Propeller aircraft yaw moment characteristic calculation method considering dynamic influence

Abstract

The invention belongs to the technical field of propeller aircraft yaw moment calculation, and particularly relates to a propeller aircraft yaw moment characteristic calculation method considering dynamic influence, which fully considers the influence of propeller aircraft attack angle, speed, engine tension, engine number, propeller diameter and rotating speed, blade efficiency and the like on yaw moment. According to the method, the yaw moment coefficient generated by the normal force of the propeller disc is accurately calculated, the yaw moment coefficient of the propeller aircraft can be accurately obtained, the method is used for calculating the yaw moment of the propeller aircraft, and effective support can be provided for design, improvement and control of the propeller aircraft.

Description

Technical Field

[0001] The present application belongs to the technical field of yaw moment calculation of propeller aircraft, and specifically relates to a method for calculating yaw moment characteristics of propeller aircraft taking into account the influence of power. Background Art

[0002] Compared with jet-powered aircraft, the yaw moment of propeller aircraft is more sensitive to power influence and the calculation method is more complicated.

[0003] Dynamic influences such as the propeller disc normal force will cause significant changes in the yaw moment of a propeller aircraft. Currently, there is a lack of a method to calculate the yaw moment characteristics of a propeller aircraft that fully considers the dynamic influence, making it difficult to accurately obtain the yaw moment of a propeller aircraft and provide effective support for the design, improvement and control of propeller aircraft.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a method for calculating the yaw moment characteristics of a propeller aircraft taking into account the influence of power, so as to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of this application is:

[0007] A method for calculating yaw moment characteristics of a propeller aircraft considering dynamic influence, comprising:

[0008] Step 1: Calculate propeller parameter β0;

[0009] Step 2: Using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on propeller speed and diameter: Nα ' and its propeller disk normal force coefficient - angle of attack derivative C Nα ;

[0010] Step 3: Use the propeller parameter β0 and the derivative of the normal force coefficient with respect to the angle of attack C defined based on the propeller speed and diameter Nα ', calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area

[0011] The derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area is Calculate the yaw moment coefficient angle of attack correction △C n ;

[0012] The yaw moment coefficient angle of attack correction △C n , make corrections and obtain the yaw moment coefficient C considering the dynamic effect n-on .

[0013] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, step 1 includes:

[0014] S11. Calculate the propeller thrust coefficient C' based on engine thrust, propeller speed, and propeller disk diameter T ;

[0015] S12. Calculate the aircraft's advancement ratio J;

[0016] S13, propeller thrust coefficient C' defined based on engine thrust, propeller speed, and propeller disk diameter T With the aircraft's advance ratio J, calculate the propeller parameter β0.

[0017] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S11 is specifically:

[0018]

[0019] in,

[0020] p e is the pulling force of the engine;

[0021] ρ is the air density;

[0022] n is the propeller speed;

[0023] d is the propeller disc diameter.

[0024] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S12 is specifically:

[0025]

[0026] in,

[0027] V0 is the incoming flow velocity.

[0028] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S13 is specifically:

[0029]

[0030] in,

[0031] σ e is the inherent effectiveness factor of the blade.

[0032] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, in S13:

[0033] σ e = = 0.0003B × AF;

[0034]

[0035] in,

[0036] B is the number of blades;

[0037] AF is the active factor of the paddle;

[0038] c b is the chord length of the blade spanwise station section;

[0039] r is the spanwise position of the blade section;

[0040] R is the radius of the propeller disc.

[0041] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, in step 2, for the propellers rotating in the same direction, the method includes:

[0042] S211, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα ';

[0043] S211, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα ';

[0044] S213, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

[0045] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S211 is specifically:

[0046]

[0047] in,

[0048] σ e is the inherent effectiveness factor of the blade;

[0049] J is the aircraft's forward ratio;

[0050] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0051] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S212 is specifically:

[0052] S p =πd 2 / 4;

[0053] in,

[0054] d is the propeller disc diameter.

[0055] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S213 is specifically:

[0056]

[0057] in,

[0058] S ref is the reference area of ​​the wing.

[0059] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, in step 2, for the propellers rotating in opposite directions, the method includes:

[0060] S221, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα ';

[0061] S222. Calculate the propeller disc area S p ;

[0062] S223, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

[0063] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S221 is specifically:

[0064]

[0065] in,

[0066] σ e is the inherent effectiveness factor of the blade;

[0067] J is the aircraft's forward ratio;

[0068] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0069] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S222 is specifically:

[0070] S p =πd 2 / 4;

[0071] in,

[0072] d is the propeller disc diameter.

[0073] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S223 is specifically:

[0074]

[0075] in,

[0076] S ref is the reference area of ​​the wing.

[0077] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, in step 3, for the propellers rotating in the same direction, the method includes:

[0078] S311, using propeller parameter β0, calculate the derivative of the yaw moment coefficient defined based on propeller speed and diameter with respect to the angle of attack

[0079] S312, derivative of the yaw moment coefficient with respect to the angle of attack defined based on the propeller speed and diameter Calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area

[0080] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S311 is specifically:

[0081]

[0082] in,

[0083] σ e is the inherent effectiveness factor of the blade;

[0084] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0085] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, S312 is specifically:

[0086]

[0087] in,

[0088] J is the aircraft's forward ratio;

[0089] S p is the paddle disc area;

[0090] d is the diameter of the propeller disc;

[0091] S ref is the wing reference area;

[0092] b w For wingspan.

[0093] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, in step 3, for the propellers rotating in opposite directions, specifically:

[0094]

[0095] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, step 4 includes:

[0096] S41. Calculate the effective angle of attack α of the propeller e , specifically:

[0097] α e =α-θ pb ;

[0098] in,

[0099] α is the fuselage angle of attack;

[0100] θ pb is the angle of attack of the tension line to the fuselage;

[0101] S42, based on the yaw moment coefficient derivative based on the incoming flow velocity pressure and the wing reference area and the effective angle of attack α of the propeller e , calculate the yaw moment coefficient angle of attack correction △C n , specifically:

[0102]

[0103] in,

[0104] N is the number of engines;

[0105] △C nα0 is the yaw moment coefficient generated by zero angle of attack power.

[0106] According to at least one embodiment of the present application, in the above-mentioned method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, step five is specifically as follows:

[0107]

[0108] in,

[0109] is the heading static stability derivative under no-power condition;

[0110] β is the sideslip angle. This application has at least the following beneficial technical effects:

[0111] A method for calculating the yaw moment characteristics of a propeller aircraft taking into account the influence of power is provided, which fully considers the influence of the propeller aircraft's angle of attack, speed, engine thrust, number of engines, propeller diameter and rotation speed, blade efficiency, etc. on the yaw moment, accurately calculates the yaw moment coefficient generated by the normal force of the propeller disc, and then can accurately obtain the yaw moment coefficient of the propeller aircraft, which is used for the calculation of the yaw moment of the propeller aircraft, and can provide effective support for the design, improvement and control of the propeller aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0112] Figure 1 It is a schematic diagram of a method for calculating the yaw moment characteristics of a propeller aircraft taking into account the influence of power provided in an embodiment of the present application.

[0113] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0114] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0115] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0116] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0117] In a relatively unpowered state, with a large pull coefficient, the yaw moment of the aircraft will increase significantly as the angle of attack increases. Therefore, this application provides a method for calculating the yaw moment characteristics of a propeller aircraft taking into account the influence of power, such as Figure 1 shown.

[0118] Step 1: Calculate propeller parameter β0.

[0119] S11. Calculate the propeller thrust coefficient C' based on engine thrust, propeller speed, and propeller disk diameter T .

[0120]

[0121] in,

[0122] p e is the pulling force of the engine;

[0123] ρ is the air density;

[0124] n is the propeller speed;

[0125] d is the propeller disc diameter.

[0126] S12. Calculate the aircraft's forward ratio J.

[0127]

[0128] in,

[0129] V0 is the incoming flow velocity.

[0130] S13, propeller thrust coefficient C' defined based on engine thrust, propeller speed, and propeller disk diameter T With the aircraft's advance ratio J, calculate the propeller parameter β0.

[0131]

[0132] in,

[0133] σ e is the inherent effective factor of the blade, which can be calculated as follows:

[0134] σ e = = 0.0003B × AF ... 2-1

[0135] in,

[0136] B is the number of blades;

[0137] AF is the activity factor of the blade, and its calculation can be referred to as follows:

[0138]

[0139] in,

[0140] c b is the chord length of the blade spanwise station section;

[0141] r is the spanwise position of the blade section;

[0142] R is the radius of the propeller disc.

[0143] To solve the propeller parameter β0, we can first calculate the propeller thrust coefficient C' defined based on the engine thrust, propeller speed, and propeller disk diameter. T , then discretize the propeller parameter β0 between [0,90], construct the propeller parameter β0 array, and use the interpolation algorithm to solve the numerical solution of the propeller parameter β0.

[0144] Step 2: Using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on propeller speed and diameter: Nα ' and its propeller disk normal force coefficient - angle of attack derivative C Nα .

[0145] For co-rotating propellers:

[0146] S211, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα '.

[0147]

[0148] in,

[0149] σ e is the inherent effectiveness factor of the blade;

[0150] J is the aircraft's forward ratio;

[0151] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0152] S212. Calculate the propeller disc area S p .

[0153] S p =πd 2 / 4……3-2

[0154] in,

[0155] d is the propeller disc diameter.

[0156] S213, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

[0157]

[0158] in,

[0159] S ref is the reference area of ​​the wing.

[0160] For counter-rotating propellers:

[0161] S221, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα '.

[0162]

[0163] in,

[0164] σ e is the inherent effectiveness factor of the blade;

[0165] J is the aircraft's forward ratio;

[0166] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0167] S222. Calculate the propeller disc area S p .

[0168] S p =πd2 / 4……4-2

[0169] in,

[0170] d is the propeller disc diameter.

[0171] S223, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

[0172]

[0173] in,

[0174] S ref is the reference area of ​​the wing.

[0175] Propeller disk normal force coefficient-angle of attack derivative C Nα , is the normal force derivative based on the incoming flow pressure and the wing reference area.

[0176] Step 3: Use the propeller parameter β0 and the derivative of the normal force coefficient with respect to the angle of attack C defined based on the propeller speed and diameter Nα ', calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area

[0177] For co-rotating propellers:

[0178] S311, using propeller parameter β0, calculate the derivative of the yaw moment coefficient defined based on propeller speed and diameter with respect to the angle of attack

[0179]

[0180] in,

[0181] σ e is the inherent effectiveness factor of the blade;

[0182] C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

[0183] S312, derivative of the yaw moment coefficient with respect to the angle of attack defined based on the propeller speed and diameter Calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area

[0184]

[0185] in,

[0186] J is the aircraft's forward ratio;

[0187] S p is the paddle disc area;

[0188] d is the diameter of the propeller disc;

[0189] S ref is the wing reference area;

[0190] b w For wingspan.

[0191] For counter-rotating propellers:

[0192]

[0193] Step 4: Derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area Calculate the yaw moment coefficient angle of attack correction △C n .

[0194] S41. Calculate the effective angle of attack α of the propeller e .

[0195] α e =α-θ pb ……7-1

[0196] in,

[0197] α is the fuselage angle of attack;

[0198] θ pb is the angle of attack of the tension line on the fuselage.

[0199] S42, based on the yaw moment coefficient derivative based on the incoming flow velocity pressure and the wing reference area and the effective angle of attack α of the propeller e , calculate the yaw moment coefficient angle of attack correction △C n .

[0200]

[0201] in,

[0202] N is the number of engines;

[0203] △C nα0 is the yaw moment coefficient generated by zero angle of attack power.

[0204] Step 5: Use the yaw moment coefficient to calculate the angle of attack correction value △C n , make corrections and obtain the yaw moment coefficient C considering the dynamic effect n-on .

[0205]

[0206] in,

[0207] is the heading static stability derivative under no-power condition;

[0208] β is the sideslip angle.

[0209] In a specific embodiment, the propeller aircraft has a wing area of ​​65m2 and a wingspan of 26.2m. Two turboprop engines rotating in the same direction are suspended under the wing, with a propeller disk diameter of 4.4m, 6 blades, and a blade parameter AF of 188. The angle of attack of the engine thrust axis relative to the fuselage axis is 1°, and the heading static stability derivative of the aircraft at zero angle of attack in the unpowered state is 0.149 / rad. The incoming flow velocity is 75m / s, the engine speed is 23.6 rpm, the corresponding engine thrust is 33.56KN, and the yaw moment coefficient at zero angle of attack and zero sideslip angle is -0.0006. The aircraft has an angle of attack of 11° and a sideslip angle of 10°. The yaw moment coefficient is calculated using the method for calculating the yaw moment characteristics of a propeller aircraft taking into account the influence of power disclosed in the above embodiment, and the specific reference may be made as follows:

[0210] 1) Calculate β0, as shown in Table 1:

[0211] 2) Calculate C Nα '、C Nα , as shown in Table 2:

[0212] 3) Calculation As shown in Table 3 below:

[0213] 4) Calculate △C n , as shown in Table 4 below:

[0214] 5) Calculate C n-on , as shown in Table 5 below:

[0215] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power, characterized in that: include: Step 1: Calculate propeller parameter β0; Step 2: Using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on propeller speed and diameter: Nα ' and its propeller disk normal force coefficient - angle of attack derivative C Nα ; Step 3: Use the propeller parameter β0 and the derivative of the normal force coefficient with respect to the angle of attack C defined based on the propeller speed and diameter Nα ', calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area Step 4: Derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area Calculate the yaw moment coefficient angle of attack correction △C n ; Step 5: Use the yaw moment coefficient to calculate the angle of attack correction value △C n , make corrections and obtain the yaw moment coefficient C considering the dynamic effect n-on .

2. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: Step one includes: S11. Calculate the propeller thrust coefficient C based on engine thrust, propeller speed, and propeller disk diameter. T ; S12. Calculate the aircraft's advancement ratio J; S13, propeller thrust coefficient C' defined based on engine thrust, propeller speed, and propeller disk diameter T With the aircraft's advance ratio J, calculate the propeller parameter β0.

3. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 2, characterized in that: S11 is as follows: in, p e is the pulling force of the engine; ρ is the air density; n is the propeller speed; d is the propeller disc diameter.

4. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 3, characterized in that: S12 is specifically: in, V0 is the incoming flow velocity.

5. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 4, characterized in that: S13 is specifically: in, σ e is the inherent effectiveness factor of the blade.

6. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 5, characterized in that: In S13: s e ==0.0003B×AF; in, B is the number of blades; AF is the active factor of the paddle; c b is the chord length of the blade spanwise station section; r is the spanwise position of the blade section; R is the radius of the propeller disc.

7. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 6, characterized in that: In step 2, for the propellers to rotate in the same direction, the following steps are performed: S211, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα '; S211, using propeller parameter β0, calculate the derivative C of the normal force coefficient ' defined based on propeller speed and diameter with respect to the angle of attack Nα ; S213, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

8. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 7, characterized in that: S211 is as follows: in, σ e is the inherent effectiveness factor of the blade; J is the aircraft's forward ratio; C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

9. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 8, characterized in that: S212 is specifically: S p =πd 2 / 4; in, d is the propeller disc diameter.

10. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 9, characterized in that: S213 is specifically: in, S ref is the reference area of ​​the wing.

11. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: In step 2, for the propellers rotating in opposite directions, the following steps are performed: S221, using propeller parameter β0, calculate the derivative C of the normal force coefficient with respect to the angle of attack defined based on the propeller speed and diameter Nα '; S222. Calculate the propeller disc area S p ; S223, the derivative of the normal force coefficient with respect to the angle of attack, C, defined based on the propeller speed and diameter Nα ' and the paddle disc area S p , calculate the propeller disk normal force coefficient-angle of attack derivative C Nα .

12. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 11, characterized in that: S221 is specifically: in, σ e is the inherent effectiveness factor of the blade; J is the aircraft's forward ratio; C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

13. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 12, characterized in that: S222 is specifically: S p =πd 2 / 4; in, d is the propeller disc diameter.

14. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: S223, specifically: in, S ref is the reference area of ​​the wing.

15. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: In step 3, for the propellers to rotate in the same direction, the following steps are performed: S311, using propeller parameter β0, calculate the derivative of the yaw moment coefficient defined based on propeller speed and diameter with respect to the angle of attack S312, derivative of the yaw moment coefficient with respect to the angle of attack defined based on the propeller speed and diameter Calculate the derivative of the yaw moment coefficient based on the incoming flow pressure and the wing reference area 16. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: S311 is as follows: in, σ e is the inherent effectiveness factor of the blade; C' T It is the propeller thrust coefficient defined based on engine thrust, propeller speed and propeller disk diameter.

17. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: S312 is specifically: in, J is the aircraft's forward ratio; S p is the paddle disc area; d is the diameter of the propeller disc; S ref is the wing reference area; b w For wingspan.

18. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: In step 3, for the propellers rotating in opposite directions, specifically:

19. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: Step 4: including: S41. Calculate the effective angle of attack α of the propeller e , specifically: a e =α-θ pb ; in, α is the fuselage angle of attack; θ pb is the angle of attack of the tension line to the fuselage; S42, based on the yaw moment coefficient derivative based on the incoming flow velocity pressure and the wing reference area and the effective angle of attack α of the propeller e , calculate the yaw moment coefficient angle of attack correction △C n , specifically: in, N is the number of engines; △C nα0 is the yaw moment coefficient generated by zero angle of attack power.

20. The method for calculating the yaw moment characteristics of a propeller aircraft considering the influence of power according to claim 1, characterized in that: Step 5 is as follows: in, is the heading static stability derivative under no-power condition; β is the sideslip angle.

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