Dual-weighing flight hanging measurement system and method for external object flight force test

Abstract

The application relates to a double-weighing hanging flight measurement system and method for external hanging flight force test, and belongs to the technical fields of aviation, aircraft design and sensor measurement. The application solves the problem of inconsistent load distribution of front and rear hanging ears in the prior art. Technical points: first and second scales are arranged in front and back of an external hanging cabin section; the outer sides of front flange plates of the first and second scales are fixed to the inner wall of the external hanging cabin section; the top ends of rear hangers of the first and second scales are extended from the top of the external hanging cabin section; the rear hanger of the first scale, a hanger fixed cylinder front section, a hanger fixed cylinder rear section, the rear hanger of the second scale are sequentially connected; and the hanger fixed cylinder rear section is installed on the outer side of the second scale. The hanger fixed cylinder is arranged, the connecting rigidity between the hanger fixed cylinder front section and the hanger fixed cylinder rear section can be adjusted, the connecting rigidity is consistent with the real structure, the load distribution of the front and rear hanging ears is consistent, local overload-induced fatigue fracture is avoided, and the service life is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aviation, aircraft design and sensor measurement, in particular to a double-balance hanging flight measurement system and method for external object flight force test. BACKGROUND

[0002] Aircraft need to carry different types of external objects when performing flight tasks. Obtaining the aerodynamic load of the external object under various flight conditions of the aircraft can provide important parameters for the design of the aircraft and the external object. Common external object load measurement methods include computer CFD simulation, wind tunnel test and flight test.

[0003] Currently, computer CFD simulation has been widely used in the field of aircraft design, and has the characteristics of short calculation period and low cost in aircraft load calculation. However, when using this method to calculate the complex model of the interaction between the aircraft and the external object, the simulation result is still not reliable enough and can only be used as a reference for design.

[0004] Wind tunnel test is a common method for studying the load of aircraft and external objects. During the test, the test model of the carrier and the external object is designed, force balances are arranged in the external object, corresponding interfaces are arranged on the carrier, and then the load of the external object is obtained by blowing in the wind tunnel. The characteristics of wind tunnel test are relatively low test cost and high test data reliability. However, the scaled model used in wind tunnel test is subject to processing capacity, and a large number of details on the carrier and the external object cannot be consistent with the actual situation, such as the simplification of the inlet of the carrier and the change of the shape of the external object and the carrier connection due to the need to install the balance. In addition, factors such as unstable wind tunnel flow field and model support structure will interfere with the measurement results. Therefore, although wind tunnel test is widely used by aircraft and external object design units, the accuracy of the test data must be evaluated and corrected in detail.

[0005] Flight test has the characteristic that the test environment is completely consistent with the actual flight, which directly determines that the data of flight test is the closest to the real situation. In addition, flight test uses full-size external object model, has sufficient space, and can perform force measurement, pressure measurement and external object and carrier interaction tests in one flight plan, so the test efficiency is high. In this background, flight test for aircraft external object force measurement to obtain accurate aerodynamic load information of the external object has become the focus of consideration for various units.

[0006] The basic principle of external store force measurement by flight test is similar to external store force measurement in wind tunnel, which needs to arrange force balance reasonably in the external store, form the "external store-balance-aircraft" measurement system through designing corresponding structural parts, and then collect the data of the balance under test conditions through the matching acquisition equipment to calculate the load condition of the external store.

[0007] In the past, there are some external store measurement schemes that arrange one or more balances in the external store, for example, a feasibility of a multi-component balance individual calibration and combined measurement technology scheme is discussed in the article "Multi-balance measurement research technology and application", and its application in a certain external store measurement is shown. However, similar schemes generally have problems, that is, the "external store-balance-aircraft" structure formed by arranging the balance as a structural part into the external store model changes the connection stiffness of the actual "external store-aircraft" structure, and the load of the front and rear hangers connecting the aircraft and the external store changes. The front and rear hangers are the most stressed parts in the structure, and the size of the connecting structure is small and the matching surface is complex, so it is difficult to accurately evaluate the strength after the load changes, and therefore the change of the front and rear load distribution will bring risks to the structural strength.

[0008] Therefore, it is urgent to provide a dual-balance external store flight measurement system and method for external store flight force test to solve the problem of inconsistent front and rear hanger load distribution in the prior art. SUMMARY

[0009] In view of the above facts, in order to solve the problem of inconsistent front and rear hanger load distribution in the prior art, a dual-balance external store flight measurement system for external store flight force test is designed.

[0010] To achieve the above purpose, the technical scheme is as follows:

[0011] Scheme one: a dual-balance external store flight measurement system for external store flight force test, comprising an external store cabin section, a first balance, a second balance, a first balance front flange, a second balance front flange, a first balance rear hanger, a second balance rear hanger, a hanger fixed connection cylinder front section, a hanger fixed connection cylinder rear section, a first amplifier, a second amplifier, a data acquisition device, and a side panel.

[0012] The external store cabin section is a hollow body of revolution, a first balance is arranged in the front section of the external store cabin section, and a second balance is arranged in the rear section of the external store cabin section.

[0013] The front side of the first balance is provided with a first balance front flange, the rear side of the first balance is provided with a first balance rear hanger, the front side of the second balance is provided with a second balance front flange, and the rear side of the second balance is provided with a second balance rear hanger.

[0014] The outer sides of the first and second front flanges are fixed to the inner wall of the external payload cabin section, and the top ends of the first and second rear hangers extend from the top of the external payload cabin section;

[0015] The first rear hanger, the hanger fixed cylinder front section, the hanger fixed cylinder rear section, and the second rear hanger are connected in sequence, the second front flange is sleeved on the connection between the hanger fixed cylinder front section and the hanger fixed cylinder rear section, and the hanger fixed cylinder rear section is sleeved on the outer side of the second balance;

[0016] The front side of the first front flange is provided with a first amplifier, and the front side of the second front flange is provided with a second amplifier;

[0017] The data acquisition device is installed on the front bracket of the external payload cabin section, and the data acquisition device is connected with the first amplifier and the second amplifier respectively, for receiving the balance signal amplified and transmitted by the first amplifier and the second amplifier.

[0018] Further, the top end of the first and second rear hangers is provided with a hanger ear connected with the carrier's hanger.

[0019] Further, the external payload cabin section is provided with a side panel.

[0020] Further, the outer side of the first and second balances is welded with a corrugated pipe.

[0021] The front and rear connecting surfaces of the first and second balances are provided with key holes and threaded holes.

[0022] Further, the first and second balances are completely identical in structure, both being rod type five-component flight test balances, and the first and second balances are coaxial and the axis is coincident with the axis of the external payload cabin section.

[0023] Scheme two: a double-balance flight test measurement method for external payload flight force test, which adopts the double-balance flight test measurement system for external payload flight force test as described in scheme one, specifically:

[0024] Step one: turn on the data acquisition device, establish the connection between the data acquisition device and the airborne equipment, calibrate the time signal and the position signal, and record the signals of the first and second balances;

[0025] Step two: after the airplane takes off, complete the flight maneuver according to the flight plan, and record the time information of each flight state;

[0026] Step three: after the airplane lands, turn off the data acquisition device, read the data and perform data analysis.

[0027] Further, in the step one, the first balance and the second balance have the same structure, and all the loads acting on the external cargo cabin are decomposed into the force and the moment acting on the center of the double-balance hanging measurement system, when the external cargo is loaded, the balance and the external cargo satisfy the balance equation, the deformation coordination equation and the constitutive equation, and thus the load distribution of the two balances is obtained;

[0028] When the external cargo cabin is subjected to the force through the center of the double-balance hanging measurement system, the first balance and the second balance have double bending deformation, the center of the first balance generates the force , the center of the second balance generates the force , the force and the force have the same size and direction, and do not generate the bending moment, and at this time:

[0029] ;

[0030] Wherein: is the force load of the external cargo cabin;

[0031] The front deflection of the first balance and the front deflection of the second balance have the same size and direction, the length of the first balance and the length of the second balance have the same size, and are denoted as , the elastic model of the material of the first balance and the elastic model of the material of the second balance have the same size, and are denoted as , the cross-sectional moment of inertia of the first balance and the cross-sectional moment of inertia of the second balance have the same size, and are denoted as :

[0032] ;

[0033] ;

[0034] The front cross-section rotation angle θ1 of the first balance and the front cross-section rotation angle θ2 of the second balance are the same, and at this time, both are 0;

[0035] When the external cargo cabin is subjected to the bending moment, the force and the force have the same size and opposite direction, according to the deformation coordination condition, the center of the first balance generates the moment M1, and the center of the second balance generates the moment M2, the moment M1 and the moment M2 have the same size and direction, and at this time:

[0036] Under the force and the force , the front deflection of the first balance and the front deflection of the second balance have the same size and opposite direction:

[0037] ;

[0038] ;

[0039] The front deflection of the first balance under the action of the moment M1 and the moment M2 and the front deflection of the second balance are equal in size and direction:

[0040] ;

[0041] ;

[0042] Under the action of the moment M1 and the moment M2:

[0043] ;

[0044] ;

[0045] According to the deformation compatibility relationship:

[0046] ;

[0047] ;

[0048] Wherein: is the front section rotation angle of the external cargo cabin section under the action of the bending moment;

[0049] L is the distance from the center of the first balance to the center of the second balance;

[0050] According to the force analysis:

[0051] ;

[0052] Wherein: is the moment load received by the external cargo cabin section;

[0053] is a small amount, and the solution is:

[0054] ;

[0055] ;

[0056] According to the deformation compatibility relationship and the force analysis, the moment distribution relationship is obtained:

[0057] .

[0058] Further, in step three, the output results of the first and second scales at any time during flight are taken as the final readings, the initial readings collected when the carrier is stationary on the ground and the scale formula obtained through calibration are calculated to obtain the output loads of the first and second scales at that time, denoted as Y1, MZ1, MX1, Z1, MY1 and Y2, MZ2, MX2, Z2, MY2, and the aerodynamic loads borne by the external object are obtained by operating the above loads;

[0059] The action point of the double-scale flight hanging measurement system is at the midpoint of the line connecting the centers of the first and second scales, and the loads of the first and second scales calculated are synthesized to the center of the double-scale flight hanging measurement system to obtain the load borne by the external object using the theoretical mechanics method:

[0060] Y=Y1+Y2;

[0061] Z=Z1+Z2;

[0062] ;

[0063] ;

[0064] MX=MX1+MX2;

[0065] Wherein:

[0066] Y is the lift load borne by the external object;

[0067] Y1 is the lift load output by the first scale;

[0068] Y2 is the lift load output by the second scale;

[0069] MZ is the pitch moment load borne by the external object;

[0070] MZ1 is the pitch moment load output by the first scale;

[0071] MZ2 is the pitch moment load output by the second scale;

[0072] MX is the roll moment load borne by the external object;

[0073] MX1 is the roll moment load output by the first scale;

[0074] MX2 is the roll moment load output by the second scale;

[0075] Z is the side force load borne by the external object;

[0076] Z1 is the side force load output by the first scale;

[0077] Z2 is the side force load output by the second scale;

[0078] MY is the yaw moment load received by the external object;

[0079] MY1 is the yaw moment load output by the first balance;

[0080] MY2 is the yaw moment load output by the second balance.

[0081] The beneficial effects of the present application are:

[0082] 1. The present application provides a hanging fixed cylinder front section and a hanging fixed cylinder rear section, by adjusting the diameter and wall thickness of the cylinder, adjusting the connection stiffness between the hanging fixed cylinder front section and the hanging fixed cylinder rear section, and making it consistent with the real structure.

[0083] 2. The load distribution of the front and rear hanging ears of the present application is consistent, which avoids fatigue fracture caused by local overload and improves the service life.

[0084] 3. The strength of the hanging ear in the present application is improved, the overload capacity is improved, the fracture is avoided, the fault tolerance is improved, the measurement error introduced by elastic deformation is reduced, and the risk of vibration and flutter is suppressed. BRIEF DESCRIPTION OF DRAWINGS

[0085] Figure 1 is a sectional view of the present application;

[0086] Figure 2 is a position relationship diagram of the first balance and the corrugated pipe in the present application;

[0087] Figure 3 is a position relationship diagram of the first balance rear hanging and the hanging ear in the present application;

[0088] Figure 4 is a position relationship diagram of the hanging fixed cylinder front section, the hanging fixed cylinder rear section and the second balance in the present application;

[0089] Figure 5 is a position relationship diagram of the hanging fixed cylinder front section and the hanging fixed cylinder rear section in the present application.

[0090] In the figure: 1-external object cabin section, 2-first balance, 3-second balance, 4-first balance front flange, 5-second balance front flange, 6-first balance rear hanging, 7-second balance rear hanging, 8-hanging fixed cylinder front section, 9-hanging fixed cylinder rear section, 10-first amplifier, 11-second amplifier, 12-data acquisition device, 13-side panel, 14-hanging ear, 15-corrugated pipe. DETAILED DESCRIPTION

[0091] In order to make the personnel in the technical field better understand the scheme of the present application, the technical scheme in the embodiments of the present application will be clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor should fall within the scope of protection of the present application.

[0092] The terms "arranged", "connected", and "fixed" should be interpreted in a broad manner. For example, "connected" can be fixed connection, detachable connection, or integral configuration; can be mechanical connection, direct connection, or indirect connection through an intermediate medium; or internal communication between two devices, elements, or components. Those of ordinary skill in the art can understand the specific meaning of the above terms in the present application according to the specific circumstances.

[0093] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0094] The preferred embodiments of the present application will be described in detail below with reference to the drawings.

[0095] Embodiment 1: Reference Figures 1 to 5 To describe this embodiment in detail, the double-balance flight test measurement system for external object flight force test in this embodiment includes an external object cabin section 1, a first balance 2, a second balance 3, a first balance front flange 4, a second balance front flange 5, a first balance rear hanger 6, a second balance rear hanger 7, a hanger fixed connection cylinder front section 8, a hanger fixed connection cylinder rear section 9, a first amplifier 10, a second amplifier 11, a data acquisition device 12, and a side panel 13.

[0096] The external object cabin section 1 is a hollow body of revolution, a first balance 2 is arranged in the front section of the external object cabin section 1, and a second balance 3 is arranged in the rear section of the external object cabin section 1.

[0097] A first balance front flange 4 is mounted on the front side of the first balance 2, a first balance rear hanger 6 is mounted on the rear side of the first balance 2, a second balance front flange 5 is mounted on the front side of the second balance 3, and a second balance rear hanger 7 is mounted on the rear side of the second balance 3.

[0098] The outer sides of the first balance front flange 4 and the second balance front flange 5 are fixed to the inner wall of the external object cabin section 1 through screws and pins, and the top ends of the first balance rear hanger 6 and the second balance rear hanger 7 extend out of the top of the external object cabin section 1.

[0099] The first balance rear hanger 6, the hanger fixed cylinder front section 8, the hanger fixed cylinder rear section 9 and the second balance rear hanger 7 are connected in sequence, the second balance front flange 5 is sleeved on the connection of the hanger fixed cylinder front section 8 and the hanger fixed cylinder rear section 9, and the hanger fixed cylinder rear section 9 is sleeved on the outside of the second balance 3, the local shape of the hanger fixed cylinder front section 8 and the hanger fixed cylinder rear section 9 is changed to avoid design, and a gap is left between the components to avoid interference on the measurement;

[0100] The first amplifier 10 is installed on the front side of the first balance front flange 4, and the second amplifier 11 is installed on the front side of the second balance front flange 5;

[0101] The data acquisition device 12 is installed on the front section support of the external cargo cabin section 1, and is connected with the first amplifier 10 and the second amplifier 11 respectively, used for receiving the balance signal amplified and transmitted by the first amplifier 10 and the second amplifier 11, and receiving the GPS signal through the connection with the carrier.

[0102] More specifically, the top end of the first balance rear hanger 6 and the second balance rear hanger 7 is provided with a hanger ear 14 connected with the hanger of the carrier.

[0103] More specifically, the external cargo cabin section 1 is provided with a side panel 13.

[0104] More specifically, the outside of the first balance 2 and the second balance 3 is welded with a corrugated pipe 15 to protect the measurement bridge on the balance element and increase the reliability of the balance.

[0105] The front and rear connecting surfaces of the first balance 2 and the second balance 3 are provided with key holes and threaded holes.

[0106] More specifically, the first balance 2 and the second balance 3 have the same structure, both are rod type five-component flight test balances, the first balance 2 and the second balance 3 are coaxial and the axis is coincident with the axis of the external cargo cabin section 1.

[0107] More specifically, the measurement principle of the rod type five-component flight test balance is basically the same as the commonly used rod type strain balance in wind tunnel test, that is, the balance element produces deformation under the action of aerodynamic load, the strain is proportional to the size of the external force, at the same time, the strain gauge pasted on the surface of the balance element also produces deformation, so that the resistance value changes and produces increment, this increment is converted into voltage increment by the full bridge circuit composed of the strain gauge, and the voltage increment value is proportional to the aerodynamic load value of the balance, and the air power and torque can be obtained by using computer processing.

[0108] The balance element is a single column beam, capable of measuring five directions of load of the balance, including lift, pitch moment, side force, yaw moment and roll moment, large size strain gauges are pasted on the balance element to improve the stability of the bridge, multiple groups of standby bridges are arranged to deal with faults caused by severe working conditions in flight test, and the surface of the strain gauge is sealed with glue.

[0109] Embodiment 2: A double-balance hanging flight measurement method for external hanging flight force test, which adopts the double-balance hanging flight measurement system for external hanging flight force test as described in Embodiment 1, specifically:

[0110] Step one: turn on the data acquisition device 12, establish the connection between the data acquisition device 12 and the airborne device, calibrate the time signal and the position signal, and record the signals of the first balance 2 and the second balance 3;

[0111] Step two: complete the flight maneuver according to the flight plan after the airplane takes off, and record the time information of each flight state;

[0112] Step three: after the airplane lands, turn off the data acquisition device 12, read the data and analyze the data.

[0113] More specifically: in the step one, the first balance 2 and the second balance 3 have the same structure, and the external hanging cabin section 1 is relatively strong in rigidity and does not displace by default, a calculation model of “external hanging object-balance” is established, at this time all the loads acting on the external hanging cabin section 1 are decomposed into forces and moments acting on the center position of the double-balance hanging flight measurement system, when the external hanging object is loaded, the balance and the external hanging object need to satisfy the balance equation, the deformation coordination equation and the constitutive equation, thereby obtaining the load distribution of the two balances;

[0114] When the external hanging cabin section 1 is subjected to the force through the center position of the double-balance hanging flight measurement system, the first balance 2 and the second balance 3 both occur double-bending deformation, the center position of the first balance 2 generates force , the center position of the second balance 3 generates force , the forces and are equal in size and direction, and do not produce bending moment, at this time:

[0115] ;

[0116] Wherein: is the force load received by the external hanging cabin section 1;

[0117] The front deflection of the first balance 2 and the front deflection of the second balance 3 are equal in size and direction, the length of the first balance 2 and the length of the second balance 3 are equal in size, and are recorded as , the elastic model of the material of the first balance 2 and the elastic model of the material of the second balance 3 are equal in size, denoted as , the cross-sectional moment of inertia of the first balance 2 and the cross-sectional moment of inertia of the second balance 3 are equal in size, denoted as :

[0118] ;

[0119] ;

[0120] The front end cross-sectional rotation angle θ1 of the first balance 2 and the front end cross-sectional rotation angle θ2 of the second balance 3 are the same, which are both 0 at this time;

[0121] When the external cargo cabin section 1 is subjected to a bending moment, the force and the force are equal in size and opposite in direction, according to the deformation compatibility condition, the center position of the first balance 2 generates a moment M1, and the center position of the second balance 3 generates a moment M2, the moments M1 and M2 are equal in size and same in direction, at this time:

[0122] Under the action of the force and the force , the front end deflection of the first balance 2 and the front end deflection of the second balance 3 are equal in size and opposite in direction:

[0123] ;

[0124] ;

[0125] Under the action of the moment M1 and the moment M2, the front end deflection of the first balance 2 and the front end deflection of the second balance 3 are equal in size and same in direction:

[0126] ;

[0127] ;

[0128] Under the action of the moment M1 and the moment M2:

[0129] ;

[0130] ;

[0131] According to the deformation compatibility relationship:

[0132] ;

[0133] ;

[0134] wherein: is the front end section rotation angle of the external cargo cabin section 1 caused by the bending moment;

[0135] L is the distance from the center of the first balance 2 to the center of the second balance 3;

[0136] According to the force analysis:

[0137] ;

[0138] wherein: is the moment load received by the external cargo cabin section 1;

[0139] is a small amount, and is solved as:

[0140] ;

[0141] ;

[0142] According to the deformation coordination relationship and the force analysis, the moment distribution relationship is obtained:

[0143] ;

[0144] The above calculation process is the load distribution principle of the first balance 2 and the second balance 3 when the external cargo cabin section 1 is loaded. The load distribution of the first balance 2 and the second balance 3 is obtained through the estimated aerodynamic load of the external cargo, which is used as the basis for balance design.

[0145] More specifically: in step three, the output results of the first balance 2 and the second balance 3 at any time during flight are taken as the final readings, and the initial readings collected when the carrier is stationary on the ground and the balance formula obtained through calibration are calculated to obtain the output load of the first balance 2 and the second balance 3 at that time, which is recorded as Y1, MZ1, MX1, Z1, MY1 and Y2, MZ2, MX2, Z2, MY2. The aerodynamic load received by the external cargo is obtained by operating the above load;

[0146] The action point of the double-balance hanging flight measurement system is at the midpoint of the line connecting the center of the first balance 2 and the center of the second balance 3. Using the theoretical mechanics method, the loads of the first balance 2 and the second balance 3 calculated are combined to the center of the double-balance hanging flight measurement system to obtain the load received by the external cargo:

[0147] Y=Y1+Y2;

[0148] Z=Z1+Z2;

[0149] ;

[0150] ;

[0151] MX = MX1 + MX2;

[0152] wherein:

[0153] Y is the lift force load experienced by the store;

[0154] Y1 is the lift force load output by the first balance 2;

[0155] Y2 is the lift force load output by the second balance 3;

[0156] MZ is the pitch moment load experienced by the store;

[0157] MZ1 is the pitch moment load output by the first balance 2;

[0158] MZ2 is the pitch moment load output by the second balance 3;

[0159] MX is the roll moment load experienced by the store;

[0160] MX1 is the roll moment load output by the first balance 2;

[0161] MX2 is the roll moment load output by the second balance 3;

[0162] Z is the side force load experienced by the store;

[0163] Z1 is the side force load output by the first balance 2;

[0164] Z2 is the side force load output by the second balance 3;

[0165] MY is the yaw moment load experienced by the store;

[0166] MY1 is the yaw moment load output by the first balance 2;

[0167] MY2 is the yaw moment load output by the second balance 3.

[0168] More specifically: the store cabin section 1 is processed using high-strength alloy materials, and is designed into multiple cabin sections for the convenience of arranging components inside, and a stop connection is designed between each cabin section, and is fixed using nails and pins. The shape of the store cabin section 1 is completely consistent with the real store, and the interface for data interaction with the carrier is reserved in the original size.

[0169] More specifically: the installation process of the double-balance store flight measurement system is as follows:

[0170] Step one: after the first and second scales 2 and 3 are calibrated, the corrugated pipe 15 is welded, the first and second scale front flanges 4 and 5 and the first and second scale rear hangers 6 and 7 are installed before and after the first and second scales 2 and 3, and end face keys are used for limiting and screws are tightened during installation;

[0171] Step two: the first and second amplifiers 10 and 11 are installed before the first and second scale front flanges 4 and 5, and the first and second scales 2 and 3 are connected with the first and second amplifiers 10 and 11 respectively;

[0172] Step three: the hanger fixed cylinder front section 8 is installed between the first scale rear hanger 6 and the second scale front flange 5, and the hanger fixed cylinder rear section 9 is installed outside the second scale 3;

[0173] Step four: the first and second scales 2 and 3 are installed in the external payload cabin section 1, the top ends of the first and second scale rear hangers 6 and 7 are extended from the reserved cavity of the external payload cabin section 1, and the outer sides of the first and second scale front flanges 4 and 5 are fixed with the inner wall of the external payload cabin section 1 using screws and pins;

[0174] Step five: the data acquisition device 12 is installed and connected with the first and second amplifiers 10 and 11;

[0175] Step six: the counterweight is installed outside the double scale flight measurement system, the weight and other parameters of the double scale flight measurement system are adjusted, and corresponding structures are installed before and after and outside the external payload cabin section 1 to make it consistent with the real external payload;

[0176] Step seven: the double scale flight measurement system is assembled, calibrated, ground tested, and used for subsequent flight tasks.

[0177] More specifically, before the flight test, the double scale flight measurement system needs to be tested on the ground in a series of tests to verify the structural reliability and measurement accuracy of the double scale flight measurement system by simulating the loading, impact, vibration, and temperature changes during flight. The tests to be performed are as follows:

[0178] Test one: loading accuracy test: the double scale flight measurement system is fixed in a simulated real state, loads are applied to its surface through hangers and weights, and the accuracy of load calculation in each direction is verified;

[0179] Test two: vibration and temperature test: the double scale flight measurement system is fixed on the corresponding test bench, vibration excitation and temperature changes are applied, and the influence of vibration and temperature conditions on the reliability of the system is verified;

[0180] Test three: strength test experiment: install the double-pan balance flight measurement system on the strength test experiment mechanism, apply the maximum impact load on the outer hanging cabin section 1, and verify the strength of the structure.

[0181] More specifically: when the double-pan balance flight measurement system is loaded for testing on the ground (weights are hung at different positions in front of and behind the outer hanging cabin section 1 to simulate the loading of the outer hanging object), the results measured by the double-pan balance flight measurement system are as follows:

[0182] A: the loading results in the lift direction are as follows:

[0183] A1: the loading position, that is, the distance between the center of the first balance 2 and the center of the second balance 3 is 800 mm, the weight of the hung weight is 280 kg, the theoretical lift is -2745.0 N, the theoretical pitch moment is -2196.0 N·m, the calculated lift is -2748.4 N, the calculated pitch moment is -2178.6 N·m, the lift accuracy is 0.1%, and the pitch moment accuracy is -0.8%;

[0184] A2: the loading position, that is, the distance between the center of the first balance 2 and the center of the second balance 3 is 800 mm, the weight of the hung weight is 120 kg, the theoretical lift is -1176.4 N, the theoretical pitch moment is -941.1 N·m, the calculated lift is -1172.5 N, the calculated pitch moment is -934.7 N·m, the lift accuracy is -0.3%, and the pitch moment accuracy is -0.6%;

[0185] A3: the loading position, that is, the distance between the center of the first balance 2 and the center of the second balance 3 is -700 mm, the weight of the hung weight is 280 kg, the theoretical lift is -2745.0 N, the theoretical pitch moment is 1921.5 N·m, the calculated lift is -2756.7 N, the calculated pitch moment is 1924.1 N·m, the lift accuracy is 0.4%, and the pitch moment accuracy is 0.1%;

[0186] A4: the loading position, that is, the distance between the center of the first balance 2 and the center of the second balance 3 is -700 mm, the weight of the hung weight is 120 kg, the theoretical lift is -1176.4 N, the theoretical pitch moment is 823.5 N·m, the calculated lift is -1173.7 N, the calculated pitch moment is 817.4 N·m, the lift accuracy is -0.2%, and the pitch moment accuracy is -0.7%;

[0187] B: the loading results in the side force direction are as follows:

[0188] B1: loading position, i.e. the distance between the center of the first balance 2 and the center of the second balance 3 is 800mm, the weight of the mounted weight is 280kg, the theoretical side force is -2745.0N, the theoretical yaw moment is 2196.0N.m, the calculated result of the side force is -2752.8N, the calculated result of the yaw moment is 2213.4N.m, the accuracy of the side force is 0.3%, and the accuracy of the yaw moment is 0.8%;

[0189] B2: loading position, i.e. the distance between the center of the first balance 2 and the center of the second balance 3 is 800mm, the weight of the mounted weight is 120kg, the theoretical side force is -1176.4N, the theoretical yaw moment is 941.1N.m, the calculated result of the side force is -1183.3N, the calculated result of the yaw moment is 947.2N.m, the accuracy of the side force is 0.6%, and the accuracy of the yaw moment is 0.6%;

[0190] B3: loading position, i.e. the distance between the center of the first balance 2 and the center of the second balance 3 is -700mm, the weight of the mounted weight is 280kg, the theoretical side force is -2745.0N, the theoretical yaw moment is -1921.5N.m, the calculated result of the side force is -2737.6N, the calculated result of the yaw moment is -1925.1N.m, the accuracy of the side force is -0.3%, and the accuracy of the yaw moment is 0.2%;

[0191] B4: loading position, i.e. the distance between the center of the first balance 2 and the center of the second balance 3 is -700mm, the weight of the mounted weight is 120kg, the theoretical side force is -1176.4N, the theoretical yaw moment is -823.5N.m, the calculated result of the side force is -1180.8N, the calculated result of the yaw moment is -828.2N.m, the accuracy of the side force is 0.4%, and the accuracy of the yaw moment is 0.6%.

[0192] Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present application, and are not intended to limit the same; although the present application has been described in detail with reference to the foregoing examples, the technical solutions described in the foregoing examples can be modified, or some or all of the technical features thereof can be replaced by equivalents; as long as there is no structural conflict, each feature in the specific embodiments disclosed in the present application can be used in any way, and the corresponding technical solutions will not deviate from the scope of the technical solutions of the present application.

[0193] In addition, it should be understood that although the present specification is described in terms of embodiments, each embodiment does not contain only one independent technical solution, and the description of the specification is only for the sake of clarity, and those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that those skilled in the art can understand.

Claims

1. A dual balance flight test measurement system for flight force testing of an external object, characterized in that, The external object cabin section (1), the first balance (2), the second balance (3), the first balance front flange (4), the second balance front flange (5), the first balance rear hanger (6), the second balance rear hanger (7), the hanger fixed connection cylinder front section (8), the hanger fixed connection cylinder rear section (9), the first amplifier (10), the second amplifier (11), the data acquisition device (12), the side panel (13); The external object cabin section (1) is a hollow body of revolution, and the first balance (2) is arranged in the front section of the external object cabin section (1), and the second balance (3) is arranged in the rear section of the external object cabin section (1); The first balance (2) is provided with the first balance front flange (4) on the front side, and the first balance rear hanger (6) is arranged on the rear side of the first balance (2); the second balance (3) is provided with the second balance front flange (5) on the front side, and the second balance rear hanger (7) is arranged on the rear side of the second balance (3); The first balance front flange (4) and the second balance front flange (5) are fixed to the inner wall of the external object cabin section (1), and the top ends of the first balance rear hanger (6) and the second balance rear hanger (7) are arranged to extend out of the top of the external object cabin section (1); The first balance rear hanger (6), the hanger fixed connection cylinder front section (8), the hanger fixed connection cylinder rear section (9) and the second balance rear hanger (7) are sequentially connected, the second balance front flange (5) is sleeved on the connection between the hanger fixed connection cylinder front section (8) and the hanger fixed connection cylinder rear section (9), and the hanger fixed connection cylinder rear section (9) is sleeved on the outer side of the second balance (3); The first balance front flange (4) is provided with the first amplifier (10) on the front side, and the second amplifier (11) is arranged on the front side of the second balance front flange (5); The data acquisition device (12) is arranged on the front section support of the external object cabin section (1), and is connected with the first amplifier (10) and the second amplifier (11) respectively, and is used for receiving the balance signal amplified and transmitted by the first amplifier (10) and the second amplifier (11).

2. The dual balance flight test measurement system for external store flight force test according to claim 1, characterized in that, The top ends of the first balance rear hanger (6) and the second balance rear hanger (7) are provided with hanger ears (14) connected with the hanger of the carrier aircraft.

3. The dual balance flight test system for external store flight force testing of claim 1, wherein, The external object cabin section (1) is provided with a side panel (13).

4. The dual balance flight test measurement system for external store flight force test according to claim 1, characterized in that, The outer sides of the first balance (2) and the second balance (3) are welded with corrugated pipes (15); Key holes and threaded holes are arranged on the front and rear connecting surfaces of the first balance (2) and the second balance (3).

5. The dual balance flight test measurement system for external store flight force test according to claim 1, characterized in that, The first balance (2) and the second balance (3) have the same structure, and are both rod type five-component hanging flight test balances, and the first balance (2) and the second balance (3) are coaxial and have the same axis as the external object cabin section (1).

6. A double balance flying measurement method for external store flight force test, using the double balance flying measurement system for external store flight force test according to claim 1, characterized in that, Specifically, Step one: turn on the data acquisition device (12), establish the connection between the data acquisition device (12) and the airborne equipment, calibrate the time signal and the position signal, and record the signals of the first balance (2) and the second balance (3); Step two: after the aircraft takes off, complete the flight operation according to the flight plan, and record the time information of each flight state; Step three: after the plane lands, turn off the data acquisition device (12), read the data and analyze the data.

7. The double balance flying measurement method for the external object flight force test according to claim 6, characterized in that, In the step one, the first balance (2) and the second balance (3) have the same structure, at this time, all the loads acting on the external cargo cabin section (1) are decomposed into forces and moments acting on the center of the double-balance hanging flight measurement system, when the external cargo is loaded, the balance and the external cargo satisfy the balance equation, the deformation compatibility equation and the constitutive equation, thus the load distribution of the two balances is obtained; When the external object cabin section (1) is subjected to force through the center position of the double-pan balance flight measurement system, the first balance (2) and the second balance (3) both occur double bending deformation, the center position of the first balance (2) generates force , the center position of the second balance (3) generates force , the size of force and force are equal and the directions are the same, no bending moment is generated, at this time: ； wherein: The forces to which the external pod section (1) is subjected are combined. The front end deflection of the first balance (2) The front end deflection of the second balance (3) The length of the first balance (2) and the length of the second balance (3) are equal in size and direction, denoted as The elastic model of the material of the first balance (2) and the elastic model of the material of the second balance (3) are equal in size, denoted as The cross-sectional moment of inertia of the first balance (2) and the cross-sectional moment of inertia of the second balance (3) are equal in size, denoted as : ； ； The front end section rotation angle θ1 of the first balance (2) and the front end section rotation angle θ2 of the second balance (3) are the same, at this time, they are both 0; When the outer hanger cabin section (1) is subjected to bending moment, the force and the force are equal in size and opposite in direction. According to the deformation compatibility condition, the center position of the first balance (2) generates a moment M1, and the center position of the second balance (3) generates a moment M2. The moments M1 and M2 are equal in size and same in direction. At this time: Under the action of force and force the deflection of the front end of the first balance (2) and the deflection of the front end of the second balance (3) are equal in size and opposite in direction: ； ； Under the action of the moment M1 and the moment M2, the front end deflection of the first balance (2) and the front end deflection of the second balance (3) are equal in size and same in direction: ； ； Under the action of the moment M1 and the moment M2: ； ； According to the deformation compatibility relationship: ； ； wherein: is the front end section rotation angle of the external pod section (1) under the action of the bending moment; L is the distance from the center of the first balance (2) to the center of the second balance (3); According to the force analysis: ； wherein: is the moment load to which the external pod section (1) is subjected; For small quantities, we find: ； ； According to the deformation compatibility relationship and the force analysis, the moment distribution relationship is obtained: 。 8. The dual balance flight measurement method for flight force test of external object according to claim 6, characterized in that, In the step three, the output results of the first balance (2) and the second balance (3) at any time during the flight are taken as the final readings, the initial readings collected when the carrier is stationary on the ground and the balance formula obtained through calibration are calculated to obtain the output loads of the first balance (2) and the second balance (3) at that time, which are recorded as Y1, MZ1, MX1, Z1, MY1 and Y2, MZ2, MX2, Z2, MY2, and the aerodynamic loads received by the external cargo are obtained by operating the above loads; The action point of the double-balance hanging flight measurement system is at the midpoint of the line connecting the center of the first balance (2) and the center of the second balance (3), using the theoretical mechanics method, the loads of the first balance (2) and the second balance (3) calculated are combined to the center of the double-balance hanging flight measurement system to obtain the loading condition of the external cargo: Y=Y1+Y2; Z=Z1+Z2; ； ； MX=MX1+MX2; Wherein: Y is the lift load received by the external cargo; Y1 is the lift load output by the first balance (2); Y2 is the lift load output by the second balance (3); MZ is the pitching moment load received by the external cargo; MZ1 is the pitching moment load output by the first balance (2); MZ2 is the pitching moment load output by the second balance (3); MX is the rolling moment load received by the external cargo; MX1 is the rolling moment load output by the first balance (2); MX2 is the rolling moment load output by the second balance (3); Z is the side force load received by the external cargo; Z1 is the side force load output by the first balance (2); Z2 is the side force load output by the second balance (3); MY is the yawing moment load received by the external cargo; MY1 is the yawing moment load output by the first balance (2); MY2 is the yawing moment load output by the second balance (3).

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