Thrust measurement method based on online range switching

Abstract

The present invention provides a thrust measurement method based on online range switching, comprising: Step 1: Establishing a thrust measurement model under different range conditions; Step 2: Calibrating under different range conditions to obtain corresponding calibration coefficients; and Step 3: Online selecting an appropriate range segment and calibration coefficient based on the thrust magnitude during the test for measurement. During high-altitude engine simulation tests, this embodiment of the present invention can automatically switch online to a thrust sensor that meets the required range and measurement accuracy, based on the engine test thrust magnitude, thereby achieving high-precision thrust measurement across the entire engine envelope.

Description

Technical Field

[0001] This specification relates to the technical field of engine testing and experiment, and in particular to a thrust measurement method based on online range switching. Background Art

[0002] With the continuous advancement of aircraft engine technology, the design of new aircraft has become increasingly dependent on high-performance aircraft engine testing and reliable performance data. The accurate evaluation of aircraft engine performance has become increasingly important. Among them, aircraft engine thrust is a key technical indicator for evaluating engine power performance. Currently, aircraft engine thrust is primarily measured through testing on high-altitude simulated test benches.

[0003] During full-envelope, high-altitude simulation tests of aircraft engines, engine thrust varies greatly, from a few hundred kilograms to tens of thousands of kilograms. If current thrust testing methods employ a single, fixed-range thrust sensor for measurement, measurement accuracy will drop dramatically at low thrust levels.

[0004] At present, the thrust sensor range cannot be switched online after the high-altitude cabin is closed. In order to ensure accurate measurement of engine thrust within the full envelope, a large-range thrust sensor is required in the high-thrust state, and a small-range thrust sensor is required in the low-thrust state. Summary of the Invention

[0005] In view of this, the embodiments of this specification provide a thrust measurement method based on online range switching to achieve the purpose of improving measurement accuracy.

[0006] The technical solution of the present invention is: a thrust measurement method based on online range switching, comprising: step 1, establishing a thrust measurement model under different range conditions; step 2, performing calibration under different range conditions to obtain corresponding calibration coefficients; step 3, online selecting a suitable range segment and calibration coefficient for measurement according to the thrust size during the test.

[0007] Furthermore, step 1 is to establish a thrust measurement model under the condition of small thrust range: F 小 =k 小 F2+b 小 ; F 小 =F 2标 , where F 小 is the standard force under the condition of small thrust range, k 小 is the linear coefficient under the condition of small thrust range, F2 is the thrust measured by the No. 2 thrust measurement component, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, b 小 is the zero-order coefficient under small thrust range conditions.

[0008] Furthermore, step 2 is specifically as follows: only the No. 2 thrust measurement component and the No. 2 thrust calibration component are in working state; multiple standard forces of different magnitudes are applied by the No. 2 thrust calibration component, the corresponding measurement forces are collected by the No. 2 thrust measurement component, and k is obtained according to the thrust measurement model under the condition of small thrust range. 小 and b 小 .

[0009] Furthermore, step 3 is specifically as follows: by formula F 小测 =k 小 F2+b 小 -F 预载 Calculate the bench thrust measurement value under the condition of small thrust range, where F 小测 is the bench thrust measurement value under small thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0010] Furthermore, step 1 is to establish a thrust measurement model under medium thrust range conditions: F 中 =k 中 (F1+F3)+b 中 ; F 中 =F 1标 +F 3标 , where F 中 is the standard force under medium thrust range conditions, k 中 is the first-order coefficient under medium thrust range conditions, F1 is the thrust measured by No. 1 thrust measurement assembly, F3 is the thrust measured by No. 3 thrust measurement assembly, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 中 is the zero-order coefficient under medium thrust range conditions.

[0011] Furthermore, step 2 is specifically as follows: put the No. 1 thrust measurement component, the No. 3 thrust measurement component, the No. 1 thrust calibration component and the No. 3 thrust calibration component into working state; apply a plurality of standard forces of different magnitudes through the No. 1 thrust calibration component and the No. 3 thrust calibration component, collect the corresponding measurement forces through the No. 1 thrust measurement component and the No. 3 thrust measurement component, and obtain k according to the thrust measurement model under the medium thrust range condition. 中 and b 中 .

[0012] Furthermore, step 3 is specifically as follows: by formula F 中测 =k 中 (F1+F3)+b 中 -F 预载 Calculate the bench thrust measurement value under medium thrust range conditions, where F 中测is the bench thrust measurement value under medium thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0013] Furthermore, step 1 is to establish a thrust measurement model under large thrust range conditions: F 大 =k 大 (F1+F2+F3)+b 大 ; F 大 =F 1标 +F 2标 +F 3标 , where F 大 is the standard force under large thrust range conditions, k 大 is the first-order coefficient under the condition of large thrust range, F1 is the thrust measured by No. 1 thrust measurement component, F2 is the thrust measured by No. 2 thrust measurement component, F3 is the thrust measured by No. 3 thrust measurement component, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 大 is the zero-order coefficient under large thrust range conditions.

[0014] Furthermore, step 2 is specifically as follows: put the No. 1 thrust measurement component, the No. 2 thrust measurement component, the No. 3 thrust measurement component, the No. 1 thrust calibration component, the No. 2 thrust calibration component and the No. 3 thrust calibration component into working state; apply a plurality of standard forces of different magnitudes through the No. 1 thrust calibration component, the No. 2 thrust calibration component and the No. 3 thrust calibration component, collect the corresponding measurement forces through the No. 1 thrust measurement component, the No. 2 thrust measurement component and the No. 3 thrust measurement component, and obtain k according to the thrust measurement model under the medium thrust range condition. 大 and b 大 .

[0015] Furthermore, step 3 is specifically as follows: by formula F 大测 =k 大 (F1+F2+F3)+b 大 -F 预载 Calculate the bench thrust measurement value under medium thrust range conditions, where F 大测 is the bench thrust measurement value under large thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0016] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: during the high-altitude simulation test of the engine, the embodiment of the present invention can automatically switch online the thrust sensor that meets the measuring range and meets the measurement accuracy according to the size of the engine test thrust, thereby realizing high-precision measurement of the thrust within the entire envelope of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0018] Figure 1 Schematic diagram of a wide-range, high-precision thrust measurement bench based on online range switching applied in the present invention;

[0019] Figure 2 It is a flowchart of an embodiment of the present invention. DETAILED DESCRIPTION

[0020] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0021] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0022] The embodiment of the present invention provides a thrust measurement method based on online range switching, which is applied Figure 1The device shown in the figure is carried out, and the device can be divided into three range segments for measurement. In the first range segment (small thrust), only the middle thrust measurement component is in working state, and the thrust measurement components on both sides are in non-working state. In the second range segment (medium thrust), the middle thrust measurement component is in non-working state, and the thrust measurement components on both sides are in working state. In the third range segment (large thrust), all three thrust measurement components are in working state. Among them, the thrust measurement component in the middle position is thrust measurement component No. 2, and the ones on both sides are thrust measurement components No. 1 and No. 3 respectively. The corresponding thrust calibration components correspond to the positions of the thrust measurement components and will not be repeated here.

[0023] like Figure 2 As shown, the thrust measurement method based on online range switching in an embodiment of the present invention includes:

[0024] Step 1: Establish a thrust measurement model under different range conditions;

[0025] Step 2: Calibrate under different range conditions to obtain the corresponding calibration coefficient;

[0026] Step 3: During the test, select the appropriate range and calibration coefficient online according to the thrust size for measurement.

[0027] The embodiment of the present invention can automatically switch online a thrust sensor that meets the measuring range and measurement accuracy according to the size of the engine test thrust during the high-altitude simulation test of the engine, thereby realizing high-precision measurement of the thrust within the full envelope of the engine.

[0028] In the first embodiment of the present invention, step 1 specifically involves establishing a thrust measurement model under small thrust range conditions:

[0029] F 小 =k 小 F2+b 小 ; F 小 =F 2标 , where F 小 is the standard force under the condition of small thrust range, k 小 is the linear coefficient under the condition of small thrust range, F2 is the thrust measured by the No. 2 thrust measurement component, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, b 小 is the zero-order coefficient under small thrust range conditions.

[0030] Step 2 is as follows: only the No. 2 thrust measurement component and the No. 2 thrust calibration component are in working state; multiple standard forces of different magnitudes are applied by the No. 2 thrust calibration component, the corresponding measurement forces are collected by the No. 2 thrust measurement component, and k is obtained according to the thrust measurement model under the condition of small thrust range. 小 and b小 .

[0031] Furthermore, step 3 is specifically as follows:

[0032] By formula F 小测 =k 小 F2+b 小 -F 预载 Calculate the bench thrust measurement value under the condition of small thrust range, where F 小测 is the bench thrust measurement value under small thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0033] In the low thrust state, the control system selects the middle No. 2 thrust measurement component to measure the thrust, and automatically calls k 小 and b 小 As a correction factor for the thrust measurement value. In addition, during the test, the maximum intake impulse is selected and the intermediate thrust calibration assembly is selected to apply an appropriate preload force to the thrust bench.

[0034] In the second embodiment of the present invention, step 1 specifically involves establishing a thrust measurement model under medium thrust range conditions:

[0035] F 中 =k 中 (F1+F3)+b 中 ; F 中 =F 1标 +F 3标 , where F 中 is the standard force under medium thrust range conditions, k 中 is the first-order coefficient under medium thrust range conditions, F1 is the thrust measured by No. 1 thrust measurement assembly, F3 is the thrust measured by No. 3 thrust measurement assembly, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 中 is the zero-order coefficient under medium thrust range conditions.

[0036] Step 2 is as follows: put the No. 1 thrust measurement component, the No. 3 thrust measurement component, the No. 1 thrust calibration component and the No. 3 thrust calibration component into working state; apply multiple standard forces of different magnitudes through the No. 1 thrust calibration component and the No. 3 thrust calibration component, collect the corresponding measurement forces through the No. 1 thrust measurement component and the No. 3 thrust measurement component, and obtain k according to the thrust measurement model under the medium thrust range condition. 中 and b 中 .

[0037] During calibration under medium thrust range conditions, only the No. 1 and No. 3 thrust measurement assemblies on either side were in operation. Multiple standard forces of varying magnitudes were applied to the No. 1 and No. 3 thrust calibration assemblies, while simultaneously collecting the measured forces of varying magnitudes from the No. 1 and No. 3 thrust measurement assemblies.

[0038] In the middle thrust state, the control system selects the thrust measurement components on both sides to measure the thrust and automatically calls k 中 and b 中 As a correction factor for the thrust measurement value. In addition, during the test, the maximum intake impulse is selected, and the middle thrust calibration assembly or the two side thrust calibration assemblies are selected to apply a preload force to the thrust bench.

[0039] Step 3 is to use formula F 中测 =k 中 (F1+F3)+b 中 -F 预载 Calculate the bench thrust measurement value under medium thrust range conditions, where F 中测 is the bench thrust measurement value under medium thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0040] In the third embodiment of the present invention, step 1 specifically involves establishing a thrust measurement model under a large thrust range condition:

[0041] F 大 =k 大 (F1+F2+F3)+b 大 ; F 大 =F 1标 +F 2标 +F 3标 , where F 大 is the standard force under large thrust range conditions, k 大 is the first-order coefficient under the condition of large thrust range, F1 is the thrust measured by No. 1 thrust measurement component, F2 is the thrust measured by No. 2 thrust measurement component, F3 is the thrust measured by No. 3 thrust measurement component, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 大 is the zero-order coefficient under large thrust range conditions.

[0042] Similar to the above embodiment, step 2 is specifically as follows: put the No. 1 thrust measurement component, the No. 2 thrust measurement component, the No. 3 thrust measurement component, the No. 1 thrust calibration component, the No. 2 thrust calibration component and the No. 3 thrust calibration component into a working state; apply a plurality of standard forces of different magnitudes through the No. 1 thrust calibration component, the No. 2 thrust calibration component and the No. 3 thrust calibration component, collect the corresponding measurement forces through the No. 1 thrust measurement component, the No. 2 thrust measurement component and the No. 3 thrust measurement component, and obtain k according to the thrust measurement model under the medium thrust range condition. 大 and b 大 .

[0043] Step 3 is as follows: 大测 =k 大 (F1+F2+F3)+b 大 -F 预载 Calculate the bench thrust measurement value under medium thrust range conditions, where F 大测 is the bench thrust measurement value under large thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

[0044] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A thrust measurement method based on online range switching, characterized in that: include: Step 1: Establish a thrust measurement model under different range conditions; Step 2: Calibrate under different range conditions to obtain the corresponding calibration coefficient; Step 3: During the test, select the appropriate range and calibration coefficient online according to the thrust size for measurement; The step 1 is specifically to establish a thrust measurement model under the condition of a small thrust range: ; , where F 小 is the standard force under the condition of small thrust range, k 小 is the linear coefficient under the condition of small thrust range, F2 is the thrust measured by the No. 2 thrust measurement component, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, b 小 is the zero-order coefficient under small thrust range conditions; The first step is to establish a thrust measurement model under medium thrust range conditions: ; , where F 中 is the standard force under medium thrust range conditions, k 中 is the first-order coefficient under medium thrust range conditions, F1 is the thrust measured by No. 1 thrust measurement assembly, F3 is the thrust measured by No. 3 thrust measurement assembly, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 中 is the zero-order coefficient under medium thrust range conditions.

2. The thrust measurement method based on online range switching according to claim 1, characterized in that: The step 2 is specifically as follows: Only the No. 2 thrust measurement assembly and the No. 2 thrust calibration assembly are in working condition; Apply multiple standard forces of different sizes through the No. 2 thrust calibration component, collect the corresponding measurement force through the No. 2 thrust measurement component, and obtain k according to the thrust measurement model under the condition of small thrust range. 小 and b 小 .

3. The thrust measurement method based on online range switching according to claim 2, characterized in that: The step 3 is specifically as follows: By formula Calculate the bench thrust measurement value under the condition of small thrust range, where F 小测 is the bench thrust measurement value under small thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

4. The thrust measurement method based on online range switching according to claim 1, characterized in that: The step 2 is specifically as follows: Put thrust measurement assembly No. 1, thrust measurement assembly No. 3, thrust calibration assembly No. 1 and thrust calibration assembly No. 3 into working condition; Apply multiple standard forces of different sizes through thrust calibration assembly No. 1 and thrust calibration assembly No. 3, collect the corresponding measurement forces through thrust measurement assembly No. 1 and thrust measurement assembly No. 3, and obtain k according to the thrust measurement model under medium thrust range conditions. 中 and b 中 .

5. The thrust measurement method based on online range switching according to claim 4, characterized in that: The step 3 is specifically as follows: By formula Calculate the bench thrust measurement value under medium thrust range conditions, where F 中测 is the bench thrust measurement value under medium thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

6. The thrust measurement method based on online range switching according to claim 1, characterized in that: The first step is to establish a thrust measurement model under the condition of large thrust range: ; , where F 大 is the standard force under large thrust range conditions, k 大 is the first-order coefficient under the condition of large thrust range, F1 is the thrust measured by No. 1 thrust measurement component, F2 is the thrust measured by No. 2 thrust measurement component, F3 is the thrust measured by No. 3 thrust measurement component, F 1标 Measure the thrust for thrust calibration assembly No. 1, F 2标 Measure the thrust for the No. 2 thrust calibration assembly, F 3标 Measure the thrust for the No. 3 thrust calibration assembly, b 大 is the zero-order coefficient under large thrust range conditions.

7. The thrust measurement method based on online range switching according to claim 6, characterized in that: The step 2 is specifically as follows: Putting thrust measurement assembly No. 1, thrust measurement assembly No. 2, thrust measurement assembly No. 3, thrust calibration assembly No. 1, thrust calibration assembly No. 2 and thrust calibration assembly No. 3 into working condition; Multiple standard forces of different sizes are applied through thrust calibration assembly No. 1, thrust calibration assembly No. 2 and thrust calibration assembly No. 3, and the corresponding measurement forces are collected through thrust measurement assembly No. 1, thrust measurement assembly No. 2 and thrust measurement assembly No. 3, and k is obtained according to the thrust measurement model under the medium thrust range condition. 大 and b 大 .

8. The thrust measurement method based on online range switching according to claim 7, characterized in that: The step 3 is specifically as follows: By formula Calculate the bench thrust measurement value under medium thrust range conditions, where F 大测 is the bench thrust measurement value under large thrust range conditions, F 预载 The preload force applied to the thrust stand by the thrust calibration assembly.

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