through the balance system.

[0026] A further improvement of the present invention is that it further includes:

[0027] Step 7: Compare the aerodynamic performance parameters obtained in Step 2 with those obtained in Step 1 to obtain the analysis results of the influence of different factors on aerodynamic performance, revealing the aerodynamic interference characteristics of the rotor and nacelle structure; compare the aerodynamic performance parameters obtained in Step 3 with those obtained in Steps 1 and 2 to obtain the analysis results of the influence of different factors on aerodynamic performance, revealing the aerodynamic performance influence law under tilt dynamic inflow distortion, and verifying the functional reliability and durability of the components of the rotor nacelle system under test; compare the aerodynamic performance parameters obtained in Step 4 with those obtained in Steps 1, 2, and 3 to obtain the analysis results of the influence of the wing test piece on the aerodynamic performance of the rotor nacelle system under test, revealing the aerodynamic interference characteristics of the rotor nacelle system under test and the wing test piece, and verifying the "…" of the rotor nacelle system under test. The flight speed at the "flutter" stall boundary and the functional reliability and durability of the components are analyzed. The aerodynamic performance parameters obtained in step 5 are compared with those obtained in steps 1, 2, 3, and 4 to obtain the analysis results of the influence of the fuselage test component on the aerodynamic performance of the rotor nacelle system under test, revealing the aerodynamic interference characteristics between the rotor nacelle system under test and the fuselage test component, and verifying the functional reliability and durability of the components of the rotor nacelle system under test. The aerodynamic performance parameters obtained in step 6 are compared with those obtained in steps 1, 2, 3, 4, and 5 to obtain the analysis results of the aerodynamic performance influence between the rotor nacelle systems under test, revealing the aerodynamic interference characteristics between the rotors of different rotor nacelle systems under test, and verifying the functional reliability and durability of the components of the rotor nacelle system under test.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] To address the technical problems of poor reliability in the testing and verification of tiltrotor nacelles, this invention proposes a ground-based integrated testing device for tiltrotor nacelles. This device can conduct component-level / system-level tests on the tiltrotor nacelles, fully verifying their functional reliability and performance characteristics. The testing process is reliable and can effectively support the development of tiltrotor aircraft models.

[0030] This invention provides a ground-based integrated test method for rotor nacelles, employing a "building block" test verification approach. The test steps are progressive and each step is reliable. This allows for the phased and comprehensive verification of the functional reliability and performance characteristics of rotor nacelles at the component / system level. It can fully expose functional performance defects of components / systems at different test verification stages, reveal the influence of different factors on their performance under different conditions, significantly shorten the aircraft model development cycle, effectively reduce process risks in model development, and thus reduce the exposure of flight safety issues during the model development process. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art are briefly introduced below; obviously, the drawings described below are some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of the structure in which the rotor nacelle ground integrated test device is directly connected to the rotor nacelle system under test in an embodiment of the present invention;

[0033] Figure 2 This is a schematic diagram of the structure in which the rotor nacelle ground integrated test device and the rotor nacelle system to be tested are connected through the first transition piece in an embodiment of the present invention;

[0034] Figure 3 This is a schematic diagram of the structure in which the rotor nacelle ground integrated test device and the rotor nacelle system to be tested are connected by a second transition piece in an embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of the structure in which the rotor nacelle ground integrated test device and the rotor nacelle system under test are connected through a wing test component in an embodiment of the present invention;

[0036] Figure 5 This is a schematic diagram of the structure of the rotor nacelle ground integrated test device and the rotor nacelle system to be tested connected by a wing test component and a fuselage test component in an embodiment of the present invention.

[0037] Figure 6 This is a schematic diagram of the overall structure of the rotor nacelle ground integrated test device and the rotor nacelle system to be tested, which are connected by wing test components and fuselage test components, in an embodiment of the present invention.

[0038] Figure 7 This is a flowchart illustrating a ground-based integrated test method for a rotor nacelle provided in an embodiment of the present invention;

[0039] The following are explanations of the reference numerals in the diagram: 1. Tower base; 2. Rotor nacelle system to be tested; 3. Balance system; 4. First transition piece; 5. Second transition piece; 6. Wing test piece; 7. Fuselage test piece. Detailed Implementation

[0040] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0041] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0042] The present invention will now be described in further detail with reference to the accompanying drawings:

[0043] This invention provides a ground-based integrated test device for a rotor nacelle, comprising: a tower base 1, a first transition component 4, a second transition component 5, a wing test component 6, a fuselage test component 7, and a balance system 3; wherein,

[0044] The top of the tower base 1 is provided with a first connecting part, a second connecting part, and a third connecting part. The first connecting part is used to install the first transition piece 4 during simulation testing. The second connecting part is used to install the fuselage test piece 7 during simulation testing. The third connecting part is used to install the rotor nacelle system 2 to be tested during simulation testing. The top side of the tower base 1 is provided with a fourth connecting part and a fifth connecting part. The fourth connecting part is used to install the second transition piece 5 during simulation testing. The fifth connecting part is used to install the wing test piece 6 during simulation testing. The balance system 3 is used to measure the functional performance characteristics of the rotor nacelle system 2 to be tested during simulation testing.

[0045] In a further preferred embodiment of the present invention, the invention further includes: a universal adjustment mechanism; when simulating and testing the functional performance characteristics at different attitude angles, the lower end of the first transition piece 4 is fixedly connected to the tower base 1 through the first connecting part, and the upper end of the first transition piece 4 is connected to the rotor nacelle system 2 to be tested through the universal adjustment mechanism.

[0046] In a further preferred embodiment of the present invention, the invention further includes: a tilt adjustment mechanism; when simulating and testing the functional performance characteristics at different tilt angles, one end of the second transition piece 5 is fixedly connected to the tower base 1 through the fourth connecting part, and the other end of the second transition piece 5 is connected to the rotor nacelle system 2 to be tested through the tilt adjustment mechanism.

[0047] In a specific and exemplary embodiment of the present invention, the balance system 3 includes a six-component balance and a torque balance, which are respectively installed on the shaft system of the rotor nacelle to be tested, the first transition piece 4, and the second transition piece 5, and can be connected by bolts.

[0048] Further illustratively, in this embodiment of the invention, the first transition member 4 can be referred to as the upper transition member, and is used to be fixedly installed on the top of the tower base 1 via the first connecting part; specifically, it can be connected by bolts. The second transition member 5 can be referred to as the side transition member, and is used to be fixedly installed on the top side of the tower base 1 via the fourth connecting part; specifically, it can be connected by bolts. The fuselage test member 7 and the wing test member 6 are consistent with the aerodynamic shape and installation interface of the model aircraft, and are respectively used to be installed on the top and top side of the tower base 1 via the second connecting part and the fifth connecting part; specifically, it can be connected by bolts.

[0049] In a specific and exemplary embodiment of the present invention, the balance system 3 includes a six-component balance and a torque balance, used to measure the six force elements of the load on the system under test, specifically the forces in three translational directions and the torques in three rotational directions; wherein, the six-component balance is a ring-type balance with a central perforation, and bolt mounting holes are pre-drilled on the upper and lower ring-type platforms, which are connected and fixed to the system under test and the support system by bolts; specifically, the measurement range of the six-component balance is 0 to 1500 kgf, and the measurement range of the torque balance is 0 to 1000 Nm.

[0050] The technical solutions provided by the above embodiments of the present invention can be used for ground simulation testing of the functional performance characteristics of a single rotor nacelle of a tiltrotor aircraft, as well as its relationship with the wing, fuselage, and rotor. More specifically, the upper mounting support between the rotor nacelle system under test and the tower base is omnidirectionally adjustable, which can be used to measure the functional performance characteristics of the rotor nacelle at different attitude angles; the side mounting support between the rotor nacelle system under test and the tower base is laterally tiltable, which can be used to measure the functional performance characteristics of the rotor nacelle at different tilt angles; the rotor nacelle system under test is connected to the wing / fuselage test component, which can be used to measure the functional performance characteristics of the rotor nacelle and the wing / fuselage / rotor under the actual dimensions of a tiltrotor aircraft. In summary, the technical solutions of the embodiments of the present invention, when applied to the field of tiltrotor aircraft, can effectively enhance the ground testing and verification methods for such aircraft, improve the functional reliability of the rotor nacelle test system, shorten the development cycle of the aircraft model, and reduce product development costs.

[0051] In specific and exemplary embodiments of the present invention, it may also include:

[0052] The data acquisition and processing system includes: a data acquisition terminal, a data transmission system, and a data processing system. The data acquisition terminal is installed on the upper part of the rotor shaft of the rotor nacelle system to be tested and can be connected by bolts to transmit the measured signal wirelessly.

[0053] The central control system includes a control system and a display system. It can be installed in the test room and is mainly used to monitor and display various test parameters of the system under test in real time, and to send and transmit commands and signals of the system under test via wired connection.

[0054] The excitation system includes a hammer and a data acquisition system, which can measure the modal characteristics of the system under test through hammer impact testing.

[0055] Further elaboration suggests that the data acquisition and processing system may include a remote computer, a PXI chassis and host, acquisition boards, supporting signal conversion equipment, power supply, preamplifier, data acquisition and processing programs, etc., mainly used for the acquisition and processing of various balance signals, rotor blade strain signals, vibration signals, temperature signals, angle signals, and main rotor blade azimuth angle signals. The central control system includes a control system and a display system.

[0056] In the specific illustrative embodiments of the present invention, the aforementioned rotor nacelle system to be tested includes a rotor system, an automatic swashplate, a servo system, an electric drive system, a rotor shaft system, a nacelle structure, etc., which are the main components of the system under test.

[0057] Please see Figure 1 and Figure 2In a specific exemplary embodiment of the present invention, the tower base 1 can be truncated cone-shaped, and is provided with a first transition piece, a second transition piece, a wing test piece, a fuselage test piece, and an installation interface for the system under test. Its height range can be between 3m and 10m, and it is used to support the system under test and prevent it from being affected by the rotor's ground effect. The installation interface connecting to the first transition piece and the system under test is located above the tower base, with several φ10 diameter through holes evenly distributed radially along the upper center of the truncated cone, and is fixed to the first transition piece by bolts. The installation interface connecting to the second transition piece is located on the top side of the tower base, with several φ10 diameter through holes radially distributed radially along the center of the tilt axis end face, and is fixed to the second transition piece by bolts. The installation interface connecting to the wing and fuselage test pieces is located on the upper side of the tower base, with multiple rows of 10mm-spaced grooves evenly distributed along the side of the truncated cone end face, and is fixed to the wing and fuselage test pieces by bolts.

[0058] Optionally, the first transition piece is provided with a tower base connection interface, a system under test connection interface, a universal adjustment mechanism, and a balance system installation interface. The tower base connection interface is located below the first transition piece and has several φ10 diameter through holes radially distributed along the boss surface, which are then bolted to the tower base for fixation. The system under test connection interface is located above the first transition piece and connects to the system under test sleeve via a flange, with several φ6 diameter through holes evenly distributed radially, which are bolted for fixation. The lower part of the first transition piece connects to the tower base for fixing the entire rotor nacelle system under test. The upper part connects to the rotor nacelle system under test via the universal adjustment mechanism. A six-component balance and a torque balance are installed in the middle for measuring the aerodynamic characteristics of the rotor nacelle system under test, specifically measuring the tension, drag, side force, pitch moment, roll moment, yaw moment, and system torque of the system under test.

[0059] In a further preferred embodiment of the present invention, the universal adjustment mechanism is either a cross universal joint or a ball-cage universal joint, and has a locking function for controlling the installation angle of the entire system under test. Explained, in the locked state, the aerodynamic performance of the system under test under different collective pitches and periodic pitches can be measured; in the unlocked state, the aerodynamic performance of the system under test under different attitude angles can be verified.

[0060] Please see Figure 3In a specific exemplary embodiment of the present invention, the second transition component includes a tower base mounting interface, a measured system mounting interface, a tilt adjustment mechanism, and a balance system mounting interface. The tower base mounting interface is located on the side of the end face of the second transition component, with several φ10 diameter through holes radially distributed along the center of the end face, and is connected and fixed to the tower base by bolts. The measured system mounting interface is located on the other end face of the second transition component, and is connected to the measured system sleeve via a flange, with several φ6 diameter through holes evenly distributed radially, and is fixed by bolts.

[0061] Optionally, one end of the second transition piece is connected to the tower base for connecting and fixing the entire rotor nacelle system under test, and the other side is installed and connected to the rotor nacelle system under test through a tilt adjustment mechanism. A six-component balance and a torque balance are installed in the middle for measuring the tilt motion characteristics of the entire system under test. Specifically, they are used to measure the tension, drag, lateral force, pitch moment, roll moment, yaw moment, and tilt moment of the system under test. Specifically, the six-component balance is installed around the sleeve of the system under test, and the torque balance is installed on the tilt shaft system.

[0062] In a further preferred embodiment of the present invention, the tilt adjustment mechanism employs either a slider linkage or a ball screw, and has a locking function to control the tilt movement of the entire system under test. Explained, in the locked state, the aerodynamic characteristics of the side of the system under test under different collective pitches and periodic pitches can be measured; in the unlocked state, the aerodynamic characteristics of the system under test under different tilt angles can be verified.

[0063] Please see Figures 4 to 6 In a specific and exemplary embodiment of the present invention, the wing test piece includes a tower base mounting interface and a test system mounting interface. One side of the wing is used to connect to the side of the tower base, and the other side is used to connect to the side of the test rotor nacelle system. Specifically, it is fixed to the side of the tower base via bolts and to the test system via through-hole bolts. The wing test piece maintains the same aerodynamic shape as the actual aircraft model. Additionally, the fuselage test piece includes a tower base mounting interface and a test system mounting interface. One end of the fuselage test piece is used to connect to the side of the tower base, and the other end is used to connect to the side of the test rotor nacelle system. The fuselage test piece maintains the same aerodynamic shape as the wing of the aircraft model.

[0064] Please see Figure 7 The present invention provides a ground integrated test method for a rotor nacelle, which specifically includes the following steps:

[0065] Step 1: A rotor nacelle system 2 to be tested is fixedly installed on the tower base 1 through the third connecting part, driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system 2 under different collective pitch and cyclic pitch are measured by the balance system 3.

[0066] Step 2: The first transition piece 4 is fixedly installed on the tower base 1 through the first connecting part, and a rotor nacelle system 2 to be tested is installed on the first transition piece 4. It is driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system 2 under the set attitude angle are measured by the balance system 3.

[0067] Step 3: The second transition piece 5 is fixedly installed on the tower base 1 through the fourth connecting part. A rotor nacelle system 2 to be tested is installed on the second transition piece 5, driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system 2 under the set tilt angle are measured by the balance system 3.

[0068] Step 4: Fix the wing test piece 6 to the tower base 1 on one side through the fifth connecting part, install a rotor nacelle system 2 to be tested on the wing test piece 6, drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system 2 under the set single-sided wing test piece working condition through the balance system 3.

[0069] Step 5: Fix the fuselage test piece 7 to the tower base 1 through the second connecting part, and fix the wing test piece 6 to the tower base 1 on one side through the fifth connecting part; install a rotor nacelle system 2 to be tested on the wing test piece 6, drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system 2 under the conditions of the fuselage test piece and the wing test piece on one side through the balance system 3;

[0070] Step 6: Fix the fuselage test piece 7 to the tower base 1 via the second connecting part, and fix the wing test piece 6 to the tower base 1 on both sides via the fifth connecting part; install the two rotor nacelle systems 2 to be tested on the wing test pieces 6 on both sides respectively, drive them through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system 2 under the conditions of the fuselage test piece and the two wing test pieces through the balance system 3.

[0071] In a specific embodiment of the present invention, a ground-based integrated test method for rotor nacelles is provided. Based on the test apparatus described above in the embodiments of the present invention, the method specifically includes the following steps:

[0072] Step 1: The rotor nacelle system to be tested is tested on the aforementioned integrated test device to verify its functional performance characteristics. Specifically, the rotor nacelle system to be tested is placed on the tower base and fixed with bolts. A balance system and a data acquisition system are installed on the rotor nacelle system and driven by an electric drive system to measure the aerodynamic performance (three translational loads and three rotational torques) of the rotor nacelle system under different collective pitch and cyclic pitch variations. At the same time, the functional reliability and durability of the components of the tested system can be verified.

[0073] Step 2: Arrange the first transition piece on the aforementioned integrated test device. The first transition piece is equipped with components such as a universal adjustment mechanism and a balance system. Then, install the rotor nacelle system to be tested on the first transition piece. Test and verify the aerodynamic thrust characteristics of the rotor nacelle system under different attitude angles. Specifically, place the first transition piece on the tower base and fix it with bolts at the reserved interface. The first transition piece and the test system are fixed with bolts at the interface on the other side. Driven by the electric drive system, the aerodynamic performance (three translational loads and three rotational torques) of the test system at a certain attitude angle and different attitude angles can be measured respectively. Furthermore, by comparing with Step 1, the influence analysis of different factors (different components, different attitude angles) on the aerodynamic performance of the test system, as well as the aerodynamic interference characteristics of the rotor system and the nacelle V-shaped structure, can be obtained.

[0074] Step 3: Install the second transition piece on the aforementioned integrated test device. The second transition piece is equipped with components such as the tilt adjustment mechanism and the balance system. Then, install the rotor nacelle system to be tested on the second transition piece. Test and verify the functional performance characteristics of the rotor nacelle system under different tilt angles. Specifically, place the second transition piece on the side of the tower base and fix it with bolts at the reserved interface. The second transition piece and the test system are fixed with bolts at the interface on the other side. Driven by the electric drive system, the aerodynamic performance (three translational loads and three rotational torques) of the test system under different tilt angles can be measured respectively. By comparing the results with those of Step 1 and Step 2, the influence analysis of different factors (different components, different tilt angles) on the aerodynamic performance of the test system can be obtained, and the influence law of the aerodynamic performance of the test system under tilt dynamic inflow distortion can be revealed. At the same time, the functional reliability and durability of the components of the test system can be verified.

[0075] Step 4: Install a wing test piece on one side of the aforementioned integrated test device. The wing test piece matches the model aircraft formed by the system under test and maintains the same aerodynamic shape. Then, install the system under test onto the wing test piece. Test and verify the aerodynamic interference characteristics between the system under test and the wing, and test and assess the "rotational flutter" stall boundary between the system under test and the wing test piece. Specifically, place the wing test piece on the side of the tower base and fix it with bolts at the reserved interface groove. The wing test piece and the system under test are fixed with bolts at the interface on the other side. Driven by an electric drive system, the aerodynamic performance (three translational loads and three rotational torques) of the system under test under different wing components can be measured. By comparing with steps 1, 2, and 3, the influence analysis of different wing components on the aerodynamic performance of the system under test can be obtained, revealing the aerodynamic interference characteristics between the system under test and the wing components. At the same time, the flight speed of the "rotational flutter" stall boundary of the system under test, as well as the functional reliability and durability of the components, can be verified.

[0076] Step 5: Install wing and fuselage test components on the aforementioned integrated test apparatus. These components are matched to the aircraft model formed by the system under test, maintaining consistent aerodynamic shape. Then, install the rotor nacelle system under test on the end of the wing test component to test and verify the aerodynamic interference characteristics between the tested system and the fuselage. Specifically, place the wing test component on the side of the tower base and fix it with bolts at the reserved interface groove. The wing test component and the tested system are fixed with bolts at the interface on the other side. The fuselage test component... The component is placed on the tower base and fixed with bolts at the reserved interface groove, maintaining a smooth transition at the splice with the wing test component. Driven by an electric drive system, the aerodynamic performance of the tested system under different fuselage components (three translational loads and three rotational torques) can be measured separately. By comparing with steps 1, 2, 3, and 4, the influence analysis of different fuselage components on the aerodynamic performance of the tested system can be obtained, revealing the aerodynamic interference characteristics between the tested system and the fuselage components. At the same time, the functional reliability and durability of the components of the tested system can be verified.

[0077] Step 6: Install wing and fuselage test pieces on both sides of the aforementioned integrated test device. These wing and fuselage test pieces are matched to the aircraft model formed by the system under test, maintaining consistency with its aerodynamic shape. Then, install the two systems under test on the ends of the wing test pieces to test and verify the aerodynamic interference characteristics of the two tested systems. Specifically, place the two wing test pieces on the side of the tower base and fix them with bolts at the reserved interface grooves. The wing test pieces on both sides are fixed to the tested systems at the interface on the other side with bolts. The fuselage test pieces are then installed... The specimen is placed on the tower base and fixed with bolts at the reserved interface groove, ensuring a smooth transition at the splice with the wing test specimen. Driven by an electric drive system, the aerodynamic performance (three translational loads and three rotational torques) of two different test systems can be measured separately. By comparing and analyzing with steps 1, 2, 3, 4, and 5, the aerodynamic performance influence analysis between different test systems can be obtained, revealing the aerodynamic interference characteristics between rotors of different test systems. At the same time, the functional reliability and durability of the test system components can be verified.

[0078] This invention proposes a comprehensive ground-based testing method for rotor nacelles. This method allows for the sequential verification of the rotor nacelle's functional performance characteristics under different conditions through a progressive testing approach. It covers the rotor nacelle's characteristics during flight, effectively supporting ground-based scientific research on tiltrotor rotor nacelles. Specifically, based on this invention, ground-based functional performance characteristic testing of the rotor nacelle effectively covers its operational conditions during flight. Furthermore, the phased, progressive ground-based testing allows for the gradual exposure of problems during development, facilitating rapid improvement and iteration. Additionally, the phased, progressive aerodynamic interference testing of the rotor nacelle's wing / fuselage / rotor allows for the acquisition of effective aerodynamic interference data at low cost on the ground. In summary, the method provided by this invention significantly improves the development efficiency of rotor nacelles and effectively ensures their safety and reliability.

[0079] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A ground-based integrated test device for rotor nacelles, characterized in that, include: The tower base (1), the first transition piece (4), the second transition piece (5), the wing test piece (6), the fuselage test piece (7), and the balance system (3); among which, The top of the tower base (1) is provided with a first connecting part, a second connecting part and a third connecting part; The first connecting part is used to install the first transition piece (4) during simulation testing; wherein, when simulating the functional performance characteristics under different attitude angles, the lower end of the first transition piece (4) is fixedly connected to the tower base (1) through the first connecting part, and the upper end of the first transition piece (4) is connected to the rotor nacelle system (2) to be tested through a universal adjustment mechanism. The second connecting part is used to install the fuselage test component (7) during simulation testing, and the third connecting part is used to install the rotor nacelle system (2) to be tested during simulation testing. The top side of the tower base (1) is provided with a fourth connecting part and a fifth connecting part. The fourth connecting part is used to install the second transition piece (5) during simulation testing. The fifth connecting part is used to install the wing test piece (6) during simulation testing. The wing test piece (6) is used to install the rotor nacelle system (2) to be tested. When simulating the functional performance characteristics at different tilt angles, one end of the second transition piece (5) is fixedly connected to the tower base (1) through the fourth connecting part, and the other end of the second transition piece (5) is connected to the rotor nacelle system (2) to be tested through a tilt adjustment mechanism. The balance system (3) is used to measure the functional performance characteristics of the rotor nacelle system (2) under test during simulation testing.

2. The integrated ground test device for rotor nacelles according to claim 1, characterized in that, The universal adjustment mechanism adopts a cross universal joint or a ball cage universal joint.

3. The integrated ground test device for rotor nacelles according to claim 1, characterized in that, The tilt adjustment mechanism uses a slider connecting rod or a ball screw.

4. The integrated ground test device for rotor nacelles according to claim 1, characterized in that, The balance system (3) includes a six-component balance and a torque balance.

5. The integrated ground test device for rotor nacelles according to claim 4, characterized in that, The functional performance characteristic parameters are one or more of the following: thrust, drag, lateral force, pitching moment, rolling moment, yaw moment, and system torque of the rotor nacelle system (2) to be tested.

6. A ground-based integrated test method for rotor nacelles, characterized in that, Based on the rotor nacelle ground integrated test device according to claim 1, the rotor nacelle ground integrated test method includes the following steps: Step 1: A rotor nacelle system (2) to be tested is fixedly installed on the tower base (1) through the third connection part, driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system (2) under different collective pitch and cyclic pitch are measured by the balance system (3). Step 2: The first transition piece (4) is fixedly installed on the tower base (1) through the first connecting part, and a rotor nacelle system (2) to be tested is installed on the first transition piece (4), driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system (2) under the set attitude angle are measured by the balance system (3). Step 3: The second transition piece (5) is fixedly installed on the tower base (1) through the fourth connecting part. A rotor nacelle system (2) to be tested is installed on the second transition piece (5), driven by the electric drive system, and the aerodynamic performance parameters of the rotor nacelle system (2) to be tested are measured by the balance system (3) at the set tilt angle. Step 4: Fix the wing test piece (6) on one side to the tower base (1) through the fifth connection part, install a rotor nacelle system (2) to be tested on the wing test piece (6), drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system (2) under the set single-sided wing test piece working condition through the balance system (3); Step 5: Fix the fuselage test piece (7) to the tower base (1) through the second connecting part, and fix the wing test piece (6) on one side to the tower base (1) through the fifth connecting part; install a rotor nacelle system (2) to be tested on the wing test piece (6), drive it through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system (2) under the conditions of the fuselage test piece and the wing test piece on one side through the balance system (3); Step 6: Fix the fuselage test piece (7) to the tower base (1) through the second connecting part, and fix the wing test piece (6) to the tower base (1) on both sides through the fifth connecting part; install the two rotor nacelle systems (2) to be tested on the wing test pieces (6) on both sides respectively, drive them through the electric drive system, and measure the aerodynamic performance parameters of the rotor nacelle system (2) under the conditions of the fuselage test piece and the wing test pieces on both sides through the balance system (3); in, Step 2 specifically includes: fixing the first transition piece (4) to the tower base (1) through the first connecting part, installing a rotor nacelle system (2) to be tested on the first transition piece (4) through the universal adjustment mechanism, driving it through the electric drive system, and measuring the aerodynamic performance parameters of the rotor nacelle system (2) under different attitude angles through the balance system (3); Step 3 specifically includes: fixing the second transition piece (5) to the tower base (1) through the fourth connecting part, installing a rotor nacelle system (2) to be tested on the second transition piece (5) through the tilt adjustment mechanism, driving it through the electric drive system, and measuring the aerodynamic performance parameters of the rotor nacelle system (2) under different tilt angles through the balance system (3).

7. The method for integrated ground testing of a rotor nacelle according to claim 6, characterized in that, Also includes: Step 7: Compare the aerodynamic performance parameters obtained in Step 2 with those obtained in Step 1 to obtain the analysis results of the influence of different factors on aerodynamic performance, revealing the aerodynamic interference characteristics of the rotor and nacelle structure; compare the aerodynamic performance parameters obtained in Step 3 with those obtained in Steps 1 and 2 to obtain the analysis results of the influence of different factors on aerodynamic performance, revealing the aerodynamic performance influence law under tilt dynamic inflow distortion, and verifying the functional reliability and durability of the components of the rotor nacelle system under test; compare the aerodynamic performance parameters obtained in Step 4 with those obtained in Steps 1, 2, and 3 to obtain the analysis results of the influence of the wing test piece on the aerodynamic performance of the rotor nacelle system under test, revealing the aerodynamic interference characteristics of the rotor nacelle system under test and the wing test piece, and verifying the "..." of the rotor nacelle system under test. The flight speed at the "flutter" stall boundary and the functional reliability and durability of the components are analyzed. The aerodynamic performance parameters obtained in step 5 are compared with those obtained in steps 1, 2, 3, and 4 to obtain the analysis results of the influence of the fuselage test component on the aerodynamic performance of the rotor nacelle system under test, revealing the aerodynamic interference characteristics between the rotor nacelle system under test and the fuselage test component, and verifying the functional reliability and durability of the components of the rotor nacelle system under test. The aerodynamic performance parameters obtained in step 6 are compared with those obtained in steps 1, 2, 3, 4, and 5 to obtain the analysis results of the aerodynamic performance influence between the rotor nacelle systems under test, revealing the aerodynamic interference characteristics between the rotors of different rotor nacelle systems under test, and verifying the functional reliability and durability of the components of the rotor nacelle system under test.

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