CN114896682A - Stable hovering performance correction method based on coupling hovering climbing test flight data - Google Patents
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Abstract
The invention provides a stable hovering performance correction method based on coupled hovering climbing test flight data. The method aims at the problems of uncertain performance of engine installed thrust and wind tunnel test aerodynamic data, low efficiency of direct test flight and the like, obtains stable hovering overload of the airplane based on the coupled hovering climbing action, and obtains stable hovering performance of different weight points of the airplane by adjusting a roll angle and changing the equivalent weight of the airplane in the test flight process. Meanwhile, the method obtains source data through actual test flight, and does not depend on rack data of an engine and wind tunnel test data of the airplane, so that the method can efficiently and accurately obtain stable hovering overload under the target weight of the airplane, and has positive significance and profound influence on subsequent continuous test flight of the airplane and the completion of performance indexes.
Description
Technical Field
The invention belongs to the technical field of aerospace flight data processing, and particularly relates to a stable hovering performance correction method based on coupled hovering climbing test flight data.
Background
The hovering performance of the airplane has important influence on the maximum climbing rate, the lifting limit, the voyage range and other performances of the airplane, and is directly related to the accessibility of important performance indexes of the airplane. Particularly, in the adjustment trial flight stage, the residual thrust specificity of each height of the airplane is not clear, and the trial flight with stable hovering performance can be completed only by successively probing edges and bottoms, so that the number of trial flight stands is increased, and the trial flight line is lengthened. However, in the trial flight phase, the successive trial flight cannot be satisfied due to constraints on the time of aircraft production, constraints on trial flight cost, and limitations on the number of flight stands. Therefore, in the test flight process, in order to obtain the stable hovering overload characteristic under different airplane weights and reasonably provide subsequent performance indexes, different methods need to be corrected according to test flight data in different states, and therefore an important data basis is provided for accurately predicting the airplane performance indexes.
At present, under the condition of different weights, the stable hovering performance of the airplane is obtained by adopting theoretical data calculation or a direct test flight mode. On one hand, during theoretical calculation, the real aircraft has differences from theoretical data (bench test data of the engine and wind tunnel test data of the aircraft) in the aspects of engine thrust, aircraft resistance and the like. Due to the installation of the engine, the forward matching and the like, the thrust loss of the engine can be caused; the incremental changes in aircraft drag can also be caused by manufacturing and installation tolerances, surface quality, etc. of the aircraft. Therefore, the stable spiraling performance of the real aircraft under different weights cannot be obtained only by relying on aircraft theoretical data; on the other hand, the direct test flight method causes a large increment of test flight numbers, reduces the test flight efficiency and cannot meet the requirement of rapid test flight.
Disclosure of Invention
The invention provides a stable spiral overload correction method based on coupled spiral climbing test flight data, aiming at the problems of uncertain performance of engine installed thrust and wind tunnel test aerodynamic data, low efficiency of direct test flight and the like. The method is used for acquiring the stable hovering overload of the airplane based on the coupled hovering climbing action, and in the test flight process, the equivalent weight of the airplane is changed by adjusting the roll angle, so that the stable hovering performance of the airplane at different weight points is acquired. Meanwhile, the method obtains source data through actual test flight, and does not depend on rack data of an engine and wind tunnel test data of the airplane, so that the method can efficiently and accurately obtain stable hovering overload under the target weight of the airplane, and has positive significance and profound influence on subsequent continuous test flight of the airplane and the completion of performance indexes.
The specific implementation content of the invention is as follows:
the invention provides a stable hovering performance correction method based on coupled hovering climbing test flight data, which specifically comprises the following steps:
step 1: selecting the height and speed of hovering climbing and a flight state, and acquiring flight data;
and 2, step: calculating the corresponding hovering overload under different rolling angles;
and step 3: correcting the hovering overload of a target state according to the existing hovering climbing flight performance;
and 4, step 4: changing the speed, repeating the operations of the step 2 to the step 3, and identifying the circling overload of the target state at the same height and different speeds;
and 5: and (4) changing the height, repeating the operations in the steps 2 to 4, and identifying the spiral overload of the target state within the range of the height-speed full envelope.
In order to better implement the method, in step 1, n different roll angles need to be selected under the condition of the same height, speed and weight, n stable hover climbers are established, and the overload and climbing rate of the airplane under different roll angles are obtained.
To better implement the present invention, further, the operation of obtaining the climbing rate data is:
calculating the climbing rate of the coupled spiral climbing action under the working conditions of selected height, speed, weight and rolling angle, wherein the specific calculation formula is as follows:
where Δ H is a value of + -100 m below the selected altitude, Δ T is the time required to climb the altitude interval, V y The climbing rate of the coupled spiral climbing at the height;
the operation of acquiring the roll angle data is as follows:
the specific calculation formula of the roll angle of the selected working condition coupled spiral climbing action is as follows:
wherein, Delta T i For the time interval between the acquisition of the data,
the roll angle for the interval of data acquisition,
the roll angle under this condition.
In order to better implement the present invention, further, the step 2 specifically includes the following steps:
step 2.1: constructing a stable spiral climbing mechanical model;
step 2.2: and constructing a stable circling mechanical model.
In order to better implement the present invention, further, the specific operations of step 2.1 are:
the specific equation set of the mechanical model for stable spiral climbing is as follows:
Lcosφ＝Gcosθ (3)
T＝D+Gsinθ (4)
CD＝CD 0 +A·CL 2 (7)
wherein L is the lift of the aircraft, G is the gravity of the aircraft, T is the thrust of the engine, D is the drag of the aircraft, ρ is the density, V is the velocity, S is the reference area, CL is the lift coefficient, CD is the drag coefficient, CD is the lift coefficient 0 Is a type resistance, A is an ascending resistance factor,
for the roll angle, theta is the rise angle, V y Is the climbing rate;
the specific operation of the step 2.2 is as follows:
constructing a stable spiral mechanical model, wherein a specific equation set is as follows:
Lcosφ＝G (9)
T＝D (10)
CD＝CD 0 +A·CL 2 (13)
wherein L is the lift force of the airplane and G is the flyGravity of the aircraft, T is thrust of the engine, D is drag of the aircraft, ρ is density, V is velocity, S is reference area, CL is lift coefficient, CD is drag coefficient 0 Is a type resistance, A is an ascending resistance factor,
as the roll angle, θ is the lift angle.
In order to better implement the present invention, further, the step 3 specifically includes the following steps:
step 3.1: counting data to obtain a relation matrix of weight, climbing rate and overload;
step 3.2: calculating a stable spiral climbing-stable climbing performance relation;
step 3.3: calculating a functional relation of stable spiral climbing;
step 3.4: correcting the roll angle and stabilizing the circling;
step 3.5: the correction method is directed to overload and spiral radius.
In order to better implement the present invention, further, the specific operations of step 3.2 are:
according to the formulas (3) to (14), the function relationship of stable spiral climbing and stable climbing is obtained as follows:
wherein T is the thrust of the engine, D is the drag of the aircraft, G is the gravity of the aircraft, V y For climb rate, V is velocity, ρ is density, S is reference area, CD 0 Is a type resistance, A is a lift-induced drag factor,
the angle is a rolling angle, and theta is a climbing angle;
and (5) simultaneous equations (15) to (16) to obtain the relationship of stable spiral climbing and stable climbing performance as follows:
in order to better implement the present invention, further, the specific operations of step 3.3 are:
obtaining the different roll angles of the airplane according to the formula (17)
And roll angle
When the stable circling is performed, the relation is satisfied:
roll angle
Roll angle
In summary, the functional relationship between equation (18) and equation (19) for stable hover climb is as follows:
namely, it is
In order to better implement the present invention, further, the step 3.4 specifically operates as follows:
when climbing angle theta 1 When the airplane is in stable circling stage at 0 degrees, the climbing rate is 0m/s, and the cos theta is measured at the moment 1 With formula (21) as 1, we obtain:
namely:
and (3) converting the formula (23) into a reference state by using the climbing of the stable disk as a reference state and the stable disk as a target state:
wherein G is the gravity of the aircraft, V is the velocity, ρ is the density, S is the reference area, A is the lift drag factor, V ybase 、 
θ base Respectively comprises a climbing rate, a rolling angle and a climbing angle of the stable spiral climbing state,
roll angle for stable hover;
then, the roll angle of the stable spiral state is corrected by combining the formula (8) and the formula (24) with the obtained stable spiral climbing test flight data.
In order to better implement the present invention, further, the step 3.5 specifically includes the following operations:
step 3.5.1: correcting normal overload;
step 3.5.2: the spiral radius is corrected.
To better implement the present invention, further, the specific modification formula of step 3.5.1 is as follows:
and (3) normal overload correction:
to better implement the present invention, further, the specific modification formula of step 3.5.2 is as follows:
the aircraft's stable hover radius is:
F＝Gtanφ (27)
G＝mg (28)
in summary, we obtain:
angle of roll
And substituting the radius into a formula to obtain the corrected stable disc radius.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the method obtains the stable hovering overload of the airplane based on the coupled hovering climbing action, and obtains the stable hovering performance of the airplane at different weight points by adjusting the roll angle and changing the equivalent weight of the airplane in the test flying process. Meanwhile, the method obtains source data through actual test flight, and does not depend on rack data of an engine and wind tunnel test data of the airplane, so that the method can efficiently and accurately obtain stable hovering overload under the target weight of the airplane, and has positive significance and profound influence on subsequent continuous test flight of the airplane and the completion of performance indexes.
Drawings
FIG. 1 is a flow chart of a coupled hover climb-stable hover performance correction method.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The meaning of the above terms in the present invention can be understood in a specific case by those skilled in the art.
Example 1:
the embodiment provides a stable hover performance correction method based on coupled hover climbing test flight data, which specifically comprises the following steps:
step 1: selecting the height and speed of hovering climbing and a flight state, and acquiring flight data;
and 2, step: calculating the corresponding hovering overload under different rolling angles;
and step 3: correcting the hovering overload of a target state according to the existing hovering climbing flight performance;
and 4, step 4: changing the speed, repeating the operations of the step 2 to the step 3, and identifying the circling overload of the target state at the same height and different speeds;
and 5: and (4) changing the height, repeating the operations in the steps 2 to 4, and identifying the spiral overload of the target state within the range of the height-speed full envelope.
Example 2:
this example is based on the above example 1, 1. test flight method
Under the conditions of the same height, speed and weight, n different roll angles are selected, n stable spiral climbing are established, and the overload and climbing rate of the airplane under different roll angles are obtained.
1.1 climb Rate data acquisition
The calculation formula of the climbing rate of the coupled spiral climbing action under the selected working condition (height, speed, weight, rolling angle and the like, the same applies below) is as follows:
wherein, DeltaH is the height value +/-100 m, DeltaT is the time required for climbing the height interval, V y The climbing rate for the coupled hover climb at that height.
1.2 roll Angle data acquisition
The roll angle calculation formula of the selected working condition coupled spiral climbing action is as follows:
wherein, Delta T i For the time interval between the acquisition of the data,
the roll angle for the interval of data acquisition,
the roll angle under this condition.
2. Mechanical model
2.1 Stable spiral climbing mechanical model
The specific equation set of the mechanical model for stable spiral climbing is as follows:
Lcosφ＝Gcosθ (3)
T＝D+Gsinθ (4)
CD＝CD 0 +A·CL 2 (7)
wherein L is the lift of the aircraft, G is the gravity of the aircraft, T is the thrust of the engine, D is the drag of the aircraft, ρ is the density, V is the velocity, S is the reference area, CL is the lift coefficient, CD is the drag coefficient, CD is the lift coefficient 0 Is a type resistance, A is an ascending resistance factor,
for the roll angle, theta is the rise angle, V y Is the rate of climb.
2.2 Steady circle mechanics model
The specific equation set of the mechanical model for stabilizing the hover is as follows:
Lcosφ＝G (9)
T＝D (10)
CD＝CD 0 +A·CL 2 (13)
wherein L is the lift of the aircraft, G is the gravity of the aircraft, T is the thrust of the engine, D is the drag of the aircraft, ρ is the density, V is the velocity, S is the reference area, CL is the lift coefficient, CD is the drag coefficient, CD is the lift coefficient 0 Is a type resistance, A is an ascending resistance factor,
as the roll angle, θ is the lift angle.
3 test flight data analysis
3.1 statistical data
From the data analysis methods in sections 1.1 and 1.2, a weight-climb rate-overload matrix can be obtained, see table 1.
TABLE 1 weight-climb Rate-overload matrix
3.2 Stable hovering climbing-Stable climbing Performance relationship
According to the equations (3) to (14), the stable spiral climbing-stable climbing function relationship is as follows:
wherein T is the thrust of the engine, D is the drag of the aircraft, G is the gravity of the aircraft, V y For climb rate, V is velocity, ρ is density, S is reference area, CD 0 Is a type resistance, A is a lift-induced drag factor,
as the roll angle, θ is the climb angle.
Simultaneous equations (15) to (16) can yield:
3.3 Stable hovering functional relationship
According to the formula (17): aircraft at different roll angles: (
And
) And (3) stable circling is carried out, and the relation is satisfied:
roll angle
Roll angle
In summary, the following expressions (18) to (19) can be obtained:
namely, it is
3.4 modified roll Angle (Steady circle)
When climbing angle theta 1 At 0 deg., the aircraft is in stable circle stepSegment, climbing rate is 0m/s, at this time, cos theta 1 With formula (21) as 1, we obtain:
namely:
taking the climbing of the stable disk as a reference state and the stable disk as a target state, and converting the formula (23) into a formula (I):
wherein G is the gravity of the aircraft, V is the velocity, ρ is the density, S is the reference area, A is the lift drag factor, V ybase 、 
θ base Respectively comprises a climbing rate, a rolling angle and a climbing angle of the stable spiral climbing state,
to stabilize the roll angle of the hover state.
Therefore, the roll angle of the stable hover state is corrected by combining the formula (8) and the formula (24) through the stable hover climb flight test data, which is shown in table 2.
TABLE 2 correction of roll angle during steady climb
3.5 correction of normal overload and spiral radius
3.5.1 correcting Normal overload
Normal overload:
3.5.2 correcting the radius of the spiral
The aircraft's stable hover radius is:
F＝Gtanφ (27)
G＝mg (28)
in conclusion, the following results are obtained
Angle of roll
Substituting to obtain the radius R of the stable disc 1 。
4 same height, different speed
To obtain the roll angle, the overload and the radius of the hover for stable hover at different speeds in order to identify the same altitude. Under the condition of different speeds, the statistics and the analysis calculation of the test flight data are carried out according to the methods of the sections 1, 2 and 3. Stable hover performance at the same height and at different speeds can be obtained, see table 3.
TABLE 3 Stable hovering Performance at equal altitude and different speeds
5 full envelope range
To obtain roll angle, overload and hover radius that identifies a stable hover over the full envelope (i.e., different altitude, different velocity). At different heights, the statistical and analytical calculation of the test flight data is carried out according to the method of section 4.1, and the stable hovering performance in the range of height-speed full envelope is obtained, which is shown in table 4.
TABLE 4 Stable hovering behavior of altitude-speed full envelope
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (12)
1. A stable hovering performance correction method based on coupled hovering climbing test flight data is characterized by specifically comprising the following steps:
step 1: selecting the height and speed of hovering climbing and a flight state, and acquiring flight data;
step 2: calculating the corresponding hovering overload under different rolling angles;
and 3, step 3: correcting the hovering overload of a target state according to the existing hovering climbing flight performance;
and 4, step 4: changing the speed, repeating the operations of the step 2 to the step 3, and identifying the circling overload of the target state at the same height and different speeds;
and 5: and (4) changing the height, repeating the operations in the steps 2 to 4, and identifying the spiral overload of the target state within the range of the height-speed full envelope.
2. The method for correcting the stable hover performance based on the coupled hover climb test flight data as claimed in claim 1, wherein in step 1, n stable hover climbers are established by selecting n different roll angles under the condition of the same height, speed and weight, and obtaining the overload and climb rate of the airplane under different roll angles.
3. The method for correcting stable hover performance based on coupled hover climb flight trial data as claimed in claim 2,
the operation of acquiring the climbing rate data is as follows:
calculating the climbing rate of the coupled spiral climbing action under the working conditions of selected height, speed, weight and rolling angle, wherein the specific calculation formula is as follows:
where Δ H is a value of + -100 m below the selected altitude, Δ T is the time required to climb the altitude interval, V y The climbing rate of the coupled spiral climbing at the height;
the operation of acquiring the roll angle data is as follows:
the specific calculation formula of the roll angle of the coupled spiral climbing action under the selected working condition is as follows:
wherein, Δ T i For the time interval between the acquisition of the data,
the roll angle for the interval of data acquisition,
the roll angle under this condition.
4. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 3, wherein the step 2 specifically comprises the steps of:
step 2.1: constructing a stable spiral climbing mechanical model;
step 2.2: and constructing a stable circling mechanical model.
5. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 4, wherein the specific operations of step 2.1 are:
the specific equation set of the mechanical model for stable spiral climbing is as follows:
L cosφ＝G cosθ (3)
T＝D+G sinθ (4)
CD＝CD 0 +A·CL 2 (7)
wherein L is the lift of the aircraft, G is the gravity of the aircraft, T is the thrust of the engine, D is the drag of the aircraft, ρ is the density, V is the velocity, S is the reference area, CL is the lift coefficient, CD is the drag coefficient, CD is the lift coefficient 0 Is a type resistance, A is a lift-induced drag factor,
for the roll angle, theta is the rise angle, V y Is the climbing rate;
the specific operation of the step 2.2 is as follows:
constructing a stable spiral mechanical model, wherein a specific equation set is as follows:
L cosφ＝G (9)
T＝D (10)
CD＝CD 0 +A·CL 2 (13)
wherein L is the lift of the aircraft, G is the gravity of the aircraft, T is the thrust of the engine, D is the drag of the aircraft, ρ is the density, V is the velocity, S is the reference area, CL is the lift coefficient, CD is the drag coefficient, CD is the lift coefficient 0 Is a type resistance, A is a lift-induced drag factor,
as the roll angle, θ is the lift angle.
6. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 5, wherein the step 3 specifically comprises the steps of:
step 3.1: counting data to obtain a relation matrix of weight, climbing rate and overload;
step 3.2: calculating the relation of stable spiral climbing and stable climbing performance;
step 3.3: calculating a functional relation of stable spiral climbing;
step 3.4: correcting the roll angle and stabilizing the circling;
step 3.5: the correction method is directed to overload and spiral radius.
7. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 6, wherein the specific operations of step 3.2 are:
according to the formulas (3) to (14), the function relationship of stable spiral climbing and stable climbing is obtained as follows:
wherein T is the thrust of the engine, D is the drag of the aircraft, G is the gravity of the aircraft, V y For climb rate, V is velocity, ρ is density, S is reference area, CD 0 Is a type resistance, A is a lift-induced drag factor,
the angle is a rolling angle, and theta is a climbing angle;
and (5) simultaneous equations (15) to (16) to obtain the relationship of stable spiral climbing and stable climbing performance as follows:
8. the method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 7, wherein the specific operations of step 3.3 are:
obtaining the different roll angles of the airplane according to the formula (17)
And roll angle
When the stable circling is performed, the relation is satisfied: roll angle
Roll angle
In summary, the functional relationship between equation (18) and equation (19) for stable hover climb is as follows:
namely, it is
9. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 8, wherein said step 3.4 is specifically operated as follows:
when climbing angle theta 1 When the airplane is in stable circling stage at 0 degrees, the climbing rate is 0m/s, and the cos theta is measured at the moment 1 With formula (21) as 1, we obtain:
namely:
and (3) converting the formula (23) into a reference state by using the climbing of the stable disk as a reference state and the stable disk as a target state:
wherein G is the gravity of the aircraft, V is the velocity, ρ is the density, S is the reference area, A is the lift drag factor, V ybase 、
θ base Respectively comprises a climbing rate, a rolling angle and a climbing angle of the stable spiral climbing state,
roll angle for stable hover;
then, the roll angle in the stable hover state is corrected by combining the equation (24) with the equation (8) based on the obtained stable hover climb flight test data.
10. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 9, wherein said step 3.5 specifically comprises the operations of:
step 3.5.1: correcting normal overload;
step 3.5.2: the spiral radius is corrected.
11. The method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 10, wherein the specific correction formula of step 3.5.1 is as follows:
and (3) normal overload correction:
12. the method for correcting stable hover performance based on coupled hover climb flight test data as claimed in claim 10, wherein the specific correction formula of step 3.5.2 is as follows:
the aircraft's stable hover radius is:
F＝G tanφ (27)
G＝mg (28)
in conclusion, we obtain:
angle of rolling
And substituting the radius into a formula to obtain the corrected stable disc radius.
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