A method for calculating large-angle glide performance of a fixed-wing turboprop aircraft

Abstract

The application belongs to the field of aviation medium-sized aircraft design, and relates to a large-angle glide performance calculation method of a fixed-wing turboprop aircraft. The method comprises the following steps: determining the combination characteristics of the power device of the turboprop aircraft according to the characteristics of the turboprop engine and the propeller; increasing the resistance and reducing the lift by using the double-open state of the spoiler, so as to realize large-angle glide; and obtaining the required large-angle glide performance of the aircraft by modeling and adjusting calculation.

Description

Technical Field

[0001] This invention belongs to the field of medium-sized aircraft design and relates to a method for calculating the glide performance of a fixed-wing turboprop aircraft at large angles. Background Technology

[0002] Turboprop aircraft are generally used for transporting and delivering cargo, equipment, and personnel. Considering the terrain during descent and landing, as well as survivability in specific mission scenarios, a steep descent angle can greatly reduce descent time and distance, thus largely determining the safety of the pilots and the aircraft.

[0003] It is impossible to obtain explicit methods and related technical data from abroad for calculating the high-angle glide performance of turboprop aircraft through publicly available channels. A search of patent websites yielded no similar or related patents, and no relevant research results were found domestically. Summary of the Invention

[0004] Purpose of the invention: To provide a method for calculating the glide performance of turboprop aircraft at large angles, solving the problem of large deviation between the current calculation of the glide performance of turboprop aircraft at large angles and the actual glide capability of the aircraft, and greatly improving the accuracy of the calculation of glide performance at large angles.

[0005] A method for calculating the large-angle glide performance of a fixed-wing turboprop aircraft is provided, including:

[0006] Based on the characteristics of turbine engines and propellers, the combined characteristics of propeller aircraft power plants are determined. By using a double-open spoiler, drag is increased and lift is reduced to achieve a large-angle glide. The required large-angle glide performance of the aircraft is obtained through modeling and adjustment calculations.

[0007] Furthermore, considering the characteristics of turbine engines and propellers, the combined power plant characteristics of propeller-driven aircraft are determined. By using spoilers in a dual-open state to increase drag and reduce lift, a high-angle glide can be achieved. The required high-angle glide performance of the aircraft is obtained through modeling and adjustment calculations, including:

[0008] Step 1: Determine the relevant parameters for large-angle glide of turboprop aircraft through wind tunnel tests and simulations, and clarify the requirements for the double opening angle of the spoilers and the glide speed requirements of the aircraft.

[0009] Step 2: Based on the impact of the spoiler on the aircraft's aerodynamic characteristics after it is deployed, compensate for the lift coefficient and drag coefficient after the spoiler is deployed.

[0010] Step 3: Based on the aircraft's glide speed requirements, calculate the true descent speed at each altitude, and then calculate the descent angle θ and angle of attack α at the corresponding altitude. Further, the horizontal distance, descent time, and fuel consumption during the entire descent process can be obtained.

[0011] Furthermore, the glide slope-related parameters include: the lift coefficient and drag coefficient after the spoiler is deployed; the lift coefficient and drag coefficient after the spoiler is deployed are respectively related to the angle of attack α, and the calculation formulas for the compensated changes in the lift coefficient and drag coefficient after the spoiler is deployed are as follows:

[0012] Δ C L =-0.01308*δ sp ;

[0013] Δ C D = (0.000001*α+0.000031)*δ sp *δ sp -(0.000130*α-0.000554)*δ sp ;

[0014] Δ C L This is the compensation value for the change in lift coefficient after the spoiler is deployed;

[0015] Δ C D This is the compensation value for the change in drag coefficient after the spoiler is deployed;

[0016] δ sp This refers to the deflection of the spoiler after it is lowered.

[0017] Furthermore, the descent angle θ and angle of attack α at different altitudes are calculated based on the force balance formula; glide slope related parameters also include drag and lift;

[0018] The formula for lateral force balance is:

[0019] P cos(α + φ p - Q + G sinθ = 0;

[0020] The longitudinal force balance formula is:

[0021] P sin(α + φ p ) + Y - G cosθ = 0;

[0022] P—Given thrust; Q—Drag; G—Known aircraft weight; Y—Lift; α—Angle of attack at the same altitude; θ—Angle of descent at the same altitude.

[0023] Furthermore, based on the aircraft's glide speed requirements, the true descent speed at each altitude is calculated, thereby determining the corresponding descent angle θ and angle of attack α, including:

[0024] a) Divide the height difference between the given starting and ending descent heights into n equal segments, so that there are several calculation heights H0, H1...Hn+1 in the descent height;

[0025] b) For the m-th calculated height Hm, determine the true descent speed; m ranges from 0 to n+1.

[0026] c) Using the corresponding calculated altitude and descent speed, find the pulling force value and fuel consumption rate, and calculate the hourly fuel consumption and kilometer fuel consumption.

[0027] d) Set an initial angle of attack α0;

[0028] e) Calculate the descent angle θ0 using the longitudinal force balance formula;

[0029] f) Substitute the descent angle θ0 into the lateral force balance formula to find α1;

[0030] g) Repeat steps d, e, and f above until |α i -α i+1 When | is less than or equal to the preset threshold ζ, θ i and α i The descent angle θ at this calculated altitude and speed m and angle of attack α m .

[0031] Furthermore, the descent distance, descent time, and fuel consumption throughout the entire descent process can be obtained, including:

[0032] Calculate the average velocity V at each adjacent height. mpj = (V m + V m+1 ) / 2;

[0033] Calculate the average descent angle θ of each adjacent height. mpj = (θ m + θ m+1 ) / 2;

[0034] Calculate the average rate of descent V at each adjacent height. ypj = V mpj sinθ mpj ;

[0035] Calculate the time and horizontal distance of this descent.

[0036] The sum of the descent times of each segment is taken as the descent time, and the sum of the horizontal distances of each segment is taken as the horizontal distance of descent.

[0037] Find the tension and fuel consumption rate based on the average descent speed of each segment; calculate the hourly fuel consumption rate, and then calculate the fuel consumption for this segment; sum the fuel consumption of each segment to get the fuel consumption for descent at constant speed.

[0038] Furthermore, this method is applicable to medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft.

[0039] This invention determines the large-angle glide lift coefficient C of a turboprop aircraft by first determining the physical and aerodynamic parameters of the turboprop aircraft, and then considering the impact of the spoiler's downward deployment on the aircraft's aerodynamic characteristics. L and drag coefficient C D Then, through force analysis, the descent angle θ and angle of attack α of the aircraft during a large-angle descent are determined. Finally, the horizontal distance, descent time, and fuel consumption during the entire descent process are calculated. This calculation method is intuitive, simple, and has clear theoretical logic, making it easy for aircraft designers to master. This method is comprehensive, highly versatile, and has wide application value, suitable for medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft.

[0040] Figure 1 This is a force analysis diagram of a turboprop aircraft descending at a large angle.

[0041] The calculation method for the high-angle glide performance of this fixed-wing turboprop aircraft includes the following steps:

[0042] Step 1: Determine the relevant parameters for the large-angle glide of the turboprop aircraft, and clarify the requirements for the double opening angle of the spoilers and the glide speed requirements;

[0043] Step 2: Determine the impact of the spoiler deployment on the aircraft's aerodynamic characteristics. The formulas for compensating for the changes in lift coefficient and drag coefficient after the spoiler is deployed are as follows:

[0044] Δ C L =-0.01308*δ sp ;

[0045] Δ C D = (0.000001*α+0.000031)*δ sp *δ sp -(0.000130*α-0.000554)*δ sp .

[0046] Step 3: After determining the indicated airspeed, the true descent speed at each altitude can be calculated. For each altitude's true speed, the descent angle θ and angle of attack α at that altitude can be derived using the following formulas. Furthermore, the horizontal descent distance, descent time, and fuel consumption throughout the entire descent process can be obtained.

[0047] P cos(α + φ p - Q + G sinθ = 0

[0048] P sin(α + φ p) + Y - G cosθ = 0

[0049] This invention provides a method for calculating the high-angle glide performance of a turboprop aircraft. It primarily focuses on the characteristics of the turbine engine and propeller, determining the combined characteristics of the propeller aircraft's power unit. By using a dual-open spoiler configuration to increase drag and reduce lift, a high-angle glide is achieved. The required high-angle glide performance is obtained through modeling and adjustment calculations. The steps of this method are as follows:

[0050] To achieve a steep glide, it is necessary to use spoilers in a double-open state to increase drag and reduce lift. Furthermore, numerical simulations and wind tunnel tests are needed to determine the formulas for the changes in lift and drag coefficients after the spoilers are deployed.

[0051] Δ C L =-0.01308*δ sp ;

[0052] Δ C D = (0.000001*α+0.000031)*δ sp *δ sp -(0.000130*α-0.000554)*δ sp .

[0053] In the formula:

[0054] Δ C L —The amount of compensation for the change in lift coefficient;

[0055] Δ C D —The amount of compensation change in the drag coefficient;

[0056] α—Angle of attack of the fuselage;

[0057] δ sp —Spoiler deflection.

[0058] When the aircraft is flying without sideslip or roll, such as Figure 1 As shown, the flight dynamics equations are:

[0059] m dV / dt=Pcos(α+ φ p )-Q+Gsinθ………………(1)

[0060] mV dθ / dt=Psin(α+ φ p )+Y-Gcosθ………………(2)

[0061] At a certain altitude, when descending in a straight line at a constant velocity, assuming that the angle of descent θ remains constant over a very short time, formulas (1) and (2) can be simplified to the following:

[0062] Pcos(α+ φ p )-Q+Gsinθ=0……………………(3)

[0063] Psin(α+ φ p )+Y-Gcosθ=0……………………(4)

[0064] In the formula:

[0065] P – Thrust;

[0066] Q – Resistance;

[0067] G – Aircraft gravity;

[0068] Y – Lift;

[0069] α—Angle of attack of the fuselage;

[0070] θ — Angle of descent.

[0071] Once the indicated airspeed is determined, the true descent speed at each altitude can be calculated. For each altitude's true airspeed, the descent angle θ and angle of attack α at that altitude can be obtained using formulas (3) and (4). Furthermore, the horizontal descent distance, descent time, and fuel consumption throughout the descent process can be obtained. The specific process is as follows:

[0072] a) Divide the height difference between the given starting descent height and the ending descent height into n equal parts, so that there are several calculation heights H0, H1...Hn+1 in the descent height;

[0073] b) At the m-th calculated height, descend at a determined descent speed (true speed); m ranges from 0 to n+1;

[0074] c) Find the pulling force and fuel consumption rate at the corresponding speed and altitude, and calculate the hourly fuel consumption and kilometer fuel consumption;

[0075] d) Set an initial angle of attack α0;

[0076] e) Calculate the descent angle θ0 according to equation (4);

[0077] f) Substitute the descent angle θ0 into equation (3) to find α1;

[0078] g) Repeat steps d, e, and f above until |α i -α i+1 When | is less than or equal to ζ (ζ is a small quantity), this calculates the descent angle θ at altitude and velocity. m and angle of attack α m It is equal to θ i and α i ;

[0079] h) Calculate the average velocity V at each adjacent height. mpj = (V m + V m+1 ) / 2;

[0080] m) Calculate the average descent angle θ of each adjacent height. mpj = (θ m + θ m+1 ) / 2;

[0081] j) Calculate the average rate of descent V at each adjacent height. ypj = V mpj sinθ mpj ;

[0082] k) Calculate the time and horizontal distance of this descent segment;

[0083] l) The sum of the descent times of each segment is the descent time, and the sum of the horizontal distances of each segment is the horizontal distance of descent;

[0084] m) Determine the tension and fuel consumption rate based on the average descent speed of each segment. Calculate the hourly fuel consumption rate, and then calculate the fuel consumption for that segment. The sum of the fuel consumption for each segment is the fuel consumption for descent at constant speed.

[0085] This invention discloses a method for determining the large-angle glide performance of a medium-sized transport aircraft. By first determining the physical and aerodynamic parameters of the turboprop aircraft, and then considering the impact of spoiler deployment on the aircraft's aerodynamic characteristics, the large-angle glide lift coefficient C of the turboprop aircraft is determined. L and drag coefficient C D Then, through force analysis, the descent angle θ and angle of attack α of the aircraft during a large-angle descent are determined. Finally, the horizontal distance, descent time, and fuel consumption during the entire descent process of the aircraft during a large-angle descent are calculated.

[0086] This calculation method is intuitive, simple, and has a clear theoretical logic, making it easy for aircraft designers to master. It is comprehensive, highly versatile, and has broad application value, suitable for medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft.

[0087]

[0088] P—Given thrust; Q—Drag; G—Known aircraft weight; Y—Lift; α—Angle of attack at the same altitude; θ—Angle of descent at the same altitude.

[0089] Furthermore, based on the aircraft's glide speed requirements, the true descent speed at each altitude is calculated, thereby determining the corresponding descent angle θ and angle of attack α, including:

[0090] a) Divide the height difference between the given starting and ending descent heights into n equal segments, so that there are several calculation heights H0, H1...Hn+1 in the descent height;

[0091] b) For the m-th calculated height Hm, determine the true descent speed; m ranges from 0 to n+1.

[0092] c) Using the corresponding calculated altitude and descent speed, find the pulling force value and fuel consumption rate, and calculate the hourly fuel consumption and kilometer fuel consumption.

[0093] d) Set an initial angle of attack α0;

[0094] e) Calculate the descent angle θ0 using the longitudinal force balance formula;

[0095] f) Substitute the descent angle θ0 into the lateral force balance formula to find α1;

[0096] g) Repeat steps d, e, and f above until |α i -α i+1 When | is less than or equal to the preset threshold ζ, θ i and α i The descent angle θ at this calculated altitude and speed m and angle of attack α m .

[0097] Furthermore, the descent distance, descent time, and fuel consumption throughout the entire descent process can be obtained, including:

[0098] Calculate the average velocity V at each adjacent height. mpj =(V m +V m+1 ) / 2;

[0099] Calculate the average descent angle θ of each adjacent height. mpj =(θ m +θ m+1 ) / 2;

[0100] Calculate the average rate of descent V at each adjacent height. ypj =V mpj sinθ mpj ;

[0101] Calculate the time and horizontal distance of this descent.

[0102] The sum of the descent times of each segment is taken as the descent time, and the sum of the horizontal distances of each segment is taken as the horizontal distance of descent.

[0103] Find the tension and fuel consumption rate based on the average descent speed of each segment; calculate the hourly fuel consumption rate, and then calculate the fuel consumption for this segment; sum the fuel consumption of each segment to get the fuel consumption for descent at constant speed.

[0104] Furthermore, this method is applicable to medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft.

[0105] Beneficial effects:

[0106] This invention determines the large-angle glide lift coefficient C of a turboprop aircraft by first determining the physical and aerodynamic parameters of the turboprop aircraft, and then considering the impact of the spoiler's downward deployment on the aircraft's aerodynamic characteristics. L and drag coefficient C D Then, through force analysis, the descent angle θ and angle of attack α of the aircraft during a large-angle descent are determined. Finally, the horizontal distance, descent time, and fuel consumption during the entire descent process are calculated. This calculation method is intuitive, simple, and has clear theoretical logic, making it easy for aircraft designers to master. This method is comprehensive, highly versatile, and has wide application value, suitable for medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft. Attached Figure Description

[0107] Figure 1 This is a force analysis diagram of a turboprop aircraft descending at a large angle. Detailed Implementation

[0108] The calculation method for the high-angle glide performance of this fixed-wing turboprop aircraft includes the following steps:

[0109] Step 1: Determine the relevant parameters for the large-angle glide of the turboprop aircraft, and clarify the requirements for the double opening angle of the spoilers and the glide speed requirements;

[0110] Step 2: Determine the impact of the spoiler deployment on the aircraft's aerodynamic characteristics. The formulas for compensating for the changes in lift coefficient and drag coefficient after the spoiler is deployed are as follows:

[0111] ΔC L =-0.01308*δ sp ;

[0112] ΔC D = (0.000001*α+0.000031)*δ sp *δ sp -(0.000130*α-0.000554)*δ sp .

[0113] Step 3: After determining the indicated airspeed, the true descent speed at each altitude can be calculated. For each altitude's true speed, the descent angle θ and angle of attack α at that altitude can be derived using the following formulas. Furthermore, the horizontal descent distance, descent time, and fuel consumption throughout the entire descent process can be obtained.

[0114]

[0115] This invention provides a method for calculating the high-angle glide performance of a turboprop aircraft. It primarily focuses on the characteristics of the turbine engine and propeller, determining the combined characteristics of the propeller aircraft's power unit. By using a dual-open spoiler configuration to increase drag and reduce lift, a high-angle glide is achieved. The required high-angle glide performance is obtained through modeling and adjustment calculations. The steps of this method are as follows:

[0116] To achieve a steep glide, it is necessary to use spoilers in a double-open state to increase drag and reduce lift. Furthermore, numerical simulations and wind tunnel tests are needed to determine the formulas for the changes in lift and drag coefficients after the spoilers are deployed.

[0117] ΔC L =-0.01308*δ sp ;

[0118] ΔC D = (0.000001*α+0.000031)*δ sp *δ sp -(0.000130*α-0.000554)*δ sp .

[0119] In the formula:

[0120] ΔCL — the amount of compensation for the change in lift coefficient;

[0121] ΔCD — the amount of compensation change in the drag coefficient;

[0122] α—Angle of attack of the fuselage;

[0123] δsp — spoiler deflection.

[0124] When the aircraft is flying without sideslip or roll, such as Figure 1 As shown, the flight dynamics equations are:

[0125] m dV / dt=Pcos(α+φ_p)-Q+Gsinθ………………(1)

[0126] mV dθ / dt=Psin(α+φ_p)+Y-Gcosθ………………(2)

[0127] At a certain altitude, when descending in a straight line at a constant velocity, assuming that the angle of descent θ remains constant over a very short time, formulas (1) and (2) can be simplified to the following:

[0128] Pcos(α+φ_p)-Q+Gsinθ=0……………………(3)

[0129] Psin(α+φ_p)+Y-Gcosθ=0……………………(4)

[0130] In the formula:

[0131] P – Thrust;

[0132] Q – Resistance;

[0133] G – Aircraft gravity;

[0134] Y – Lift;

[0135] α—Angle of attack of the fuselage;

[0136] θ — Angle of descent.

[0137] Once the indicated airspeed is determined, the true descent speed at each altitude can be calculated. For each altitude's true airspeed, the descent angle θ and angle of attack α at that altitude can be obtained using formulas (3) and (4). Furthermore, the horizontal descent distance, descent time, and fuel consumption throughout the descent process can be obtained. The specific process is as follows:

[0138] a) Divide the height difference between the given starting descent height and the ending descent height into n equal parts, so that there are several calculation heights H0, H1...Hn+1 in the descent height;

[0139] b) At the m-th calculated height, descend at a determined descent speed (true speed); m ranges from 0 to n+1;

[0140] c) Find the pulling force and fuel consumption rate at the corresponding speed and altitude, and calculate the hourly fuel consumption and kilometer fuel consumption;

[0141] d) Set an initial angle of attack α0;

[0142] e) Calculate the descent angle θ0 according to equation (4);

[0143] f) Substitute the descent angle θ0 into equation (3) to find α1;

[0144] g) Repeat steps d, e, and f above until |α i -α i+1 When | is less than or equal to ζ (ζ is a small quantity), this calculates the descent angle θ at altitude and velocity. m and angle of attack α m It is equal to θ i and α i ;

[0145] h) Calculate the average velocity V at each adjacent height. mpj =(V m +V m+1 ) / 2;

[0146] m) Calculate the average descent angle θ of each adjacent height. mpj =(θ m +θ m+1 ) / 2;

[0147] j) Calculate the average rate of descent V at each adjacent height. ypj =V mpj sinθ mpj ;

[0148] k) Calculate the time and horizontal distance of this descent segment;

[0149] l) The sum of the descent times of each segment is the descent time, and the sum of the horizontal distances of each segment is the horizontal distance of descent;

[0150] m) Determine the tension and fuel consumption rate based on the average descent speed of each segment. Calculate the hourly fuel consumption rate, and then calculate the fuel consumption for that segment. The sum of the fuel consumption for each segment is the fuel consumption for descent at constant speed.

[0151] This invention discloses a method for determining the large-angle glide performance of a medium-sized transport aircraft. By first determining the physical and aerodynamic parameters of the turboprop aircraft, and then considering the impact of spoiler deployment on the aircraft's aerodynamic characteristics, the large-angle glide lift coefficient C of the turboprop aircraft is determined. L and drag coefficient C D Then, through force analysis, the descent angle θ and angle of attack α of the aircraft during a large-angle descent are determined. Finally, the horizontal distance, descent time, and fuel consumption during the entire descent process of the aircraft during a large-angle descent are calculated.

[0152] This calculation method is intuitive, simple, and has a clear theoretical logic, making it easy for aircraft designers to master. It is comprehensive, highly versatile, and has broad application value, suitable for medium and large turboprop passenger aircraft, transport aircraft, and related platform aircraft.

Claims

1. A method for calculating the high angle glide performance of a fixed wing turboprop aircraft, characterized in that, The application relates to a method for calculating the performance of a turbo-propeller airplane in a large-angle glide. The method comprises the following steps: Step 1: determining the parameters related to the large-angle glide of a turbo-propeller airplane through wind tunnel tests and simulation, and determining the opening angle of the anti-flow plate and the glide speed of the airplane; Step 2: compensating the lift coefficient and the drag coefficient after the anti-flow plate is opened according to the influence of the opened anti-flow plate on the aerodynamic characteristics of the airplane; The parameters related to the glide include the lift coefficient and the drag coefficient after the anti-flow plate is opened, and the lift coefficient and the drag coefficient after the anti-flow plate is opened have corresponding relations with the angle of attack alpha; the compensation change value of the lift coefficient and the compensation change value of the drag coefficient are calculated according to the following formula: Step 3: calculating the descent angle theta and the angle of attack alpha at the corresponding height according to the airplane glide speed, and further calculating the horizontal distance, the time and the fuel consumption of the entire descent process. AC L = -0.01308 * delta sp ; AC D = (0.000001 * a + 0.000031) * d sp * d sp - (0.000130 * a - 0.000554) * d sp ; AC L Cp is the lift coefficient of the airfoil; and Cp is the lift coefficient of the airfoil; and AC D Cp is the pressure coefficient of the airfoil section; and Cp is the pressure coefficient of the airfoil section; and Cp is the pressure coefficient of the airfoil section; and Cp is the pressure delta sp delta is the deflection after the damper is lowered; The descent angle theta and the angle of attack alpha at different heights are calculated based on the force balance formula; the parameters related to the glide further include the drag and the lift; 2. The method of claim 1, wherein, The lateral force balance formula is: The longitudinal force balance formula is: P cos(a + φ p ) - Q + G sinθ = 0; The descent angle theta and the angle of attack alpha at the corresponding height are calculated according to the airplane glide speed, including: P sin(a + f p ) + Y - G cos 0 = 0; P - given thrust; Q - drag; G - known aircraft weight; Y - lift; a - angle of attack at the same height; Θ - angle of descent at the same height; φ p - angle of the propeller pull line to the aircraft reference axis.

3. The method of claim 2, wherein, a) equally dividing the height difference between the given initial descent height and the final descent height into n segments, so that there are H0, H1... Hn+1 calculation heights on the descent height; b) descending at the determined true airspeed for the mth calculation height Hm; the range of m is 0 to n+1; c) searching for the tension value and the fuel consumption rate according to the corresponding calculation height and the true airspeed, and calculating the hourly fuel consumption and the kilometer fuel consumption; d) setting an initial angle of attack alpha0; e) calculating the descent angle theta0 according to the longitudinal force balance formula; f) substituting the descent angle theta0 into the lateral force balance formula to obtain alpha1; The horizontal distance, the time and the fuel consumption of the entire descent process are further calculated, including: g) repeat the above d, e, f until |a i - a i+1 | is less than or equal to a preset threshold x, then set a i and a i as the descent angle a m and the angle of attack a m at this calculated height and speed.

4. The method of claim 3, wherein, calculating the time and the horizontal distance of the segment; The average velocity V of each adjacent height is calculated mpj = (V m + V m+1 ) / 2; The average angle of descent θ of each adjacent height is calculated mpj = (θ m + θ m+1 ) / 2; The average rate of descent V is calculated for each adjacent height ypj = V mpj sinθ mpj ; summing the descent time of each segment as the descent time, and summing the horizontal distance of each segment as the horizontal distance; searching for the tension and the fuel consumption rate according to the average descent speed of each segment; calculating the hourly fuel consumption, and further calculating the fuel consumption of the segment; and summing the fuel consumption of each segment as the fuel consumption of the constant airspeed descent. The method is suitable for medium and large turbo-propeller airplanes, transport airplanes and related platform airplanes.

5. The method of claim 1, wherein, The computer program is executed by a processor to realize the method according to any one of claims 1-5.

6. A computer-readable storage medium having stored thereon a computer program, characterized in that ​

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