CN114647994A - Climbing performance rapid processing method - Google Patents

Climbing performance rapid processing method Download PDF

Info

Publication number
CN114647994A
CN114647994A CN202210566220.5A CN202210566220A CN114647994A CN 114647994 A CN114647994 A CN 114647994A CN 202210566220 A CN202210566220 A CN 202210566220A CN 114647994 A CN114647994 A CN 114647994A
Authority
CN
China
Prior art keywords
climbing
rate
speed
calculating
typical
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202210566220.5A
Other languages
Chinese (zh)
Other versions
CN114647994B (en
Inventor
张超
商立英
任江涛
徐声明
赵科社
张泰安
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AVIC First Aircraft Institute
Original Assignee
AVIC First Aircraft Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AVIC First Aircraft Institute filed Critical AVIC First Aircraft Institute
Priority to CN202210566220.5A priority Critical patent/CN114647994B/en
Publication of CN114647994A publication Critical patent/CN114647994A/en
Application granted granted Critical
Publication of CN114647994B publication Critical patent/CN114647994B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

Abstract

The disclosed embodiment relates to a method for rapidly processing climbing performance. 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 quick 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

Climbing performance rapid processing method
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 method for rapidly processing climbing performance.
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 various speeds are calculated and compared to obtain favorable climbing performance data at various 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
It is an object of embodiments of the present disclosure to provide a method for fast processing of climb performance, thereby overcoming, at least to some extent, one or more of the problems due to limitations and disadvantages of the related art.
According to the embodiment of the disclosure, a method for rapidly processing climbing performance is provided, and 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 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 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 airplane climbing rate and the climbing altitude.
In an embodiment of the disclosure, the process of obtaining the typical altitude climb rate and climb speed curve 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 a climbing angle by utilizing an airplane aerodynamic model and an engine power model, 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 the error requirement to obtain a corresponding speed climbing rate;
and iteratively calculating the climbing rates corresponding to different climbing speeds, and obtaining a climbing rate and climbing speed curve 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 full climb performance parameters include:
the whole climbing time and the whole climbing fuel consumption.
In an embodiment of the disclosure, the calculation formula of the typical height is:
Hc=2/3*(Hend-Hbegin)+Hbegin （1）
wherein HCIs a typical height, HbeginIs the starting height, HendIs the terminal height.
In an embodiment of the disclosure, the calculation formula of the climbing rate at the preset speed is as follows:
Figure DEST_PATH_IMAGE001
wherein, VyFor the rate of climb, P is the engine thrust,
Figure 889584DEST_PATH_IMAGE002
and
Figure DEST_PATH_IMAGE003
respectively is an aircraft climbing attack angle and an engine installation angle, Q is pneumatic resistance, G is climbing weight,
Figure 371512DEST_PATH_IMAGE004
is a climb acceleration factor; cyIs the climbing aerodynamic lift coefficient, q is dynamic pressure, S is the wing area,
Figure DEST_PATH_IMAGE005
the climbing angle and V is the speed.
In an embodiment of the present disclosure, the residual thrust calculation formula is:
Figure 427193DEST_PATH_IMAGE006
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE007
for residual thrust, PavailFor available engine thrust, PreqTo require thrust;
in addition, the climbing acceleration factor is calculated by the following formula:
Figure 384785DEST_PATH_IMAGE008
（5）
wherein M is the flight Mach number, k is the air adiabatic exponent, TsCurrent altitude atmospheric temperature, T, for standard atmospheric conditionsnsIs the current altitude actual atmospheric temperature;
the calculation formula for calculating the climbing angle by using the climbing rate is as follows:
Figure DEST_PATH_IMAGE009
wherein the content of the first and second substances,
Figure 934846DEST_PATH_IMAGE005
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:
Vy’（Vclimb）=0 （7）
wherein, Vy’（Vclimb) Is the first derivative of the climbing rate-climbing speed curve function.
In an embodiment of the present disclosure, the formulas of the whole climbing time and the whole climbing fuel consumption are respectively:
Time=(Hend-Hbegin)/Vy （8）
Fuel=Time*Wf （9）
wherein, Time is the whole climbing Time, Fuel is the whole climbing Fuel consumption, WfIn a unit timeFuel consumption rate of an aircraft engine.
The technical scheme provided by the embodiment of the disclosure can have the following beneficial effects:
in the embodiment of the disclosure, through the method for rapidly processing the climbing performance, 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 method and flow for rapidly resolving the climbing performance 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 is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 is a diagram illustrating the steps of the inventive processing method of the present disclosure;
FIG. 2 illustrates a typical climb calculated altitude climb rate-climb speed graph for the disclosed embodiment.
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 disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and a repetitive description thereof 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 method for rapidly processing climbing performance is provided in the present exemplary embodiment. Referring to fig. 1, the fast processing method for climb performance 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.
Through the method for quickly processing the climbing performance, 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 method and a flow favorable for quickly resolving the climbing performance 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 rapid 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;
in particular, a climbing starting height H calculated according to the climbing performance of the aircraftbeginEnd height HendAccording to the aircraft climbing rate VyObtaining a typical calculation height H of the favorable climbing performance of the airplane based on the characteristic analysis of the climbing rate value domain interval of the airplane and the curve characteristic of the climbing height HcThe calculation formula is as follows:
Hc=2/3*(Hend-Hbegin)+Hbegin （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 obtainedy～VclimbCurve line. The rate of climb at a given speed is calculated as follows:
Figure 51706DEST_PATH_IMAGE010
wherein, VyFor the rate of climb, P is the engine thrust,
Figure 950392DEST_PATH_IMAGE002
and
Figure 533296DEST_PATH_IMAGE003
respectively is an aircraft climbing attack angle and an engine installation angle, Q is pneumatic resistance, G is climbing weight,
Figure 277261DEST_PATH_IMAGE004
is a climb acceleration factor; cyAnd q is dynamic pressure, and S is the wing area.
In addition, the specific process for obtaining the curve of the climbing rate and the climbing speed under the typical altitude comprises the following steps:
1) according toAcquiring the residual thrust of the plane at different speeds of the plane flight by 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 planecmin～VcmaxThe calculation formula is as follows:
Figure DEST_PATH_IMAGE011
in the above formula, the first and second carbon atoms are,
Figure 248628DEST_PATH_IMAGE007
for residual thrust, PavailFor available engine thrust, PreqIn order to require thrust.
2) Calculating a climbing acceleration factor by taking the actual climbing mode of the airplane as a constraint condition according to the given climbing speed, wherein the calculation model is as follows:
Figure 928002DEST_PATH_IMAGE008
（5）
in the above formula, M is the flight Mach number, k is the air adiabatic index, and the value is 1.4; t is a unit ofsCurrent altitude atmospheric temperature, T, for standard atmospheric conditionsnsIs the current altitude actual atmospheric temperature.
3) An initial climbing attack angle is assumed by using an airplane aerodynamic force and engine power model
Figure 125765DEST_PATH_IMAGE012
And climbing angle
Figure DEST_PATH_IMAGE013
Calculating initial condition climbing rate V by using climbing rate calculation modely0And coefficient of lift Cy0(ii) a Calculating a new round of climbing attack angle by using the calculation result
Figure 266896DEST_PATH_IMAGE014
And climbing angle
Figure DEST_PATH_IMAGE015
Calculating the sum of climb rates by iterationLift coefficient until the results of two adjacent iterative calculations meet the error requirement, and obtaining the current given speed climbing rate; using VyThe calculation model for calculating the climbing angle is as follows:
Figure 843502DEST_PATH_IMAGE016
4) repeating the steps 2) to 3), iteratively calculating the climbing rates corresponding to different climbing speeds, and obtaining V by using the calculation resulty～VclimbCurve line.
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 altitude based on a typical climby～Vclimb) Curve, finding Vy（Vclimb) Maximum value point, obtaining typical climbing calculation height maximum climbing rate VymaxAnd its corresponding climb rate. Vy（Vclimb) The computation model for the maximum point is as follows:
Vy’（Vclimb）=0 （7）
wherein, Vy’（Vclimb) 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=(Hend-Hbegin)/Vy （8）
Fuel=Time*Wf （9）
in the above formula, Time is the full climb Time, Fuel is the full climb Fuel consumption, WfIs the specific fuel consumption of the aircraft engine per unit time.
According to the method for rapidly processing the climbing performance, 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 method and a flow favorable for rapidly resolving the climbing performance 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.
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 300m2The mounting angle of the engine is 2 degrees, the climbing initial weight is 160t, the climbing height is 450 m-9000 m, and the model comprises an aircraft aerodynamic data model and an engine aerodynamic data model.
Step S101: according to the aircraft climbing rate VyCharacteristic of the curve with the climb altitude H, a typical calculated altitude H for the advantageous climb behaviour of the aircraft is selectedc：
Hc=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:
Figure DEST_PATH_IMAGE017
3) an initial climbing attack angle is assumed by using an airplane aerodynamic force and engine power model
Figure 677466DEST_PATH_IMAGE018
Angle of climbing
Figure 96946DEST_PATH_IMAGE019
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 resulty～Vclimb) 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 climby～Vclimb) And (4) curve, solving the maximum value of the curve. Obtaining the maximum climbing rate V of the typical climbing calculation heightymax7.43m/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 within 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 (10)

1. A climbing performance rapid processing method is characterized by comprising 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 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.
2. The method for rapidly processing climbing performance according to claim 1, wherein the process of calculating the typical height comprises:
and 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 airplane climbing rate and the climbing altitude.
3. The method for rapidly processing climbing performance according to claim 1, wherein the process of obtaining the typical altitude climbing rate and climbing speed curve comprises:
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 a climbing angle by utilizing an airplane aerodynamic model and an engine power model, 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 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.
4. The method for rapidly processing climbing performance 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.
5. The method for rapidly processing climbing performance according to claim 1, wherein the full-stroke climbing performance parameters comprise:
the whole climbing time and the whole climbing fuel consumption.
6. The method for rapidly processing climbing performance according to claim 2, wherein the calculation formula of the typical height is as follows:
Hc=2/3*(Hend-Hbegin)+Hbegin（1）
wherein HCIs a typical height, HbeginIs the starting height, HendIs the termination height.
7. The method for rapidly processing climbing performance according to claim 3, wherein the calculation formula of the climbing rate at the preset speed is as follows:
Figure DEST_PATH_IMAGE002
wherein, VyFor the rate of climb, P is the engine thrust,
Figure DEST_PATH_IMAGE004
and
Figure DEST_PATH_IMAGE006
respectively is an aircraft climbing attack angle and an engine installation angle, Q is pneumatic resistance, G is climbing weight,
Figure DEST_PATH_IMAGE008
is a climb acceleration factor; cyIs the climbing aerodynamic lift coefficient, q is dynamic pressure, S is the wing area,
Figure DEST_PATH_IMAGE010
the climbing angle, V is the speed.
8. The method for rapidly processing the climbing performance according to claim 7, wherein the residual thrust force calculation formula is as follows:
Figure DEST_PATH_IMAGE012
wherein the content of the first and second substances,
Figure DEST_PATH_IMAGE014
for residual thrust, PavailFor available engine thrust, PreqThe thrust is required;
in addition, the climbing acceleration factor is calculated by the following formula:
Figure DEST_PATH_IMAGE016
（5）
wherein M is the flight Mach number, k is the air adiabatic exponent, TsCurrent altitude atmospheric temperature, T, for standard atmospheric conditionsnsIs the current altitude actual atmospheric temperature;
the calculation formula for calculating the climbing angle by using the climbing rate is as follows:
Figure DEST_PATH_IMAGE018
wherein the content of the first and second substances,
Figure 107693DEST_PATH_IMAGE010
the climbing angle and V is the speed.
9. The method for rapidly processing the climbing performance according to claim 4, wherein the calculation formula of the climbing rate maximum value point is as follows:
Vy’（Vclimb）=0 （7）
wherein, Vy’（Vclimb) Is the first derivative of the climbing rate-climbing speed curve function.
10. The method for rapidly processing the climbing performance according to claim 5, wherein the formulas of the whole climbing time and the whole climbing fuel consumption are respectively as follows:
Time=(Hend-Hbegin)/Vy（8）
Fuel=Time*Wf（9）
wherein, Time is the whole climbing Time, Fuel is the whole climbing Fuel consumption, WfIs the specific fuel consumption of the aircraft engine per unit time.
CN202210566220.5A 2022-05-24 2022-05-24 Climbing performance processing method Active CN114647994B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210566220.5A CN114647994B (en) 2022-05-24 2022-05-24 Climbing performance processing method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210566220.5A CN114647994B (en) 2022-05-24 2022-05-24 Climbing performance processing method

Publications (2)

Publication Number Publication Date
CN114647994A true CN114647994A (en) 2022-06-21
CN114647994B CN114647994B (en) 2022-10-28

Family

ID=81996944

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210566220.5A Active CN114647994B (en) 2022-05-24 2022-05-24 Climbing performance processing method

Country Status (1)

Country Link
CN (1) CN114647994B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115081252A (en) * 2022-08-16 2022-09-20 中国航空工业集团公司西安飞机设计研究所 Correction method for climbing performance data of multi-configuration airplane
CN116552804A (en) * 2023-07-10 2023-08-08 四川腾盾科技有限公司 Test flight planning method for verifying practical limit rise index of low-speed unmanned aerial vehicle
CN117332512A (en) * 2023-12-01 2024-01-02 中国航空工业集团公司西安飞机设计研究所 Processing method for correcting airspeed climbing performance and acceleration factor of aircraft and the like

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1602995A1 (en) * 2004-05-18 2005-12-07 AIRBUS France Method and device for generating a low altitude flight path to be followed by an aircraft
CN101393458A (en) * 2008-10-30 2009-03-25 北京控制工程研究所 Longitudinal control method for high altitude lifting of aerospaceplane
US20120277935A1 (en) * 2011-04-29 2012-11-01 Mn Veeresh Kumar System and method for aircraft performance predictions for climb flight phase
US20200026307A1 (en) * 2018-07-17 2020-01-23 Ge Aviation Systems, Llc Method and system for determining a climb profile
CN111767609A (en) * 2020-05-22 2020-10-13 成都飞机工业（集团）有限责任公司 Method for correcting climbing rate based on standard weight of test flight data
CN112069731A (en) * 2020-09-02 2020-12-11 中国航空无线电电子研究所 Flight simulation maneuver control optimization method based on genetic algorithm
CN113895645A (en) * 2021-12-09 2022-01-07 四川腾盾科技有限公司 Propeller unmanned aerial vehicle autonomous takeoff obstacle crossing capability analysis method
CN114065399A (en) * 2021-11-23 2022-02-18 北京航空航天大学 Unmanned aerial vehicle flight performance calculation method considering complex meteorological conditions
CN114065398A (en) * 2021-11-23 2022-02-18 北京航空航天大学 Flight performance calculation method for high-aspect-ratio flexible aircraft
CN114491793A (en) * 2021-12-31 2022-05-13 中国航空工业集团公司西安飞机设计研究所 Real-time calculation method for climbing performance data of transport aircraft

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1602995A1 (en) * 2004-05-18 2005-12-07 AIRBUS France Method and device for generating a low altitude flight path to be followed by an aircraft
CN101393458A (en) * 2008-10-30 2009-03-25 北京控制工程研究所 Longitudinal control method for high altitude lifting of aerospaceplane
US20120277935A1 (en) * 2011-04-29 2012-11-01 Mn Veeresh Kumar System and method for aircraft performance predictions for climb flight phase
US20200026307A1 (en) * 2018-07-17 2020-01-23 Ge Aviation Systems, Llc Method and system for determining a climb profile
CN111767609A (en) * 2020-05-22 2020-10-13 成都飞机工业（集团）有限责任公司 Method for correcting climbing rate based on standard weight of test flight data
CN112069731A (en) * 2020-09-02 2020-12-11 中国航空无线电电子研究所 Flight simulation maneuver control optimization method based on genetic algorithm
CN114065399A (en) * 2021-11-23 2022-02-18 北京航空航天大学 Unmanned aerial vehicle flight performance calculation method considering complex meteorological conditions
CN114065398A (en) * 2021-11-23 2022-02-18 北京航空航天大学 Flight performance calculation method for high-aspect-ratio flexible aircraft
CN113895645A (en) * 2021-12-09 2022-01-07 四川腾盾科技有限公司 Propeller unmanned aerial vehicle autonomous takeoff obstacle crossing capability analysis method
CN114491793A (en) * 2021-12-31 2022-05-13 中国航空工业集团公司西安飞机设计研究所 Real-time calculation method for climbing performance data of transport aircraft

Non-Patent Citations (9)

* Cited by examiner, † Cited by third party
Title
ANONYMOUS: "Examples of flight path optimisation using a multivariate gradient-search method. Addendum a: variation of optimumflight profile parameters with range", 《ENGINEERING SCIENCES DATA UNIT 2006 (E04)》 *
XIAOYAN ZHANG 等: "Research on Climb Performance and 4D Trajectory Prediction of Aircraft", 《2013 INTERNATIONAL CONFERENCE ON COMPUTER SCIENCES AND APPLICATIONS》 *
丁鼎等: "考虑波阻的民用飞机爬升性能计算方法", 《长江大学学报(自然科学版)理工卷》 *
傅职忠: "航路爬升性能计算", 《中国民航大学学报》 *
李乐等: "TBCC飞行器发动机尺寸选型及爬升策略设计", 《宇航学报》 *
李昌明: "基于平飞性能飞行试验的某型直升机爬升性能计算研究", 《科技传播》 *
李晓冬等: "超高层爬模系统通过伸臂桁架层时的设计及应用", 《中国港湾建设》 *
王玉等: "飞机最佳爬升速度计算与研究", 《中国民航飞行学院学报》 *
董新民等: "飞机等表速运动方程与稳态爬升参数计算", 《飞行力学》 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115081252A (en) * 2022-08-16 2022-09-20 中国航空工业集团公司西安飞机设计研究所 Correction method for climbing performance data of multi-configuration airplane
CN116552804A (en) * 2023-07-10 2023-08-08 四川腾盾科技有限公司 Test flight planning method for verifying practical limit rise index of low-speed unmanned aerial vehicle
CN117332512A (en) * 2023-12-01 2024-01-02 中国航空工业集团公司西安飞机设计研究所 Processing method for correcting airspeed climbing performance and acceleration factor of aircraft and the like
CN117332512B (en) * 2023-12-01 2024-03-19 中国航空工业集团公司西安飞机设计研究所 Processing method for correcting airspeed climbing performance and acceleration factor of aircraft and the like

Also Published As

Publication number Publication date
CN114647994B (en) 2022-10-28

Similar Documents

Publication Publication Date Title
CN114647994B (en) Climbing performance processing method
CN112947534B (en) Hypersonic aircraft hold-down section self-adaptive pseudo-spectrum method track optimization method
CN109858106A (en) Aircraft winglet stroke optimization method based on Gauss puppet spectrometry
CN112528478B (en) Rapid compilation method for gust load spectrum of unmanned aerial vehicle
CN114065399B (en) Unmanned aerial vehicle flight performance calculation method considering complex meteorological conditions
CN114065398B (en) Flight performance calculation method for high-aspect-ratio flexible aircraft
CN113589847B (en) Method for determining flight radius of flexible aircraft
Chyczewski et al. Summary of the First AIAA Stability and Control Prediction Workshop
CN114611420A (en) Unsteady aerodynamic force calculation precision evaluation and correction method
CN114638129B (en) Climbing capacity data obtaining method based on engine state change
CN116700013A (en) Mixed optimization method for fastest climbing track of aircraft
CN114912284A (en) Flight management system climbing performance prediction algorithm based on first rule
CN115017721B (en) Method and device for identifying cruise characteristics of airplane and flight control system
CN114218684B (en) Method for determining dynamic load amplification factor in civil aircraft load spectrum
CN111717411B (en) Method for correcting cruise thrust increment based on test flight data standard weight
Guruswamy et al. Efficient algorithm for unsteady transonic aerodynamics of low-aspect-ratio wings
CN106873363A (en) A kind of modeling method of aircraft angle of attack signal
CN110532604A (en) Calculation method with rear winglet blade aerodynamic load under a kind of dynamic stall state
CN117332512B (en) Processing method for correcting airspeed climbing performance and acceleration factor of aircraft and the like
Hasan et al. Optimal airfoil design and wing analysis for solar-powered high altitude platform station
CN111191358B (en) Air-breathing supersonic missile trajectory optimization design method
CN115081252B (en) Correction method for climbing performance data of multi-configuration airplane
Derbunovich et al. Effect of flow contraction on the level of turbulence
CN117744539B (en) Method for generating initial flow field of hypersonic vehicle based on flow characteristics
Yajnik Energy-turn-rate characteristics and turn performance of an aircraft

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant