CN219956904U - Aeroengine thrust measuring device - Google Patents
Aeroengine thrust measuring device Download PDFInfo
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- CN219956904U CN219956904U CN202321028436.2U CN202321028436U CN219956904U CN 219956904 U CN219956904 U CN 219956904U CN 202321028436 U CN202321028436 U CN 202321028436U CN 219956904 U CN219956904 U CN 219956904U
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Abstract
The utility model discloses an aeroengine thrust measuring device, comprising: the lifting frame comprises two lifting rods and a cross rod connected with the two lifting rods, the top ends of the two lifting rods are respectively connected with two ends of the cross rod, and fixing points are arranged on the cross rod; the connecting rod is perpendicular to the cross rod, one end of the connecting rod is connected with the fixed point, and the other end of the connecting rod is connected with the airplane to be tested; the transverse rod is provided with a thrust detection device, and the connecting rod is provided with a pressure detection device. The utility model can measure the thrust of the engine after the engine is installed, and simultaneously avoids the influence of ground effect, and improves the accuracy of measuring the thrust of the aeroengine.
Description
Technical Field
The utility model belongs to the technical field of aero-engines, and particularly relates to an aero-engine thrust measuring device.
Background
The thrust of the aero-engine is an important index of the maneuvering performance of the aero-engine, and the thrust measurement of the aero-engine has important significance for the performance analysis of the engine and the guarantee of the flight safety of the aircraft. At present, a thrust measuring device for an engine mainly measures thrust independently for the engine, the measuring device is complex in structure, single in measuring environment and incapable of measuring in different environments, and thrust generated after the engine is installed is inconsistent with thrust generated independently for the engine, so that differences exist, inaccurate engine thrust measuring data can be caused, and potential safety hazards are brought to aviation and flight. The device for measuring the thrust of the engine after installation can only be carried out on the ground, the thrust measurement on the ground can be influenced by the ground effect, the ground effect is that the induced resistance of the aircraft is reduced, meanwhile, the hydrodynamic effect with higher lift-drag ratio than that of the air flight can be obtained, the thrust measurement data of the engine can be influenced, and errors are generated. Therefore, it is desirable to design an engine thrust measuring device that can measure thrust after the engine is installed and avoid the influence of ground effects.
Disclosure of Invention
The utility model aims to overcome the defects in the prior art, and provides an aero-engine thrust measuring device which can measure engine thrust after an engine is installed, meanwhile, the influence of ground effect is avoided, and the accuracy of aero-engine thrust measurement is improved.
In order to achieve the above purpose, the technical scheme adopted by the utility model is to provide an aero-engine thrust measuring device, which comprises: the lifting frame comprises two lifting rods and a cross rod connected with the two lifting rods, the top ends of the two lifting rods are respectively connected with two ends of the cross rod, and fixing points are arranged on the cross rod; the connecting rod is perpendicular to the cross rod, one end of the connecting rod is connected with the fixed point, and the other end of the connecting rod is connected with the airplane to be tested; the transverse rod is provided with a thrust detection device, and the connecting rod is provided with a pressure detection device.
Further, the fixed points comprise a first fixed point and a second fixed point, and the first fixed point and the second fixed point are both positioned on the central axis of the aircraft to be tested.
Further, the connecting rod comprises a first connecting rod and a second connecting rod, one end of the first connecting rod is connected with the first fixed point, and the other end of the first connecting rod is connected with a connecting lug in a rear frame of the aircraft cabin to be tested; the second connecting rod is connected with the second fixed point, and the other end of the second connecting rod is connected with a lug in the front frame of the engine of the aircraft to be tested.
Further, the first connecting rod and the second connecting rod are steel rods and are identical in length, and spherical joints are arranged at two ends of the first connecting rod and two ends of the second connecting rod.
Further, the number of the thrust detection devices is two, one of the thrust detection devices is arranged between the first fixed point and the second fixed point, the other thrust detection device is arranged between the end part of the cross rod and the first fixed point, and the two thrust detection devices comprise a thrust sensor and a thrust display screen.
Further, the number of the pressure detection devices is two, one pressure detection device is arranged in the middle of the first connecting rod, the other pressure detection device is arranged in the middle of the second connecting rod, and the two pressure detection devices comprise a pressure sensor and a pressure display screen.
Compared with the prior art, the utility model has the following advantages:
1. according to the method, the real-time thrust of the engine arranged in the aircraft to be tested can be rapidly obtained through the force balance and moment balance calculation formula according to the related parameters of the aircraft to be tested and the measured partial data which are convenient to obtain, and the problems that the thrust measurement is difficult and the real-time performance is not high after the aircraft engine is installed are solved.
2. According to the utility model, the aircraft to be tested is lifted to the half space through the lifting frame, so that the ground effect of the aircraft to be tested is effectively eliminated or weakened, and the measured thrust of the aeroengine is more accurate.
3. The method is simple to operate, convenient and practical, low in economic cost and convenient and quick to calculate, and can provide method guidance for measuring the installation thrust of the aero-engine in an actual external field.
The utility model is described in further detail below with reference to the drawings and examples.
Drawings
FIG. 1 is a schematic diagram of the connection of an aero-engine thrust measuring device to an aircraft to be tested during a test according to the present utility model.
FIG. 2 is a diagram showing the stress analysis of the test run according to the present utility model.
FIG. 3 is a flow chart of the thrust measurement of the aircraft engine of the present utility model.
Reference numerals illustrate:
1-a cross bar; 2-lifting rod; 3-a first connecting rod;
4-a second connecting rod; 5-a first fixed point; 6-a second fixed point;
7-a thrust detection device; 8-a pressure detection device; 9-aircraft to be tested.
Detailed Description
Embodiments of the present utility model will be described in more detail below with reference to the accompanying drawings. While the utility model is susceptible of embodiment in the drawings, it is to be understood that the utility model may be embodied in various forms and should not be construed as limited to the embodiments set forth herein, but rather are provided to provide a more thorough and complete understanding of the utility model. It should be understood that the drawings and embodiments of the utility model are for illustration purposes only and are not intended to limit the scope of the present utility model.
It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other. The utility model will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1-3, the present utility model provides an aero-engine thrust measuring device comprising:
the device comprises a liftable frame, wherein the liftable frame is fixedly arranged on the basis of a test site or an experimental platform of the test site, the liftable frame is used for fixing an aircraft 9 to be tested on a certain height so as to be far away from the ground, the influence of ground effect on an aircraft engine after installation during thrust test is avoided, the liftable frame comprises two lifting rods 2 and a cross rod 1 connected with the two lifting rods 2, the two lifting rods 2 are hydraulic lifting rods and have the same length, the top ends of the two lifting rods 2 are respectively connected with two ends of the cross rod 1, and the cross rod 1 is provided with a fixed point;
the connecting rod is perpendicular to the cross rod 1, one end of the connecting rod is connected with the fixed point, the other end of the connecting rod is connected with the aircraft 9 to be tested, and the connecting rod is used for connecting the aircraft 9 to be tested with the liftable frame;
because the direction of the tail pipe of the aero-engine deflects up and down, or the installation angle of the aero-engine has errors, or is influenced by the external wind direction, the thrust direction of the aero-engine is not necessarily horizontal, so that the horizontal force and the vertical force of the aircraft 9 to be tested need to be measured simultaneously. Therefore, the horizontal rod 1 is provided with a thrust detection device 7, the thrust detection device 7 is used for displaying the horizontal external force born by the connecting rod, the connecting rod is provided with a pressure detection device 8, and the pressure detection device 8 can display the plumb external force born by the connecting rod.
The fixing points comprise a first fixing point 5 and a second fixing point 6, the first fixing point 5 and the second fixing point 6 are both positioned on the central axis of the aircraft 9 to be tested, and meanwhile, the first fixing point 5 and the second fixing point 6 are both positioned on the cross rod 1, namely, the aircraft 9 to be tested is symmetrical left and right by taking the cross rod 1 as a symmetrical axis and keeps a balanced state.
The connecting rods comprise a first connecting rod 3 and a second connecting rod 4, the two connecting rods are adopted to fix the aircraft 9 to be tested, the whole aircraft body can be ensured to be more stable, one end of the first connecting rod 3 is connected with the first fixed point 5, and the other end of the first connecting rod is connected with a lug in a rear frame of a cabin of the aircraft 9 to be tested; the second connecting rod 4 is connected with the second fixed point 6, and the other end of the second connecting rod is connected with a lug in the front frame of the engine of the aircraft 9 to be tested. The utility model is mainly used for measuring the thrust of a fighter plane, an engine is arranged at the rear part of a cabin, and a cabin rear frame refers to a 14-frame of the plane, namely a transverse frame at the rear part of a cabin cover of a fighter machine base, and is connected with a first connecting rod 3 through a connecting lug; the front frame of the engine refers to the 36 frames of the aircraft, namely the transverse frames at the front of the fighter engine, and is connected with the second connecting rod 4 through the lugs.
The head rod 3 with the second connecting rod 4 is steel pole and length unanimity to guarantee to wait to test the equilibrium and the stability of the whole organism of aircraft 9, simultaneously, in this embodiment steel pole's intensity and rigidity can satisfy the demand of taking a trial run, the both ends of head rod 3 with the both ends of second connecting rod 4 all are provided with ball joint, easy to assemble and dismantlement.
The number of the thrust detection devices 7 is two, the shapes of the two thrust detection devices 7 are cylindrical, one thrust detection device 7 is arranged between the first fixed point 5 and the second fixed point 6 and used for detecting horizontal direction force borne by the second connecting rod 4, the other thrust detection device 7 is arranged between the end part of the cross rod 1 and the first fixed point 5 and used for detecting horizontal direction force borne by the first connecting rod 3, the two thrust detection devices 7 comprise a thrust sensor and a thrust display screen, the thrust sensor is used for detecting the thrust, and the thrust display screen is used for displaying the thrust value detected by the thrust sensor.
The quantity of pressure detection device 8 is two, two the appearance of pressure detection device 8 is cylindrical, one of them pressure detection device 8 sets up the middle part of head rod 3, another one pressure detection device 8 sets up the middle part of second connecting rod 4, two pressure detection device 8 all include pressure sensor and pressure display screen, pressure sensor is used for detecting pressure size, pressure display screen is used for showing the pressure numerical value that pressure sensor detected.
The method for measuring the thrust of the aero-engine by the aero-engine thrust measuring device comprises the following steps:
step one, installing an aeroengine on the aircraft 9 to be tested, and acquiring relevant parameters of the aircraft 9 to be tested;
step two, installing an aero-engine thrust measuring device, wherein specific requirements include: firstly, ensuring that the connection state of the first connecting rod 3 and the lug in the rear frame of the cabin of the aircraft 9 to be tested is the same as the connection state of the second connecting rod 4 and the lug in the front frame of the engine of the aircraft 9 to be tested, secondly, ensuring that the first connecting rod 3 and the second connecting rod 4 are fixedly connected with the cross rod 1 and the aircraft 9 to be tested is distributed in bilateral symmetry by taking the cross rod 1 as a symmetry axis, and finally, lifting the lifting frame to a certain height and fixing;
and thirdly, starting a test run test and recording data measured by the thrust detection device 7 and the pressure detection device 8. The two thrust detection devices 7 respectively measure the forces in the horizontal direction borne by the first connecting rod 3 and the second connecting rod 4, and the two pressure detection devices 8 respectively measure the forces in the vertical direction on the first connecting rod 3 and the second connecting rod 4. In test, the aircraft to be tested is more susceptible to ground effect as approaching the ground, wherein the ground effect is that the aircraft is blocked due to the interference of the ground or the water surface, the downward washing action of the lifting surface (usually referred to as a wing) of the aircraft is blocked, so that the air flow between the ground or the water surface and the lifting surface of the aircraft is compressed, namely the pressure under the wing is increased, thereby increasing the lifting force of the wing and reducing the blockingTwo aerodynamic properties of force (i.e., wing induced drag decreases due to changes in conditions of airflow flow). When the aircraft 9 to be tested is close to the ground during test, the increase of the wing lift force can lead to F 1 And F 2 An increase, a decrease in resistance results in T 1 And T 2 The error of the calculated engine thrust P value is larger, so that the aircraft 9 to be tested is lifted to the half space by using the aeroengine thrust measuring device and fixed at a certain height, the ground effect of the aircraft can be effectively eliminated or weakened, the measurement data of the thrust detecting device 7 and the pressure monitoring device 8 are more accurate, and the measured thrust of the aeroengine is more accurate;
and step four, calculating the installation thrust of the aero-engine in a plurality of rotating speed states and analyzing to obtain an installation thrust characteristic diagram of the aero-engine.
Specifically, the relevant parameters of the aircraft 9 to be tested in the first step include the total mass of the aircraft, the position of the center of gravity of the aircraft, the thrust point of the aero-engine, the horizontal distance between the lug in the rear frame of the cabin of the aircraft 9 to be tested and the lug in the front frame of the engine of the aircraft 9 to be tested, and the included angle between the thrust of the engine and the horizontal direction. The related data are recorded before the thrust test is carried out, so that the engine thrust can be calculated and evaluated conveniently according to the force balance and the moment balance.
Specifically, in the third step, in order to measure the installation thrust under a plurality of rotation speed states as much as possible, the throttle lever is required to be uniformly and slowly pushed to change the rotation speed of the aeroengine during test, so that each group of data under a plurality of stable states is recorded, the accuracy of each group of data influences the accuracy of the thrust measurement value, and each group of data under the stable states can more reflect the real performance of the engine.
Specifically, the method for calculating the installation thrust in a plurality of rotation speed states of the aero-engine in the fourth step comprises the following steps:
step 401, for the accuracy of calculation, make the following assumptions: the engine thrust is supposed to act on the plane of symmetry of the aircraft 9 to be tested, the thrust acting point and the gravity center of the aircraft 9 to be tested are positioned at the same horizontal height, the gravity center position of the aircraft 9 to be tested is supposed to be basically unchanged along with fuel consumption in the test process of test run, the thrust of the aeroengine is supposed to be changed only in the test run process, and the acting direction is not deviated,
step 402, based on the above assumption, the overall stress relationship of the aircraft 9 to be tested is obtained:
P×sinθ＝F 1 +F 2 +G
P×cosθ＝T 1 +T 2
F 1 ×a+P×b×sinθ＝T 1 ×d+T 2 ×e+F 2 ×c
wherein P is the total thrust of the aero-engine, G is the total weight of the aircraft 9 to be tested, F 1 Downward pressure provided to the first connecting rod 3, F 2 Downward pressure, T, provided for said second connecting rod 4 1 、T 2 The horizontal rod 1 provides backward thrust, θ is an included angle between the total thrust of the aero-engine and the horizontal direction, a is a horizontal distance between the first fixed point 5 and the center of gravity of the aircraft 9 to be tested, b is a horizontal distance between the total thrust action point of the aero-engine and the center of gravity of the aircraft 9 to be tested, c is a horizontal distance between the second fixed point 6 and the center of gravity of the aircraft 9 to be tested, d is the length of the first connecting rod 3 during testing, and e is the length of the second connecting rod 4 during testing;
the gross aircraft weight G includes aircraft empty weight, occupant weight, fuel weight, payload weight, and other load bearing weights.
And obtaining the thrust value of the airplane 9 to be tested through the calculation formulas of the force balance and the moment balance.
The foregoing description is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model, and any simple modification, variation and equivalent structural transformation of the above embodiment according to the technical substance of the present utility model still fall within the scope of the technical solution of the present utility model.
Claims (6)
1. An aero-engine thrust measuring device, comprising:
the lifting frame comprises two lifting rods (2) and a cross rod (1) connected with the two lifting rods (2), the top ends of the two lifting rods (2) are respectively connected with two ends of the cross rod (1), and fixing points are arranged on the cross rod (1);
the connecting rod is perpendicular to the cross rod (1), one end of the connecting rod is connected with the fixed point, and the other end of the connecting rod is connected with the airplane (9) to be tested;
the transverse rod (1) is provided with a thrust detection device (7), and the connecting rod is provided with a pressure detection device (8).
2. An aeroengine thrust measuring device according to claim 1, wherein said fixed points comprise a first fixed point (5) and a second fixed point (6), said first fixed point (5) and said second fixed point (6) being both located on the central axis of said aircraft (9) to be tested.
3. An aeroengine thrust measuring device according to claim 2, wherein the connecting rods comprise a first connecting rod (3) and a second connecting rod (4), one end of the first connecting rod (3) being connected to the first fixing point (5) and the other end being connected to a lug in the cabin back frame of the aircraft (9) to be tested; the second connecting rod (4) is connected with the second fixed point (6), and the other end of the second connecting rod is connected with a lug in the front frame of the engine of the aircraft (9) to be tested.
4. An aeroengine thrust measuring device according to claim 3, wherein the first connecting rod (3) and the second connecting rod (4) are steel rods and have the same length, and spherical joints are arranged at both ends of the first connecting rod (3) and both ends of the second connecting rod (4).
5. An aeroengine thrust measuring device according to claim 2, wherein the number of said thrust detecting means (7) is two, one of said thrust detecting means (7) being arranged between said first fixed point (5) and said second fixed point (6), the other of said thrust detecting means (7) being arranged between the end of said cross bar (1) and said first fixed point (5), both of said thrust detecting means (7) comprising a thrust sensor and a thrust display.
6. An aeroengine thrust measuring device according to claim 4, wherein the number of said pressure detecting devices (8) is two, one of said pressure detecting devices (8) being arranged in the middle of said first connecting rod (3) and the other of said pressure detecting devices (8) being arranged in the middle of said second connecting rod (4), both of said pressure detecting devices (8) comprising a pressure sensor and a pressure display.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321028436.2U CN219956904U (en) | 2023-04-28 | 2023-04-28 | Aeroengine thrust measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321028436.2U CN219956904U (en) | 2023-04-28 | 2023-04-28 | Aeroengine thrust measuring device |
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| Publication Number | Publication Date |
|---|---|
| CN219956904U true CN219956904U (en) | 2023-11-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321028436.2U Active CN219956904U (en) | 2023-04-28 | 2023-04-28 | Aeroengine thrust measuring device |
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| Country | Link |
|---|---|
| CN (1) | CN219956904U (en) |
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2023
- 2023-04-28 CN CN202321028436.2U patent/CN219956904U/en active Active
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