Method and system for calculating balance position of taper sleeve of airplane soft refueling system

Abstract

The invention belongs to the technical field of structural dynamics, and particularly relates to a method and system for calculating the balance position of a taper sleeve of an aircraft soft refueling system, the aerodynamic force direction of the taper sleeve and the pneumatic differential pressure force direction of a refueling hose are determined, the aerodynamic force of the taper sleeve is calculated according to basic parameters, and the pneumatic differential pressure force coefficient cn and the pneumatic differential pressure force of the refueling hose are calculated; the method comprises the following steps: acquiring stress state data of a hose-taper sleeve combination in a balanced state, establishing a torque balance equation by combining a taper sleeve aerodynamic force, a refueling hose pneumatic differential pressure force coefficient and a refueling hose pneumatic differential pressure torque, and combining the torque balance equation with a hose length distance equation to obtain a binary quadratic equation set; and solving to obtain a vertical distance z and a heading distance x of the balance position of the taper sleeve relative to the root of the hose. According to a small amount of data, the winding moment of the reel of the soft refueling system of the airplane can be quickly calculated, solving by unsteady fluid-solid coupling analysis or mathematical model establishment through programming is avoided, and the calculation cost and period of the balance position of the taper sleeve are greatly reduced.

Description

Technical Field

[0001] The present application belongs to the field of structural dynamics technology, and in particular relates to a method and system for calculating the equilibrium position of a cone sleeve of an aircraft soft refueling system. Background Art

[0002] Aerial refueling is mainly divided into hard refueling and soft refueling. my country currently uses soft refueling, that is, a hose-drogue refueling system. When the hose is fully released and in a towing balance state, the balance position of the drogue will determine the flow field environment of the receiving aircraft during refueling. The tanker wake and engine jet will affect the aerodynamic compatibility of the tanker and the receiving aircraft. If the receiving aircraft is in an improper position, it may affect the handling stability of the receiving aircraft, and in severe cases it may cause the receiving aircraft to lose control or even crash.

[0003] The calculation of the equilibrium position of the drogue sleeve of the aircraft soft refueling system's hose-drogue sleeve combination during drag balance is often solved through unsteady fluid-solid coupling analysis or programming to establish a mathematical model. The above methods have high calculation costs and long cycles, and are difficult to meet the rapid iteration requirements of the initial stage of aircraft design. The determination of the drogue sleeve equilibrium position often lacks a simple and universal calculation method. Summary of the invention

[0004] The purpose of the present application is to provide a method and system for calculating the equilibrium position of a cone sleeve of an aircraft soft refueling system, so as to solve the problems of high cost and long cycle of the existing cone sleeve equilibrium position calculation.

[0005] The technical solution of the present application is: a method for calculating the equilibrium position of a cone sleeve of an aircraft soft refueling system comprises:

[0006] Determine the basic parameters required for calculation;

[0007] Determine the aerodynamic direction of the drogue, and calculate the aerodynamic force of the drogue based on the basic parameters of the drogue aerodynamic drag coefficient, the equivalent aerodynamic area of ​​the drogue, the true air speed of the far-field incoming flow, and the air density corresponding to the flight altitude;

[0008] According to the basic parameters of hose diameter, far-field incoming flow true air speed, aerodynamic viscosity coefficient corresponding to the flight altitude and air density, the local Reynolds number Re of the aerodynamic pressure difference force is calculated. p =ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient C according to the local Reynolds number of the aerodynamic pressure difference force n ;

[0009] Determine the direction of the aerodynamic pressure differential force of the refueling hose, and according to the basic parameters including hose length, hose diameter, far-field incoming flow true air speed, and air density corresponding to the flight altitude, assume that the vertical distance of the drogue sleeve equilibrium position relative to the hose root is z, and the heading distance is x, to obtain the aerodynamic pressure differential force of the refueling hose; obtain the stress state data of the hose-drogue sleeve combination in the equilibrium state, and establish a moment balance equation by combining the drogue sleeve aerodynamic force, the aerodynamic pressure differential force coefficient of the refueling hose, and the aerodynamic pressure differential moment of the refueling hose; combine the moment balance equation with the hose length distance equation to obtain a set of two-variable quadratic equations, and solve the set of two-variable quadratic equations to obtain the vertical distance of the drogue sleeve equilibrium position relative to the hose root as z and the heading distance as x.

[0010] Preferably, the basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

[0011] Preferably, the aerodynamic force direction of the cone sleeve is in the direction of the airflow; the aerodynamic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

[0012] Preferably, the calculation formula of the cone sleeve aerodynamic force is:

[0013]

[0014] Preferably, the pneumatic pressure differential force coefficient C of the refueling hose n The calculation formula is:

[0015]

[0016] Preferably, the calculation formula for the pneumatic pressure difference force of the refueling hose is:

[0017]

[0018] Preferably, the torque balance equation is:

[0019]

[0020] The hose length distance equation is x 2 +z 2 = l 2 .

[0021] As a specific implementation, a drogue equilibrium position calculation system for an aircraft soft refueling system includes a basic parameter acquisition module, a drogue aerodynamic force acquisition module, a refueling hose aerodynamic pressure difference force coefficient acquisition module, a refueling hose aerodynamic pressure difference force acquisition module, and an equation solving module. The basic parameter acquisition module is used to determine the basic parameters required for calculation;

[0022] The drogue aerodynamic force acquisition module is used to determine the drogue aerodynamic force direction and calculate the drogue aerodynamic force according to the drogue aerodynamic drag coefficient, drogue equivalent aerodynamic area, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters.

[0023] The aerodynamic pressure differential force coefficient acquisition module of the refueling hose is used to calculate the local Reynolds number Re of the aerodynamic pressure differential force according to the hose diameter, the true air speed of the far-field incoming flow, the aerodynamic viscosity coefficient corresponding to the flight altitude, and the air density in the basic parameters. p =ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient C according to the local Reynolds number of the aerodynamic pressure difference force n ;

[0024] The pneumatic pressure differential force acquisition module of the refueling hose is used to determine the direction of the pneumatic pressure differential force of the refueling hose. According to the hose length, hose diameter, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters, it is assumed that the vertical distance of the drogue balance position relative to the hose root is z and the heading distance is x, and the pneumatic pressure differential force of the refueling hose is obtained;

[0025] The equation solving module is used to obtain the stress state data of the hose-drogue combination in the equilibrium state, and to establish the moment balance equation by combining the drogue aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference moment of the refueling hose. The moment balance equation is combined with the hose length distance equation to obtain a set of two-variable quadratic equations. By solving the set of two-variable quadratic equations, the vertical distance z and the heading distance x of the equilibrium position of the drogue relative to the root of the hose are obtained.

[0026] Preferably, the basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

[0027] Preferably, the aerodynamic force direction of the cone sleeve is in the direction of the airflow; the aerodynamic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

[0028] Preferably, the calculation formula of the cone sleeve aerodynamic force is:

[0029]

[0030] Preferably, the pneumatic pressure differential force coefficient C of the refueling hose n The calculation formula is:

[0031]

[0032] Preferably, the calculation formula for the pneumatic pressure difference force of the refueling hose is:

[0033]

[0034] Preferably, the torque balance equation is:

[0035]

[0036] The hose length distance equation is x 2 +z 2 = l 2 .

[0037] The method and system for calculating the equilibrium position of the cone sleeve of an aircraft soft refueling system of the present application can quickly calculate the reel rewinding torque of the aircraft soft refueling system based on a small amount of data, avoiding unsteady fluid-solid coupling analysis or programming to establish a mathematical model for solution, greatly reducing the calculation cost and cycle of the cone sleeve equilibrium position, and providing a simple and universal calculation method for the design of an aircraft soft refueling system. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0039] Figure 1 This is a schematic diagram of the overall process of this application;

[0040] Figure 2 This is a schematic diagram of the stress state of the hose-cone sleeve combination in this application. DETAILED DESCRIPTION

[0041] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] A method for calculating the equilibrium position of the drogue of an aircraft soft refueling system, such as Figure 1 As shown, the following steps are included:

[0043] Step S100, determining the basic parameters required for calculation

[0044] The basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

[0045] Step S200, calculating the aerodynamic force of the drogue

[0046] Determine the direction of the drogue aerodynamic force, and calculate the drogue aerodynamic force based on the basic parameters including the drogue aerodynamic drag coefficient, the drogue equivalent aerodynamic area, the true air speed of the far-field incoming flow, and the air density corresponding to the flight altitude.

[0047] Among them, the direction of the aerodynamic force of the cone sleeve is in the direction of the airflow (that is, in the opposite direction of the aircraft).

[0048] The calculation formula of the cone sleeve aerodynamic force is:

[0049]

[0050] Step S300, calculating the pneumatic pressure differential force coefficient of the refueling hose

[0051] According to the basic parameters of hose diameter, far-field incoming flow true air speed, aerodynamic viscosity coefficient corresponding to the flight altitude and air density, the local Reynolds number Re of the aerodynamic pressure difference force is calculated. p =ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient C according to the local Reynolds number of the aerodynamic pressure difference force n .

[0052] Pneumatic pressure differential force coefficient C of refueling hose n The calculation formula is:

[0053]

[0054] Step S400, calculating the pneumatic pressure difference of the refueling hose

[0055] Determine the direction of the aerodynamic pressure differential force of the refueling hose. According to the basic parameters of the hose length, hose diameter, far-field incoming true air speed, and air density corresponding to the flight altitude, assume that the vertical distance of the drogue equilibrium position relative to the root of the hose is z and the heading distance is x, and obtain the aerodynamic pressure differential force of the refueling hose.

[0056] The pneumatic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

[0057] The calculation formula of the pneumatic pressure difference force of the refueling hose is:

[0058]

[0059] Step S500, solving a set of simultaneous quadratic equations

[0060] The stress state data of the hose-drogue combination in the equilibrium state are obtained, and the torque balance equation is established by combining the drogue aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference moment of the refueling hose. The torque balance equation is combined with the hose length distance equation to obtain a set of two-variable quadratic equations. By solving the set of two-variable quadratic equations, the vertical distance z and the heading distance x of the equilibrium position of the drogue relative to the root of the hose are obtained.

[0061] The stress state data is as follows Figure 2 As shown, according to the moment balance, the equation relationship is as follows.

[0062]

[0063] According to the calculation results of the cone sleeve aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference force of the refueling hose, the moment balance equation is converted to:

[0064]

[0065] The hose length distance equation is x 2 +z 2 = l 2 .

[0066] Through the above design, the reel winding torque of the aircraft soft refueling system can be quickly calculated based on a small amount of data, avoiding the unsteady fluid-solid coupling analysis or programming to establish a mathematical model for solution, greatly reducing the calculation cost and cycle of the cone sleeve equilibrium position, and providing a simple and universal calculation method for the design of the aircraft soft refueling system.

[0067] As a specific implementation, it also includes a cone sleeve equilibrium position calculation system for an aircraft soft refueling system, which adopts the above design and includes a basic parameter acquisition module, a cone sleeve aerodynamic force acquisition module, a refueling hose aerodynamic pressure difference force coefficient acquisition module, a refueling hose aerodynamic pressure difference force acquisition module and an equation solving module.

[0068] The basic parameter acquisition module is used to determine the basic parameters required for calculation;

[0069] The drogue aerodynamic force acquisition module is used to determine the drogue aerodynamic force direction and calculate the drogue aerodynamic force according to the drogue aerodynamic drag coefficient, drogue equivalent aerodynamic area, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters.

[0070] The aerodynamic pressure differential force coefficient acquisition module of the refueling hose is used to calculate the local Reynolds number Re of the aerodynamic pressure differential force according to the hose diameter, the true air speed of the far-field incoming flow, the aerodynamic viscosity coefficient corresponding to the flight altitude, and the air density in the basic parameters. p=ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient C according to the local Reynolds number of the aerodynamic pressure difference force n ;

[0071] The pneumatic pressure differential force acquisition module of the refueling hose is used to determine the direction of the pneumatic pressure differential force of the refueling hose. According to the hose length, hose diameter, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters, it is assumed that the vertical distance of the drogue balance position relative to the hose root is z and the heading distance is x, and the pneumatic pressure differential force of the refueling hose is obtained;

[0072] The equation solving module is used to obtain the stress state data of the hose-drogue combination in the equilibrium state, and to establish the moment balance equation by combining the drogue aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference moment of the refueling hose. The moment balance equation is combined with the hose length distance equation to obtain a set of two-variable quadratic equations. By solving the set of two-variable quadratic equations, the vertical distance z and the heading distance x of the equilibrium position of the drogue relative to the root of the hose are obtained.

[0073] Preferably, the basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

[0074] Preferably, the aerodynamic force direction of the cone sleeve is in the direction of the airflow; the aerodynamic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

[0075] Preferably, the calculation formula of the cone sleeve aerodynamic force is:

[0076]

[0077] Preferably, the pneumatic pressure differential force coefficient C of the refueling hose n The calculation formula is:

[0078]

[0079] Preferably, the calculation formula for the pneumatic pressure difference force of the refueling hose is:

[0080]

[0081] Preferably, the torque balance equation is:

[0082]

[0083] The hose length distance equation is x 2 +z 2 = l 2 .

[0084] As a specific implementation method, a specific example is used to illustrate:

[0085] Step S100, hose length l = 22.86m, hose diameter D = 0.067m, hose gravity G l =921N, cone sleeve aerodynamic drag coefficient C D =0.831, cone sleeve equivalent aerodynamic area S D =0.283m 2 , cone sleeve weight G D =295N, assuming that the true air velocity of the far-field incoming flow is v = 200m / s, the aerodynamic viscosity coefficient u corresponding to the flight altitude of 8000m is u = 1.527×10 - 5 kg / (m·s), air density ρ=0.526kg / m 3 .

[0086] Step S200, calculating and obtaining the aerodynamic force of the drogue.

[0087]

[0088] Step S300, calculating the aerodynamic pressure differential force coefficient.

[0089] Re p =ρ·v·D / u=0.526×200×0.067+1.527÷10 -5 =4.6×10 5

[0090]

[0091] Step S400, calculating the pneumatic pressure difference force of the refueling hose.

[0092]

[0093] Step S500, listing equations for moment balance.

[0094]

[0095] 2474×z+0.5×6.47×22.86×z 2 =295×x+0.5×921×x

[0096] The above formula and x 2 +z 2 = l 2 By combining the two-variable quadratic equations, we can get the vertical distance z=5.76m and the heading distance x=22.12m of the cone sleeve equilibrium position relative to the root of the hose.

[0097] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0098] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for calculating the equilibrium position of a drogue of an aircraft soft refueling system, characterized in that: include: Determine the basic parameters required for calculation; Determine the aerodynamic direction of the drogue, and calculate the aerodynamic force of the drogue based on the basic parameters of the drogue aerodynamic drag coefficient, the equivalent aerodynamic area of ​​the drogue, the true air speed of the far-field incoming flow, and the air density corresponding to the flight altitude; According to the basic parameters of hose diameter, far-field incoming flow true air speed, aerodynamic viscosity coefficient corresponding to the flight altitude and air density, the local Reynolds number Re of the aerodynamic pressure difference force is calculated. p =ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient c according to the local Reynolds number of the aerodynamic pressure difference force n ; Determine the direction of the pneumatic pressure differential force of the refueling hose. According to the basic parameters of the hose length, hose diameter, far-field incoming flow true air speed, and air density corresponding to the flight altitude, assume that the vertical distance of the drogue equilibrium position relative to the hose root is z and the heading distance is x, and obtain the pneumatic pressure differential force of the refueling hose. The stress state data of the hose-drogue combination in the equilibrium state are obtained, and the torque balance equation is established by combining the drogue aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference moment of the refueling hose. The torque balance equation is combined with the hose length distance equation to obtain a set of two-variable quadratic equations. By solving the set of two-variable quadratic equations, the vertical distance z and the heading distance x of the equilibrium position of the drogue relative to the root of the hose are obtained.

2. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 1, characterized in that: The basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

3. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 1, characterized in that: The pneumatic force direction of the cone sleeve is along the airflow direction; the pneumatic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

4. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 2, characterized in that: The calculation formula of the cone sleeve aerodynamic force is:

5. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 2, characterized in that: Pneumatic pressure differential force coefficient c of refueling hose n The calculation formula is:

6. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 2, characterized in that: The calculation formula of the pneumatic pressure difference force of the refueling hose is:

7. The method for calculating the equilibrium position of the drogue of the aircraft soft refueling system according to claim 2, characterized in that: The torque balance equation is: The hose length distance equation is x 2 +z 2 = l 2 (The general direction of how to combine has been explained in claim 1, and here we just add details and there is no need to repeat them).

8. A drogue balance position calculation system for an aircraft soft refueling system, using the method according to any one of claims 1 to 7, characterized in that: It includes a basic parameter acquisition module, a cone sleeve aerodynamic force acquisition module, a refueling hose aerodynamic pressure difference force coefficient acquisition module, a refueling hose aerodynamic pressure difference force acquisition module and an equation solving module. The basic parameter acquisition module is used to determine the basic parameters required for calculation; The drogue aerodynamic force acquisition module is used to determine the drogue aerodynamic force direction and calculate the drogue aerodynamic force according to the drogue aerodynamic drag coefficient, drogue equivalent aerodynamic area, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters. The aerodynamic pressure differential force coefficient acquisition module of the refueling hose is used to calculate the local Reynolds number Re of the aerodynamic pressure differential force according to the hose diameter, the true air speed of the far-field incoming flow, the aerodynamic viscosity coefficient corresponding to the flight altitude, and the air density in the basic parameters. p =ρ·v·D / u, and then calculate the aerodynamic pressure difference force coefficient c according to the local Reynolds number of the aerodynamic pressure difference force n ; The pneumatic pressure differential force acquisition module of the refueling hose is used to determine the direction of the pneumatic pressure differential force of the refueling hose. According to the hose length, hose diameter, far-field incoming flow true air speed, and air density corresponding to the flight altitude in the basic parameters, it is assumed that the vertical distance of the drogue balance position relative to the hose root is z and the heading distance is x, and the pneumatic pressure differential force of the refueling hose is obtained; The equation solving module is used to obtain the stress state data of the hose-drogue combination in the equilibrium state, and to establish the moment balance equation by combining the drogue aerodynamic force, the aerodynamic pressure difference force coefficient of the refueling hose and the aerodynamic pressure difference moment of the refueling hose. The moment balance equation is combined with the hose length distance equation to obtain a set of two-variable quadratic equations. By solving the set of two-variable quadratic equations, the vertical distance z and the heading distance x of the equilibrium position of the drogue relative to the root of the hose are obtained.

9. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 8, characterized in that: The basic parameters include hose length l, hose diameter D, hose weight G l , Driving sleeve aerodynamic drag coefficient C D , cone sleeve equivalent aerodynamic area S D , cone sleeve gravity G D , the true air speed v of the far-field incoming flow, the aerodynamic viscosity coefficient u corresponding to the flight altitude, and the air density ρ.

10. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 8, characterized in that: The pneumatic force direction of the cone sleeve is along the airflow direction; the pneumatic pressure difference force direction of the refueling hose is perpendicular to the hose axis and upward.

11. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 9, characterized in that: The calculation formula of the cone sleeve aerodynamic force is:

12. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 9, characterized in that: Pneumatic pressure differential force coefficient c of refueling hose n The calculation formula is:

13. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 9, characterized in that: The calculation formula of the pneumatic pressure difference force of the refueling hose is:

14. The aircraft soft refueling system drogue equilibrium position calculation system according to claim 9, characterized in that: The torque balance equation is: The hose length distance equation is x 2 +z 2 = l 2 .

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