CN114647994B - Climbing performance processing method - Google Patents
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Abstract
The disclosed embodiments relate to a climbing performance processing method. The method comprises the following steps: calculating a typical height; establishing an aerodynamic model and an engine power model, calculating climbing rates in different climbing speed ranges under the typical altitude by using the aerodynamic model and the engine power model, and obtaining climbing rate and climbing speed curves under the typical altitude; analyzing a climbing rate and climbing speed curve to obtain the optimal climbing rate and the corresponding climbing speed; and establishing an aircraft full-range climbing equation according to the optimal climbing rate and the climbing speed, and calculating a full-range climbing performance parameter. On one hand, a set of favorable climbing performance fast resolving method and flow is formed through calculation and analysis of typical calculated height climbing capacity; on the other hand, the favorable climbing speed under the typical altitude is obtained as the favorable climbing speed of the whole-course climbing through solving the curve of the typical altitude climbing rate and the climbing speed, so that the climbing performance of the airplane is calculated, and the calculation efficiency of the favorable climbing performance is greatly improved.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of calculation of flight performance of an aviation aircraft, in particular to a climbing performance processing method.
Background
The airplane climbs at a favorable speed in the climbing process, so that the time consumed by the climbing of the airplane can be shortened, and the fuel consumption can be saved. In the existing climbing performance calculation, in order to calculate the climbing performance data of an airplane from low altitude to high altitude, integration is gradually carried out from the low altitude according to a certain step length, and a calculation result is obtained after the altitude is met; on the basis of favorable climbing performance, climbing performance data at all speeds are calculated and compared to obtain favorable climbing performance data at all heights, and further favorable climbing performance data of all climbing sections are obtained.
The calculation method of the climbing performance beneficial to the existing engineering design needs to iteratively calculate climbing performance data at different speeds and needs to calculate for multiple times according to a certain height step length, so that a large amount of calculation time is consumed, and the calculation in the aircraft mission planning system according to the existing method causes slow response of the mission planning system.
Accordingly, there is a need to ameliorate one or more of the problems with the related art solutions described above.
It is noted that this section is intended to provide a background or context to the disclosure as recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
Disclosure of Invention
An object of the disclosed embodiments is to provide a climb performance handling method, thereby overcoming, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.
According to an embodiment of the present disclosure, a climbing performance processing method is provided, which includes:
calculating a typical height;
establishing an aerodynamic model and an engine power model, calculating climbing rates in different climbing speed ranges under the typical altitude by using the aerodynamic model and the engine power model, and obtaining a climbing rate and climbing speed curve under the typical altitude;
analyzing the climbing rate and climbing speed curve to obtain the optimal climbing rate and the corresponding climbing speed;
and establishing an aircraft full-range climbing equation according to the optimal climbing rate and the climbing speed, and calculating a full-range climbing performance parameter.
In an embodiment of the present disclosure, the calculating the typical height includes:
and calculating a climbing starting height and a climbing ending height according to the climbing performance of the airplane, and obtaining a typical height favorable for the climbing performance based on characteristic analysis of the climbing rate value domain interval of the airplane according to the curve characteristics of the climbing rate and the climbing height of the airplane.
In an embodiment of the disclosure, the process of obtaining the curve of the typical altitude climb rate and the climb speed includes:
establishing a pneumatic power model and an engine power model according to the aircraft climbing configuration parameters, acquiring residual thrust of the aircraft at different speeds under the typical altitude, and using the residual thrust as the climbing speed range of the positively selected aircraft;
calculating a climbing acceleration factor by taking the actual climbing mode of the airplane as a constraint condition according to a preset climbing speed;
calculating an initial condition climbing rate and a lifting force coefficient according to an initial climbing attack angle and an initial climbing angle by using an airplane aerodynamic model and an engine power model, solving a new round of climbing attack angle and a new round of climbing angle according to the initial condition climbing rate and the initial condition lifting force coefficient, and calculating the climbing rate and the lifting force coefficient through iteration until the results of two adjacent iterations meet the error requirement to obtain a corresponding speed climbing rate;
and (4) iteratively calculating the climbing rates corresponding to different climbing speeds, and obtaining a curve of the climbing rate and the climbing speed by using the calculation result.
In an embodiment of the present disclosure, the process of obtaining the optimal climbing rate and the corresponding climbing speed includes:
and calculating a maximum value point of the climbing rate based on the climbing rate and climbing speed curve of the typical height, and acquiring the maximum climbing rate of the typical height and the corresponding climbing speed.
In an embodiment of the present disclosure, the whole climbing performance parameter includes:
the whole climbing time and the whole climbing fuel consumption.
In an embodiment of the disclosure, the calculation formula of the typical height is:
H c =2/3*(H end -H begin )+H begin （1）
wherein H C Is a typical height, H begin Is the starting height, H end Is the terminal height.
In an embodiment of the disclosure, the calculation formula of the climbing rate at the preset speed is as follows:
wherein, V y For the rate of climb, P is the engine thrust,
and with
Respectively a climbing attack angle of the airplane and an installation angle of an engine, Q is aerodynamic resistance, G is climbing weight,
is a climb acceleration factor; c y Is the climbing aerodynamic lift coefficient, q is dynamic pressure, S is the wing area,
the climbing angle and V is the speed.
In an embodiment of the present disclosure, the residual thrust calculation formula is:
wherein,
for residual thrust, P avail Available thrust for the engine, P req To require thrust;
in addition, the climbing acceleration factor is calculated by the following formula:
wherein M is the flight Mach number, k is the air adiabatic exponent, T s Current altitude atmospheric temperature, T, for standard atmospheric conditions ns Actual atmospheric temperature at the current altitude;
the formula for calculating the climbing angle by using the climbing rate is as follows:
wherein,
the climbing angle and V is the speed.
In an embodiment of the present disclosure, a calculation formula of the maximum value point of the climbing rate is as follows:
V y ’（V climb ）=0 （7）
wherein, V y ’（V climb ) Is the first derivative of the climbing rate-climbing speed curve function relation.
In an embodiment of the present disclosure, the formulas of the whole climbing time and the whole climbing fuel consumption are respectively:
Time=(H end -H begin )/V y （8）
Fuel=Time*W f （9）
wherein, time is the whole climbing Time, fuel is the whole climbing Fuel consumption, W f Is the specific fuel consumption of the aircraft engine per unit time.
The technical scheme provided by the embodiment of the disclosure can have the following beneficial effects:
in the embodiment of the disclosure, through the climbing performance processing method, on one hand, the invention fully considers the change rule of the maximum climbing rate along with the height, establishes a typical climbing calculation height model, and forms a set of favorable climbing performance fast resolving method and flow through calculation and analysis of the climbing capacity of the typical calculation height; on the other hand, the method and the device solve through a typical climbing calculation altitude climbing rate-climbing speed curve, obtain the favorable climbing speed under the typical altitude as the favorable climbing speed of the whole-course climbing to calculate the climbing performance of the airplane, solve the problems of multiple iteration cycles and long time consumption of the conventional favorable climbing performance calculation of the airplane, and greatly improve the calculation efficiency of the favorable climbing performance.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It should be apparent that the drawings in the following description are merely examples of the disclosure and that other drawings may be derived by those of ordinary skill in the art without inventive effort.
FIG. 1 shows a process method step diagram of the present disclosure;
FIG. 2 illustrates a typical climb calculated altitude-climb rate-climb speed graph for the present disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of embodiments of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
First, a climb performance handling method is provided in the present exemplary embodiment. Referring to FIG. 1, the climb performance processing method may include: step S101 to step S104.
Step S101: calculating a typical height;
step S102: establishing an aerodynamic model and an engine power model, calculating climbing rates in different climbing speed ranges under the typical altitude by using the aerodynamic model and the engine power model, and obtaining a climbing rate and climbing speed curve under the typical altitude;
step S103: analyzing the climbing rate and climbing speed curve to obtain the optimal climbing rate and the corresponding climbing speed;
step S104: and establishing an aircraft full-range climbing equation according to the optimal climbing rate and the climbing speed, and calculating a full-range climbing performance parameter.
According to the climbing performance processing method, on one hand, the change rule of the maximum climbing rate along with the height is fully considered, a typical climbing calculation height model is established, and a set of favorable climbing performance fast resolving method and flow are formed through calculation and analysis of the climbing capacity of the typical calculation height; on the other hand, the method and the device solve through a typical climbing calculation altitude climbing rate-climbing speed curve, obtain the favorable climbing speed under the typical altitude as the favorable climbing speed of the whole-course climbing to calculate the climbing performance of the airplane, solve the problems of multiple iteration cycles and long time consumption of the conventional favorable climbing performance calculation of the airplane, and greatly improve the calculation efficiency of the favorable climbing performance.
Next, the respective steps of the above-described climbing performance processing method in the present exemplary embodiment will be described in more detail with reference to fig. 1 to 2.
Step S101: calculating a typical height;
specifically, the climbing starting height H is calculated according to the climbing performance of the airplane begin End height H end According to the aircraft climbing rate V y The typical calculation height H of the favorable climbing performance of the airplane is obtained based on the characteristic analysis of the climbing rate value domain interval of the airplane and the curve characteristic of the climbing height H c The calculation formula is as follows:
H c =2/3*(H end -H begin )+H begin （1）
step S102: establishing an aerodynamic model and an engine power model, calculating climbing rates in different climbing speed ranges under the typical altitude by using the aerodynamic model and the engine power model, and obtaining a climbing rate and climbing speed curve under the typical altitude;
according to the climbing configuration parameters of the airplane, an aerodynamic model and an engine power model are established, the climbing rate of the typical altitude in different climbing speed ranges is calculated, and the V under the altitude is obtained y ～V climb Curve line. The rate of climb at a given speed is calculated as follows:
wherein, V y For the rate of climb, P is the engine thrust,
and with
Respectively a climbing attack angle of the airplane and an installation angle of an engine, Q is aerodynamic resistance, G is climbing weight,
is a climb acceleration factor; c y And q is dynamic pressure, and S is the wing area.
In addition, the specific process for obtaining the climbing rate and climbing speed curve under the typical altitude is as follows:
1) Obtaining the residual thrust of the plane at different speeds according to the climbing weight, the configuration and the engine state of the plane, and using the residual thrust as the climbing speed range V of the positively selected plane cmin ～V cmax The calculation formula is as follows:
in the above-mentioned formula, the compound has the following structure,
for residual thrust, P avail For available engine thrust, P req In order to require thrust.
2) According to the given climbing speed, taking the actual climbing mode of the airplane as a constraint condition, calculating a climbing acceleration factor, wherein the calculation model is as follows:
in the above formula, M is the flight Mach number, k is the air adiabatic exponent, and the value is 1.4; t is s Current altitude atmospheric temperature, T, for standard atmospheric conditions ns Is the current altitude actual atmospheric temperature.
3) An initial climbing attack angle is assumed by using an airplane aerodynamic force and engine power model
And climbing angle
Calculating initial condition climbing rate V by using climbing rate calculation model y0 And coefficient of lift C y0 (ii) a Calculating a new round of climbing attack angle by using the calculation result
And climbing angle
Calculating the climbing rate and the lift coefficient through iteration until the results of two adjacent iterative calculations meet the error requirement, and obtaining the current given speed climbing rate; by means of V y The calculation model for calculating the climbing angle is as follows:
4) Repeating the steps 2) to 3), iteratively calculating the climbing rates corresponding to different climbing speeds, and obtaining V by using the calculation result y ～V climb A curve.
Step S103: analyzing the climbing rate and climbing speed curve to obtain the optimal climbing rate and the corresponding climbing speed;
specifically, the rate of climb-the rate of climb (V) is calculated for the altitude based on the typical climb y ～V climb ) Curve, finding V y （V climb ) Maximum value point, obtaining typical climbing calculation height maximum climbing rate V ymax And its corresponding climb rate. V y （V climb ) The computation model for the maximum point is as follows:
V y ’（V climb ）=0 （7）
wherein, V y ’（V climb ) Is the first derivative of the climbing rate-climbing speed curve function.
Step S104: and establishing an aircraft full-range climbing equation according to the optimal climbing rate and the climbing speed, and calculating a full-range climbing performance parameter.
Specifically, the maximum climbing rate of the height and the calculation result of the climbing speed are calculated by using the climbing typical calculation, and the whole-course climbing performance parameter is calculated. The climbing performance parameter calculation model based on the current method is as follows:
Time=(H end -H begin )/V y （8）
Fuel=Time*W f （9）
in the above formula, time is the full climb Time, fuel is the full climb Fuel consumption, W f Is the specific fuel consumption of the aircraft engine per unit time.
Through the climbing performance processing method, on one hand, the change rule of the maximum climbing rate along with the height is fully considered, a typical climbing calculation height model is established, and a set of favorable climbing performance fast resolving method and flow are formed through calculation and analysis of the climbing capacity of the typical calculation height; on the other hand, the favorable climbing speed under the typical altitude is obtained through solving the curve of the climbing rate to the climbing speed of the typical climbing calculation altitude, and is used as the favorable climbing speed of the whole climbing to calculate the climbing performance of the airplane, so that the problems of multiple iteration cycle times and long time consumption of the conventional calculation of the favorable climbing performance of the airplane are solved, and the calculation efficiency of the favorable climbing performance is greatly improved.
The invention is further illustrated below with reference to specific examples.
The flow chart of the present invention is shown in FIG. 1, which is a subsonic conveyor, and the wing area of the known aircraft is 300m 2 The mounting angle of the engine is 2 degrees, the climbing initial weight is 160t, the climbing height is 450 m-9000 m, and the airplane aerodynamic data model and the engine aerodynamic data model are obtained.
Step S101: according to the aircraft climbing rate V y Characteristic of the curve with the climbing height H, a typical calculated height H for the favourable climbing performance of the selected aircraft c ：
H c =6150m
Step S102: solving a typical climbing height climbing rate-climbing speed curve, which comprises the following specific steps:
1) Based on basic parameters of the airplane and an engine power model, the calculated range of the climbing speed of the typical calculated altitude 6150m is determined to be 0.3Ma to 0.75Ma, namely 292km/h CAS to 643km/h CAS.
2) Given a climbing speed of 0.3Ma, taking a corrected airspeed climbing mode of an airplane and the like as a constraint condition, calculating a climbing acceleration factor under a standard atmospheric condition:
3) An initial climbing attack angle is assumed by using an airplane aerodynamic force and engine power model
Angle of climbing
And iteratively calculating the climbing rate at the current climbing speed to be 4.005m/s and the climbing angle to be 1.671 degrees by using a climbing rate calculation model.
4) Taking a speed step of 0.05Ma, repeating the steps 1) to 3), iteratively calculating climbing rates corresponding to different climbing speeds in the climbing speed range, and drawing the climbing rate-climbing speed (V) by using the calculation result y ～V climb ) The curves are shown in fig. 2.
Step S103: calculating a rate of climb-a rate of climb (V) for the altitude based on the typical climb y ～V climb ) And (4) curve, solving the maximum value of the curve. Obtaining the maximum climbing rate V of the typical climbing calculation height ymax 7.43m/s, corresponding to a climbing speed of 0.49Ma (408 km/h CAS).
Step S104: calculating the whole-course climbing time and the fuel consumption by using an engine fuel consumption model based on the maximum climbing rate and the climbing speed calculation result of the climbing typical calculation height:
Time=19.18min
Fuel=4424kg
in the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by one skilled in the art.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice in the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (7)
1. A climb performance processing method, comprising:
calculating a climbing starting altitude and a climbing ending altitude according to the climbing performance of the airplane, and obtaining a typical altitude favorable for the climbing performance based on characteristic analysis of an airplane climbing rate value domain interval according to the curve characteristic of the climbing rate and the climbing altitude of the airplane;
establishing an aerodynamic model and an engine power model according to the climbing configuration parameters of the airplane, acquiring residual thrust of the airplane at different speeds under the typical altitude, and selecting a climbing speed range of the airplane by using the residual thrust as positive;
according to a preset climbing speed, calculating a climbing acceleration factor by taking an actual climbing mode of the airplane as a constraint condition, wherein the calculation formula of the climbing acceleration factor is as follows:
where M is the flight Mach number, k is the air adiabatic index, T s Current altitude atmospheric temperature, T, for standard atmospheric conditions ns Is the current altitude actual atmospheric temperature;
calculating an initial condition climbing rate and a lifting force coefficient according to an initial climbing attack angle and a climbing angle by utilizing an airplane aerodynamic model and an engine power model, then calculating a new round of climbing attack angle and a new round of climbing angle according to the initial condition climbing rate and the lifting force coefficient, and calculating the climbing rate and the lifting force coefficient through iteration until the results of two adjacent iterations meet an error requirement to obtain the climbing rate corresponding to the preset climbing speed, wherein the calculation formula of the climbing rate corresponding to the preset climbing speed is as follows:
in the formula, V y In order to obtain the climbing rate, P is the thrust of the engine,
and
respectively is an aircraft climbing attack angle and an engine installation angle, Q is pneumatic resistance, G is climbing weight,
as a climbing acceleration factor, C y Is the climbing aerodynamic lift coefficient, q is dynamic pressure, S is the wing area,
is the climbing angle, V is the speed;
iteratively calculating climbing rates corresponding to different climbing speeds, and obtaining a climbing rate and climbing speed curve by using a calculation result;
analyzing the climbing rate and climbing speed curve to obtain the optimal climbing rate and the corresponding climbing speed;
and establishing a climbing performance parameter calculation model according to the optimal climbing rate and the climbing speed, and calculating the whole climbing performance parameter.
2. The climbing performance processing method according to claim 1, wherein the obtaining of the optimal climbing rate and the corresponding climbing speed process comprises:
and calculating a maximum value point of the climbing rate based on the climbing rate and climbing speed curve of the typical height, and acquiring the maximum climbing rate of the typical height and the corresponding climbing speed.
3. The climb performance processing method according to claim 2, wherein the full climb performance parameters include:
the whole climbing time and the whole climbing fuel consumption.
4. The climb performance processing method according to claim 3, wherein the typical altitude is calculated by the formula:
H c =2/3*(H end -H begin )+H begin （1）
wherein H C Is a typical height, H begin Is the starting height, H end Is the termination height.
5. The climb performance processing method according to claim 4, wherein the residual thrust calculation formula is:
wherein,
for residual thrust, P avail Available thrust for the engine, P req To require thrust;
the formula for calculating the climbing angle by using the climbing rate is as follows:
wherein,
the climbing angle and V is the speed.
6. The climbing performance processing method according to claim 5, wherein the calculation formula of the climbing rate maximum value point is as follows:
V y ’（V climb ）=0 （7）
wherein, V y ’（V climb ) Is the first derivative of the climbing rate-climbing speed curve function.
7. The climbing performance processing method according to claim 6, wherein the formulas of the whole climbing time and the whole climbing fuel consumption are respectively:
Time=(H end -H begin )/V y （8）
Fuel=Time*W f （9）
wherein, time is the whole climbing Time, fuel is the whole climbing Fuel consumption, W f Is the specific fuel consumption of the aircraft engine per unit time.
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