Tilt-rotor aircraft detector

Abstract

The utility model relates to the technical field of aircrafts, and discloses a tilt-rotor aircraft detector, which is characterized by comprising a frame body, a tilt-rotor aircraft, six data acquisition parts and a support adjusting part, the tilt-rotor aircraft is detachably mounted on the frame body, the six data acquisition parts are arranged on the frame body, are mounted around the tilt-rotor aircraft and are used for acquiring rotor aerodynamic force data and analyzing the rotor aerodynamic force data, and the support adjusting part is arranged on one surface, far away from the tilt-rotor aircraft, of the frame body and is used for adjusting the tilt angle and position of the frame body. The six data acquisition parts are used for performing data detection on six rotors of the tilt-rotor aircraft respectively, so that three forces (normal force, axial force and transverse force) and three moments (pitching moment, yawing moment and pitching moment) of the aircraft under the current pneumatic condition can be measured and transmitted to the data acquisition system; therefore, the problem of lack of rotor characteristics and pneumatic interference data between the rotor and the fuselage during electric multi-rotor design is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and more particularly to a tiltrotor aircraft detector. Background Art

[0002] Tiltrotor aircraft are a new type of aircraft that combine the inherent advantages of vertical takeoff and landing (VTOL) of helicopters with the high speed and long range of fixed-wing propeller aircraft. Due to their unique configuration, aerodynamic interference between their various components is significant. Analyzing and recording these intercomponent aerodynamic interactions and aerodynamic forces during flight is difficult, especially when accurately recording the aerodynamic forces of each component during transitions between fixed-wing and helicopter modes. Therefore, a comprehensive test method for multi-rotor characteristics is urgently needed. This method can be used to study the rotor characteristics of electric multi-rotors, electric composite wings, and tiltrotors. This test system will help us gain a head start in the development of tiltrotors, enabling us to publish high-quality papers in areas such as overall design, aerodynamic interference, aerodynamic noise, motor-rotor matching, advanced rotor design, and flight dynamics modeling and simulation, and also enable us to undertake related research projects. It will also accumulate a wealth of test data for rotor development, and even for the development of tiltrotors. Conventional rotor test benches usually test a single aerodynamic state of a single rotor, and are unable to measure the aerodynamic interference between multiple rotors, let alone achieve transitions between different states. Their functionality is limited. Even if multi-rotor test benches exist, currently only pure rotor test benches exist, ignoring the interference when the fuselage is present. However, during the flight of a rotorcraft, the interference between the rotor and the fuselage is very serious. This part of the aerodynamic interference cannot be ignored during actual flight, and it is difficult to find the corresponding empirical interference coefficient in existing literature. Utility Model Content

[0003] In view of the shortcomings of the existing technology, the purpose of the present invention is to provide a tilt-rotor aircraft detector for overcoming the above-mentioned defects in the existing technology. Through six data acquisition parts, data detection is performed on the six rotors of the tilt-rotor aircraft respectively, and the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under the current aerodynamic conditions can be measured and transmitted to the data acquisition system, so that the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotors is solved, and the test of multi-rotor characteristics is carried out. In order to meet the test requirements, an innovative multi-rotor test system was developed (this solution can measure the number of rotors of six or less). The solution uses a multi-rotor test bench to study the rotor characteristics of electric multi-rotor, composite wing and tilt-rotor aircraft in various flight states, as well as the aerodynamic interference characteristics between the rotor and the fuselage. It can be used to study the rotor characteristics of electric multi-rotor, composite wing and tilt-rotor aircraft in various flight states (vertical take-off, tilting process and level flight state) and the aerodynamic interference between the rotor and the fuselage, thereby solving the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotors.

[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a tiltrotor aircraft detector, comprising a frame, a tiltrotor aircraft, six data acquisition units and a support and adjustment unit; the tiltrotor aircraft is detachably mounted on the frame, the six data acquisition units are arranged on the frame and installed around the tiltrotor aircraft, for collecting and analyzing data on the rotor aerodynamics, the support and adjustment unit is arranged on a side of the frame away from the tiltrotor aircraft, for adjusting the tilt angle and position of the frame, and the six data acquisition units are used to perform data detection on the six rotors of the tiltrotor aircraft respectively, so that the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft model under current aerodynamic conditions can be measured and transmitted to the data acquisition system, so that the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotors is solved, and an innovative multi-rotor test system is developed in response to the test requirements of multi-rotor characteristics (this solution can measure the number of rotors of six or less).

[0005] As a further improvement of the present invention, the frame includes at least three transverse frames, at least two reinforcement frames, at least four vertical frames, at least six sliding sleeves, and at least six fixed frames; two of the vertical frames form a group, and the three transverse frames are fixedly connected between the two groups of vertical frames. The two reinforcement frames are respectively fixedly connected to the two ends of the two groups of vertical frames. The six sliding sleeves form a group of two, and each group of sliding sleeves is slidably connected to a transverse frame. The six fixed frames are respectively fixedly connected to the six sliding sleeves, and are respectively detachably connected to the six data acquisition parts. Through the connection of the transverse and vertical frames, the formal force strength is increased, which makes it convenient to cooperate; the sliding sleeve that can slide to adjust the distance makes it possible to detect tilt-rotor aircraft of different sizes.

[0006] As a further improvement of the present invention, the data acquisition unit includes a main body, a sensor group, two rotating blades, two swinging pieces, two connecting rods, a motor, two chips and a six-component strain gauge balance; the main body is detachably connected to a fixed frame, the sensor group is fixedly connected to one end of the main body away from the fixed frame, the two rotating blades are rotatably mounted on the main body and close to the sensor group, the six-component strain gauge balance is fixedly connected to the main body and close to the two rotating blades, the two swinging pieces are rotatably mounted on the main body, the two ends of each connecting rod are respectively hinged at the two ends of the two swinging pieces, the motor is fixedly set on the main body and connected to one of the swinging pieces, the two chips are respectively mounted on the main body and located on both sides of the motor, and by installing the six-component strain gauge balance, the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under current aerodynamic conditions are measured and transmitted to the data acquisition system, thereby realizing the collection and analysis of aerodynamic data of a single rotor, the analysis between aerodynamic data of multiple motors and the analysis of aerodynamic data of the entire machine, providing flexibility and convenience for the test.

[0007] As a further improvement to the present invention, the support adjustment unit includes a support base, several reinforcing ribs, a support rod, a telescopic device, and a mounting bracket. The mounting bracket is fixedly connected to two of the vertical brackets, the support rod is rotatably connected to the side of the support base away from the vertical brackets, and one end of the telescopic device is hinged to the support rod and the other end is hinged to the support base. The wind tunnel wind speed is adjusted via a remote control system, and the telescopic device is used to adjust the pitch angle and heading angle of the support base, the cyclic pitch of each rotor, the collective pitch, the motor speed, and other variables related to the electric multi-rotor characteristics. The longitudinal axis of the fuselage is parallel to the support adjustment unit, and the pitch angle and heading angle of the fuselage change simultaneously with the mounting base.

[0008] As a further improvement of the present invention, the tilt-rotor aircraft includes a fuselage and six rotors; the six rotors are arranged on the fuselage, the position of each rotor corresponds to the position of six data acquisition parts, and the telescopic device is an electric cylinder.

[0009] Beneficial effects of the utility model:

[0010] (1) The utility model uses six data acquisition units to perform data detection on the six rotors of the tilt-rotor aircraft respectively, and can measure the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under the current aerodynamic conditions and transmit them to the data acquisition system, so that the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotor is solved, and an innovative multi-rotor test system is developed according to the test requirements of multi-rotor characteristics (this invention) The program can test the number of rotors of six rotors or less). This program uses a multi-rotor test bench to study the rotor characteristics of electric multi-rotor, compound wing and tilt-rotor aircraft in various flight states, as well as the aerodynamic interference characteristics of the rotor and the fuselage. It can be used to study the rotor characteristics of electric multi-rotor, compound wing and tilt-rotor aircraft in various flight states (vertical take-off, tilting process and level flight state) and the aerodynamic interference between the rotor and the fuselage, thereby solving the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotors.

[0011] (2) The utility model increases the formal stress strength by connecting the horizontal and vertical racks, making it easier to match; and the sliding sleeve with adjustable sliding distance allows the detection of tilt-rotor aircraft of different sizes.

[0012] (3) By installing a six-component strain gauge balance, the utility model can measure the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under the current aerodynamic conditions and transmit them to the data acquisition system, thereby realizing the collection and analysis of aerodynamic data of a single rotor, the analysis of aerodynamic data between multiple motors and the analysis of aerodynamic data of the entire aircraft, providing flexibility and convenience for the test.

[0013] (4) The present invention adjusts the wind tunnel wind speed through a remote control system and utilizes a telescopic device to adjust the pitch angle of the support base, the yaw angle of the support base, the cyclic pitch of each rotor, the collective pitch, the motor speed, and other variables related to the characteristics of the electric multi-rotor. The longitudinal axis of the fuselage is parallel to the support adjustment portion, and the pitch angle and yaw angle of the fuselage change simultaneously with the mounting base. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the main structure of the utility model;

[0015] Figure 2 It is a structural schematic diagram of the utility model from other perspectives;

[0016] Figure 3 This utility model Figure 2 An enlarged structural diagram of the middle support seat;

[0017] Figure 4 This utility model Figure 1 Schematic diagram of part of the structure at the middle horizontal frame;

[0018] Figure 5 This utility model Figure 1 A schematic diagram of the enlarged structure of the data acquisition unit;

[0019] Figure 6 This utility model Figure 5 Schematic diagram of the structure from other angles.

[0020] Figure numerals: 1. frame; 11. horizontal frame; 12. reinforcement frame; 13. vertical frame; 14. sliding sleeve; 15. fixed frame; 2. tilt-rotor aircraft; 3. data acquisition unit; 31. main body; 32. sensor group; 33. rotating blade; 34. swing plate; 35. connecting rod; 36. motor; 37. chip; 38. six-component strain balance; 4. support and adjustment unit; 41. support seat; 42. reinforcement rib; 43. support rod; 44. telescopic device; 45. mounting frame. DETAILED DESCRIPTION

[0021] The present invention will be further described below in conjunction with the accompanying drawings and embodiments. Identical components are denoted by the same reference numerals. It should be noted that the terms "front," "rear," "left," "right," "upper," and "lower" used in the following description refer to directions in the accompanying drawings, and the terms "bottom," "top," "inner," and "outer" refer to directions toward or away from the geometric center of a particular component, respectively.

[0022] Reference Figure 1-6 As shown, a tiltrotor aircraft detector of this embodiment includes a frame 1, a tiltrotor aircraft 2, six data acquisition units 3 and a support and adjustment unit 4; the tiltrotor aircraft 2 is detachably mounted on the frame 1, the six data acquisition units 3 are arranged on the frame 1 and installed around the tiltrotor aircraft 2, for collecting and analyzing data on the rotor aerodynamic force, and the support and adjustment unit 4 is arranged on a side of the frame 1 away from the tiltrotor aircraft 2, for adjusting the tilt angle and position of the frame 1. The six data acquisition units 3 are used to perform data detection on the six rotors of the tiltrotor aircraft 2 respectively, and the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under current aerodynamic conditions can be measured and transmitted to the data acquisition system, so that the problem of lack of rotor characteristics and aerodynamic interference data between the rotor and the fuselage in the design of electric multi-rotors is solved, and an innovative multi-rotor test system is developed according to the test requirements of multi-rotor characteristics (this solution can measure the number of rotors of six or less).

[0023] like Figure 1-6As shown, the frame 1 includes at least three transverse frames 11, at least two reinforcement frames 12, at least four vertical frames 13, at least six sliding sleeves 14, and at least six fixed frames 15; two of the vertical frames 13 form a group, and the three transverse frames 11 are fixedly connected between the two groups of vertical frames 13, the two reinforcement frames 12 are fixedly connected to the two ends of the two groups of vertical frames 13, and the six sliding sleeves 14 form a group of two, and each group of sliding sleeves 14 is slidably connected to a transverse frame 11, and the six fixed frames 15 are respectively fixedly connected to the six sliding sleeves 14, and are respectively detachably connected to the six data acquisition units 3. Through the connection of the transverse and vertical frames, the formal force strength is increased, which is convenient for coordination; the sliding sleeves 14 that can slide and adjust the distance can be used to detect tilt-rotor aircraft 2 of different sizes.

[0024] like Figure 1-6 As shown, the data acquisition unit 3 includes a main body 31, a sensor group 32, two rotating leaves 33, two swinging pieces 34, two connecting rods 35, a motor 36, two chips 37 and a six-component strain gauge balance 38; the main body 31 is detachably connected to the fixed frame 15, the sensor group 32 is fixedly connected to one end of the main body 31 away from the fixed frame 15, the two rotating leaves 33 are rotatably mounted on the main body 31 and close to the sensor group 32, the six-component strain gauge balance 38 is fixedly connected to the main body 31 and close to the two rotating leaves 33, the two swinging pieces 34 are rotatably mounted on the main body 31, and the two ends of each connecting rod 35 are fixedly connected to the main body 31. The motor 36 is hinged at both ends of the two swing pieces 34, and is fixed on the main body 31 and connected to one of the swing pieces 34. The two chips 37 are respectively installed on the main body 31 and are located on both sides of the motor 36. By installing a six-component strain gauge balance 38, the three forces (normal force, axial force and lateral force) and three moments (pitch moment, yaw moment and pitch moment) of the aircraft under the current aerodynamic conditions can be measured and transmitted to the data acquisition system to realize the collection and analysis of aerodynamic data of a single rotor, the analysis of aerodynamic data of multiple motors 36, and the analysis of aerodynamic data of the entire machine, providing flexibility and convenience for the test.

[0025] like Figure 1-6 As shown, the support and adjustment unit 4 includes a support base 41, several reinforcing ribs 42, a support rod 43, a telescopic device 44, and a mounting bracket 45. The mounting bracket 45 is fixedly connected to two of the vertical frames 13. The support rod 43 is rotatably connected to the side of the support base 41 away from the vertical frames 13. The telescopic device 44 is hinged at one end to the support rod 43 and at the other end to the support base 41. The wind tunnel wind speed is adjusted via a remote control system, and the telescopic device 44 is used to adjust the pitch angle and heading angle of the support base 41, the cyclic pitch of each rotor, the collective pitch, the speed of the motor 36, and other variables related to the electric multi-rotor characteristics. The longitudinal axis of the fuselage is parallel to the support and adjustment unit 4, and the pitch angle and heading angle of the fuselage change simultaneously with the mounting bracket.

[0026] like Figure 1-6 As shown, the tilt-rotor aircraft 2 includes a fuselage and six rotors; the six rotors are arranged on the fuselage, and the position of each rotor corresponds to the position of six data acquisition units 3, and the telescopic device 44 is an electric cylinder.

[0027] Working principle: Figure 1-6 As shown, during use, the telescopic device 44 is activated, and then the mounting bracket 45 is pushed to adjust the angle, thereby adjusting the overall angle of the frame 1 and, in turn, the angle of the tiltrotor 2. When data measurement is required, the external control system is activated to simulate different wind speeds, and the six data acquisition units 3 are used to collect data. When the rotor blades 33 rotate, the six-component strain gauge balance 38 can measure the three forces (normal force, axial force, and lateral force) and three moments (pitch moment, yaw moment, and pitch moment) of the aircraft model under the current aerodynamic conditions. The sensor group 32 also collects data. When different models of tiltrotor aircraft 2 need to be tested, the distance between the sliding sleeves 14 can be adjusted. The motor 36 is activated, which controls the swing of one of the swing plates 34, thereby driving the two connecting rods 35 to swing, causing the other swing plate 34 to swing.

[0028] The above are only preferred embodiments of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions based on the concept of the present invention are within the scope of protection of the present invention. It should be noted that for those skilled in the art, certain improvements and modifications that do not depart from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A tiltrotor aircraft detector, characterized in that: It comprises a frame (1), a tiltrotor aircraft (2), six data acquisition units (3) and a support and adjustment unit (4); The tiltrotor aircraft (2) is detachably mounted on the frame (1); six data acquisition units (3) are arranged on the frame (1) and are installed around the tiltrotor aircraft (2) for collecting and analyzing rotor aerodynamic data; and a support adjustment unit (4) is arranged on a side of the frame (1) away from the tiltrotor aircraft (2) for adjusting the tilt angle and position of the frame (1).

2. The tiltrotor aircraft detector according to claim 1, characterized in that: The frame (1) comprises at least three transverse frames (11), at least two reinforcement frames (12), at least four vertical frames (13), at least six sliding sleeve frames (14), and at least six fixed frames (15); The two vertical frames (13) form a group, three transverse frames (11) are fixedly connected between the two groups of vertical frames (13), two reinforcing frames (12) are fixedly connected to the two ends of the two groups of vertical frames (13), six sliding sleeve frames (14) form a group of two, each group of sliding sleeve frames (14) is slidably connected to a transverse frame (11), and six fixed frames (15) are fixedly connected to the six sliding sleeve frames (14) and are detachably connected to the six data acquisition units (3).

3. The tiltrotor aircraft detector according to claim 2, characterized in that: The data acquisition unit (3) comprises a main body (31), a sensor group (32), two rotating blades (33), two swinging pieces (34), two connecting rods (35), a motor (36), two chips (37) and a six-component strain gauge balance (38); The main body (31) is detachably connected to the fixing frame (15), the sensor group (32) is fixedly connected to one end of the main body (31) away from the fixing frame (15), the two rotating leaves (33) are rotatably mounted on the main body (31) and close to the sensor group (32), the six-component strain gauge balance (38) is fixedly connected to the main body (31) and close to the two rotating leaves (33), the two swinging pieces (34) are both rotatably mounted on the main body (31), the two ends of each connecting rod (35) are respectively hinged to the two ends of the two swinging pieces (34), the motor (36) is fixedly arranged on the main body (31) and connected to one of the swinging pieces (34), and the two chips (37) are respectively mounted on the main body (31) and located on both sides of the motor (36).

4. The tiltrotor aircraft detector according to claim 1, characterized in that: The support adjustment portion (4) comprises a support seat (41), a plurality of reinforcing ribs (42), a support rod (43), a telescopic device (44) and a mounting frame (45); The mounting frame (45) is fixedly connected to two of the vertical frames (13); the support rod (43) is rotatably connected to a side of the support base (41) away from the vertical frames (13); one end of the telescopic device (44) is hinged to the support rod (43) and the other end is hinged to the support base (41).

5. The tiltrotor aircraft detector according to claim 1, characterized in that: The tiltrotor aircraft (2) comprises a fuselage and six rotors; The six rotors are arranged on the fuselage, and the position of each rotor corresponds to the position of six data acquisition parts (3).

6. The tiltrotor aircraft detector according to claim 4, characterized in that: The telescopic device (44) is an electric cylinder.

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