CN113218552A - Auxiliary equipment and method for evaluating installation thrust of aero-engine - Google Patents
Auxiliary equipment and method for evaluating installation thrust of aero-engine Download PDFInfo
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- CN113218552A CN113218552A CN202110310613.5A CN202110310613A CN113218552A CN 113218552 A CN113218552 A CN 113218552A CN 202110310613 A CN202110310613 A CN 202110310613A CN 113218552 A CN113218552 A CN 113218552A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
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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
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention discloses an aero-engine installation thrust evaluation auxiliary device which comprises a first connecting piece, a second connecting piece and a wheel chock. The invention also discloses an aircraft engine installation thrust evaluation method adopting the auxiliary equipment, which comprises the following steps: acquiring relevant parameters of the airplane; installing a thrust evaluation auxiliary device; starting test run and recording data measured by the thrust evaluation auxiliary equipment; and calculating the installation thrust of the aircraft engine in a plurality of rotating speed states and analyzing to obtain an installation thrust characteristic diagram of the aircraft engine. The auxiliary equipment provided by the invention performs test run according to the test run requirement, utilizes the known and recorded measured data, adopts a mechanical analysis method and combines external equipment to obtain the measured data with higher consistency with the real installation thrust at lower economic cost, has the advantages of low economic cost, simple operation and convenient and fast calculation, and provides method guidance for the installation thrust measurement of the aero-engine in the actual external field.
Description
Technical Field
The invention belongs to the technical field of design of aero-engines, and particularly relates to an aero-engine installation thrust evaluation method.
Background
The mounting thrust test of the aircraft engine plays an indispensable role in guaranteeing the normal flight of the aircraft. At present, the domestic thrust test is mainly carried out when the aeroengine is not installed. The thrust that tests this moment and the thrust after the installation have great difference, and the test bench is bulky, and the structure is complicated, and supporting system is many, can't test in different environment. Accurate thrust measurement data is essential in order to ensure that the airplane can fly safely and efficiently and quickly repair faults occurring in the flight. Therefore, there is a need to design and develop a device that can not only ensure the test after the engine is installed, but also simplify the present complicated test system to quickly test the real-time installation thrust of the engine.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provides an aero-engine installation thrust evaluation auxiliary device and method.
In order to achieve the purpose, the invention adopts the technical scheme that: the auxiliary equipment for evaluating the installation thrust of the aircraft engine is characterized by comprising a first connecting piece, a second connecting piece and a wheel block, wherein one end of the first connecting piece is connected with a connecting lug on a main landing gear strut on one side of an aircraft to be tested, the other end of the first connecting piece is connected with a first fixed connecting point, the first fixed connecting point is positioned behind the aircraft to be tested, one end of the second connecting piece is connected with a connecting lug on a main landing gear strut on the other side of the aircraft to be tested, the other end of the second connecting piece is connected with a second fixed connecting point, the second fixed connecting point is positioned behind the aircraft to be tested, the second fixed connecting point and the first fixed connecting point are symmetrically arranged along the central axis of the aircraft to be tested respectively, the number of the wheel blocks is equal to that of the wheels of the aircraft to be tested, and the wheel block is fixedly arranged in front of the wheels of the aircraft to be tested, the first connecting piece and the second connecting piece are both provided with a tension detection device for testing the tension borne by the connecting pieces, and the wheel block is provided with a pressure detection device for testing the thrust borne by the wheel block.
Foretell aeroengine installation thrust aassessment auxiliary assembly which characterized in that: the one end of first connecting piece is provided with first joint, the other end of first connecting piece is provided with the second and connects, first joint with the second connects and is the couple shape, first connecting piece and second connecting piece are the cable wire and the length of first connecting piece and second connecting piece equals.
Foretell aeroengine installation thrust aassessment auxiliary assembly which characterized in that: the wheel chock includes the hemispherical base and supports the down tube with the wheel contact, support the down tube with base fixed connection, pressure measurement sets up again and supports on the down tube, tension measurement device is including being used for detecting tensile force sensor and being used for showing tension sensor detects the pulling force display screen of numerical value, pressure measurement device is including being used for detecting the pressure sensor of pressure and being used for showing pressure sensor detects the pressure display screen of numerical value.
The invention also discloses an aircraft engine installation thrust evaluation method adopting the aircraft engine installation thrust evaluation auxiliary equipment, which is characterized by comprising the following steps of:
the method comprises the following steps of firstly, installing an aircraft engine on an airplane to be tested, and obtaining relevant parameters of the airplane;
step two, installing thrust evaluation auxiliary equipment;
starting test run and recording data measured by the thrust evaluation auxiliary equipment;
and fourthly, calculating the installation thrust of the aircraft engine in a plurality of rotating speed states and analyzing to obtain an installation thrust characteristic diagram of the aircraft engine.
The aircraft engine installation thrust evaluation method is characterized by comprising the following steps: the relevant parameters of the airplane in the first step comprise: the aircraft comprises an aircraft total mass, the position of the center of gravity of the aircraft, an aero-engine thrust action point, a static friction coefficient of contact between an aircraft wheel and a wheel block, a horizontal distance between a nose wheel of an undercarriage and a contact point between a main wheel and the ground, and an included angle formed by engine thrust and the horizontal direction.
The aircraft engine installation thrust evaluation method is characterized by comprising the following steps: the specific requirements for installing the thrust evaluation auxiliary equipment in the step two comprise:
the lengths of the two connecting pieces are kept consistent and the connecting states of the two connecting pieces and the connecting lugs on the main landing gear supporting columns on the two sides are the same, all wheels of the test airplane are completely arranged on the wheel block, the two sides are symmetrically arranged by taking the central axis of the test airplane as the central line, and the horizontal distance between the contact point of the front wheel and the wheel block and the center of gravity of the airplane is measured.
The aircraft engine installation thrust evaluation method is characterized by comprising the following steps:
in the third step, in order to measure the installation thrust in a plurality of rotating speed states as much as possible, the throttle lever is required to be pushed uniformly and slowly to change the rotating speed of the engine during test run so as to record each group of data in a plurality of stable states.
The aircraft engine installation thrust evaluation method is characterized by comprising the following steps: the method for calculating the installation thrust of the aircraft engine in the multiple rotating speed states in the fourth step comprises the following steps:
step 401, for the accuracy of the calculation, make the following assumptions: the thrust of an engine acts on the symmetrical plane of the airplane, the acting point and the center of gravity of the airplane are at the same horizontal height, the center of gravity position of the airplane is basically unchanged along with the fuel consumption in the test run process, the thrust of the engine only changes in the test run process but the acting direction does not shift, and the stress conditions of the left main undercarriage wheel and the right main undercarriage wheel are the same,
step 402, based on the above assumptions, according to the overall stress relationship of the aircraft, it can be obtained:
f1＝μ1×N1
f2＝μ2×N2
wherein P is total thrust of the engine, G is total weight of the airplane, and F2Tension, X, provided for arresting the wire rope1，X2Backward supporting force applied to wheel block1，N2Upward supporting force f applied to wheel block1，f2Friction force, mu, exerted on wheel block of airplane wheel1，μ2The coefficient of static friction is determined, alpha is the horizontal distance between the thrust action point of the engine and the center of gravity of the airplane, b is the horizontal distance between the connecting point of the blocking steel cable and the ground and the center of gravity of the airplane, c is the horizontal distance between the contact point of the front wheel and the wheel block and the center of gravity of the airplane, h is the plumb distance between the center of gravity of the airplane and the ground, L is the vertical distance between the center of gravity of the airplane and the ground0The horizontal distance between the front wheel of the landing gear and the lowest point of contact between the main wheel and the wheel chock, theta is an included angle formed by the blocking steel cable and the horizontal direction,
The included angle is formed between the thrust of the engine and the horizontal direction;
the total weight G of the airplane comprises the empty weight of the airplane, the weight of passengers, the weight of fuel oil, the weight of mounted loads, other bearing weights and the like.
Compared with the prior art, the invention has the following advantages:
1. the thrust evaluation auxiliary equipment is simple in structure, convenient and practical, and can quickly acquire the force actually applied by the thrust evaluation auxiliary equipment in the test run process, and the thrust real-time value of the aircraft engine can be calculated through a formula and the parameters of the existing aircraft.
2. According to the invention, the surface parameter values do not need to be acquired as part method simulation calculation, the test run is only needed according to the test run requirement, the mounting thrust of the engine under multiple states can be rapidly and accurately obtained by using the known and recorded and measured data, and the mounting thrust characteristic diagram of the engine is obtained by analysis.
Drawings
Fig. 1 is a schematic view of a stress state of an airplane in a test run stage.
Fig. 2 is a schematic view of the relationship between the thrust evaluation assisting apparatus of the present invention and the installation position of the aircraft.
FIG. 3 is a flow chart of an aircraft engine installation thrust estimation of the present invention.
Description of reference numerals:
1 — a first connecting member; 2-a second connector; 3, wheel chock;
4-a first fixed attachment point; 5-a second fixed attachment point; 6-a tension detection device;
7-pressure detecting means; 8-airplane to be tested.
Detailed Description
Embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While certain embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but rather are provided for a more thorough and complete understanding of the present invention. It should be understood that the drawings and the embodiments of the present invention are illustrative only and are not intended to limit the scope of the present invention.
It should be noted that the terms "first", "second", and the like in the present invention are only used for distinguishing different devices, modules or units, and are not used for limiting the order or interdependence relationship of the functions performed by the devices, modules or units.
The invention discloses an aircraft engine installation thrust evaluation method based on external field improved test auxiliary equipment, the auxiliary equipment is shown in a figure and a figure 2, the auxiliary equipment comprises a first connecting piece 1, a second connecting piece 2 and a wheel chock 3, one end of the first connecting piece 1 is connected with a lug on a main undercarriage pillar on one side of an airplane 8 to be tested, the other end of the first connecting piece 1 is connected with a first fixed connecting point 4, the first fixed connecting point 4 is positioned behind the airplane 8 to be tested, one end of the second connecting piece 2 is connected with a lug on a main undercarriage pillar on the other side of the airplane 8 to be tested, the other end of the second connecting piece 2 is connected with a second fixed connecting point 5, the second fixed connecting point 5 is positioned behind the airplane 8 to be tested, and the second fixed connecting point 5 and the first fixed connecting point 4 are respectively and symmetrically arranged along the central axis of the airplane 8 to be tested The number of the wheel blocks 3 is equal to the number of the to-be-tested airplane 8 wheels, the wheel blocks 3 are fixedly arranged in front of the to-be-tested airplane 8 wheels, the first connecting piece 1 and the second connecting piece 2 are provided with tension detection devices 6 for testing the magnitude of tension borne by the connecting pieces, and the wheel blocks 3 are provided with pressure detection devices 7 for testing the thrust borne by the wheel blocks.
One end through first connecting piece 1 and second connecting piece 2 in this embodiment is connected with the ear that connects on the 8 main landing gear pillars of the aircraft that await measuring, and the other end is connected with fixed connection point, first fixed connection point 4 and second fixed connection point 5 are all the rigid's tie point, and it can provide sufficient pulling force for the test aircraft, and it can be the fixed point on setting up the basis in test place or setting up the experiment platform in test place. The wheel chock 3 is also fixedly arranged on the basis of a test site or on an experiment platform of the test site and used for stopping the airplane wheel and providing a thrust force for the airplane wheel. The auxiliary equipment can obtain the pulling force provided by the first connecting piece 1 and the second connecting piece 2 to the test airplane and the pushing force provided by the wheel block 3 to the airplane wheel during the test run. And obtaining the aircraft engine installation thrust value of the test aircraft through stress analysis and calculation.
As shown in fig. 2, one end of the first connecting member 1 is provided with a first joint, the other end of the first connecting member 1 is provided with a second joint, the first joint and the second joint are both in a hook shape, the first connecting member 1 and the second connecting member 2 are both steel cables, and the lengths of the first connecting member 1 and the second connecting member 2 are equal.
As shown in fig. 2, the wheel chock 3 includes a hemispherical base and a supporting diagonal rod which are in contact with the wheel, the supporting diagonal rod is fixedly connected to the base, the pressure detection device 7 is disposed on the supporting diagonal rod, the tension detection device 6 includes a tension sensor for detecting tension and a tension display screen for displaying a detection value of the tension sensor, and the pressure detection device 7 includes a pressure sensor for detecting pressure and a pressure display screen for displaying a detection value of the pressure sensor.
In the embodiment, the auxiliary equipment consists of two arresting steel cables capable of displaying the internal force born by the arresting steel cables and at least 3 wheel blocks capable of displaying the horizontal and vertical external forces born by the arresting steel cables, one end of each arresting steel cable is fixedly connected with the ground, and the joints are connected by adopting hooks, so that the installation and the removal are convenient; the other end of the arresting steel cable is connected with an extending lug at the strut part of the landing gear of the airplane, and the connection part is also connected by a hook, so that the installation and the removal are convenient; the tension detection device 6 is arranged in the middle of the arresting steel cable, and the tension detection device 6 is cylindrical in shape. In the test process, the arresting steel cable is in a tensioned state, the axes of one end of the arresting steel cable, the tensile force detection device 6 and the other end of the arresting steel cable are positioned on the same straight line, and the strength and the rigidity of the arresting steel cable meet the test run requirement. The wheel chock body comprises an approximately hemispherical base and an inclined rod for supporting, wherein the approximately hemispherical base is in contact with the wheel, and the wheel chock is of a steel static structure fixed on the ground. The method is simple to operate, convenient and practical, the real-time thrust of the engine used for test run can be rapidly obtained by utilizing the measured partial data and combining the known parameters of the machine type, the problems that the thrust of the engine is difficult to measure and the real-time performance is low are solved, and the method can be popularized and used.
The invention discloses an aircraft engine installation thrust evaluation method of an aircraft engine installation thrust evaluation auxiliary device based on the auxiliary device, which is characterized by comprising the following steps of:
the method comprises the following steps of firstly, installing an aircraft engine on an airplane to be tested, and obtaining relevant parameters of the airplane;
step two, installing thrust evaluation auxiliary equipment;
starting test run and recording data measured by the thrust evaluation auxiliary equipment;
and fourthly, calculating the installation thrust of the aircraft engine in a plurality of rotating speed states and analyzing to obtain an installation thrust characteristic diagram of the aircraft engine.
In this embodiment, the relevant parameters of the aircraft in the first step include: the aircraft comprises an aircraft total mass, the position of the center of gravity of the aircraft, an aero-engine thrust action point, a static friction coefficient of contact between an aircraft wheel and a wheel block, a horizontal distance between a nose wheel of an undercarriage and a contact point between a main wheel and the ground, and an included angle formed by engine thrust and the horizontal direction. A series of parameters required for evaluating the installation thrust are obtained after the engine is installed, the basis for accurately obtaining the installation thrust of the aero-engine is provided, and the accuracy of solving the installation thrust is guaranteed.
In this embodiment, the specific requirements for installing the thrust evaluation auxiliary device in the second step include: the lengths of the two connecting pieces are kept consistent and the connecting states of the two connecting pieces and the connecting lugs on the main landing gear supporting columns on the two sides are the same, all wheels of the test airplane are completely arranged on the wheel block, the two sides are symmetrically arranged by taking the central axis of the test airplane as the central line, and the horizontal distance between the contact point of the front wheel and the wheel block and the center of gravity of the airplane is measured. In this embodiment, the installation requirements of the external test-run auxiliary equipment are made clear, and installing the auxiliary equipment according to the requirements is an important guarantee that the mechanical relationship is established in the installation thrust evaluation, and is a guarantee that the installation thrust of the aircraft engine is accurately obtained.
In this embodiment, in the third step, in order to measure the installation thrust in a plurality of rotation speed states as much as possible, the throttle lever is required to be pushed uniformly and slowly to change the rotation speed of the engine during the test run, so as to record each set of data in a plurality of stable states. And step three, the implementation requirement of test run is determined, stable data under a plurality of states can be obtained as far as possible, the method is a core step of the whole installation thrust evaluation implementation scheme, and is a key link for accurately obtaining the installation thrust of the aircraft engine.
In this embodiment, the method for calculating the installation thrust of the aircraft engine in the fourth step in the multiple rotation speed states includes the following steps:
step 401, for the accuracy of the calculation, make the following assumptions: the thrust of an engine acts on the symmetrical plane of the airplane, the acting point and the center of gravity of the airplane are at the same horizontal height, the center of gravity position of the airplane is basically unchanged along with the fuel consumption in the test run process, the thrust of the engine only changes in the test run process but the acting direction does not shift, and the stress conditions of the left main undercarriage wheel and the right main undercarriage wheel are the same,
step 402, based on the above assumptions, according to the overall stress relationship of the aircraft, it can be obtained:
f1＝μ1×N1
f2＝μ2×N2
wherein P is total thrust of the engine, G is total weight of the airplane, and F2Tension, X, provided for arresting the wire rope1，X2Backward supporting force applied to wheel block1，N2Upward supporting force f applied to wheel block1，f2Friction force, mu, exerted on wheel block of airplane wheel1，μ2Is static friction coefficient, alpha is engine thrust action point and airplaneThe horizontal distance between the centers of gravity, b is the horizontal distance between the connecting point of the blocking steel cable and the ground and the center of gravity of the airplane, c is the horizontal distance between the contact point of the front wheel and the wheel chock and the center of gravity of the airplane, h is the plumb distance between the center of gravity of the airplane and the ground, L0The horizontal distance between the front wheel of the landing gear and the lowest point of contact between the main wheel and the wheel chock, theta is an included angle formed by the blocking steel cable and the horizontal direction,
The included angle is formed between the thrust of the engine and the horizontal direction; the total weight G of the airplane comprises the empty weight of the airplane, the weight of passengers, the weight of fuel oil, the weight of mounted loads, other bearing weights and the like. And fourthly, solving the installation thrust of the specific engine in a plurality of states on the basis of the previous work, and analyzing to obtain an engine installation thrust characteristic diagram.
The invention aims to solve the technical problems that the difficulty in accurately measuring the installation thrust of an engine after the existing outfield engine is installed is high, and the section parameters required by simulation calculation of a component method are difficult to obtain, and provides an aero-engine installation thrust evaluation method based on outfield improved test auxiliary equipment.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (8)
1. The auxiliary equipment for evaluating the installation thrust of the aircraft engine is characterized by comprising a first connecting piece (1), a second connecting piece (2) and a wheel chock (3), wherein one end of the first connecting piece (1) is connected with a lug on a main landing gear strut on one side of an aircraft (8) to be tested, the other end of the first connecting piece (1) is connected with a first fixed connecting point (4), the first fixed connecting point (4) is positioned behind the aircraft (8) to be tested, one end of the second connecting piece (2) is connected with a lug on a main landing gear strut on the other side of the aircraft (8) to be tested, the other end of the second connecting piece (2) is connected with a second fixed connecting point (5), the second fixed connecting point (5) is positioned behind the aircraft (8) to be tested, and the second fixed connecting point (5) and the first fixed connecting point (4) are respectively arranged symmetrically along the central axis of the aircraft (8) to be tested, the number of fender (3) equals with the quantity of examination aircraft (8) wheel of awaiting measuring, fender (3) are fixed to be set up in the place ahead of examination aircraft (8) wheel of awaiting measuring, all be provided with tensile force detection device (6) of the tensile force size that the test connecting piece bore on first connecting piece (1) and second connecting piece (2), be provided with pressure detection device (7) of thrust that the test fender bore on fender (3).
2. An aircraft engine installation thrust evaluation aid as claimed in claim 1, wherein: the one end of first connecting piece (1) is provided with first joint, the other end of first connecting piece (1) is provided with the second and connects, first joint with the second connects and is the couple shape, first connecting piece (1) and second connecting piece (2) are the cable wire and the length of first connecting piece (1) and second connecting piece (2) equals.
3. An aircraft engine installation thrust evaluation aid as claimed in claim 1, wherein: the wheel chock (3) comprises a hemispherical base and a supporting inclined rod which are in contact with the wheel, the supporting inclined rod is fixedly connected with the base, the pressure detection device (7) is arranged on the supporting inclined rod, the tension detection device (6) comprises a tension sensor used for detecting tension and a tension display screen used for displaying the detection value of the tension sensor, and the pressure detection device (7) comprises a pressure sensor used for detecting pressure and a pressure display screen used for displaying the detection value of the pressure sensor.
4. An aircraft engine installation thrust force evaluation method using the aircraft engine installation thrust force evaluation auxiliary device according to any one of claims 1 to 3, characterized by comprising the steps of:
the method comprises the following steps of firstly, installing an aircraft engine on an airplane to be tested, and obtaining relevant parameters of the airplane;
step two, installing thrust evaluation auxiliary equipment;
starting test run and recording data measured by the thrust evaluation auxiliary equipment;
and fourthly, calculating the installation thrust of the aircraft engine in a plurality of rotating speed states and analyzing to obtain an installation thrust characteristic diagram of the aircraft engine.
5. An aircraft engine installation thrust evaluation method according to claim 4, wherein: the relevant parameters of the airplane in the first step comprise: the aircraft comprises an aircraft total mass, the position of the center of gravity of the aircraft, an aero-engine thrust action point, a static friction coefficient of contact between an aircraft wheel and a wheel block, a horizontal distance between a nose wheel of an undercarriage and a contact point between a main wheel and the ground, and an included angle formed by engine thrust and the horizontal direction.
6. An aircraft engine installation thrust evaluation method according to claim 4, wherein: the specific requirements for installing the thrust evaluation auxiliary equipment in the step two comprise:
the lengths of the two connecting pieces are kept consistent and the connecting states of the two connecting pieces and the connecting lugs on the main landing gear supporting columns on the two sides are the same, all wheels of the test airplane are completely arranged on the wheel block, the two sides are symmetrically arranged by taking the central axis of the test airplane as the central line, and the horizontal distance between the contact point of the front wheel and the wheel block and the center of gravity of the airplane is measured.
7. An aircraft engine installation thrust evaluation method according to claim 4, wherein:
in the third step, in order to measure the installation thrust in a plurality of rotating speed states as much as possible, the throttle lever is required to be pushed uniformly and slowly to change the rotating speed of the engine during test run so as to record each group of data in a plurality of stable states.
8. An aircraft engine installation thrust evaluation method according to claim 4, wherein: the method for calculating the installation thrust of the aircraft engine in the multiple rotating speed states in the fourth step comprises the following steps:
step 401, for the accuracy of the calculation, make the following assumptions: the thrust of an engine acts on the symmetrical plane of the airplane, the acting point and the center of gravity of the airplane are at the same horizontal height, the center of gravity position of the airplane is basically unchanged along with the fuel consumption in the test run process, the thrust of the engine only changes in the test run process but the acting direction does not shift, and the stress conditions of the left main undercarriage wheel and the right main undercarriage wheel are the same,
step 402, based on the above assumptions, according to the overall stress relationship of the aircraft, it can be obtained:
f1＝μ1×N1
f2＝μ2×N2
wherein P is total thrust of the engine, G is total weight of the airplane, and F2Tension, X, provided for arresting the wire rope1，X2Backward supporting force applied to wheel block1，N2For aircraft wheelsUpward supporting force f applied by wheel chock1，f2Friction force, mu, exerted on wheel block of airplane wheel1，μ2The coefficient of static friction is determined, alpha is the horizontal distance between the thrust action point of the engine and the center of gravity of the airplane, b is the horizontal distance between the connecting point of the blocking steel cable and the ground and the center of gravity of the airplane, c is the horizontal distance between the contact point of the front wheel and the wheel block and the center of gravity of the airplane, h is the plumb distance between the center of gravity of the airplane and the ground, L is the vertical distance between the center of gravity of the airplane and the ground0The horizontal distance between the front wheel of the landing gear and the lowest point of contact between the main wheel and the wheel chock, theta is an included angle formed by the blocking steel cable and the horizontal direction,
The included angle is formed between the thrust of the engine and the horizontal direction;
the total weight G of the airplane comprises the empty weight of the airplane, the weight of passengers, the weight of fuel oil, the weight of mounted loads, other bearing weights and the like.
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| CN114313305A (en) * | 2021-12-15 | 2022-04-12 | 中国航空工业集团公司成都飞机设计研究所 | Inspection method for reducing ground test run slippage risk of jet plane |
| CN115355868A (en) * | 2022-07-27 | 2022-11-18 | 成都飞机工业（集团）有限责任公司 | Device for testing axial alignment of aircraft engine and mounting and testing method thereof |
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