CN113567083A - Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter - Google Patents
Multi-component aerodynamic interference characteristic test simulation method for full-motion horizontal tail helicopter Download PDFInfo
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Abstract
The invention discloses a multi-component aerodynamic interference characteristic test simulation method of a full-dynamic horizontal tail helicopter, which is characterized in that rotor wing aerodynamic load test data of the helicopter in a coaxial system, fuselage aerodynamic load test data of the helicopter in the coaxial system and full-dynamic horizontal tail aerodynamic load test data are obtained based on a wind tunnel test bench test of a rotor wing and fuselage combined model; analyzing by using an interference characteristic model according to rotor wing pneumatic load test data, fuselage pneumatic load test data and full-dynamic horizontal tail pneumatic load test data to obtain the pneumatic interference characteristics among all parts of the helicopter; the method can accurately acquire the aerodynamic interference law among the rotor, the fuselage and the full-motion horizontal tail, and provides important basis for the design of the aerodynamic components, layout optimization and the design of the flight control law of the helicopter.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests, in particular to a multi-component aerodynamic disturbance characteristic test simulation method of a full-motion horizontal tail helicopter.
Background
Helicopters, due to the complexity of their aerodynamic layout, have a number of aerodynamic components including rotors, fuselage and vertical tail. Under the conditions of hovering, climbing, flying ahead, descending and the like of the helicopter, due to the change of flight attitude and speed, pneumatic interference of different degrees exists in each pneumatic component, and great influence is generated on the flight performance, flight characteristics and flight quality of the helicopter. Among them, the horizontal tail has an important influence on the aerodynamic characteristics and the control stability of the helicopter as one of the important components for adjusting the flight attitude of the helicopter. Especially for the full-motion horizontal tail with a large area, when the full-motion horizontal tail flies before hovering and at a low speed, the influence of the rotor wake is large, the lift coefficient is suddenly changed, the pitching moment of the helicopter body is suddenly increased, and the control stability and the safety of the helicopter are seriously reduced. Therefore, the aerodynamic interference law among the rotor, the fuselage and the horizontal tail must be accurately acquired, reference basis is provided for the design and optimization of each aerodynamic component, and the longitudinal static stability of the helicopter is further improved.
The wind tunnel test of the helicopter is one of important means for developing the research on the aerodynamic characteristics of the helicopter. Aerodynamic interference characteristics among the various aerodynamic components can be obtained by measuring aerodynamic forces of the various independent aerodynamic components of the helicopter and the combined test model under different incoming flows, wherein the aerodynamic interference characteristics comprise weight increment of a fuselage caused by rotor wake flow when the helicopter hovers and flies forward at a low speed, the influence of the fuselage on the performance of the rotor and the influence of the rotor wake flow on the full-motion horizontal tail aerodynamic performance.
Disclosure of Invention
A method for simulating a multi-component aerodynamic interference characteristic test of a full-motion horizontal tail helicopter can accurately acquire an aerodynamic interference rule among a rotor wing, a helicopter body and the full-motion horizontal tail, and provides powerful wind tunnel test data support for design, layout optimization and flight control rule design of aerodynamic components of the helicopter.
The invention is realized by the following technical scheme:
a multi-component aerodynamic interference characteristic test simulation method of a full-motion horizontal tail helicopter is realized based on a wind tunnel test bed of a rotor and fuselage combined model, and comprises the following steps: the system comprises a rotor wing balance and a torque balance for measuring the aerodynamic load of a rotor wing, a fuselage balance for measuring the aerodynamic load of a fuselage, and a horizontal tail balance for measuring the full-motion horizontal tail load;
s1, acquiring rotor wing pneumatic load test data of the helicopter under the coaxial system based on a rotor wing and fuselage combined model wind tunnel test bench test, and fuselage pneumatic load test data and full-dynamic horizontal tail pneumatic load test data of the helicopter under the coaxial system, and the method specifically comprises the following steps:
step 1, carrying out a single rotor model hovering test on the basis of a rotor and fuselage combined model wind tunnel test bed, and obtaining rotor aerodynamic load R1 during hovering;
and S2, carrying out aerodynamic interference characteristic analysis by using an interference characteristic model according to the rotor wing aerodynamic load test data, the fuselage aerodynamic load test data and the full-dynamic horizontal tail aerodynamic load test data to obtain aerodynamic interference characteristics among all parts of the helicopter.
The single rotor model hover test: develop in the experimental room that hovers for measure the aerodynamic characteristic of individual rotor under the state of hovering, the manipulated variable includes rotor speed, rotor collective pitch, mainly used obtains the aerodynamic load when individual rotor suspends.
The rotor and fuselage combined model hovering test: the method is developed in a hovering test room and used for measuring the aerodynamic characteristics of a rotor and a fuselage in a hovering state, and the manipulated variables comprise the rotating speed of the rotor and the total distance of the rotor and are mainly used for acquiring the aerodynamic loads of the fuselage and a horizontal tail when the rotor is suspended in a combined state of the rotor and the fuselage.
The independent fuselage model forward flight test: the device is developed in a wind tunnel and used for measuring the aerodynamic characteristics of an independent machine body in a forward flight state, the manipulated variables comprise incoming flow wind speed, a machine body attack angle, a machine body sideslip angle and a horizontal tail installation angle, and the device is mainly used for measuring the aerodynamic loads of the machine body and the horizontal tail of the independent machine body in the forward flight state.
The single rotor model forward flight test: the method is developed in a wind tunnel and used for measuring the aerodynamic characteristics of the single rotor in the forward flight state, the manipulated variables comprise incoming flow wind speed, rotor shaft inclination angle, rotor rotating speed, rotor total pitch and periodic pitch angle, and the method is mainly used for measuring the aerodynamic load of the single rotor in the forward flight state.
The rotor and fuselage combined model is subjected to forward flight test: the method is developed in a wind tunnel and used for measuring the aerodynamic characteristics of a rotor and a fuselage in a forward flight state, the manipulated variables comprise incoming flow wind speed, rotor shaft inclination angle, rotor rotating speed, rotor total pitch, rotor periodic pitch, fuselage attack angle, fuselage sideslip angle and horizontal tail installation angle, and the method is mainly used for measuring the aerodynamic loads of the rotor, the fuselage and the horizontal tail of a rotor and fuselage combined model in the forward flight state.
The further optimization scheme is that the test states of the independent rotor model hovering test in the step 1 and the rotor and fuselage combined model hovering test in the step 2 are the same, and the test is carried out in a mode of fixing the rotating speed and changing the total distance of the rotors.
The further optimization scheme is that the balancing strategies of the forward flight test of the single rotor wing model in the step 4 and the forward flight test of the rotor wing and fuselage combined model in the step 5 adopt fixed vertical force coefficient balancing.
The further optimization scheme is that the fixed vertical force coefficient balancing process of the independent rotor model forward flight test and the rotor and fuselage combined model forward flight test is as follows: under the condition of a given main shaft inclination angle, a given fuselage attitude, a given wind speed and a given rotor wing rotating speed, the required vertical force coefficient is balanced by controlling the rotor wing collective pitch; and in the balancing process, the pitch variation of the rotor wing is controlled to enable the pitching moment and the rolling moment of the hub to be less than 20 N.m, and after the hub is balanced to a specified test value and is stable, the pitching moment and the rolling moment of the hub are less than or equal to 3 N.m.
The further optimization scheme is that the rotor wing aerodynamic load test data comprises: rotor aerodynamic loads R1 during suspension, rotor aerodynamic loads R2 in a rotor and fuselage combined model during hovering, rotor aerodynamic loads R3 during forward flight and rotor aerodynamic loads R4 during forward flight; the rotor wing aerodynamic load test data are obtained by firstly converting the rotor wing model aerodynamic load coefficient to the center of gravity of the helicopter in a unified way and then carrying out normalization processing;
the aerodynamic loading test data of the fuselage include: hovering time body pneumatic load F1, front flying time body pneumatic load F2 and front flying time body pneumatic load F3; the test data of the aerodynamic load of the helicopter body are obtained by uniformly converting the aerodynamic load coefficient of the helicopter body model to the center of gravity of the helicopter and then carrying out normalization treatment;
the full-dynamic horizontal tail pneumatic load test data comprises the following steps: the system comprises a suspension full-motion horizontal tail pneumatic load H1, a front flying full-motion horizontal tail pneumatic load H2 and a front flying full-motion horizontal tail pneumatic load H3; the full-dynamic horizontal tail pneumatic load test data are obtained by firstly converting the full-dynamic horizontal tail pneumatic load coefficient to the center of gravity of the helicopter in a unified mode and then performing normalization processing.
The further optimization scheme is that the rotor wing aerodynamic load test data is given by a propeller hub wind shaft system, the fuselage aerodynamic load test data is given by a fuselage wind shaft system, and the full-dynamic horizontal tail aerodynamic load test data is given by the fuselage wind shaft system.
The further optimization scheme is that the rotor aerodynamic load test data normalization processing uses a rotor model reference force F01 and a rotor model reference moment M01 as normalization factors, wherein:
in the formula (I), the compound is shown in the specification,
is at atmospheric density,
Is the speed of the rotor wing tip,
The rotor wing is the area of a rotor wing disc, and R is the radius of the rotor wing;
the method is characterized in that the normalization factors of the airframe model reference force F02 and the airframe model reference moment M02 are used in the normalization processing of the airframe pneumatic load test data and the full-dynamic horizontal tail pneumatic load test data, wherein:
in the formula (I), the compound is shown in the specification,
in order to be at the density of the atmosphere,
in order to obtain the speed of the incoming wind,
the resistance area of the machine body is the resistance area,
is the fuselage model length.
The further optimization scheme is that the original point of the wind axis system of the propeller hub is the center of the propeller hub model, the X axis of the wind axis system of the propeller hub is positive along the incoming flow direction, the Y axis of the wind axis system of the propeller hub is positive perpendicular to the incoming flow direction, and the Z axis of the wind axis system of the propeller hub is determined according to a right-hand rule;
the original point of a wind axis system of the machine body is the center of a balance of the machine body, the X axis is positive along the incoming flow direction, the Y axis is positive in the direction perpendicular to the incoming flow direction, and the Z axis is determined according to the right-hand rule.
The further optimization scheme is that the specific process of S2 is as follows:
t1, by interference characteristic model: rotor wing aerodynamic load R2-rotor wing aerodynamic load R1 in the rotor wing and fuselage combined model during hovering, and the interference characteristic of the fuselage to rotor wing wake flow during hovering is obtained;
t2, constructing a graph of rotor aerodynamic load R2 and body aerodynamic load F1 in a rotor and fuselage combination model during hovering, analyzing the relation of the change of the fuselage load along with the rotor load under the effect of rotor wake flow, and obtaining the interference characteristic of the rotor wake flow on the fuselage; constructing a curve graph of rotor wing aerodynamic load R2 and full-motion horizontal tail aerodynamic load H1 in a rotor wing and fuselage combined model during hovering, and analyzing the relation of the full-motion horizontal tail load changing along with the rotor wing load under the effect of rotor wing wake flow, thereby obtaining the interference characteristic of the rotor wing wake flow on the full-motion horizontal tail;
t3, by interference characteristic model: the method comprises the following steps of obtaining the interference characteristic of rotor wake on a fuselage in a front flying state through a front flying time body aerodynamic load F3-a front flying time body aerodynamic load F2, and through an interference characteristic model: the method comprises the steps that a front-flying full-motion horizontal tail pneumatic load H3-a front-flying full-motion horizontal tail pneumatic load H2 is used for obtaining the interference characteristic of rotor wake on a full-motion horizontal tail in a front-flying state;
t4, by interference characteristic model: and the interference characteristic of the fuselage to the rotor wake in the forward flight state is obtained by the rotor aerodynamic load R4-the rotor aerodynamic load R3 in the forward flight state.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the invention provides a multi-component aerodynamic interference characteristic test simulation method of a full-motion horizontal tail helicopter, which can carry out an independent rotor model hovering test, a rotor and fuselage combined model hovering test, an independent fuselage model forward flight test, an independent rotor model forward flight test and a rotor and fuselage combined model forward flight test on the basis of a rotor and fuselage combined model wind tunnel test stand; the method has the advantages that the aerodynamic load test data of each part of the helicopter in different test states are obtained, the aerodynamic interference influence law among all parts of the helicopter is really and efficiently obtained according to the interference characteristic model, the aerodynamic interference law among the rotor, the helicopter body and the full-motion horizontal tail can be accurately obtained, and important basis is provided for the design of the aerodynamic parts, layout optimization and flight control law of the helicopter.
2. The invention provides a multi-component aerodynamic interference characteristic test simulation method of a full-motion horizontal tail helicopter, which mainly considers the interference characteristic of a fuselage to rotor wake under a forward flight state or a hovering state, and considers the fuselage and the full-motion horizontal tail as a whole, so that the interference characteristic of the full-motion horizontal tail to the rotor wake is superposed to the interference characteristic of the fuselage to the rotor wake, and unnecessary test processes are reduced on the premise of ensuring the test to be real and effective.
Drawings
In order to more clearly illustrate the technical solutions of the exemplary embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and that for those skilled in the art, other related drawings can be obtained from these drawings without inventive effort. In the drawings:
FIG. 1 is a schematic flow chart of a multi-component aerodynamic disturbance characteristic test simulation method of a full-motion horizontal tail helicopter;
FIG. 2 is a schematic view of a forward flight test flow of a rotor and fuselage combined model;
FIG. 3 is a schematic diagram of an experimental model and an apparatus according to an embodiment.
1-rotor model; 2-fuselage model; 3-a rotor balance; 4-torque balance; 5-a test bed; 6-fuselage balance; 7-full-motion horizontal tail model; 8-horizontal tail balance.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
The embodiment provides a method for simulating a multi-component aerodynamic interference characteristic test of a full-motion horizontal tail helicopter, based on a wind tunnel test bed of a rotor and fuselage combined model, a measurement system of the wind tunnel test bed of the rotor and fuselage combined model comprises a rotor balance 3, a torque balance 4, a fuselage balance 6 and a horizontal tail balance 8, test contents comprise an independent rotor model test, an independent fuselage model test and a rotor and fuselage combined model test, and as shown in fig. 1, the method specifically comprises the following steps:
step 1, carrying out a single rotor model hovering test on the basis of a rotor and fuselage combined model wind tunnel test bed, and obtaining rotor aerodynamic load R1 during hovering;
and 5, carrying out a forward flight test of the rotor and fuselage combined model based on the rotor and fuselage combined model wind tunnel test stand to obtain a rotor aerodynamic load R4 during forward flight, a fuselage aerodynamic load F3 during forward flight and a full-motion horizontal tail aerodynamic load H3 during forward flight.
After the aerodynamic load test data of each part are obtained according to the steps, the aerodynamic interference characteristic of the rotor wing and the airframe is obtained through the following method:
(1) the interference characteristic of the aircraft body to the rotor wake flow in the hovering state can be obtained through the rotor aerodynamic load R2 in the rotor and aircraft body combined model when the interference characteristic model hovers-the rotor aerodynamic load R1 when the aircraft body hovers;
(2) by constructing a curve graph of rotor aerodynamic load R2 in a rotor and fuselage combined model during hovering and body aerodynamic load F1 during hovering, analyzing the relation of the fuselage load changing along with the rotor load under the effect of rotor wake, and obtaining the interference characteristic of the rotor wake on the fuselage; constructing a curve graph of rotor wing aerodynamic load R2 and full-motion horizontal tail aerodynamic load H1 in a rotor wing and fuselage combined model during hovering, and analyzing the relation of the full-motion horizontal tail load changing along with the rotor wing load under the effect of rotor wing wake flow, thereby obtaining the interference characteristic of the rotor wing wake flow on the full-motion horizontal tail;
(3) acquiring the interference characteristic of rotor wake on the fuselage in a forward flight state through an interference characteristic model forward flight time body aerodynamic load F3-forward flight time body aerodynamic load F2; acquiring the interference characteristic of rotor wake on the full-motion horizontal tail in the forward flight state through an interference characteristic model forward flight full-motion horizontal tail pneumatic load H3-forward flight full-motion horizontal tail pneumatic load H2;
(4) the interference characteristic of the fuselage to the rotor wake in the forward flight state can be obtained through the forward flight rotor aerodynamic load R4-the forward flight rotor aerodynamic load R3.
The single rotor model hovering test and the rotor and fuselage combined model hovering test are usually tested in a mode of fixing the rotating speed and changing the total distance of the rotors, the test states are basically the same, the rotor wing balance and the torque balance are mainly used for measuring the rotor wing aerodynamic load and the rotor wing power respectively in the test process, and the fuselage balance and the horizontal tail balance are used for measuring the fuselage aerodynamic load and the full-motion horizontal tail aerodynamic load respectively; the independent machine body test mode is that under the condition of setting the main shaft inclination angle, the machine body posture, the wind speed and the propeller hub rotating speed, the machine body balance and the horizontal tail balance are mainly used for respectively measuring the machine body load and the full-motion horizontal tail load in the test process; the test method of the independent rotor wing model forward flight test and the rotor wing and fuselage combined model forward flight test comprises the steps that under the condition of a given main shaft inclination angle, a fuselage attitude, a wind speed and a rotor wing rotating speed, the total distance of the rotor wing is controlled to be balanced to a given vertical force coefficient, the periodic variable distance of the rotor wing is controlled in the balancing process to enable the pitching moment and the rolling moment of a hub to be smaller than 20 N.m, after the hub is balanced to a specified test value and is stable, the pitching moment and the rolling moment of the hub are not larger than 3 N.m, the rotor wing aerodynamic load and the rotor wing power are respectively measured mainly by a rotor wing balance and a torque balance in the test process, and the fuselage balance and a tail balance respectively measure the fuselage and the full-motion tail-trim aerodynamic load.
The measured rotor wing model test data is given by a propeller hub wind axis system, and the fuselage model test data and the full-dynamic horizontal tail model test data are given by a fuselage wind axis system. As shown in fig. 3, the test model and the device of the embodiment relate to a rotor model 1, a fuselage model 2, a test bed 5 and a full-motion horizontal tail model 7 of a wind tunnel test bed of a rotor and fuselage combination model; the original point of the wind axis system of the propeller hub is the center of the model of the propeller hub, XHThe axis being positive in the direction of incoming flow, YHThe axis being positive perpendicular to the incoming flow, ZHThe axes are determined according to the right hand rule; the original point of the fuselage wind axis system is the balance center of the fuselage, XFThe axis being positive in the direction of oncoming flow, YFThe axis being positive perpendicular to the incoming flow, ZFThe axis is determined according to the right-hand rule, the center of gravity of the whole machine is an O point, and the corresponding coordinate system is X-Y-Z.
Different normalization factors are adopted when calculating the force and moment coefficients of a rotor model, a fuselage model and a full-motion horizontal tail model.
Calculating rotor model reference force and rotor model reference moment by rotor tip speedωRAtmospheric densityρRotor disc areaπR 2 The formula is as follows:
the reference force of the fuselage model and the reference moment of the fuselage model adopt the incoming flow wind speedVAtmospheric densityρResistance area of the fuselageS f Length of fuselage modelL f The formula is as follows:
force and moment coefficients of rotor model are used respectivelyF01、M01Calculating; the force and moment coefficients of the fuselage model and the full-motion horizontal tail model are respectively usedF02AndM02and (6) performing calculation.
Before carrying out the pneumatic interference characteristic analysis, the pneumatic load coefficient of a rotor model, the pneumatic load coefficient of a fuselage model and the pneumatic load coefficient of a full-motion horizontal tail model are converted to the center of gravity of the whole aircraft in a unified manner, and then the next analysis is carried out.
Example 2
As shown in fig. 2, in the present embodiment, a rotor and fuselage combined model wind tunnel test bench is used to perform a rotor and fuselage combined model forward flight test to obtain a rotor aerodynamic load R4 during forward flight, a fuselage aerodynamic load F3 during forward flight, and a full-motion horizontal tail aerodynamic load H3 during forward flight.
Before the test is started, whether the wind tunnel test bed of the rotor and fuselage combination model can normally work is judged, under the condition that the system can normally work, the installation angle of a full-motion horizontal tail is changed to a test value, zero reading is collected and stored, the wind tunnel test bed of the rotor and fuselage combination model is started, the rotating speed of the rotor is increased to the working rotating speed to safely operate under the condition that the total pitch angle and the periodic pitch angle are zero, and the wind tunnel is driven;
(1) adjusting the wind speed to a given test value, and operating the inclination angle of the main shaft to the given test value;
(2) the total pitch of the rotor wing is controlled to be balanced to a given vertical force coefficient, and the periodic variable pitch of the rotor wing is controlled in the balancing process to enable the pitching moment and the rolling moment of a hub to be smaller than 20 N.m;
(3) after the balance is carried out to a specified test value and the stabilization time delta t is passed, the pitching moment and the rolling moment of the hub are controlled within 3 N.m;
(4) collecting data, processing and outputting results;
(5) repeating the steps 1-4 until all test points under the horizontal tail installation angle are completed. (wherein the balancing strategies adopt fixed vertical force coefficient balancing.)
Stopping the wind tunnel; the rotor platform is stopped, and the test is repeated until all test points under the horizontal tail installation angle are reached.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. A multi-component aerodynamic interference characteristic test simulation method of a full-motion horizontal tail helicopter is realized based on a wind tunnel test bed of a rotor and fuselage combined model, and is characterized by comprising the following steps:
s1, acquiring rotor aerodynamic load test data of the helicopter under the coaxial system based on a rotor and fuselage combined model wind tunnel test bench test, and acquiring fuselage aerodynamic load test data and full-dynamic horizontal tail aerodynamic load test data of the helicopter under the coaxial system, wherein the steps comprise:
step 1, carrying out a single rotor model hovering test on the basis of a rotor and fuselage combined model wind tunnel test bed, and obtaining rotor aerodynamic load R1 during hovering;
step 2, carrying out a hovering test on the rotor and fuselage combined model based on a wind tunnel test bed of the rotor and fuselage combined model, and obtaining rotor aerodynamic loads R2, fuselage aerodynamic loads F1 and full-motion horizontal tail aerodynamic loads H1 in the rotor and fuselage combined model during hovering;
step 3, carrying out a front flight test of an independent fuselage model based on a wind tunnel test bed of a rotor wing and fuselage combined model, and obtaining a front flight fuselage aerodynamic load F2 and a front flight full-motion horizontal tail aerodynamic load H2;
step 4, carrying out a front flight test of the single rotor model based on a wind tunnel test bed of the rotor and fuselage combined model to obtain rotor aerodynamic load R3 in front flight;
step 5, carrying out a rotor wing and fuselage combined model forward flight test based on a rotor wing and fuselage combined model wind tunnel test stand to obtain a rotor wing aerodynamic load R4 in forward flight, a fuselage aerodynamic load F3 in forward flight and a full-motion horizontal tail aerodynamic load H3 in forward flight;
and S2, carrying out aerodynamic interference characteristic analysis by using an interference characteristic model according to the rotor wing aerodynamic load test data, the fuselage aerodynamic load test data and the full-dynamic horizontal tail aerodynamic load test data to obtain aerodynamic interference characteristics among all parts of the helicopter.
2. The method for simulating the multi-component aerodynamic disturbance characteristic test of the full-motion horizontal tail helicopter according to claim 1, wherein the test states of the individual rotor model hovering test in the step 1 and the rotor and fuselage combined model hovering test in the step 2 are the same, and the test is performed in a mode of changing the total distance of the rotors by adopting a fixed rotating speed.
3. The method for simulating the multi-component aerodynamic interference characteristic test of the full-motion horizontal tail helicopter according to claim 1, wherein the balancing strategies of the forward flight test of the independent rotor model in the step 4 and the forward flight test of the rotor and fuselage combination model in the step 5 adopt fixed vertical force coefficient balancing.
4. The method for simulating the multi-component aerodynamic interference characteristic test of the full-motion horizontal tail helicopter according to claim 3, wherein the fixed vertical force coefficient balancing process of the independent rotor model forward flight test and the rotor and fuselage combined model forward flight test is as follows: under the condition of a given main shaft inclination angle, a given fuselage attitude, a given wind speed and a given rotor wing rotating speed, the required vertical force coefficient is balanced by controlling the rotor wing collective pitch; and in the balancing process, the pitch variation of the rotor wing is controlled to enable the pitching moment and the rolling moment of the hub to be less than 20 N.m, and after the hub is balanced to a specified test value and is stable, the pitching moment and the rolling moment of the hub are less than or equal to 3 N.m.
5. The method for simulating the multi-component aerodynamic interference characteristics of the full-motion horizontal tail helicopter according to claim 1,
rotor aerodynamic load test data include: rotor aerodynamic loads R1 during suspension, rotor aerodynamic loads R2 in a rotor and fuselage combined model during hovering, rotor aerodynamic loads R3 during forward flight and rotor aerodynamic loads R4 during forward flight; the rotor wing aerodynamic load test data are obtained by firstly converting the rotor wing model aerodynamic load coefficient to the center of gravity of the helicopter in a unified way and then carrying out normalization processing;
the aerodynamic loading test data of the fuselage include: hovering time body pneumatic load F1, front flying time body pneumatic load F2 and front flying time body pneumatic load F3; the test data of the aerodynamic load of the helicopter body are obtained by uniformly converting the aerodynamic load coefficient of the helicopter body model to the center of gravity of the helicopter and then carrying out normalization treatment;
the full-dynamic horizontal tail pneumatic load test data comprises the following steps: the system comprises a suspension full-motion horizontal tail pneumatic load H1, a front flying full-motion horizontal tail pneumatic load H2 and a front flying full-motion horizontal tail pneumatic load H3; the full-dynamic horizontal tail pneumatic load test data are obtained by firstly converting the full-dynamic horizontal tail pneumatic load coefficient to the center of gravity of the helicopter in a unified mode and then performing normalization processing.
6. The method for simulating the multi-component aerodynamic interference characteristics of the all-dynamic horizontal tail helicopter according to claim 5, wherein the rotor aerodynamic load test data is given by a rotor hub wind axis system, the fuselage aerodynamic load test data is given by a fuselage wind axis system, and the all-dynamic horizontal tail aerodynamic load test data is given by a fuselage wind axis system.
7. The method for simulating the multi-component aerodynamic disturbance characteristic test of the full-motion horizontal tail helicopter according to claim 6, wherein the rotor aerodynamic load test data are normalized by taking a rotor model reference force F01 and a rotor model reference moment M01 as normalization factors, wherein:
in the formula (I), the compound is shown in the specification,
is at atmospheric density,
Is the speed of the rotor wing tip,
Is the area of a rotor blade disc and R is the rotationA wing radius;
the method is characterized in that the normalization factors of the airframe model reference force F02 and the airframe model reference moment M02 are used in the normalization processing of the airframe pneumatic load test data and the full-dynamic horizontal tail pneumatic load test data, wherein:
in the formula (I), the compound is shown in the specification,
in order to be at the density of the atmosphere,
in order to obtain the speed of the incoming wind,
the resistance area of the machine body is the resistance area,
is the fuselage model length.
8. The method for simulating the multi-component aerodynamic interference characteristics of the full-motion horizontal tail helicopter according to claim 5,
the original point of a propeller hub wind axis system is the center of a propeller hub model, the X axis of the propeller hub wind axis system is positive along the incoming flow direction, the Y axis is positive in the direction perpendicular to the incoming flow direction, and the Z axis is determined according to a right-hand rule;
the original point of the wind axis system of the machine body is the center of the balance of the machine body, the X axis of the wind axis system of the machine body is positive along the incoming flow direction, the Y axis of the wind axis system is positive in the direction perpendicular to the incoming flow direction, and the Z axis of the wind axis system of the machine body is determined according to the right-hand rule.
9. The method for simulating the multi-component aerodynamic disturbance characteristic test of the full-motion horizontal tail helicopter according to claim 1, wherein the S2 is implemented by the following specific processes:
t1, by interference characteristic model: when hovering, subtracting the aerodynamic load R1 of the suspended rotor from the aerodynamic load R2 of the rotor in the rotor and fuselage combined model to obtain the interference characteristic of the hovering rotor wake caused by the fuselage;
t2, constructing a graph of rotor aerodynamic load R2 and body aerodynamic load F1 in a rotor and fuselage combination model during hovering, analyzing the relation of the change of the fuselage load along with the rotor load under the effect of rotor wake flow, and obtaining the interference characteristic of the rotor wake flow on the fuselage; constructing a curve graph of rotor wing aerodynamic load R2 and full-motion horizontal tail aerodynamic load H1 in a rotor wing and fuselage combined model during hovering, and analyzing the relation of the full-motion horizontal tail load changing along with the rotor wing load under the effect of rotor wing wake flow, thereby obtaining the interference characteristic of the rotor wing wake flow on the full-motion horizontal tail;
t3, by interference characteristic model: subtracting the front flying body aerodynamic load F2 from the front flying body aerodynamic load F3 to obtain the interference characteristic of the rotor wake on the aircraft body in the front flying state; by means of the interference characteristic model: subtracting the front-flying full-motion horizontal tail aerodynamic load H2 from the front-flying full-motion horizontal tail aerodynamic load H3 to obtain the interference characteristic of the rotor wake on the full-motion horizontal tail in the front-flying state;
t4, by interference characteristic model: and subtracting the front-flying rotor aerodynamic load R3 from the front-flying rotor aerodynamic load R4 to obtain the interference characteristic of the fuselage to the rotor wake flow in the front-flying state.
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