Aircraft control surface loading device and testing method

Abstract

The present invention discloses an aircraft rudder loading device and a testing method, wherein the device comprises a clamping mechanism, a fan-shaped mechanism and a steel cable, the clamping mechanism comprises a first clamping part and a second clamping part, the first clamping part and the second clamping part cooperate with each other to clamp the rudder; the rudder comprises a first surface and a second surface arranged opposite to each other, the first surface and the second surface are connected to the edge of the rudder, the first clamping part abuts against the first surface, and the second clamping part abuts against the second surface and the edge; the center of the fan-shaped mechanism is fixed to the clamping mechanism, one end of the arcuate edge of the fan-shaped mechanism is provided with a mounting piece, the fan-shaped mechanism comprises a guide groove, and the guide groove is arranged along the arcuate edge of the fan-shaped mechanism; the steel cable is connected to the mounting piece and is pulled, at least a part of the steel cable is located in the guide groove, and the fan-shaped surface of the fan-shaped mechanism is parallel to the plane where the deflection track of the rudder is located. The testing method is to use the above device to load on the rudder for testing. The present application is easy to install and disassemble on the aircraft rudder.

Description

Technical Field

[0001] The invention relates to the field of aircraft testing, and in particular to an aircraft control surface loading device and a testing method. Background Art

[0002] Aircraft control surfaces can be deflected in the airflow when the aircraft is flying to generate control force to manipulate the aircraft's flight attitude. The control surface loading device is mainly used to simulate aerodynamic force on the ground and load the aerodynamic force to the aircraft control surface for testing.

[0003] The existing rudder loading device generally adopts the form of a tape plus a lever system, specifically, the tape is pasted on the rudder, and the lever system then pulls the rudder through the tape to apply a simulated force to the rudder. However, this method has the following problems: first, the positioning requirements of the tape are high, and the tape pasting process is labor-intensive and complicated; second, the tape cannot be reused after the test is completed, the cost is high, and the tape pasting will damage the rudder. Summary of the invention

[0004] The first object of the present invention is to provide an aircraft control surface loading device which is easy to install and disassemble.

[0005] The second object of the present invention is to provide an aircraft control surface loading test method that is easy to install and disassemble.

[0006] The first purpose of the present invention provides an aircraft rudder surface loading device, including a clamping mechanism, a fan-shaped mechanism and a steel cable, the clamping mechanism including a first clamping part and a second clamping part, the first clamping part and the second clamping part cooperate with each other to clamp the rudder surface; the rudder surface includes a first surface and a second surface arranged opposite to each other, the first surface and the second surface are connected to the edge of the rudder surface, the first clamping part abuts against the first surface, and the second clamping part abuts against the second surface and the edge; the center of the fan-shaped mechanism is fixed to the clamping mechanism, one end of the arc-shaped edge of the fan-shaped mechanism is provided with a mounting piece, the fan-shaped mechanism includes a guide groove, and the guide groove is arranged along the arc-shaped edge of the fan-shaped mechanism; the steel cable includes a first extension end and a second extension end arranged opposite to each other, the first extension end is fixedly connected to the mounting piece, the second extension end is pulled, at least a portion of the steel cable is located in the guide groove, and the fan-shaped surface of the fan-shaped mechanism is parallel to the plane where the deflection trajectory of the rudder surface is located.

[0007] As can be seen from the above scheme, the first clamping part and the second clamping part are used to fix the aircraft rudder surface, which is not only quick and convenient to install, but also easy to disassemble, and is not easy to cause damage to the aircraft rudder surface. After disassembly, the loading device can be reused to save costs. The first clamping part abuts the first surface of the rudder surface, and the second clamping part abuts the second surface of the rudder surface and the edge of the rudder surface. The three abutments can make the clamping mechanism more firmly combined with the aircraft rudder surface. Since the traction direction of the steel cable remains unchanged, as the aircraft rudder surface deflects, the angle between the traction direction of the steel cable and the rudder surface changes. If the steel cable is directly connected to the clamping mechanism, the traction force transmitted by the steel cable to the rudder surface will change greatly with the change of the angle between the traction direction of the steel cable and the rudder surface. In order to prevent the traction force of the steel cable on the rudder surface from having a large difference from the preset value due to the deflection of the rudder surface, a fan-shaped mechanism and a guide groove at the arc edge of the fan-shaped mechanism are used to guide and adjust the traction position of the steel cable, so that the traction force of the steel cable on the rudder surface is conducted by the fan-shaped mechanism and maintained within the range of the preset value. In addition, making the fan-shaped surface of the fan-shaped mechanism parallel to the plane where the deflection trajectory of the rudder surface is located can allow the traction force of the steel cable to be transmitted to the aircraft rudder surface more accurately.

[0008] A preferred solution is that the clamping mechanism also includes an adjustment track, the first clamping portion is fixed to the adjustment track, the center of the fan-shaped mechanism is fixed to the adjustment track, the second clamping portion is adjustably mounted on the adjustment track, and the adjustment track extends radially along the center of the circle.

[0009] It can be seen that due to the inconsistency of the shapes of the control surfaces of different aircraft, the provision of an adjustment track allows the clamping mechanism to be installed on different aircraft control surfaces. In order to better transmit the traction force of the steel cable to the aircraft control surface without deviation, this solution makes the extension direction of the adjustment track, that is, the clamping direction of the clamping mechanism, parallel to the fan surface of the fan mechanism.

[0010] A further solution is that the fan-shaped mechanism is connected to the adjustment track at a connecting position, and the distance between the connecting position and the first clamping portion is smaller than the distance between the connecting position and the second clamping portion.

[0011] It can be seen that when testing the aircraft control surface, the traction force needs to be applied to the position of the first surface of the control surface, that is, the contact position between the first clamping part and the control surface is the main force transmission area, and the second clamping part mainly plays a fixing role. Therefore, setting the connection position to be closer to the first clamping part can make the traction force mainly applied to the first surface of the control surface.

[0012] A further solution is that the first clamping portion and the second clamping portion are arranged on the same side of the adjusting track, and the first clamping portion and the mounting member are respectively arranged on two opposite sides of the adjusting track.

[0013] It can be seen that the first clamping portion and the second clamping portion are arranged on the same side of the adjusting track to clamp the rudder surface, and the mounting piece and the first clamping portion are arranged on opposite sides of the adjusting track so that the traction force of the steel cable on the rudder surface passes through the guide groove, the center of the circle and the clamping mechanism of the fan-shaped mechanism in one direction in turn and is finally transmitted to the rudder surface.

[0014] A further solution is that the second clamping part includes a rod body, a slider, a fastener and a block, the first end of the rod body is fixed to the slider, the block is fixed to the second end of the rod body, the slider is slidably connected to the adjustment track, the fastener is installed on the slider and can cooperate with the adjustment track to limit the sliding of the slider, the block is "L"-shaped, and the block is provided with a first side wall and a second side wall perpendicular to each other, the first side wall is perpendicular to the extension direction of the adjustment track, the second side wall is perpendicular to the extension direction of the rod body, the first side wall is used to abut the edge, and the second side wall is used to abut the second surface.

[0015] It can be seen that the fastener cooperates with the adjustment track to adjust the fixed position of the second clamping portion on the adjustment track, and the "L"-shaped block can be used to abut the second surface and edge of the rudder surface.

[0016] A further solution is that the second clamping portion also includes an adjusting member, the adjusting member is screwed to the second end of the rod body, the clamping block cooperates with the adjusting member, and the position of the clamping block on the rod body can be changed by rotating the adjusting member.

[0017] It can be seen that the position of the block on the rod body can be changed by rotating the adjusting member, so that the second side wall of the block can abut against the second surface of the rudder surface.

[0018] A further solution is that the first clamping part includes a screw and a pressure block, the screw is screwed to the adjustment track, the extension direction of the screw is perpendicular to the extension direction of the adjustment track, the pressure block is fixed to one end of the screw, and the pressure block abuts against the first surface of the rudder surface.

[0019] It can be seen from this that the screw connection position of the adjusting screw rod in the adjusting track can change the position of the pressing block so that the pressing block can abut against the first surface of the rudder surface.

[0020] A further solution is that the contact position between the pressure block and the rudder surface is made of soft material.

[0021] It can be seen that soft materials can avoid damage to the rudder surface.

[0022] A further solution is that the angle at which the guide groove extends relative to the center of the circle on the arc side of the fan-shaped mechanism is greater than 30°.

[0023] It can be seen from this that the extension angle of the arcuate side of the guide groove needs to be large enough and needs to exceed the angle at which the rudder surface can deflect, so as to prevent the steel cable from exceeding the guide groove and causing deviation in traction.

[0024] The second object of the present invention provides a method for testing the loading of an aircraft control surface, which uses a loading device to test the deflection of the control surface, and the loading device uses the above-mentioned aircraft control surface loading device, comprising the following steps:

[0025] The first clamping part is abutted against the first surface of the rudder surface, and the second clamping part is abutted against the second surface of the rudder surface and the edge of the rudder surface, so that the clamping mechanism is fixed to the rudder surface;

[0026] Apply traction to the steel cable and transmit it to the rudder surface through the fan mechanism and the clamping mechanism in turn;

[0027] Control the deflection of the rudder surface and collect test data of the rudder surface. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] The present invention is further described using the accompanying drawings, but the embodiments in the accompanying drawings do not constitute any limitation to the present invention. A person skilled in the art can obtain other drawings based on the following drawings without creative work.

[0029] Figure 1 It is a structural diagram of an embodiment of an aircraft control surface loading device of the present invention.

[0030] Figure 2 The present invention is a side view of an aircraft control surface loading device embodiment of the present invention.

[0031] Figure 3 The present invention is a structural diagram of an aircraft control surface loading device embodiment with control surfaces and steel cables added.

[0032] Figure 4 The present invention is a structural diagram of a fan-shaped mechanism of an aircraft control surface loading device embodiment.

[0033] Figure 5 The present invention is a schematic diagram of a control surface deflection of an aircraft control surface loading device embodiment.

[0034] Figure 6 The present invention is a flowchart of an embodiment of a method for testing a loading surface of an aircraft. DETAILED DESCRIPTION

[0035] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] Reference Figures 1 to 5As shown, this embodiment provides an aircraft control surface loading device, including a clamping mechanism, a fan-shaped mechanism 2 and a steel cable 3. The clamping mechanism includes a first clamping portion 11, a second clamping portion 12 and an adjustment track 13. When the control surface 4 is tested, the control surface 4 is fixed between the first clamping portion 11 and the second clamping portion 12. Figure 3 As shown, the rudder surface 4 includes a first surface 41 and a second surface 42 which are arranged opposite to each other in the vertical direction. The first surface 41 and the second surface 42 extend and narrow toward the edge 43 of the rudder surface 4 and finally meet at the edge 43. The first clamping portion 11 is fixedly connected to the adjustment track 13, and the second clamping portion 12 is adjustably mounted on the adjustment track 13 along the extension direction of the adjustment track 13.

[0037] The first clamping portion 11 includes a screw rod 111 and a pressure block 112, wherein the screw rod 111 is screwed and fixed to the adjusting track 13 by two nuts, the extension direction of the screw rod 111 is perpendicular to the extension direction of the adjusting track 13, and the pressure block 112 is fixed to the end of the screw rod 111, and the position of the pressure block 112 relative to the adjusting track 13 can be changed by changing the installation position of the screw rod 111. The pressure block 112 abuts against the first surface 41 of the rudder surface 4. It should be noted that the position where the pressure block 112 contacts the first surface 41 of the rudder surface 4 is made of soft materials such as rubber or foam to avoid damage to the rudder surface 4.

[0038] like Figure 1 and Figure 2 As shown, the second clamping portion 12 includes a rod body 121, a slider 122, a fastener 123, a block 124 and an adjusting member 125. The first end of the rod body 121 is fixed to the slider 122, and the second end of the rod body 121 is fixed with the block 124. The rod body 121 is arranged perpendicular to the extension direction of the adjusting track 13. The slider 122 is slidably connected to the adjusting track 13. The fastener 123 is screwed and penetrated through the slider 122. After the slider 122 is slid to a specific position of the adjusting track 13, the fastener 123 is rotated to make the fastener 123 abut against the adjusting track 13, thereby limiting the sliding of the slider 122 and fixing the slider 122 to the adjusting track 13. The end of the rod body 121 has a threaded column, and the adjusting member 125 is screwed to the threaded column and cooperates with the block 124. The position of the block 124 on the rod body 121 can be changed by rotating the adjusting member 125.

[0039] like Figure 1 and Figure 2As shown, the block 124 is in an "L" shape, and the block 124 includes a first side wall 1241 and a second side wall 1242 which are perpendicular to each other, the first side wall 1241 is perpendicular to the extension direction of the adjustment track 13, and the second side wall 1242 is perpendicular to the extension direction of the rod body 121, wherein the first side wall 1241 is used to abut against the edge 43 of the rudder surface 4, and the second side wall 1242 is used to abut against the second surface 42 of the rudder surface 4. During the installation process, the position of the second clamping portion 12 on the slide rail can be changed by the cooperation of the fastener 123 and the adjustment track 13, so that the first side wall 1241 can just abut against the edge 43 of the rudder surface 4, and at the same time, the position of the block 124 on the rod body 121 can be changed by rotating the adjustment member 125, so that the second side wall 1242 can just abut against the second surface 42 of the rudder surface 4, and the material of the block 124 is selected to be wooden.

[0040] In addition, if Figure 1 As shown, in this embodiment, the block 124 is longer along the edge 43 of the rudder surface 4 so that it can abut against a larger area of ​​the rudder surface 4 to prevent the traction force from being concentrated in a smaller area of ​​the rudder surface 4 and causing damage to the edge 43 of the rudder surface 4.

[0041] like Figure 1 and Figure 4 As shown, the center 21 of the fan-shaped mechanism 2 provided in this embodiment is fixed to the adjustment track 13 by two studs, and the connection position between the fan-shaped mechanism 2 and the adjustment track 13 is close to the first clamping part 11, but far from the second clamping part 12, and the fan-shaped mechanism 2 and the first clamping part 11 are respectively arranged on opposite sides of the adjustment track 13. A mounting member 22 is arranged at one end of the arc-shaped edge of the fan-shaped mechanism 2 close to the second clamping part 12, and a guide groove 23 is arranged from the mounting member 22 to the direction away from the second clamping part 12 and along the arc-shaped edge of the fan-shaped mechanism 2. The steel cable 3 includes a first extension end and a second extension end, wherein the first extension end is fixedly connected to the mounting member 22, and the second extension end is connected to a weight or an actuator to provide traction to the first extension end.

[0042] It should be noted that the pulling direction of the steel cable 3, the plane where the deflection track of the rudder surface 4 is located, and the extending direction of the adjustment track 13 are all parallel to the fan-shaped surface of the fan-shaped mechanism 2. Figure 5 As shown, Figure 5 The rudder surface 4 shown is in Figure 3 The same observation angle of the rudder surface 4 shown, Figure 5The rudder surface 4 shown by the dotted line is the deflected rudder surface 4, wherein the plane where the deflection track 44 passed by the edge 43 is located is parallel to the fan surface of the fan-shaped mechanism 2. The traction direction of the steel cable 3 remains unchanged. When the rudder surface 4 is deflected, at least a continuous portion of the steel cable 3 starting from the connection with the mounting member 22 will be located in the guide groove 23, so that the traction force can be accurately transmitted to the rudder surface 4. In addition, in this embodiment, the angle of the guide groove 23 relative to the center 21 of the fan-shaped mechanism 2 at the arc side of the fan-shaped mechanism 2 is set to be greater than 30°.

[0043] The present application also provides an aircraft control surface loading test method, which uses an aircraft control surface loading device of the above embodiment to test the deflection of the control surface 4, referring to Figure 6 As shown, the specific steps include:

[0044] S1. Place the first clamping portion 11 in contact with the first surface 41 of the rudder surface 4, and place the second clamping portion 12 in contact with the second surface 42 of the rudder surface 4 and the edge 43 of the rudder surface 4, so that the clamping mechanism is fixed to the rudder surface 4. In this step, it is necessary to adjust the screw connection position of the screw 111 of the first clamping portion 11 on the adjustment track 13, the matching position of the fastener 123 and the adjustment track 13, and the adjustment member 125, so that the first side wall 1241 and the second side wall 1242 of the pressing block 112 and the clamping block 124 can respectively accurately abut against the first surface 41 of the rudder surface 4, the edge 43 of the rudder surface 4 and the second surface 42 of the rudder surface 4.

[0045] S2. Apply traction to the steel cable 3 by hanging a weight or connecting an actuator, etc. The traction can be transmitted to the rudder surface 4 through the fan-shaped mechanism 2 and the clamping mechanism in turn. The traction on the rudder surface 4 can be used to simulate the force of the airflow on the rudder surface 4 during the flight of the aircraft. In addition, when the traction is applied to the rudder surface 4 in this step, the rudder surface 4 resists the traction through the locking mechanism or the supporting mechanism to maintain the deflection angle unchanged. In addition, in this process, the traction direction of the steel cable 3 remains unchanged, the initial deflection position of the rudder surface 4 can be changed, and the rudder surface 4 can be limited to the deflection position through the locking mechanism or the supporting mechanism, so as to more comprehensively collect the test data of the rudder surface 4 at different initial deflection positions.

[0046] S3. Control the deflection of the rudder surface 4. During this process, the rudder surface 4 releases the cooperation with the locking mechanism or the supporting mechanism and counteracts the traction force of the steel cable 3 through the deflection drive device. During the process of controlling the deflection of the rudder surface 4, the deflection angle of the rudder surface 4 can be continuously and dynamically adjusted. During this process, the steel cable 3 will continuously change its length in the guide groove 23. At this time, the test data of the rudder surface 4 is collected by setting up a variety of sensors. The test data includes but is not limited to the deflection angle of the rudder surface 4, the driving force of the deflection drive device and the movement amplitude of the handle for controlling the deflection of the rudder surface 4.

[0047] The above embodiment only expresses one implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. Therefore, the protection scope of the patent of the present invention shall be based on the attached claims.

Claims

1. An aircraft control surface loading device, characterized in that: It comprises a clamping mechanism, a fan-shaped mechanism and a steel cable, wherein the clamping mechanism comprises a first clamping part and a second clamping part, and the first clamping part and the second clamping part cooperate with each other to clamp the rudder surface; The rudder surface comprises a first surface and a second surface which are arranged opposite to each other, the first surface and the second surface are connected to an edge of the rudder surface, the first clamping portion abuts against the first surface, and the second clamping portion abuts against the second surface and the edge; The center of the fan-shaped mechanism is fixed to the clamping mechanism, one end of the arc-shaped edge of the fan-shaped mechanism is provided with a mounting member, and the fan-shaped mechanism includes a guide groove, and the guide groove is provided along the arc-shaped edge of the fan-shaped mechanism; The steel cable comprises a first extending end and a second extending end which are arranged opposite to each other, the first extending end is fixedly connected to the mounting member, the second extending end is pulled, at least a portion of the steel cable is located in the guide groove, and the fan-shaped surface of the fan-shaped mechanism is parallel to the plane where the deflection track of the rudder surface is located; The clamping mechanism further includes an adjustment track, the first clamping portion is fixed to the adjustment track, the center of the fan-shaped mechanism is fixed to the adjustment track, the second clamping portion is adjustably mounted on the adjustment track, and the adjustment track extends radially along the center of the circle; The fan-shaped mechanism is connected to the adjustment track at a connection position, and the distance between the connection position and the first clamping portion is smaller than the distance between the connection position and the second clamping portion; The first clamping portion and the second clamping portion are arranged on the same side of the adjusting track, and the first clamping portion and the mounting member are respectively arranged on two opposite sides of the adjusting track.

2. The aircraft control surface loading device according to claim 1, characterized in that: The second clamping portion includes a rod body, a slider, a fastener and a block, the first end of the rod body is fixed to the slider, the block is fixed to the second end of the rod body, the slider is slidably connected to the adjustment track, the fastener is installed on the slider and can cooperate with the adjustment track to limit the sliding of the slider, the block is "L"-shaped, and the block is provided with a first side wall and a second side wall perpendicular to each other, the first side wall is perpendicular to the extension direction of the adjustment track, the second side wall is perpendicular to the extension direction of the rod body, the first side wall is used to abut the edge, and the second side wall is used to abut the second surface.

3. The aircraft control surface loading device according to claim 2, characterized in that: The second clamping portion further comprises an adjusting member, which is threadedly connected to the second end of the rod body. The clamping block cooperates with the adjusting member, and the position of the clamping block on the rod body can be changed by rotating the adjusting member.

4. The aircraft control surface loading device according to claim 1, characterized in that: The first clamping portion includes a screw and a pressure block, the screw is screwed to the adjustment track, the extension direction of the screw is perpendicular to the extension direction of the adjustment track, the pressure block is fixed to one end of the screw, and the pressure block abuts against the first surface of the rudder surface.

5. The aircraft control surface loading device according to claim 4, characterized in that: The contact position between the pressing block and the rudder surface is made of soft material.

6. An aircraft control surface loading device according to any one of claims 1 to 5, characterized in that: The angle at which the guide groove extends relative to the center of the circle on the arcuate side of the fan-shaped mechanism is greater than 30°.

7. A method for testing the deflection of an aircraft control surface by loading a loading device, characterized in that: The loading device adopts an aircraft control surface loading device according to any one of claims 1 to 6; The following steps are involved: The first clamping portion is abutted against the first surface of the rudder surface, and the second clamping portion is abutted against the second surface of the rudder surface and the edge of the rudder surface, so that the clamping mechanism is fixed to the rudder surface; Applying traction to the steel cable, and transmitting the traction to the rudder surface through the fan-shaped mechanism and the clamping mechanism in sequence; The deflection of the control surface is controlled, and test data of the control surface is collected.

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