CN113148225B - Testing device and testing method for fixing and rotating helicopter blades - Google Patents
Testing device and testing method for fixing and rotating helicopter blades Download PDFInfo
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- CN113148225B CN113148225B CN202110423706.9A CN202110423706A CN113148225B CN 113148225 B CN113148225 B CN 113148225B CN 202110423706 A CN202110423706 A CN 202110423706A CN 113148225 B CN113148225 B CN 113148225B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M5/00—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings
- G01M5/0016—Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings of aircraft wings or blades
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Abstract
The invention belongs to the technical field of helicopter blade tests, and particularly relates to a test device and a test method for fixing and rotating a helicopter blade. The device is characterized by comprising an index plate (1), an automatic control module (2), a hydraulic substation module (3) and a test fixture (4); the test fixture (4) is fixed on the vertical end face; the indexing disc (1) is mounted on the test fixture (4), the automatic control module (2) is located on the side face of the indexing disc (1), the automatic control module (2) is used for controlling the rotation angle of the indexing disc (1) and receiving and sending signals, and meanwhile, a hydraulic oil port is formed in the side face of the indexing disc (1) and is used for being connected with the hydraulic substation module (3) through a hydraulic oil pipe; the hydraulic substation module (3) is used for driving the automatic control module (2) to move so as to drive the dividing plate (1) to rotate.
Description
Technical Field
The invention belongs to the technical field of helicopter blade tests, and particularly relates to a test device and a test method for fixing and rotating a helicopter blade.
Background
The composite material paddle forming method and the technological parameters have great influence on the structural characteristics of the paddle, and a stiffness measurement test of the paddle needs to be carried out to verify the conformance of the manufacture and the design of the paddle. Due to the particularity of the shape of the blade and the performance difference of each section, the flapping and shimmy stiffness of a plurality of sections needs to be tested, and the relative torsion angle of each section is different from that of the section 0, so that a blade mounting and fixing device which can drive the blade to rotate and can be fixed in a certain angle state needs to be designed to ensure that the chord line of the section to be tested is in a horizontal position.
For example, the test piece assembly is shown in FIG. 1, and the sectional structure is shown in FIG. 2. As shown in fig. 2, the string line forms an angle with the horizontal direction, and the direction of the load F is always vertically downward, so that the string line is not perpendicular to the direction of the load, which results in that the strain gauge, when loaded, deforms in the horizontal direction in addition to the vertical downward direction, which results in a large test error, which is not allowed in the test. A special mechanism must be provided to rotate the blade so that the chord line of the measured section of the blade is in a horizontal position, as shown in figure 3.
For such tests, the following test methods are currently used:
as shown in figure 1, a test fixture with a gear inside is designed, a manual load is used for driving a helicopter blade to rotate together, and after the helicopter blade reaches a certain angle, the helicopter blade is locked by the manual load.
The analysis shows that the method has the following defects:
1) This test method results in large test errors. As mentioned above, the manual load used in the test method is rotated and locked, and the manual load is not well controlled, so that the test fixture is likely to loosen, the angle of the section of the blade of the helicopter cannot be accurately realized, and the test error is increased;
2) This test method has limitations in use. For small and medium-sized blades, the self weight is not large, and the applied flapping and shimmy loads are not large, so that the method can be suitable. However, for a large-sized blade with a large load, such as a heavy-duty main blade (the self-weight is about 500kg, and the maximum applied load is about 1T), the manual load cannot be added so much that the test method cannot be used.
Disclosure of Invention
The purpose of the invention is: aiming at the problems in the prior art, the test device and the test method for fixing and rotating the helicopter blade are provided, and the test method is improved, and the control system and the hydraulic substation with higher precision are introduced, so that on one hand, the precision of an angle can be ensured, and the test precision can be improved, on the other hand, the mechanism can accurately position and lock the heavy blade at any position, and can prevent a test piece from loosening in the test loading process.
The technical scheme of the invention is as follows: in order to achieve the above object, according to a first aspect of the present invention, there is provided a test apparatus for fixing and rotating a helicopter blade, comprising an index plate 1, an automatic control module 2, a hydraulic substation module 3, a test fixture 4;
the test fixture 4 is fixed on the vertical end face and used for fixing a blade root of the helicopter to be tested; the index plate 1 is mounted on the test fixture 4 and is coaxial with the test fixture 4, the automatic control module 2 is located on the side surface of the index plate 1 and is connected with the index plate 1 through a cable, the automatic control module 2 controls the rotation angle of the index plate 1 and receives and sends signals, and meanwhile, the side surface of the index plate 1 is further provided with a hydraulic oil port for connecting with the hydraulic substation module 3 through a hydraulic oil pipe; a control cabinet (205) in the automatic control module (2) drives a servo motor (201) to move, so that the index plate 1 is driven to rotate, and the index plate is connected with the automatic control module 2 through a cable.
In a possible embodiment, the indexing disk 1 comprises a zero sensor 101 arranged inside it for signal zero clearing; a zero-signaling block 102 for receiving a signal; a transmitting block 103 for transmitting a control signal; a brake pad 104 for preventing the gear 105 from rotating after braking; the inner edge position of the dividing disc 1 is provided with a gear 105 which is used for being matched and connected with a servo motor 201 in the automatic control module 2;
the automatic control module 2 comprises a servo motor 201, a fairing 202 arranged outside the servo motor 201, a loosening sensor 203 arranged inside the fairing 202, and a brake sheet 104 loosening when the loosening sensor receives a loosening signal, wherein the fairing 202 is fixedly arranged on the side surface of the dividing plate 1; a brake sensor 204 for braking the brake sheet 104 when receiving a brake signal; the control cabinet 205 is used for sending various control commands, and the control cabinet 205 is electrically connected with the servo motor 201, the loosening sensor 203 and the tightening sensor 204 through cables to realize signal transmission;
the hydraulic substation module 3 comprises a hydraulic interface 301 correspondingly connected with the hydraulic oil port 106 on the side surface of the indexing disc 1.
In a possible embodiment, the commands issued by the control cabinet 205 include index plate release commands, index plate angle clear commands, angle commands, and index plate brake commands.
According to a second aspect of the present invention, there is provided a test method for fixing and rotating a helicopter blade, using the above test apparatus, characterized by comprising the following steps:
s1: fixedly mounting the index plate 1 on a bearing wall;
s2: installing a test fixture 4 connected with the root of the blade to be tested on the index plate 1;
s3: fixedly clamping the blade to be tested on a test fixture 4;
s4: the hydraulic substation module 3 is connected with the index plate 1 by using a hydraulic oil pipe, the control cabinet 205 is connected with the servo motor 201 by a cable, and the hydraulic substation module 3 is connected with the control cabinet 205 by a cable;
s5: when an index plate loosening command is input into the control cabinet 205, the hydraulic pipeline of the hydraulic substation module 3 starts oil return to enable the index plate 1 to reach a loosening state, when the index plate 1 is completely loosened, the loosening sensor 203 transmits a command to the control cabinet 205, after receiving the command, the control cabinet 205 transmits a corresponding command to the servo motor 201, and at the moment, the servo motor 201 is driven to drive the index plate (1) to rotate;
s6: an index plate angle zero clearing command is input into the control cabinet 205, and after the zero sensor 101 receives the command, the zero signaling block 102 starts to work, and defaults the position of the index plate 1 to 0 degree;
s7: an angle command is input into the control cabinet 205, and the control cabinet 205 drives the servo motor 201 to drive the index plate 1 to rotate to reach a specified angle and then stop;
s8: inputting a dial braking command on the control cabinet 205, supplying oil to a pipeline of the hydraulic substation module 3 to enable the index plate 1 to be in a braking state, and transmitting an instruction to the control cabinet 205 by the braking sensor 204 when the index plate 1 is in the braking state and is completely braked;
s9: and carrying out subsequent formal loading tests.
In one possible embodiment, the input of commands to the control cabinet 205 may take the form of manual or automatic input; the automatic input is realized by programming.
In one possible embodiment, the control cabinet 205 inputs speed control commands to control the rotational speed of the helicopter blades based on their mass.
In one possible embodiment, the control cabinet 205 selects a servo motor with an appropriate power according to the size of the index plate.
In a possible embodiment, the hydraulic substation module 3 selects the flow capacity of the hydraulic substation according to the load size in the test.
The invention has the advantages that: the technical effect of the test device is mainly shown in the following aspects when the test device is used for blade rigidity test:
1. the precision is high. Due to the introduction of the control system, the precision of the angle can be ensured, and the precision of the test can be improved;
2. the mechanism can accurately position and lock the paddle at any position, and can avoid the loosening of a test piece in the test loading process;
3. the test device has wide application range, can be used on small and medium-sized blades of the helicopter, and can also be used on large blades;
4. the test device is simple and practical, and can effectively improve the working efficiency.
Drawings
FIG. 1 is an assembly schematic diagram of a helicopter blade flapping stiffness test apparatus in the prior art
FIG. 2 is a schematic diagram of a test state of a tested section of a blade flapping stiffness test of a helicopter in the prior art
FIG. 3 is a schematic diagram of a helicopter blade flap stiffness test of the prior art after a tested section test is completed
FIG. 4 is a schematic view of the structure of the testing apparatus of the present invention
FIG. 5 is a schematic view of the index plate 1 of the present invention
FIG. 6 is a schematic diagram of an automatic control module 2 according to the present invention
FIG. 7 is a flow chart of the test method of the present invention
Wherein:
1-index plate, 2-automatic control module, 3-hydraulic substation module, 4-test fixture, 5-helicopter blade to be tested, 6-section to be tested, 7-loading wing-shaped fixture and 8-bearing wall
101-zero position sensor 102-zero position transmitting block 103-brake sheet 104-gear 105-hydraulic pipeline interface 106-servo motor and control cabinet cable interface
201-servo motor 202-servo motor fairing 203-release sensor 204-brake sensor 205-control cabinet
301-hydraulic line interface
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
As shown in fig. 4, the test device for fixing and rotating the helicopter blade comprises an index plate 1, an automatic control module 2, a hydraulic substation module 3 and a test fixture 4;
the test fixture 4 is fixed on the vertical end face and used for fixing a blade root of the helicopter to be tested; the index plate 1 is mounted on the test fixture 4 and is coaxial with the test fixture 4, the automatic control module 2 is located on the side surface of the index plate 1 and is connected with the index plate 1 through a cable, the automatic control module 2 controls the rotation angle of the index plate 1 and receives and sends signals, and meanwhile, the side surface of the index plate 1 is further provided with a hydraulic oil port for connecting with the hydraulic substation module 3 through a hydraulic oil pipe; the hydraulic substation module 3 is used for driving the servo motor 201 to move so as to drive the index plate 1 to rotate, and is connected with the automatic control module 2 through a cable.
As shown in fig. 5, the index plate 1 includes a zero position sensor 101 disposed therein for signal zero clearing; a zero-signaling block 102 for receiving a signal; a transmitting block 103 for transmitting a control signal; a brake pad 104 for preventing the gear 105 from rotating after braking; the indexing disc 1 has a gear 105 at its inner edge for cooperating with a servo motor 201 in the automatic control module 2.
The automatic control module 2 comprises a servo motor 201, a fairing 202 arranged outside the servo motor 201, a loosening sensor 203 arranged inside the fairing 202, and a brake sheet 104 loosening when the loosening sensor receives a loosening signal, wherein the fairing 202 is fixedly arranged on the side surface of the dividing plate 1; the tightening sensor 204 is used for tightening the tightening sheet 104 when receiving a tightening signal; the control cabinet 205 is used for sending various control commands, and the control cabinet 205 is electrically connected with the servo motor 201, the loosening sensor 203 and the tightening sensor 204 through cables to realize signal transmission.
As shown in fig. 6, the hydraulic substation module 3 is configured to drive the servo motor 201 to move, so as to drive the index plate 1 to rotate, and the hydraulic substation module 3 includes a hydraulic interface 301 correspondingly connected to the hydraulic oil port 106 on the side of the index plate 1.
The commands sent by the control cabinet 205 include an index plate release command, an index plate angle zero clearing command, an angle command and an index plate brake command.
As shown in fig. 7, a test method for fixing and rotating a helicopter blade, using the test apparatus, is characterized by comprising the following steps:
s1: fixedly mounting the index plate 1 on a bearing wall;
s2: installing a test fixture 4 connected with the root of the blade to be tested on the index plate 1;
s3: fixing and clamping the blade to be tested on a test fixture 4;
s4: the hydraulic substation module 3 is connected with the index plate 1 by using a hydraulic oil pipe, the control cabinet 205 is connected with the servo motor 201 by a cable, and the hydraulic substation module 3 is connected with the control cabinet 205 by a cable;
s5: inputting an index plate loosening command on the control cabinet 205, starting oil return through a hydraulic pipeline of the hydraulic substation module 3 to enable the index plate 1 to reach a loosening state, transmitting a command to the control cabinet 205 by the loosening sensor 203 when the index plate 1 is completely loosened, transmitting a corresponding command to the servo motor 201 after the control cabinet 205 receives the command, and driving the servo motor 201 to drive the index plate 1 to rotate;
s6: an index plate angle zero clearing command is input into the control cabinet 205, and after the zero sensor 101 receives the command, the zero signaling block 102 starts to work, and defaults the position of the index plate 1 to 0 degree;
s7: an angle command is input into the control cabinet 205, and the control cabinet 205 drives the servo motor 201 to drive the index plate 1 to rotate to reach a specified angle and then stop;
s8: inputting a dial braking command on the control cabinet 205, supplying oil to a pipeline of the hydraulic substation module 3 to enable the index plate 1 to be in a braking state, and transmitting an instruction to the control cabinet 205 by the braking sensor 204 when the index plate 1 is in the braking state and is completely braked;
s9: carrying out a subsequent formal loading test;
the angle command input to the control cabinet 205 can be in a manual or automatic input form; the automatic input is realized by programming;
the control cabinet 205 inputs a speed control command, and controls the rotating speed of the helicopter blades according to the mass of the helicopter blades;
the control cabinet 205 selects a servo motor with appropriate power according to the size of the index plate;
the hydraulic substation module 3 selects a hydraulic substation with flow capacity according to the size of the load in the test.
The foregoing is illustrative of the present invention and is not to be construed as limiting thereof. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (6)
1. A test method for fixing and rotating a helicopter blade is characterized in that a test device for fixing and rotating the helicopter blade is adopted, and the test device comprises an index plate (1), an automatic control module (2), a hydraulic substation module (3) and a test fixture (4);
the test fixture (4) is fixed on the vertical end face and used for fixing a blade root of the helicopter to be tested; the index plate (1) is mounted on the test fixture (4) and is coaxial with the test fixture (4), the automatic control module (2) is located on the side face of the index plate (1) and is connected with the index plate (1) through a cable, the rotation angle of the index plate (1) is controlled through the automatic control module (2) and signals are received and sent, and meanwhile, a hydraulic oil port is formed in the side face of the index plate (1) and is used for being connected with the hydraulic substation module (3) through a hydraulic oil pipe; a control cabinet (205) in the automatic control module (2) drives a servo motor (201) to move so as to drive the index plate (1) to rotate, and the hydraulic substation module (3) is connected with the automatic control module (2) through a cable;
the index plate (1) comprises a zero position sensor (101) arranged in the index plate and is used for signal zero clearing; a zero-signaling block (102) for receiving a signal; a signaling block (103) for sending a control signal; a brake pad (104) for preventing the gear (105) from rotating after braking; the inner edge position of the dividing plate (1) is provided with a gear (105) which is used for being matched and connected with a servo motor (201) in the automatic control module (2);
the automatic control module (2) comprises a servo motor (201), a fairing (202) arranged outside the servo motor (201), a release sensor (203) arranged inside the fairing (202), and a brake sheet (104) released when the release sensor receives a release signal, wherein the fairing (202) is fixedly arranged on the side surface of the dividing plate (1); a tightening sensor (204) which, when receiving a tightening signal, causes the tightening sheet (104) to tighten; the control cabinet (205) is used for sending various control commands, and the control cabinet (205), the servo motor (201), the loosening sensor (203) and the tightening sensor (204) are mutually and electrically connected through cables to realize signal transmission;
the hydraulic substation module (3) comprises a hydraulic interface (301) correspondingly connected with a hydraulic oil port (106) on the side surface of the indexing disc (1); the test method specifically comprises the following steps:
s1: fixedly mounting the index plate (1) on a bearing wall;
s2: installing a test fixture (4) connected with the root of the blade to be tested on the index plate (1);
s3: fixing and clamping the blade to be tested on a test fixture (4);
s4: the hydraulic substation module (3) is connected with the index plate (1) by using a hydraulic oil pipe, the control cabinet (205) is connected with the servo motor (201) through a cable, and the hydraulic substation module (3) is connected with the control cabinet (205) through a cable;
s5: inputting a dividing plate loosening command on the control cabinet (205), enabling a hydraulic pipeline of the hydraulic substation module (3) to start oil return to enable the dividing plate (1) to reach a loosening state, when the dividing plate (1) is completely loosened, transmitting an instruction to the control cabinet (205) by the loosening sensor (203), transmitting a corresponding instruction to the servo motor (201) after the control cabinet (205) receives the instruction, and driving the servo motor (201) to drive the dividing plate (1) to rotate;
s6: inputting an index plate angle zero clearing command on the control cabinet (205), wherein after the zero sensor (101) receives the command, the zero position signaling block (102) starts to work, and defaults the position of the index plate (1) to 0 degree;
s7: inputting an angle command on the control cabinet (205), wherein the control cabinet (205) drives the servo motor (201) to drive the index plate (1) to rotate to reach a specified angle and then stop;
s8: inputting a dividing plate braking command on the control cabinet (205), supplying oil to a pipeline of the hydraulic substation module (3) to enable the dividing plate (1) to be in a braking state, and transmitting an instruction to the control cabinet (205) by the braking sensor (204) when the dividing plate (1) is in the braking state and is completely braked;
s9: and carrying out subsequent formal loading tests.
2. A test method for fixing and rotating a helicopter blade according to claim 1 characterized in that said command input to said control cabinet (205) can be in the form of manual or automatic input; the automatic input is realized by programming.
3. A test method for fixing and rotating a helicopter blade according to claim 1 characterized in that said control cabinet (205) inputs speed control commands to control the rotational speed of the helicopter blade according to its mass.
4. A test method for fixing and rotating a helicopter blade according to claim 1 characterized in that said control cabinet (205) selects a servo motor of appropriate power depending on the size of the indexing disc.
5. A test method for fixing and rotating a helicopter blade according to claim 1 characterized by that said hydraulic substation module (3) selects the flow capacity of the hydraulic substation according to the size of the load in the test.
6. A test method for fixing and rotating a helicopter blade according to claim 1 characterized in that said commands issued by said control cabinet (205) comprise index plate release commands, index plate angle clear commands, angle commands, index plate brake commands.
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| CN202110423706.9A CN113148225B (en) | 2021-04-20 | 2021-04-20 | Testing device and testing method for fixing and rotating helicopter blades |
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| CN202110423706.9A CN113148225B (en) | 2021-04-20 | 2021-04-20 | Testing device and testing method for fixing and rotating helicopter blades |
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