CN113788159B - Method for solving abnormal balance speed of aircraft on ground - Google Patents
Method for solving abnormal balance speed of aircraft on ground Download PDFInfo
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- CN113788159B CN113788159B CN202111096336.9A CN202111096336A CN113788159B CN 113788159 B CN113788159 B CN 113788159B CN 202111096336 A CN202111096336 A CN 202111096336A CN 113788159 B CN113788159 B CN 113788159B
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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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- 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
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Abstract
The invention discloses a method for solving the problem of abnormal balance speed of an airplane on the ground, which comprises the following steps: step 1, inquiring designed flat flight deflection delta z0 and corresponding longitudinal driving rod displacement Xz0; step 2, performing a ground simulation test to obtain the plane deviation delta z1 of the flight parameter and the corresponding longitudinal driving rod displacement Xz1; step 3: calculating the displacement difference of the longitudinal steering column according to the results of the steps 1 and 2; step 4: performing parameter adjustment according to the longitudinal driving rod displacement difference calculated in the step 3; step 5: performing ground simulation test again to obtain the plane deviation delta z2 of the flight parameter and the corresponding displacement Xz2 of the longitudinal driving rod; step 6: the rod displacement Xz3 is converted when the air flight rod force is zero, and if Xz3 is approximately equal to Xz0, the air flight balance speed condition of the aircraft is met; otherwise, if the requirements are not met, repeating the steps 4 to 6. By adopting the method, the parameters of the aircraft balance speed control system are adjusted by using the ground simulation test data, so that the number of times of flight test frames can be reduced, and the outgoing flight test cost of the aircraft can be reduced.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a method for solving the problem of abnormal balance speed of an airplane on the ground.
Background
With the development of aviation technology, aircraft are widely used in life as a kind of equipment and vehicles. When the aircraft leaves the factory and tries to fly, the traditional method for dealing with the problem of the abnormal balance speed of the aircraft is that ground service maintainers adjust the parameters of a plane flying control system of the aircraft according to the specific comment of pilots on the abnormal balance speed, and then try to fly, if not, adjust the mode of try to fly again. The traditional method only solves the problem of abnormal balance speed by a method of adjusting the balance speed for multiple times, and the problem of abnormal balance speed of the airplane is treated by the traditional method because of high flight cost, so that the factory test cost of the airplane is higher.
Therefore, when the problem of abnormal balance speed of the aircraft is solved, a new method is expected to reduce the number of test frames and the outgoing test cost of the aircraft.
Disclosure of Invention
The invention aims to solve the technical problems in the background technology, and provides a method for solving the balance speed abnormality, by using the method, the number of test frames can be reduced, the factory test cost of an airplane can be reduced, and in particular, the method for solving the balance speed abnormality of the airplane on the ground is provided.
In order to solve the technical problems, the invention adopts the following technical scheme: a method of ground solving an aircraft balance speed anomaly, the method comprising the steps of:
step 1, inquiring a plane balance speed test flight parameter with abnormal balance speed, and designing a plane flight deflection delta z0 and a corresponding longitudinal steering column displacement Xz0 required by plane flight of the plane with the balance speed;
step 2, directly performing a ground pumping static pressure simulation test on the aircraft with abnormal balance speed without any adjustment, namely performing a ground simulation test 1 to obtain the plane deflection delta z1 of the flight parameter and the corresponding longitudinal steering column displacement Xz1, wherein the rod force corresponding to the rod displacement Xz1 is zero;
step 3: according to the results of the step 1 and the step 2, when the designed balance speed aerial flight and the ground simulation flight parameter are the same in plane deviation, the displacement difference dXz =xz0- δz0/(δz1/xz1) of the longitudinal steering column is calculated;
step 4: according to the displacement difference of the longitudinal steering column calculated in the step 3, according to the technical conditions, parameter adjustment is carried out through an operating system;
step 5: performing a ground dynamic and static pressure simulation test again, wherein the test conditions are the same as those in the step 2, namely performing the ground simulation test 2 to obtain the plane flight deflection delta z2 of the ground test flight parameter and the corresponding longitudinal driving rod displacement Xz2, and the rod force corresponding to the rod displacement Xz2 is zero;
step 6: when the converted air flight rod force is zero, the rod displacement Xz3=δz0/(δz2/xz2) + dXz, and if Xz3 is approximately equal to Xz0, the air flight balance speed condition of the aircraft is met; otherwise, if the requirements are not met, repeating the steps 4 to 6.
In step 2, the specific operation method of the ground whip static pressure simulation test is that the steering column switches the arm regulator in the steering system to an automatic state under the unmanned condition, the ground whip static pressure simulation test is directly carried out, the design balance speed at the air pressure height of 3000m is simulated, the arm deflection is measured, the ground test flight parameter plane deflection delta z1 corresponding to the gauge speed and the corresponding longitudinal steering column displacement Xz1 are inquired, and the rod displacement Xz1 corresponds to the rod force to be zero.
In step 4, the parameter adjustment refers to length adjustment of the first, second, third and fourth pull rods in the control system according to technical conditions, and the lengths of the first, second, third and fourth pull rods can be adjusted by adjusting the inclination direction of the arm regulator so as to conform to the displacement difference of the longitudinal steering rod.
Further, the method for solving the problem of abnormal balance speed of the airplane on the ground comprises the steps of arranging three rocker arms, namely a rocker arm I, a rocker arm II and a rocker arm III, wherein one end of the rocker arm I is connected with the rocker arm I, the other end of the rocker arm I is connected with the moment arm regulator, the load mechanism is connected with the effect regulating mechanism through the rocker arm II, the other end of the load mechanism is connected with the moment arm regulator through the rocker arm II, the tension arm III is connected with the tension arm IV through the rocker arm III, the other end of the tension arm III is connected with the moment arm regulator, and the lengths of the tension arm I, the tension arm II, the tension arm III and the tension arm IV can be adjusted through the moment arm regulator under the action of the rocker arm.
Compared with the prior art, the method for solving the problem of abnormal balance speed of the aircraft on the ground has the beneficial effects that: aiming at the anomaly of the balance speed of the aircraft, the aircraft balance speed control system parameters can be adjusted by using the ground simulation test data more accurately by using the ground static pressure simulation test data and Ping Fei flight parameter data when the balance speed is anomalous and adopting a method for converting the air flight rod force into zero rod displacement, and the required number of times of the balance test flight frame is small, so that the aircraft balance speed control system parameters can be adjusted by using the ground simulation test data more accurately. The universal machine is strong in universality, safe, practical and suitable for popularization and use.
Drawings
The invention is described in further detail below with reference to the accompanying drawings.
FIG. 1 is a schematic flow diagram of the structural principle simulation of the present invention;
fig. 2 is a schematic diagram of a connection state structure of a pull rod in the manipulation system according to the present invention.
The figure shows: 1-arm regulator, 2-load mechanism, 3-effect adjusting mechanism, 4-pull rod I, 5-pull rod II, 6-pull rod III, 7-pull rod IV, 8-rocker arm I, 9-rocker arm II, 10-rocker arm III.
Detailed Description
As shown in fig. 1 and 2, the method for solving the problem of abnormal equilibrium speed of an aircraft on the ground according to the invention comprises the following steps:
step 1, inquiring a plane balance speed test flight parameter with abnormal balance speed, and designing a plane flight deflection delta z0 and a corresponding longitudinal steering column displacement Xz0 required by plane flight of the plane with the balance speed;
step 2, the aircraft with abnormal balance speed is not regulated at all, a steering column is switched to an automatic state under the unmanned condition, a ground pumping static pressure simulation test is directly carried out, namely, a ground simulation test 1 is carried out, the design balance speed when the simulated air pressure is 3000m is carried out, the variable arm deflection is measured, the ground test flight parameter flat deflection delta z1 corresponding to the gauge speed and the corresponding longitudinal steering column displacement Xz1 are inquired, and the corresponding column force of the column displacement Xz1 is zero;
step 3: according to the results of the step 1 and the step 2, when the designed balance speed aerial flight and the ground simulation flight parameter are the same in plane deviation, the displacement difference dXz =xz0- δz0/(δz1/xz1) of the longitudinal steering column is calculated;
step 4: according to the longitudinal steering column displacement difference calculated in the step 3, parameter adjustment is carried out through an operating system according to technical conditions, the specific adjustment mode is that length adjustment is carried out on a first pull rod, a second pull rod, a third pull rod and a fourth pull rod in the operating system according to technical conditions, and the lengths of the first pull rod, the second pull rod, the third pull rod and the fourth pull rod can be adjusted by adjusting the inclination direction of a force arm regulator, so that the longitudinal steering column displacement difference is met;
step 5: performing a ground dynamic and static pressure simulation test again, wherein the test conditions are the same as those in the step 2, namely performing the ground simulation test 2 to obtain the plane flight deflection delta z2 of the ground test flight parameter and the corresponding longitudinal driving rod displacement Xz2, and the rod force corresponding to the rod displacement Xz2 is zero;
step 6: when the converted air flight rod force is zero, the rod displacement Xz3=δz0/(δz2/xz2) + dXz, and if Xz3 is approximately equal to Xz0, the air flight balance speed condition of the aircraft is met; otherwise, if the requirements are not met, repeating the steps 4 to 6.
Further, the method for solving the problem of the abnormal balance speed of the airplane on the ground comprises a moment arm regulator 1, a load mechanism 2, an effect regulating mechanism 3, a first pull rod 4, a second pull rod 5, a third pull rod 6, a fourth pull rod 7 and a rocker arm, wherein three rocker arms are arranged, namely, a first rocker arm 8, a second rocker arm 9 and a third rocker arm 10 respectively, one end of the first pull rod 4 is connected with the first rocker arm 8, the other end of the first pull rod is connected with the moment arm regulator 1, the load mechanism 2 is connected with the effect regulating mechanism 3 through the second rocker arm 9, the other end of the load mechanism 2 is connected with the moment arm regulator 1 through the second pull rod 5, the third pull rod 6 is connected with the fourth pull rod 7 through the third rocker arm 10, the other end of the third pull rod 6 is connected with the moment arm regulator 1, and the lengths of the first pull rod 4, the second pull rod 5, the third pull rod 6 and the fourth pull rod 7 can be regulated respectively through the moment arm regulator 1 under the action of the rocker arms.
Aiming at the balance speed abnormality of the aircraft balance test, the method that the balance speed abnormality can only be tested by multiple adjustment and multiple test runs is solved by the traditional method, and the conventional method is used for processing the aircraft delivery test run cost is higher due to high flight cost. The method can fully utilize ground simulation test, utilize ground static pumping pressure simulation test data and Ping Fei flight parameter data when the balance speed is abnormal, and utilize a method of converting the force of an aerial flight rod into zero rod displacement, so that the aircraft balance speed control system parameter can be adjusted by utilizing the ground simulation test data more accurately, the number of test frames can be effectively reduced, the aircraft balance speed control system parameter can be adjusted by utilizing the ground simulation test data more accurately, and the factory test cost of the aircraft is reduced.
The above description is only of the preferred embodiments of the present invention, and it should be understood that various changes and modifications can be made by those skilled in the art, and any modifications, equivalents, improvements and the like made by the present invention should be included in the scope of the present invention.
Claims (4)
1. A method for solving the problem of abnormal balance speed of an airplane on the ground is characterized by comprising the following steps of: the method comprises the following steps:
step 1, inquiring a plane balance speed test flight parameter with abnormal balance speed, wherein the plane flight deflection delta z0 and the corresponding longitudinal steering column displacement Xz0 required by plane flight when the balance speed is designed;
step 2, directly performing a ground dynamic and static pressure simulation test without any adjustment on the aircraft with abnormal balance speed, namely, a ground simulation test 1, to obtain the flat flight deflection delta z1 and the corresponding longitudinal steering column displacement Xz1 in flight parameters, wherein the rod force corresponding to the rod displacement Xz1 is zero;
step 3: according to the results of the step 1 and the step 2, when the plane deviation degree of the designed balance speed aerial flight and the ground simulated flight with the same parameters is calculated, the displacement difference dXz =xz0- δz0/(δz1/xz1) of the longitudinal steering column;
step 4: according to the displacement difference of the longitudinal steering column calculated in the step 3, according to the technical conditions, parameter adjustment is carried out through an operating system;
step 5: performing a ground dynamic and static pressure simulation test again, wherein the test conditions are the same as those in the step 2, namely, the ground simulation test 2, so as to obtain the flat flight deflection delta z2 of the flight parameters of the ground test and the corresponding longitudinal steering column displacement Xz2, and the rod force corresponding to the rod displacement Xz2 is zero;
step 6: when the converted air flight rod force is zero, the rod displacement Xz3=δz0/(δz2/xz2) + dXz, and if Xz3 is approximately equal to Xz0, the air flight balance speed condition of the aircraft is met; otherwise, if the requirements are not met, repeating the steps 4 to 6.
2. A method of ground solving aircraft balance speed anomalies according to claim 1, characterized in that: in the step 2, the specific operation method of the ground dynamic-static pressure simulation test is that the steering column switches the arm regulator in the steering system to an automatic state under the unmanned condition, directly performs the ground dynamic-static pressure simulation test, simulates the design balance speed when the air pressure is high at 3000m, measures the variable arm deflection, and inquires the flat flight deflection delta z1 of the ground test flight parameter corresponding to the gauge speed and the corresponding longitudinal steering column displacement Xz1, and the corresponding column force of the column displacement Xz1 is zero.
3. A method of ground solving aircraft balance speed anomalies according to claim 1, characterized in that: the control system comprises a force arm regulator (1), a load mechanism (2), a regulating mechanism (3), a first pull rod (4), a second pull rod (5), a third pull rod (6), a fourth pull rod (7) and a rocker arm, wherein the three rocker arms are respectively provided with a first rocker arm (8), a second rocker arm (9) and a third rocker arm (10), one end of the first pull rod (4) is connected with the first rocker arm (8), the other end of the first pull rod is connected with the force arm regulator (1), the load mechanism (2) is connected with the regulating mechanism (3) through the second rocker arm (9), the other end of the load mechanism (2) is connected with the force arm regulator (1) through the second pull rod (5), the third pull rod (6) is connected with the fourth pull rod (7) through the third rocker arm (10), and the other end of the third pull rod (6) is connected with the force arm regulator (1) under the action of the rocker arm, and the length of the first pull rod (4), the second pull rod (5), the third pull rod (6) and the fourth pull rod (7) can be regulated respectively.
4. A method of ground solving aircraft balance speed anomalies according to claim 3, characterized in that: the parameter adjustment is to adjust the length of a first pull rod (4), a second pull rod (5), a third pull rod (6) and a fourth pull rod (7) in the control system according to technical conditions, and the length of the first pull rod (4), the second pull rod (5), the third pull rod (6) and the fourth pull rod (7) can be adjusted by adjusting the inclination direction of the force arm regulator (1) so as to meet the displacement difference of the longitudinal driving rod.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111096336.9A CN113788159B (en) | 2021-09-18 | 2021-09-18 | Method for solving abnormal balance speed of aircraft on ground |
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| CN202111096336.9A CN113788159B (en) | 2021-09-18 | 2021-09-18 | Method for solving abnormal balance speed of aircraft on ground |
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| CN113788159B true CN113788159B (en) | 2023-09-12 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102591348A (en) * | 2012-03-01 | 2012-07-18 | 孟祥谦 | Calculation and analysis control method of drag load effect on airplane maneuverability |
| CN110987420A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Operating force and operating displacement detection method |
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- 2021-09-18 CN CN202111096336.9A patent/CN113788159B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102591348A (en) * | 2012-03-01 | 2012-07-18 | 孟祥谦 | Calculation and analysis control method of drag load effect on airplane maneuverability |
| CN110987420A (en) * | 2019-12-25 | 2020-04-10 | 中国航空工业集团公司西安飞机设计研究所 | Operating force and operating displacement detection method |
Non-Patent Citations (1)
| Title |
|---|
| 飞机平尾偏角故障的自动检测;严共鸣,赵学军,董海平;计算机测量与控制(第11期);第719-720,724页 * |
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Effective date of registration: 20230626 Address after: 561000 Songqi Town, Anshun economic and Technological Development Zone, Guizhou Province Applicant after: AVIC GUIZHOU AIRPLANE Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Applicant before: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. |
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