Flight test equipment for aircraft

Abstract

The present application relates to a flight test device for an aircraft. The device includes a support frame, the top of which is provided with a rotating support portion; a balance arm, including a first end, a second end, and a rotating connection portion provided between the first end and the second end, the rotating connection portion being rotatably mounted on the rotating support portion, the two ends of the balance arm along the length direction being able to move around the support frame in the first direction and the second direction, the first end and the rotating support portion having a first center distance, and the second end and the rotating support portion having a second center distance; a test frame, movably mounted on the first end of the balance arm; a supporting mechanism, mounted on the top of the test frame, the supporting mechanism being used to support the aircraft to be tested, the supporting mechanism being able to move with the test machine in at least one degree of freedom; a torque adjustment device, mounted on the second end of the balance arm, including at least one torque adjustment component. The solution provided by the present application can test various flight parameters of an aircraft under different flight modes.

Description

Technical Field

[0001] The present application relates to the field of aviation technology, and in particular to a flight test device for aircraft. Background Art

[0002] During production and modification testing of aircraft, various flight parameters and their stability must be tested and analyzed. Flight test equipment used in related technologies is typically designed for specific verification test items, which has certain limitations and makes it difficult to test various flight parameters under different flight modes. Summary of the Invention

[0003] In order to solve or partially solve the problems existing in the related art, the present application provides a flight test device for an aircraft, which can test various flight parameters of the aircraft in different flight modes.

[0004] A first aspect of the present application provides a flight test device for an aircraft, comprising:

[0005] A support frame, wherein a rotating support portion is provided on the top of the support frame;

[0006] a balancing arm, the balancing arm being rotatably mounted on the rotating support portion, the balancing arm being movable around the support frame at both ends along the length direction, the balancing arm being a first end and a second end, the first end being spaced from the rotating support portion by a first center distance, and the second end being spaced from the rotating support portion by a second center distance;

[0007] A test frame, movably mounted on one end of the balance arm along the length direction;

[0008] a carrying mechanism, mounted on the top of the test frame, for carrying the aircraft to be tested, and capable of moving with the test aircraft in at least one degree of freedom;

[0009] The torque regulating device is installed at the other end of the balancing arm along the length direction. The torque regulating device includes at least one torque regulating component, and the at least one torque regulating component is used to adjust the load in the vertical direction and / or the resistance torque in the rotational direction.

[0010] In one embodiment, the support frame includes a first support, a rotary connector and a connecting seat;

[0011] The swivel connector is connected between the first support and the connecting seat, and the balance arm is rotatably mounted on the connecting seat; wherein the swivel connector rotates in a first direction relative to the first support, and the balance arm rotates in a second direction relative to the connecting seat.

[0012] In one embodiment, the test stand comprises:

[0013] a second support, the second support being rotatably connected to the first end of the balance arm in the second direction;

[0014] A carrying mechanism is arranged on the top of the second support, and the carrying mechanism includes a first support member and a second support member that are spaced apart in the vertical direction and movably connected. A supporting assembly is provided above the second support member, and the supporting assembly is used to be connected to the aircraft to be tested.

[0015] In one embodiment, the first support member and the second support member are movably connected via a rotary support mechanism;

[0016] The second support member is movable relative to the first support member along at least one degree of freedom.

[0017] In one embodiment, the rotary support mechanism includes at least two rotary support assemblies spaced apart from each other;

[0018] The rotation support assembly includes a first connecting member connected to the first supporting member, a second connecting member connected to the second supporting member, and a bearing connected between the first connecting member and the second connecting member;

[0019] The rotation direction of the bearing is the same as the pitch direction of the aircraft.

[0020] In one embodiment, the rotary support mechanism includes at least two rotary support assemblies spaced apart from each other;

[0021] The rotation support assembly includes a third connecting member connected to the first supporting member, a fourth connecting member connected to the second supporting member, and a universal joint connected between the third connecting member and the fourth connecting member;

[0022] The universal joint has multiple rotation directions, and at least some of the multiple rotation directions are the same as the pitch direction and / or roll direction of the aircraft.

[0023] In one embodiment, the at least one torque adjustment assembly comprises:

[0024] a first adjustment assembly comprising a plurality of counterweights detachably mounted on the balance arm, for adjusting a vertical moment when the number and / or weight of the counterweights is changed, wherein a flight parameter of the aircraft in vertical flight is measured based on the weight of the counterweight at the second end, the first center distance, and the second center distance;

[0025] The second adjustment component includes a wind resistance plate whose tilt angle can be changed relative to the horizontal direction. When the tilt angle of the wind resistance plate is changed, it is used to adjust the resistance torque in the tilt direction; when the tilt angle of the rotor of the aircraft changes, the flight parameters of the aircraft in a uniform forward flight state are measured by controlling the resistance of the wind resistance plate.

[0026] In one embodiment, the first adjustment assembly includes a shaft fixed to the mounting frame, the length direction of the shaft is perpendicular to the length direction of the mounting frame, and the parts of the shaft extending on both sides of the mounting frame form a bearing portion, which is used to install the counterweight.

[0027] In one embodiment, the second adjustment assembly includes a mounting member fixed to the balance arm, the wind resistance plate is connected to the mounting member, and the wind resistance plate is tilted relative to the mounting member;

[0028] One side of the wind resistance plate is rotatably connected to the mounting member, and the other side is connected to the mounting member via at least one telescopic member. When the telescopic member is extended or retracted, it is used to adjust the inclination angle of the wind resistance plate relative to the mounting member; a drive control unit connected to the telescopic member is also included, and the drive control unit is used to control the telescopic length of the telescopic member.

[0029] In one embodiment, the first wheel assembly is mounted on the bottom of the first support, and the first wheel assembly is supported on the ground or an external support, and is used to move the first support in at least one direction relative to the ground; and / or,

[0030] a second wheel assembly mounted on the bottom of the second support, the second wheel assembly being supported on the ground or an external support and configured to move the second support in at least one direction relative to the ground; and / or

[0031] The third running wheel assembly is installed at the bottom of the torque regulating device. The third running wheel assembly is supported on the ground or an external support and is used to move the torque regulating device in at least one direction relative to the ground.

[0032] The technical solution provided by this application may have the following beneficial effects:

[0033] In the solution provided by this embodiment, the bearing mechanism and the torque adjustment component of the flight test device are respectively installed at the first end and the second end of the balance arm. At least one torque adjustment component is used to adjust the resistance torque in different directions, for example, it can adjust the load in the vertical direction and / or the resistance torque in the rotational direction. The bearing mechanism can move in multiple degrees of freedom. For example, the bearing mechanism can not only rotate around the support frame with the balance arm, but also rise and fall in the vertical direction with the first end of the balance arm, so that the flight parameters of the aircraft in different flight modes can be tested.

[0034] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The above and other objects, features and advantages of the present application will become more apparent through a more detailed description of exemplary embodiments of the present application in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the present application.

[0036] Figure 1 1 is a schematic structural diagram of a flight test device according to an embodiment of the present application;

[0037] Figure 2 1 is a schematic structural diagram of a support member of a flight test device according to an embodiment of the present application;

[0038] Figure 3 1 is a schematic structural diagram of a balance arm of a flight test device shown in an embodiment of the present application;

[0039] Figure 4 1 is a schematic structural diagram of a test stand for a flight test device according to an embodiment of the present application;

[0040] Figure 5 1 is a schematic structural diagram of a supporting mechanism of a flight test device shown in an embodiment of the present application;

[0041] Figure 6 It is a structural diagram shown in an embodiment of the present application;

[0042] Figure 7 1 is a schematic structural diagram of a first adjustment assembly of a flight test device shown in an embodiment of the present application;

[0043] Figure 8 1 is a schematic structural diagram of a second adjustment assembly of a flight test device shown in an embodiment of the present application;

[0044] Figure 9 is a structural schematic diagram of a supporting mechanism of a flight test device shown in another embodiment of the present application;

[0045] Figure 10 yes Figure 9 A schematic structural diagram of a rotary support mechanism shown in an embodiment.

[0046] Reference numerals: 500, aircraft; 300, test frame; 400, bearing mechanism; 100, support frame; 200, balance arm; 600, first adjustment assembly; 120, support column; 110, first running wheel assembly; 130, slewing connector; 140, connecting seat; 210, profile; 720, first shaft; 230, support block; 310, second running wheel assembly; 320, connecting base; 330, truss structure; 331, first mounting portion; 332, second mounting portion; 322, second connecting hole; 321, first connecting hole; 410, first support member; 450, second support member; 460, first rotor bracket; 470, second rotor bracket; 480, head support member; 490, stand; 411, tail support member; 420, first connecting member; 440, second connecting member; 430, bearing; 610, third walking wheel assembly; 620, mounting seat; 700, counterweight assembly; 710, limit member; 220, second axis; 730, counterweight; 800, second adjustment assembly; 810, mounting member; 820, telescopic member; 830, hinged portion; 840, wind resistance plate; 910, third connecting member; 920, fourth connecting member; 930, cavity; 911, connecting plate; 921, first assembly; 922, second assembly. DETAILED DESCRIPTION

[0047] The preferred embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although the preferred embodiments of the present application are shown in the accompanying drawings, it should be understood that the present application can be implemented in various forms and should not be limited by the embodiments described herein. Instead, these embodiments are provided to make the present application more thorough and complete, and to fully convey the scope of the present application to those skilled in the art.

[0048] The terms used in this application are for the purpose of describing specific embodiments only and are not intended to limit this application. As used in this application and the appended claims, the singular forms "a," "an," "the," and "the" are intended to include the plural forms, unless the context clearly indicates otherwise. It should also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0049] It should be understood that although the terms "first", "second", "third", etc. may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0050] In the description of this application, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0051] Unless otherwise expressly specified or limited, terms such as "mounted," "connected," "connect," and "fixed" should be interpreted broadly. For example, they may refer to fixed or detachable connections, or integration; mechanical or electrical connections; direct or indirect connections through an intermediary; and internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0052] Related art flight test devices are generally designed for specific verification test items, which have certain limitations and make it difficult to test various flight parameters of an aircraft in different flight modes. To address the above issues, embodiments of the present application provide a flight test device for an aircraft that can verify and test various flight parameters of an aircraft under test in different flight modes.

[0053] The technical solutions of the embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0054] Figure 1 It is a structural schematic diagram of a flight test device shown in one embodiment of the present application.

[0055] See also Figure 1 The flight test device provided in the embodiment of the present application includes:

[0056] The support frame 100 has a rotating support portion at the top thereof;

[0057] The balancing arm 200 includes a first end, a second end, and a rotating connection portion disposed between the first and second ends. The rotating connection portion is rotatably mounted on the rotating support portion. The balancing arm 200 can move around the support frame 100 at both ends along its length, moving in a first direction and a second direction. A first center distance is defined between the first end and the rotating support portion, and a second center distance is defined between the second end and the rotating support portion.

[0058] The test frame 300 is movably mounted on the first end of the balance arm 200;

[0059] A carrying mechanism 400 is mounted on top of the test frame and is used to carry the aircraft 500 to be tested. The carrying mechanism 400 can move with the test aircraft in at least one degree of freedom.

[0060] The torque adjustment device is installed at the second end of the balance arm 200. The torque adjustment device includes at least one torque adjustment component. The at least one torque adjustment component is used to adjust the resistance torque in different directions to test the flight parameters of the aircraft in different flight modes.

[0061] In the solution provided by this embodiment, the bearing mechanism and the torque adjustment component are respectively installed at the first end and the second end of the balance arm, and at least one torque adjustment component is used to adjust the resistance torque in different directions, for example, it can adjust the load in the vertical direction and / or the resistance torque in the rotational direction. The bearing mechanism 400 can move in multiple degrees of freedom. For example, the bearing mechanism 400 can not only rotate around the support frame 100 with the balance arm 200, but also can rise and fall in the vertical direction with the first end of the balance arm 200. Therefore, the flight parameters of the aircraft in different flight modes can be tested, such as testing various flight parameters of the aircraft in the tilting and vertical lifting flight modes.

[0062] The aircraft may be a tiltrotor aircraft, and the flight test device of the present application is at least capable of testing the flight parameters of the tiltrotor aircraft in vertical ascent and descent and horizontal uniform forward flight modes.

[0063] It is understandable that the aircraft that can be tested in this application is not limited to tilt-rotor aircraft, but can also be other types of aircraft, and this application does not limit this.

[0064] In this embodiment, the support frame 100 includes a first support, a rotating connection 130 and a connecting seat 140; the connecting seat 140 is rotatably connected to the first support through the rotating connection 130, and the balance arm 200 is rotatably installed on the connecting seat 140; wherein, the rotating connection 130 can rotate along a first direction relative to the first support, and the balance arm 200 can rotate along a second direction relative to the connecting seat 140.

[0065] In this embodiment, a plurality of first running wheel assemblies 110 are installed at the bottom of the first support. The first running wheel assemblies 110 are used to move the first support in at least one direction relative to the ground. The first rotating member may be a universal wheel.

[0066] See also Figure 2 The first support includes a support column 120 arranged along the vertical direction and a plurality of reinforcement members 121 connected to the support column 120. The plurality of reinforcement members 121 are arranged along the circumference of the support column 120 and can stabilize the support column 120 in a vertical state.

[0067] The rotary connector 130 can be a bearing, the axial direction of the bearing being parallel to the axial direction of the support column. The bearing is mounted on the upper end surface of the support column 120, the outer ring of the bearing is fixed to the support column 120, and the inner ring is rotatable, or the outer ring of the bearing is rotatable and the inner ring is fixed to the support column 120. The connecting seat 140 is fixed to the rotatable inner ring or outer ring of the bearing.

[0068] In some embodiments, the connecting base 140 has a U-shaped structure. Specifically, the connecting base 140 includes a bottom 141 and two side panels 142 connected to the bottom 141. The bottom 141 is horizontally oriented, and the two side panels 142 are vertically oriented and spaced apart. The balancing arm 200 is accommodated near its center between the two side panels 142. The balancing arm 200 has a hole, in which a sleeve is installed. A bearing is installed in the sleeve. A rotating shaft passes through the bearing. The balancing arm 200 is connected to the side panels 142 via the rotating shaft. The axial direction of the rotating shaft is perpendicular to the axial direction of the rotary connector 130, allowing the balancing arm 200 to rotate vertically around the rotating shaft.

[0069] See also Figure 3 In some embodiments, the balancing arm 200 is constructed from a plurality of parallel metal profiles 210 (e.g., aluminum alloy profiles), providing excellent structural strength. The metal profiles 210 may be separated by support blocks 230. It is understood that the balancing arm 200 may also be a one-piece rod-shaped structure.

[0070] See also Figure 4 and Figure 5 In some embodiments, the test frame 300 includes a second support, which is rotatably connected to the first end of the balance arm 200 in a second direction. This supports the stability of the test frame when the first end of the balance arm 200 is raised or lowered. A supporting mechanism 400 is disposed on top of the second support. The supporting mechanism 400 includes a first support member 410 and a second support member 450 that are vertically spaced and movably connected. A support assembly is disposed above the second support member 450 and is used to support the aircraft to be tested.

[0071] In some embodiments, the first support member 410 and the second support member 450 are rotatably connected via a rotary support mechanism, and the second support member 450 rotates relative to the first support member 410 in at least one direction.

[0072] The second support can include a truss structure 330 and a connecting base 320. The truss structure 330 is formed by connecting a number of rod-shaped members, which can be angle irons. The connecting base 320 is connected to the bottom of the truss structure 330. The connecting base 320 can be a U-shaped structure. A second running wheel assembly 310 is mounted on the bottom of the connecting base 320. The second running wheel assembly 310 is supported on the ground or an external support and is used to enable the second support to move in at least one direction relative to the ground or external support. In some embodiments, the second running wheel assembly 310 can be a universal wheel.

[0073] In some embodiments, the connecting base 320 is provided with a first connecting hole 321 and a second connecting hole 322. The first connecting hole 321 is provided on the bottom wall of the connecting base 320, and the second connecting hole 322 is provided on the side wall of the connecting base 320. The first connecting hole 321 is used to install the second walking wheel assembly 310, and the second connecting hole 322 is used to install the rotating shaft. The rotating shaft is rotatably connected to the balancing arm 200, so that the connecting base 320 and the balancing arm 200 can rotate relative to each other around the rotating shaft, and the axial direction of the rotating shaft is perpendicular to the length direction of the balancing arm 200.

[0074] In this embodiment, a first mounting portion 331 is provided at the bottom of the truss structure 330 , and the first mounting portion 331 is used to connect to the connecting base 320 . A second mounting portion 332 is provided at the top of the truss structure 330 , and the second mounting portion 332 is used to connect to the supporting mechanism 400 .

[0075] See also Figure 5 In some embodiments, the first support member 410 and the second support member 450 may be plate-like structures, with the first support member 410 fixedly connected to the second mounting portion 332 of the truss structure 330. A support structure is provided above the second support member 450 to support the aircraft 500 to be tested. This eliminates the need to connect the aircraft 500 to the support structure during testing, making it easier to operate.

[0076] See also Figure 1 and Figure 6 The aircraft 500 to be tested consists of a fuselage 510, blades 520, a drive motor 530, a motor connection assembly 540, a joint motor 550 and a joint mounting assembly 560; wherein the drive motor 530 is transmission-connected to the blades 520 for driving the blades 520 to rotate, and the shutdown motor 550 is used to change the inclination angle of the blades 520 relative to the fuselage 510, thereby realizing the function of converting the vertical flight state into the horizontal tilt state.

[0077] In some embodiments, the support structure may include a gantry 490, a first rotor bracket 460 and a second rotor bracket 470 arranged on the left and right sides of the gantry 490, and a bow support member 480 and a tail support member 411 arranged on the front and rear sides of the gantry 490. The gantry 490 is used to support the fuselage of the aircraft 500, and the support structure can stabilize the aircraft 500 relative to the second support member 450.

[0078] See also Figure 5 In some embodiments, the slewing support mechanism includes a first connecting member 420, a second connecting member 440 and a bearing 430; the first connecting member 420 is connected to the first support member 410, and the second connecting member 440 is connected to the second support member 450. The first connecting member and the second connecting member 440 are connected by a bearing 430. The rotation direction of the bearing 430 is the same as the pitch direction of the aircraft 500, which can release the degree of freedom in the pitch direction.

[0079] In this embodiment, two rotary support mechanisms may be provided, and the two rotary support mechanisms are arranged along the left and right directions of the aircraft 500 , and the axial directions of the bearings 430 of the two rotary support mechanisms are parallel or along the same axis.

[0080] See also Figure 9 In some embodiments, the rotation support assembly includes a third connector 910 connected to the first support member 410, a fourth connector 920 connected to the second support member 450, and a universal joint connected between the third connector 910 and the fourth connector 920. The universal joint has multiple rotation directions, at least some of which coincide with the pitch and / or roll directions of the aircraft. In this embodiment, since the third connector 910 and the fourth connector 920 are connected by the universal joint, testing of the aircraft 500 in both pitch and roll degrees of freedom is possible.

[0081] See also Figure 10 In some embodiments, the universal joint includes a spherical member 912 fixed to a connecting plate 911 of a third connecting member 910 and a cavity 930 provided in a fourth connecting member 920. The spherical member 912 is received in the cavity 930 and can rotate in different directions within the cavity 930. In some embodiments, the fourth connecting member 920 includes a first assembly 921 and a second assembly 922 connected thereto. The cavity 930 is defined by the first assembly 921 and the second assembly 922.

[0082] See also Figure 7In some embodiments, at least one torque adjustment assembly includes a first adjustment assembly 600 for adjusting vertical torque. Flight parameters of the aircraft during vertical flight can be measured based on the total weight of the second-end counterweight 730, the first center distance, and the second center distance. For example, when the aircraft is in vertical flight, the vertical drag torque can be the product of the total weight of the first-end counterweight 730 and the first center distance.

[0083] The first adjustment assembly 600 includes a mounting base 620 and a first shaft 720 fixed to the mounting base 620. The length of the first shaft 720 is perpendicular to the length of the balance arm 200. The portions of the first shaft 720 extending from both sides of the mounting base 620 form mounting portions for mounting the counterweight assembly 700. The counterweight assembly includes at least one counterweight 730 of a specific size and / or weight. A stopper 710 is provided at the end of the first shaft 720. The stopper is used to position the counterweight 730 at the upper axial limit of the first shaft 720, thereby maintaining the counterweight 730 stable. In some embodiments, the stopper 710 can be a positioning pin extending through the end of the first shaft 720. In some embodiments, the mounting base 620 is connected to the balance arm 200 via the second shaft 220.

[0084] Some embodiments further include a third wheel assembly 610 mounted on the bottom of the torque adjustment device, for example, mounted on the bottom of the mounting base 620. The third wheel assembly 610 is supported on the ground or an external support and is configured to move the torque adjustment device in at least one direction relative to the ground. In some embodiments, the third wheel assembly 610 can be a universal wheel.

[0085] See also Figure 8 In some embodiments, at least one torque adjustment component includes a second adjustment component 800, which includes a mounting member 810 fixed to the balance arm 200 and a windage plate 840 connected to the mounting member 810. When the inclination angle of the windage plate 840 is changed, the resistance torque in the tilt direction is adjusted. When the tilt angle of the rotor of the aircraft changes, the flight parameters of the aircraft in the uniform forward flight mode are measured by controlling the resistance of the windage plate 840.

[0086] In some embodiments, the mounting member 810 is arranged in a horizontal direction, and the wind resistance plate 840 is arranged at an angle relative to the mounting member 810; wherein, one side of the wind resistance plate 840 is rotatably connected to the mounting member 810, and the other side is connected to the mounting member 810 through at least one telescopic member 820, and when the telescopic member 820 is extended or retracted, it is used to adjust the inclination angle of the wind resistance plate 840 relative to the mounting member 810, wherein, a drive control unit connected to the telescopic member 820 is also included, and the drive control unit is used to control the telescopic distance of the telescopic member.

[0087] When the tilt angle of the rotor of the aircraft is 0 degrees (that is, when the plane where the rotor is located is parallel to the horizontal plane), since the value of the first center distance between the first end of the balance arm and the rotating support part is known, the vertical resistance torque at the second end can be adjusted by adjusting the total weight of the counterweight 730 at the second end, and the vertical tensile torque of the aircraft can be measured. The aerodynamic performance of the aircraft in the vertical lifting flight mode can be evaluated based on the tensile torque and the blade speed, where the blade speed can be obtained from the flight control unit of the aircraft.

[0088] When the tilt angle of the aircraft's rotor changes (i.e., gradually rotates from 0 degrees to tilt), the magnitude of the horizontal resistance torque can be controlled by adjusting the angle of the wind resistance plate 840 by the drive control unit, thereby controlling the aircraft's uniform forward flight. At this time, the aircraft's flight control unit and navigation control unit can read the aircraft's uniform forward flight speed, blade tilt angle, blade speed and other information, thereby evaluating the aircraft's tilt flight performance in the uniform forward flight state.

[0089] In some embodiments, the mounting member 810 may be a plate-like structure, the telescopic member 820 may be a combination of a telescopic motor or a hydraulic cylinder and a telescopic shaft, and the drive control unit may be a hydraulic control unit. By controlling the telescopic member 820 to extend or retract via the hydraulic control unit, the angle between the wind resistance plate 840 and the mounting member 810 can be adjusted, thereby changing the windward area of ​​the wind resistance plate 840 and, in turn, adjusting the horizontal resistance.

[0090] In some embodiments, the mounting member 810 is provided with a plurality of first hinges 830 and second hinges. The wind deflector plate has a plurality of first connection points on one horizontal side, and the plurality of first connection points are hingedly connected to the first hinges 830. The wind deflector plate has a plurality of second connection points on the other horizontal side. The telescopic member includes a main body and a telescopic rod provided on the main body. The plurality of second connection points are hingedly connected to the ends of the telescopic rod, and the second hinge is hingedly connected to the main body of the telescopic member.

[0091] In this embodiment, by placing a counterweight 730 and a windage plate 840 at the first end, the vertical drag torque can be varied by adjusting the weight of the counterweight, while the rotational drag torque can be varied by adjusting the windage area of ​​the windage plate 840. This allows for testing of flight parameters in vertical and constant forward flight. The testing process only requires adjusting the inclination angle of the windage plate and the weight of the counterweight. There is no need to drive a motor to apply a load, collect data from sensors, or secure the aircraft to a support structure. This results in a simple structure, ease of operation, and reduced costs.

[0092] The embodiments of the present application have been described above. The above description is illustrative and not exhaustive, and is not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is selected to best explain the principles of the embodiments, their practical applications, or improvements to the technology in the market, or to enable other persons skilled in the art to understand the embodiments disclosed herein.

Claims

1. A flight test device for an aircraft, characterized in that: include: A support frame, wherein a rotating support portion is provided on the top of the support frame; a balancing arm, the balancing arm comprising a first end, a second end, and a rotational connection portion disposed between the first end and the second end, the rotational connection portion being rotatably mounted on the rotational support portion, the balancing arm being movable along both ends of its length around the support frame in a first direction and a second direction, the first end and the rotational support portion being spaced apart by a first center distance, and the second end and the rotational support portion being spaced apart by a second center distance; a test stand, movably mounted on the first end; a carrying mechanism, mounted on the top of the test frame, for carrying the aircraft to be tested, and capable of moving with the aircraft in at least one degree of freedom; a torque adjustment device mounted on the second end, the torque adjustment device comprising at least one torque adjustment component, the at least one torque adjustment component being used to adjust the drag torque in different directions to test flight parameters of the aircraft in different flight modes; The torque adjustment assembly includes: a first adjustment assembly comprising a plurality of counterweights detachably mounted on the balance arm, for adjusting a vertical moment when the number and / or weight of the counterweights is changed, wherein a flight parameter of the aircraft in vertical flight is measured based on the weight of the counterweight at the second end, the first center distance, and the second center distance; The second adjustment component includes a wind resistance plate whose tilt angle can be changed relative to the horizontal direction. When the tilt angle of the wind resistance plate is changed, it is used to adjust the resistance torque in the tilt direction. When the tilt angle of the rotor of the aircraft changes, the flight parameters of the aircraft in a uniform forward flight state are measured by controlling the resistance of the wind resistance plate.

2. The flight test device according to claim 1, characterized in that: The support frame includes a first support, a rotary connector and a connecting seat; The swivel connector is connected between the first support and the connecting seat, and the balance arm is rotatably mounted on the connecting seat; wherein, the swivel connector can rotate in a first direction relative to the first support, and the balance arm can rotate in a second direction relative to the connecting seat.

3. The flight test device according to claim 2, characterized in that: The test stand comprises: a second support, the second support being rotatably connected to the first end of the balance arm in the second direction; A carrying mechanism is arranged on the top of the second support, and the carrying mechanism includes a first support member and a second support member that are spaced apart in the vertical direction and movably connected. A supporting assembly is provided above the second support member, and the supporting assembly is used to be connected to the aircraft to be tested.

4. The flight test device according to claim 3, characterized in that: The first support member and the second support member are movably connected via a rotary support mechanism; The second support member is movable relative to the first support member along at least one degree of freedom.

5. The flight test device according to claim 4, characterized in that: The rotary support mechanism includes at least two rotary support assemblies arranged at intervals; The rotation support assembly includes a first connecting member connected to the first supporting member, a second connecting member connected to the second supporting member, and a bearing connected between the first connecting member and the second connecting member; The rotation direction of the bearing is the same as the pitch direction of the aircraft.

6. The flight test device according to claim 5, characterized in that: The rotary support mechanism includes at least two rotary support assemblies arranged at intervals; The rotation support assembly includes a third connecting member connected to the first supporting member, a fourth connecting member connected to the second supporting member, and a universal joint connected between the third connecting member and the fourth connecting member; The universal joint has multiple rotation directions, and at least some of the multiple rotation directions are the same as the pitch direction and / or the tilt direction of the aircraft.

7. The flight test device according to claim 1, characterized in that: The first adjustment component includes a mounting seat and a shaft fixed to the mounting seat, the length direction of the shaft is perpendicular to the length direction of the balance arm, and the parts of the shaft extending on both sides of the mounting seat form mounting portions, which are used to install the counterweight.

8. The flight test device according to claim 1, characterized in that: The second adjustment assembly includes a mounting member fixed to the balance arm and a wind resistance plate connected to the mounting member, wherein the wind resistance plate is tilted relative to the mounting member; One side of the wind resistance plate is rotatably connected to the mounting member, and the other side is connected to the mounting member via at least one telescopic member. When the telescopic member is extended or retracted, it is used to adjust the inclination angle of the wind resistance plate relative to the mounting member; a drive control unit connected to the telescopic member is also included, and the drive control unit is used to control the telescopic length of the telescopic member.

9. The flight test device according to claim 3, characterized in that: Also includes: a first running wheel assembly mounted on the bottom of the first support, the first running wheel assembly being supported on the ground or an external support and configured to move the first support in at least one direction relative to the ground; and / or a second wheel assembly mounted on the bottom of the second support, the second wheel assembly being supported on the ground or an external support and configured to move the second support in at least one direction relative to the ground; and / or The third running wheel assembly is installed at the bottom of the torque regulating device. The third running wheel assembly is supported on the ground or an external support and is used to move the torque regulating device in at least one direction relative to the ground.

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