Coaxial helicopter main rotor load measuring and mounting device

Abstract

The invention provides a coaxial helicopter main rotor load measuring and mounting device. The coaxial helicopter main rotor load measuring and mounting device comprises a mounting module (1), a hoop (2) and a packaging cover plate (4), the mounting module (1) is semi-arc-shaped, the radian of the inner side surface is attached to the radian of the outer surface of a propeller hub support arm of a coaxial helicopter main rotor, and a fixed fork lug is arranged on the end face of one side; the mounting module (1) is arranged on the rotating leeside of a propeller hub support arm, and an onboard propeller hub mounting bolt penetrates through a fixed fork lug to fix the mounting module (1) at the root of a propeller hub; a plurality of mounting cavities are formed in the mounting module (1) and are used for accommodating the test acquisition module and the energy storage unit; the packaging cover plate (4) is arranged on the mounting module (1) and is used for sealing and covering the mounting cavity; the hoop (2) is in a semi-arc shape and is connected with the installation module (1) to form a circular ring which is arranged on a propeller hub supporting arm in a sleeved mode. According to the invention, the coaxial helicopter flight test main rotor load measurement system can be efficiently and reliably installed on a high-speed rotating main rotor system.

Description

Technical Field

[0001] The present invention belongs to the technical field of helicopter flight test load measurement and modification, and particularly relates to a coaxial helicopter main rotor load measurement and installation device. Background Art

[0002] Helicopter flight test load measurement is an important link in helicopter scientific research and certification flight tests. Its test data can be used for helicopter flight load spectrum analysis and fatigue life determination. Due to the special nature of the rotor structure of coaxial helicopters, it is more important to measure the flight loads of key components such as the upper / lower rotor main blades, main hub, inner and outer rotor shafts, and main rotor pitch links that rotate at high speeds. It is necessary to install a test system on the main rotor structure to collect, encode, and transmit the load signals of the rotor system, and to solve the power supply for the test system. When the helicopter is flying, the test system additionally installed on the helicopter main rotor system rotates synchronously at high speed with the helicopter main rotor system. Therefore, not only the reliability and safety of the equipment installation are required, but also the impact on the helicopter's aerodynamic shape should be avoided, and higher requirements are imposed on the installation method, quality, size, and dynamic balance of the installation device. Limited by the coaxial rotor structure, the power supply situation for the test equipment is more demanding.

[0003] Therefore, designing a reasonable and effective installation device for the coaxial helicopter main rotor measurement system is crucial for the load test of the main rotor system during the flight test of coaxial helicopters. Currently, there is no relevant installation device in China. No relevant public literature has been retrieved at home and abroad. Summary of the Invention

[0004] The present invention provides a coaxial helicopter main rotor load measurement and installation device for the flight load test and modification of the coaxial helicopter main rotor system. Using the device of the present invention, the reliable installation of the coaxial helicopter main rotor load test system can be achieved without affecting the aerodynamics during the high-speed flight of the helicopter, providing technical support for the flight load test and modification of coaxial helicopters.

[0005] The present invention provides a coaxial helicopter main rotor load measurement and installation device, including: installation module 1, clamp 2, and encapsulation cover plate 4;

[0006] The installation module 1 is semi-circular, and the inner surface curvature fits the outer surface curvature of the hub arm of the coaxial helicopter main rotor. A fixed fork ear is provided on one end face; the installation module 1 is arranged on the rotating leeward side of the hub arm, and the on-board hub installation bolt passes through the fixed fork ear to fix the installation module 1 at the root of the hub;

[0007] A plurality of installation cavities are arranged in the installation module 1 for accommodating the test acquisition module and the energy storage unit; the encapsulation cover plate 4 is arranged on the installation module 1 for covering the installation cavities;

[0008] The clamp 2 is semi-circular and is connected to the installation module 1 to form a ring that is sleeved on the hub arm.

[0009] Optionally, the test acquisition module and the energy storage unit are fixed in the installation cavity in a form of potting.

[0010] Optionally, the installation cavity is milled out of the installation module 1 according to the external dimensions of the test acquisition module and the energy storage unit.

[0011] Optionally, the coaxial helicopter main rotor load measurement installation device further includes: cover plate fixing bolts 5;

[0012] The encapsulation cover plate 4 is fixed on the end face of the installation cavity through the cover plate fixing bolts 5.

[0013] Optionally, the coaxial helicopter main rotor load measurement installation device further includes: 4 clamp fixing bolts 3;

[0014] Two bolt mounting holes are provided at both ends of the installation module 1 and the clamp 2. The 4 clamp fixing bolts 3 are inserted into the bolt mounting holes to connect the clamp 2 and the installation module 1 on the hub arm to form a hub-holding mode.

[0015] Optionally, a counterweight is provided in the installation cavity to balance the weights of the load measurement installation devices on different hub arms of the same coaxial helicopter.

[0016] Optionally, a cable through hole is provided at the bottom of the installation cavity.

[0017] Optionally, a bottom plate is provided at the bottom of the installation cavity. A metal connector is provided on the bottom plate, and a socket connected to the metal connector is provided on the outside of the installation module 1.

[0018] The present invention provides a coaxial helicopter main rotor load measurement and installation device, comprising: an installation module 1, a clamp 2 and a packaging cover plate 4; the installation module 1 is semi-circular, the inner surface radian thereof fits the outer surface radian of the hub arm of the coaxial helicopter main rotor, and a fixed fork ear is arranged on one end face; the installation module 1 is arranged on the rotation leeward side of the hub arm, and the on-board hub installation bolt passes through the fixed fork ear to fix the installation module 1 at the root of the hub; a plurality of installation cavities are arranged in the installation module 1 for accommodating a test acquisition module and an energy storage unit; the packaging cover plate 4 is arranged on the installation module 1 for covering the installation cavity; the clamp 2 is semi-circular, connected with the installation module 1, and forms a ring to be sleeved on the hub arm. The present invention can realize the efficient and reliable installation of the coaxial helicopter flight test main rotor load measurement system on the high-speed rotating main rotor system, can be applicable to the installation of a modular main rotor test system, has strong adaptability to the shape of the test system, has high reliability in the mechanical form of hugging the hub near the root of the arm, can be evenly distributed and installed on each arm, the mass of the installation modules on each arm is basically the same, the additional installation mass is light, and it is easy to realize the adjustment of the dynamic balance of the main rotor system; it is installed on the leeward side of the hub arm, and the width is smaller than the diameter of the hub arm, and no additional aerodynamic influence will be generated. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is a schematic diagram of the overall structure of the coaxial helicopter main rotor load measurement and installation device Figure 1 ;

[0020] Figure 2 is a schematic diagram of the overall structure of the coaxial helicopter main rotor load measurement and installation device Figure 2 ;

[0021] DESCRIPTION OF THE REFERENCE NUMERALS:

[0022] 1 - installation module;

[0023] 2 - clamp;

[0024] 3 - clamp fixing bolt;

[0025] 4 - packaging cover plate;

[0026] 5 - cover plate fixing bolt. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0027] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0028] The features and exemplary embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely provided to better understand the present invention by way of illustrating examples of the present invention. The present invention is in no way limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. In the drawings and the following description, well-known structures and technologies are not shown to avoid unnecessarily obscuring the present invention.

[0029] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other, and the various embodiments may refer to and cite each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.

[0030] The present invention will be further described in detail below in combination with the embodiments and the drawings, but the embodiments of the present invention are not limited thereto.

[0031] The coaxial helicopter main rotor load measurement and installation device provided by the present invention will be explained below in conjunction with the drawings.

[0032] As Figure 1-2 shown, the present invention provides a modular test system installation device for the flight load test modification of the coaxial helicopter main rotor system. By using the device of the present invention, the reliable installation of the coaxial helicopter main rotor load test system can be achieved without causing aerodynamic influence on the high-speed flight of the helicopter, providing technical support for the flight load test modification of the coaxial helicopter.

[0033] The present invention is a coaxial helicopter main rotor load measurement and installation device. The main rotor load measurement and installation device includes 1 installation module 1, 1 clamp 2, 4 clamp fixing bolts 3, 1 encapsulation cover plate 4, and 18 cover plate fixing bolts 5.

[0034] The installation module 1 is held in the form of a hub on the rotating leeward side of the hub arm, and is fixed to the root of the hub by borrowing the on-board hub installation bolts through the fixed fork ears reserved on the installation module 1; the clamp (2) is used to clamp the installation module and the hub arm together through the connection holes reserved on the installation module 1, and the clamp fixing bolts 3 are used to fix the clamp; according to the external dimensions of the test acquisition module and the energy storage unit, an installation cavity is milled on the side of the column structure of the installation module, and the test acquisition module and the energy storage unit are fixed by means of glue sealing; then the encapsulation cover plate 4 is used to cover the end face of the installation cavity and is fixed by the cover plate fixing bolts 5.

[0035] In the coaxial helicopter rotor load measurement and installation device, the inner surface of the installation module 1 adopts a contoured design so that the curvature of the shell is consistent with the outer surface of the hub support arm, ensuring that the inner surface of the shell and the outer surface of the hub support arm can be tightly combined; the clamp 2 can be connected to the installation module 1 on the support arm through bolts to form a hub-holding mode, thereby increasing the installation stability; the root of the installation module 1 can be designed according to the position of the mounting hole of the on-board hub to fix the module fork ear, and can be directly fixed using the original mounting hole position on the aircraft without changing the on-board structure; the installation module 1 adjusts the external dimensions according to the actual size of the test acquisition module and the energy storage unit, and mills the corresponding installation cavity on the side of the column structure.

[0036] In the coaxial helicopter rotor load measurement and installation device, the installation module can be installed on the rotating leeward side of the hub support arm, which will not affect the aerodynamic shape of the helicopter; the installation module is fixed on the hub support arm in the form of a hub hugging, and has extremely high installation stability; the same number of installation modules with completely identical structures can be designed according to the number of hubs, and the weight of the installation modules can be kept basically consistent through counterweights, and can be evenly distributed on each hub support arm, greatly reducing the impact on the dynamic balance of the rotor; the installation module is installed at the root of the hub, as close to the center of the hub as possible, reducing centrifugal force and increasing installation reliability.

[0037] The above description is only a further embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical solutions and concepts of the present invention within the scope disclosed by the present invention, which belong to the protection scope of the present invention.

Claims

1. A coaxial helicopter main rotor load measurement and installation device, characterized in that Including: Mounting module (1), clamp (2) and encapsulation cover plate (4); The mounting module (1) is semi-circular, and the inner surface curvature fits the outer surface curvature of the hub arm of the coaxial helicopter's main rotor. A fixed fork ear is provided at one end face. The mounting module (1) is arranged on the rotation leeward side of the hub arm, and the on-board hub mounting bolt passes through the fixed fork ear to fix the mounting module (1) at the root of the hub; A plurality of mounting cavities are provided in the mounting module (1) for accommodating the test acquisition module and the energy storage unit; the encapsulation cover plate (4) is arranged on the mounting module (1) for covering the mounting cavities; The clamp (2) is semi-circular and is connected to the mounting module (1) to form a ring that is sleeved on the hub arm.

2. The coaxial helicopter main rotor load measurement and installation device according to claim 1, wherein The test acquisition module and the energy storage unit are fixed in the mounting cavity in a form of sealing glue.

3. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that, The mounting cavity is milled out of the mounting module (1) according to the external dimensions of the test acquisition module and the energy storage unit.

4. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that, Also included: Cover plate fixing bolt (5); The encapsulation cover plate (4) is fixed to the end face of the mounting cavity through the cover plate fixing bolt (5).

5. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that Also included: 4 clamp fixing bolts (3); Two bolt mounting holes are provided at both ends of the mounting module (1) and the clamp (2). The 4 clamp fixing bolts (3) are passed through the bolt mounting holes to connect the clamp (2) and the mounting module (1) on the hub arm to form a hub-holding mode.

6. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that, A counterweight is arranged in the mounting cavity for balancing the weight of the load measurement and installation device on different hub arms of the same coaxial helicopter.

7. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that A cable through hole is provided at the bottom of the mounting cavity.

8. The coaxial helicopter main rotor load measurement and installation device according to claim 1, characterized in that A bottom plate is provided at the bottom of the mounting cavity. A metal connector is provided on the bottom plate, and a socket connected to the metal connector is provided on the outside of the mounting module (1).

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