CN116558766A - Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment - Google Patents
Ground simulation method for tail rotor aerodynamic characteristic test in aerodynamic interference environment Download PDFInfo
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- CN116558766A CN116558766A CN202310833902.2A CN202310833902A CN116558766A CN 116558766 A CN116558766 A CN 116558766A CN 202310833902 A CN202310833902 A CN 202310833902A CN 116558766 A CN116558766 A CN 116558766A
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- 238000000034 method Methods 0.000 title claims abstract description 35
- 238000004088 simulation Methods 0.000 title claims abstract description 25
- 230000008859 change Effects 0.000 claims abstract description 7
- 230000008569 process Effects 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 3
- 238000010998 test method Methods 0.000 abstract 2
- 230000007246 mechanism Effects 0.000 description 3
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004379 similarity theory Methods 0.000 description 1
Classifications
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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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
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention discloses a ground simulation method for a tail rotor aerodynamic characteristic test in a pneumatic interference environment, which comprises the following steps: s1: tail rotor hubs with different mounting torsion angles are designed, and during a test, tail rotor blades are assembled with different tail rotor hubs to realize the change of the total tail rotor pitch; s2: because the tail blade is twisted linearly around the variable-pitch axis, the torsion angle of the root of the tail blade hub is designed to be equal to the torsion angle at the section (section 0.7R from the rotation center) of the tail blade She Tezheng, so that the total pitch of the tail blade is truly reflected; s3: optimizing a hover test method and steps, and improving hover test efficiency under a fixed tail rotor collective pitch working condition; s4: optimizing a wind tunnel test method and steps, and improving wind tunnel test efficiency under the working condition of the total pitch of the fixed tail rotor; s5: the analysis and research of the tail rotor aerodynamic characteristics under the interference of rotor trail. The invention can accurately obtain the aerodynamic performance of the tail rotor under different working conditions, and provides reliable test basis for optimizing the integral aerodynamic layout research of the helicopter.
Description
Technical Field
The invention relates to a ground simulation method for a tail rotor aerodynamic characteristic test in a pneumatic interference environment, and belongs to the technical field of helicopter wind tunnel tests.
Background
The rotor and tail rotor of a helicopter with conventional layout can generate rotary airflow, so that the motion is complex, mutual interference is caused, and the airflow is more complex due to interaction with other parts of the helicopter. The most direct effect of rotor wake interference on the tail rotor is represented by the impact of the rotor wake on the tail rotor, causing unsteady aerodynamic loads on the tail rotor blades, reduced tail rotor handling efficiency, and additional noise caused by interference. Through advanced wind tunnel test equipment and test technology, effective ground simulation research can be carried out on the aerodynamic characteristics of the tail rotor under the aerodynamic interference environment, adverse factors generated by aerodynamic interference are avoided and solved, the aerodynamic layout of the helicopter is optimized, and the overall performance of the helicopter is optimized.
Helicopter test models include rotor models, fuselage models, tail rotor models, automatic inclinators that connect rotor (or tail rotor) models for steering control thereof, and the like. In order to convert the wind tunnel test result of the reduced scale model into the aerodynamic characteristics of the real object (helicopter or rotor wing) in the actual flight state, according to the similarity theory, the conditions of geometric similarity, motion similarity and the like between the model and the real object must be satisfied. For the helicopter scaling model, the size of the tail rotor relative to the rotor is smaller, if the conditions of geometric similarity and motion similarity are to be met, the size is difficult to achieve in a limited space, otherwise, the aerodynamic characteristic test error of the tail rotor is larger.
Disclosure of Invention
The invention aims at: aiming at the problems, the ground simulation method for the tail rotor aerodynamic characteristics test under the aerodynamic interference environment is provided, so that the geometrical similarity and the motion similarity between a tail rotor model and a real object are met, test research is efficiently carried out, the aerodynamic performance of the tail rotor under the aerodynamic interference environment is accurately obtained, and a test basis with higher reliability is provided for optimizing the aerodynamic layout of a helicopter.
The technical scheme adopted by the invention is as follows:
a ground simulation method for a tail rotor aerodynamic characteristic test in a pneumatic interference environment comprises the following steps:
s1, designing tail rotor hubs with different mounting torsion angles, and assembling different tail rotor hubs on tail rotor blades during a test to realize the change of the total pitch of the tail rotor;
s2, designing that the torsion angle of the root of the tail rotor hub is equal to the torsion angle of the characteristic section of the tail rotor blade because the tail rotor blade is linearly twisted around the variable-pitch axis, so that the total pitch of the tail rotor is truly reflected;
s3, performing a hover test, and adopting the hover test under the working condition of a fixed tail rotor collective pitch;
in step S3, the sub-steps are included:
s31, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s32, simultaneously starting the rotor wing and the tail rotor at the state that the given tail rotor total distance and the given rotor wing total distance are 0 degrees, and respectively adjusting the rotor wing and the tail rotor to respective test rotating speeds;
s33, operating the rotor wings, respectively giving different rotor wing collective distances, and measuring and obtaining the pneumatic load of the tail rotor in the different rotor wing collective distance states;
s34, the total distance of the rotor wings is reduced to 0 degree, the rotor wings and the tail rotor systems are stopped, and tail rotor hubs with different mounting torsion angles are replaced;
s35, repeating the steps S31-S34 until the test contents under the total tail rotor pitch are completed;
s4, performing a forward flight test, wherein the forward flight test under the working condition of a fixed tail rotor total distance is adopted;
in step S4, the sub-steps are included:
s41, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s42, simultaneously starting the rotor wing and the tail rotor to adjust to respective test rotating speeds under the condition that the given tail rotor total distance and the rotor wing total distance are 0 degrees;
s43, adjusting wind tunnel wind speed and airframe attack angle to test appointed values;
s44, operating the rotor wing to balance the vertical force of the rotor wing to a specified value, and enabling the moment of the hub to be closer to zero;
s45, measuring and obtaining the pneumatic load of the tail rotor;
s46, repeating the steps S43 to S45 until the test contents under all wind speeds and angles of attack of the airframe are completed;
s47, after the test contents of all wind speeds and angles of attack of the airframe are completed, the total distance of the rotor wing is reduced to 0 ℃, the rotor wing and tail rotor system is stopped, and tail rotor hubs with different installation torsion angles are replaced;
s48, repeating the steps S41 to S46 until the test contents under the total pitch of all tail paddles are completed;
s5, analyzing and researching the aerodynamic characteristics of the tail rotor under the interference of the tail rotor.
Further, in step S1, the model of the tail rotor is made to be completely geometrically similar to the real helicopter tail rotor in size, so that under the condition that the mach numbers of the blade tips are similar, the aerodynamic phenomenon of the tail rotor is more accurately researched through the similar model.
Furthermore, in the running process of the tail rotor model, the tail rotor total distance adopts a constant given fixed value, so that the working links of tail rotor control in the test process are reduced.
Further, in step S1, the tail rotor hub is formed by numerical control machining, the middle is connected with the tail rotor shaft by adopting an involute internal spline, and the tail rotor shaft end is fixed on the tail rotor shaft by adopting a compression nut.
Further, in step S2, the tail rotor She Tezheng is sectioned at 0.75R from the center of rotation.
Further, in step S2, during the test preparation, the collective pitch of the tail rotor is directly measured and checked at the root of the tail rotor hub as required.
Further, in step S5, the tail rotor aerodynamic characteristics under rotor wake disturbances include hover performance and forward flight performance.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
according to the ground simulation method for the tail rotor aerodynamic characteristics test under the aerodynamic interference environment, a ground simulation means is provided for accurately acquiring the tail rotor aerodynamic characteristics under the aerodynamic interference environment, the tail rotor hubs with different torsion angles are adopted to change the total tail rotor pitch, the complete geometric similarity of a tail rotor model and the tail rotor size of a real helicopter is realized, the bracket interference influence caused by a tail rotor control system, an automatic inclinator and other mechanisms is avoided, the test safety is enhanced, the hover and forward flight aerodynamic characteristics of the tail rotor under the aerodynamic interference environment can be accurately acquired, and reliable test support is provided for optimizing the aerodynamic layout of the helicopter and optimizing the overall performance of the helicopter.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
fig. 1 is a flow chart of the present invention.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Examples
A ground simulation method for a tail rotor aerodynamic characteristic test in a pneumatic interference environment is shown in fig. 1, and comprises the following steps:
s1, designing tail rotor hubs with different mounting torsion angles, and assembling different tail rotor hubs on tail rotor blades during a test to realize the change of the total pitch of the tail rotor;
s2, designing that the torsion angle of the root of the tail rotor hub is equal to the torsion angle of the characteristic section of the tail rotor blade because the tail rotor blade is linearly twisted around the variable-pitch axis, so that the total pitch of the tail rotor is truly reflected;
s3, performing a hover test, and adopting the hover test under the working condition of a fixed tail rotor collective pitch;
in step S3, the sub-steps are included:
s31, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s32, simultaneously starting the rotor wing and the tail rotor at the state that the given tail rotor total distance and the given rotor wing total distance are 0 degrees, and respectively adjusting the rotor wing and the tail rotor to respective test rotating speeds;
s33, operating the rotor wings, respectively giving different rotor wing collective distances, and measuring and obtaining the pneumatic load of the tail rotor in the different rotor wing collective distance states;
s34, the total distance of the rotor wings is reduced to 0 degree, the rotor wings and the tail rotor systems are stopped, and tail rotor hubs with different mounting torsion angles are replaced;
s35, repeating the steps S31-S34 until the test contents under the total tail rotor pitch are completed;
s4, performing a forward flight test, wherein the forward flight test under the working condition of a fixed tail rotor total distance is adopted;
in step S4, the sub-steps are included:
s41, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s42, simultaneously starting the rotor wing and the tail rotor to adjust to respective test rotating speeds under the condition that the given tail rotor total distance and the rotor wing total distance are 0 degrees;
s43, adjusting wind tunnel wind speed and airframe attack angle to test appointed values;
s44, operating the rotor wing to balance the vertical force of the rotor wing to a specified value, and enabling the moment of the hub to be closer to zero;
s45, measuring and obtaining the pneumatic load of the tail rotor;
s46, repeating the steps S43 to S45 until the test contents under all wind speeds and angles of attack of the airframe are completed;
s47, after the test contents of all wind speeds and angles of attack of the airframe are completed, the total distance of the rotor wing is reduced to 0 ℃, the rotor wing and tail rotor system is stopped, and tail rotor hubs with different installation torsion angles are replaced;
s48, repeating the steps S41 to S46 until the test contents under the total pitch of all tail paddles are completed;
s5, analyzing and researching the aerodynamic characteristics of the tail rotor under the interference of the tail rotor.
In this embodiment, as specific advantages and designs, in the design of the steps, the tail rotor is adopted without real-time pitch change, so that the influence of bracket interference caused by a tail rotor control system, an automatic inclinator and other mechanisms is avoided, the quality of test data can be improved, the working links of tail rotor control in the test process are further reduced, the failure rate of the tail rotor pneumatic characteristic test is reduced, and the test safety is enhanced.
On the basis of the specific design, in step S1, the model of the tail rotor is completely geometrically similar to the size of the tail rotor of the real helicopter, so that the aerodynamic phenomenon of the tail rotor is more accurately researched through the similar model under the condition that the Mach numbers of the blade tips are similar. In this design, based on the small size of the tail rotor, and in addition, a more intimate and realistic test is performed, a complete geometrical similarity to the size of the real helicopter tail rotor is achieved in the design of the model, i.e. a scaling down according to the geometrical dimensions not yet achieved by the real helicopter.
The method is more specifically designed, and in the running process of the tail rotor model, the total tail rotor distance adopts a constant given fixed value so as to reduce the working links of tail rotor operation in the test process.
Further, in step S1, the tail rotor hub is formed by numerical control machining, the middle is connected with the tail rotor shaft by adopting an involute internal spline, and the tail rotor shaft end is fixed on the tail rotor shaft by adopting a compression nut.
Based on the above specific design, as a more specific design, in step S2, the tail rotor She Tezheng section is a section of 0.75R from the rotation center.
In a specific design, more specifically, in step S2, the collective pitch of the tail rotor is directly measured and checked at the root of the hub of the tail rotor as required during the test preparation.
As a still further design, in step S5, the tail rotor aerodynamic characteristics under rotor wake disturbances include hover performance and forward flight performance.
In summary, the ground simulation method for the tail rotor aerodynamic characteristics test in the aerodynamic interference environment provides a ground simulation means for accurately acquiring the tail rotor aerodynamic characteristics in the aerodynamic interference environment, adopts the tail rotor hubs with different torsion angles to change the total tail rotor pitch, realizes the complete geometric similarity of a tail rotor model and the tail rotor size of a real helicopter, avoids the bracket interference influence caused by a tail rotor control system, an automatic inclinator and other mechanisms, enhances the test safety, can accurately acquire the hover and forward flight aerodynamic characteristics of the tail rotor in the aerodynamic interference environment, and provides reliable test support for optimizing the aerodynamic layout of the helicopter and ensuring the overall performance of the helicopter to be optimal.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (7)
1. A ground simulation method for a tail rotor aerodynamic characteristic test in a pneumatic interference environment is characterized by comprising the following steps of: the method comprises the following steps:
s1, designing tail rotor hubs with different mounting torsion angles, and assembling different tail rotor hubs on tail rotor blades during a test to realize the change of the total pitch of the tail rotor;
s2, designing that the torsion angle of the root of the tail rotor hub is equal to the torsion angle of the characteristic section of the tail rotor blade because the tail rotor blade is linearly twisted around the variable-pitch axis, so that the total pitch of the tail rotor is truly reflected;
s3, performing a hover test, and adopting the hover test under the working condition of a fixed tail rotor collective pitch;
in step S3, the sub-steps are included:
s31, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s32, simultaneously starting the rotor wing and the tail rotor at the state that the given tail rotor total distance and the given rotor wing total distance are 0 degrees, and respectively adjusting the rotor wing and the tail rotor to respective test rotating speeds;
s33, operating the rotor wings, respectively giving different rotor wing collective distances, and measuring and obtaining the pneumatic load of the tail rotor in the different rotor wing collective distance states;
s34, the total distance of the rotor wings is reduced to 0 degree, the rotor wings and the tail rotor systems are stopped, and tail rotor hubs with different mounting torsion angles are replaced;
s35, repeating the steps S31-S34 until the test contents under the total tail rotor pitch are completed;
s4, performing a forward flight test, wherein the forward flight test under the working condition of a fixed tail rotor total distance is adopted;
in step S4, the sub-steps are included:
s41, installing a tail rotor model for specifying the total tail rotor distance according to requirements;
s42, simultaneously starting the rotor wing and the tail rotor to adjust to respective test rotating speeds under the condition that the given tail rotor total distance and the rotor wing total distance are 0 degrees;
s43, adjusting wind tunnel wind speed and airframe attack angle to test appointed values;
s44, operating the rotor wing to balance the vertical force of the rotor wing to a specified value, and enabling the moment of the hub to be closer to zero;
s45, measuring and obtaining the pneumatic load of the tail rotor;
s46, repeating the steps S43 to S45 until the test contents under all wind speeds and angles of attack of the airframe are completed;
s47, after the test contents of all wind speeds and angles of attack of the airframe are completed, the total distance of the rotor wing is reduced to 0 ℃, the rotor wing and tail rotor system is stopped, and tail rotor hubs with different installation torsion angles are replaced;
s48, repeating the steps S41 to S46 until the test contents under the total pitch of all tail paddles are completed;
s5, analyzing and researching the aerodynamic characteristics of the tail rotor under the interference of the tail rotor.
2. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in step S1, the model of the tail rotor is made to achieve a complete geometrical similarity to the real helicopter tail rotor dimensions.
3. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in the running process of the tail rotor model, the tail rotor total distance adopts a constant given fixed value so as to reduce the working links of tail rotor operation in the test process.
4. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in the step S1, the tail rotor hub is formed through numerical control machining, the middle part of the tail rotor hub is connected with a tail rotor shaft through an involute internal spline, and the tail rotor shaft end is fixed on the tail rotor shaft through a compression nut.
5. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in step S2, the tail rotor She Tezheng profile is 0.75R profile from the center of rotation.
6. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in step S2, during the test preparation, the collective pitch of the tail rotor is directly measured and checked at the root of the tail rotor hub as required.
7. The ground simulation method for the tail rotor aerodynamic characteristic test under the aerodynamic interference environment according to claim 1, wherein the ground simulation method comprises the following steps: in step S5, the tail rotor aerodynamic properties under rotor wake disturbances include hover performance and forward flight performance.
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| GIOVANETTI, E.B: "Optimal Aerodynamic Design of Conventional and Coaxial Helicopter Rotors in Hover and Forward Flight", OPTIMAL AERODYNAMIC DESIGN OF CONVENTIONAL AND COAXIAL HELICOPTER ROTORS IN HOVER AND FORWARD FLIGHT * |
| 樊枫 等: "直升机旋翼干扰对尾桨气动噪声影响的数值研究", 南京航空航天大学学报, vol. 53, no. 02 * |
| 王宇辰: "小型无人直升机飞行控制系统及其试验台的研究", 中国优秀硕士学位论文全文数据库工程科技Ⅱ辑 * |
| 聂博文 等: "复合式高速直升机螺旋桨变距性能评估与测试", 飞行力学, vol. 41, no. 2 * |
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