A method for calculating the fuel consumption of an aircraft mission

Abstract

The application provides a kind of aircraft mission fuel consumption calculation method, which divides the flight route into two parts according to the characteristics of each section of the aircraft mission route, equivalent conversion is carried out for the flight section and calculation method in each part, a fuel calculation model of the entire flight route is established, the calculation model is simplified, the error probability of the calculation process can be significantly reduced, the calculation efficiency is improved, the calculation of the aircraft mission fuel consumption can be quickly realized, and the development of related calculation auxiliary tools and equipment is facilitated.

Description

A method for calculating aircraft mission fuel consumption Technical Field

[0001] This application belongs to the field of aircraft mission fuel consumption calculation technology, specifically relating to a method for calculating aircraft mission fuel consumption. Background Technology

[0002] In aircraft mission planning, the calculation of fuel consumption is involved. The conventional calculation method is to establish force balance equations and motion equations based on the flight characteristics of the aircraft in each flight segment of the entire route, solve the equations according to the aircraft configuration, flight weight, flight speed, and engine operating status of each flight segment, and integrate the fuel consumption to obtain the total fuel consumption. This calculation method involves many aircraft configurations, is complex, inefficient, and prone to errors, making it difficult to develop relevant calculation aids and equipment.

[0003] This application is made in view of the aforementioned technical deficiencies.

[0004] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0005] The purpose of this application is to provide a method for calculating aircraft mission fuel consumption in order to overcome or mitigate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A method for calculating aircraft mission fuel consumption includes:

[0008] Step 1: Divide the aircraft's mission flight path into two parts, including:

[0009] The first part includes the takeoff segment and the landing segment, which consist of the departure and arrival procedures of the takeoff / landing airport;

[0010] The second part includes the climb, cruise, and descent phases, consisting of a vertical and horizontal profile formed by a series of waypoints from the end of the departure procedure to the start of the arrival procedure. The track in this part includes a straight climb phase, a straight level flight phase, a horizontal turn phase, an ascending turn phase, a straight descent phase, and a circling descent phase.

[0011] Step 2: Calculate the fuel consumption for the first part:

[0012] Takeoff segment fuel consumption calculation converts the horizontal track provided by the departure procedure of the expected takeoff airport into a straight-line distance L. takeoff The flight time required for takeoff is calculated based on the aircraft's expected takeoff configuration, the preset takeoff weight, and the corresponding safe takeoff speed. This flight time is then multiplied by the engine takeoff power state fuel flow rate corresponding to the safe takeoff speed to calculate the fuel consumption Wf for the takeoff segment. takeoff ;

[0013] The landing segment fuel consumption calculation converts the horizontal track provided by the approach procedure of the expected landing airport into a straight-line distance L. land Under the expected landing weight, in cruise configuration and the corresponding V REF Flight L calculated based on stable level flight land折算 The fuel consumption required for the distance traveled is used as the fuel consumption Wf for the landing segment. land ,in,

[0014] L land折算 =L land ×K0 / K land ;

[0015] Wherein, K0 is the cruise configuration in V REF The corresponding lift-to-drag ratio; K land For landing configuration in V REF The corresponding lift-to-drag ratio;

[0016] Step 3: Calculate the fuel consumption for Part 2:

[0017] The total flight distance L is obtained by adding up the segment distances between each waypoint in the second part. c The distance of the straight line segment is the great circle distance between the two points, and the distance of the arc segment is calculated by multiplying the radius of curvature by the central angle: L circle =r circle .Ψ, where L circle r is the distance of the arc segment. circle Let be the radius of curvature of the arc segment; Ψ be the central angle of the arc segment;

[0018] For the straight climb, horizontal turn, and ascending turn sections in Part Two, the increase in stable level flight distance is calculated as follows:

[0019] For the straight climb phase, the stable level flight distance increases by a calculated amount ΔL. climb =Δh climb ×K max , where Δh climb K represents the increase in height during the straight climb section. max This represents the maximum lift-to-drag ratio at the cruising Mach number.

[0020] For horizontal turns, the stable level flight distance increases by a calculated amount ΔL. circle1 =L circle / cosθ-L circle , where θ is the bank angle of the aircraft during a horizontal turn;

[0021] For the ascending turning segment, it is decomposed into a straight climb segment and a horizontal turning segment, and the stable level flight distance is increased by the equivalent amount ΔL. cli-circle =Δh climb ×K max +L circle / cosθ-L circle ;

[0022] Total flight distance L c The increase in stable level flight distance ΔL compared to the straight climb, horizontal turn, and ascending turn sections. climb ΔL circle1 ΔL cli-circle By summing these up, we obtain the second part of the total flight distance Lc, calculated based on fuel consumption during stable level flight. 折算 At this flight distance, the force balance equations and motion equations for stable level flight of the aircraft in cruise configuration, at a given cruise altitude and speed are solved. The calculated fuel consumption per kilometer is then integrated to obtain the second part of the fuel consumption, Wf. Lc ;

[0023] Step 4: Calculate the fuel consumption Wf during takeoff. takeoff Fuel consumption during landing (Wf) land Part Two: Fuel Consumption Wf Lc By summing the results, we obtain the aircraft mission fuel consumption Wf. a =Wf takeoff +Wf land +Wf Lc .

[0024] According to at least one embodiment of this application, in the above-described method for calculating aircraft mission fuel consumption, if the second part includes an airdrop / parachute segment, then the fuel consumption Wf in the second part... Lc Add Wf airdrop =Wf airdrop_cruise ×K max_cruise / K max_airdrop ;

[0025] Among them, Wf airdrop This refers to the fuel consumption during the airdrop phase; Wf airdrop_cruise K represents the fuel consumption of the cruise configuration during the required airdrop and descent time. max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_airdropThis represents the maximum lift-to-drag ratio for the airdrop / airborne configuration.

[0026] According to at least one embodiment of this application, in the above-described method for calculating aircraft mission fuel consumption, if the second part includes a refueling / receiving section, then the fuel consumption Wf in the second part is... Lc Add Wf refuel =Wf refuel_cruise ×K max_cruise / K max_airdrop ,

[0027] Among them, Wf refuel Fuel consumption at the refueling / receiving section; Wf cruise Fuel consumption of the cruise configuration during the required refueling / reloading time; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_refuel This represents the maximum lift-to-drag ratio for the oil-feeding / oil-receiving configuration.

[0028] According to at least one embodiment of this application, in the above-described method for calculating aircraft mission fuel consumption, if the second part includes a warning patrol segment, then the fuel consumption Wf in the second part... Lc Add Wf patrol =Wf patrol_cruise ×K max_cruise / K max_patrol / cosθ patrol ,

[0029] Among them, Wf patrol Fuel consumption of the early warning patrol segment; Wf lpatrol_cruise This refers to the fuel consumption calculated during the early warning patrol segment in stable level flight configuration during cruise; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_patrol The maximum lift-to-drag ratio for the early warning patrol configuration; θ patrol The average slope angle of the early warning patrol section.

[0030] This application has at least the following beneficial technical effects:

[0031] This paper provides a method for calculating aircraft mission fuel consumption. Based on the characteristics of each segment of the mission route, the method divides the flight route into two parts, performs equivalent transformation on the flight segments and calculation methods in each part, and establishes a fuel calculation model for the entire flight route. The simplified calculation model can significantly reduce the probability of errors in the calculation process, facilitate the rapid calculation of aircraft mission fuel consumption, and promote the development of related calculation auxiliary tools and equipment. Attached Figure Description

[0032] Figure 1 is a vertical cross-sectional schematic diagram of an aircraft mission provided in an embodiment of this application;

[0033] Figure 2 is a schematic diagram of the aircraft takeoff section provided in an embodiment of this application;

[0034] Figure 3 is a schematic diagram of an aircraft climb and turn segment provided in an embodiment of this application;

[0035] Figure 4 is a schematic diagram of the horizontal turning bank of an aircraft provided in an embodiment of this application;

[0036] Figure 5 is a schematic diagram of the aircraft's straight climb section provided in an embodiment of this application;

[0037] Figure 6 is a schematic diagram of the aircraft landing section provided in an embodiment of this application. Detailed Implementation

[0038] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0039] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0040] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral 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; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0041] The method for calculating aircraft mission fuel consumption provided in this application will be further explained in detail below with reference to Figures 1 to 6.

[0042] 1. Divide the aircraft's mission flight path into two parts, of which:

[0043] The first part includes the takeoff segment and the landing segment, which consist of the departure and arrival procedures of the takeoff / landing airport;

[0044] The second part includes the climb, cruise, and descent phases, consisting of a vertical and horizontal profile formed by a series of waypoints from the end of the departure procedure to the start of the approach procedure. The track in this part includes a straight climb phase, a straight level flight phase, a horizontal turn phase, an ascending turn phase, a straight descent phase, and a circling descent phase.

[0045] 2. Calculate the fuel consumption for the first part:

[0046] Takeoff segment fuel consumption calculation converts the horizontal track provided by the departure procedure of the expected takeoff airport into a straight-line distance L. takeoff The flight time required for takeoff is calculated based on the aircraft's expected takeoff configuration, the preset takeoff weight, and the corresponding safe takeoff speed. This flight time is then multiplied by the engine takeoff power state fuel flow rate corresponding to the safe takeoff speed to calculate the fuel consumption Wf for the takeoff segment. takeoff ;

[0047] The landing segment fuel consumption calculation converts the horizontal track provided by the approach procedure of the expected landing airport into a straight-line distance L. land Under the expected landing weight, in cruise configuration and the corresponding V REF Flight L calculated based on stable level flight land折算 The fuel consumption required for the distance traveled is used as the fuel consumption Wf for the landing segment. land ,in,

[0048] L land折算 =L land ×K0 / K land ;

[0049] Wherein, K0 is the cruise configuration in VREF The corresponding lift-to-drag ratio; K land For landing configuration in V REF The corresponding lift-to-drag ratio.

[0050] 3. Calculate the fuel consumption for the second part:

[0051] First, add up the segment distances between each waypoint to obtain the total flight distance L required for the flight. c The distance of the straight line segment is the great circle distance between the two points, and the distance of the arc segment is calculated by multiplying the radius of curvature by the central angle, as shown in the following formula:

[0052] L circle =r circle .Ψ;

[0053] Among them, L circle Let r be the distance of the arc segment. circle Let Ψ be the radius of curvature of the arc segment, and Ψ be the central angle of the arc segment.

[0054] Furthermore, the different flight segments are converted to a stable level flight state for calculation:

[0055] 1) For the straight ascent section:

[0056] Divide the straight climb phase into a level flight phase and an altitude increase phase. Let the fuel consumption during the altitude increase phase be equal to the fuel consumption during a stable level flight of a certain distance. Then, the method for calculating the stable level flight distance during this phase is as follows:

[0057] ΔL climb =Δh climb ×K max ;

[0058] Where, Δh climb K represents the increase in altitude during the ascent phase. max This represents the maximum lift-to-drag ratio at the cruising Mach number.

[0059] 2) For horizontal turning sections:

[0060] Convert the increased fuel consumption required for level turns into an increase in range:

[0061] ΔL circle1 =L circle / cosθ-L circle ;

[0062] If a horizontal turn is added to the flight path, the total length of the flight increases by ΔL. circle1 Similarly, when there are multiple horizontal turning sections, ΔL is increased. circle1 ΔL circle2 ...

[0063] 3) For the upward turning section:

[0064] The climbing and turning phase can be broken down into a straight climb phase and a horizontal turn phase. The increase in fuel consumption resulting from the relatively stable level flight during the straight climb and horizontal turn is converted into an increase in total flight distance using the following formula:

[0065] ΔL cli-circle1 =Δh climb ×K max +L circle / cosθ-L circle ;

[0066] If the flight path includes an ascent and turn segment, the total length of the flight increases by ΔL. cli-circle1 Similarly, when there are multiple horizontal turning sections, ΔL is increased. cli-circle1 ΔL cli-circle2 ...

[0067] 4) For the descent segment and the spiraling descent segment:

[0068] The descent and circling descent phases do not consider the effects of altitude reduction and turning, and are calculated in the same way as the cruise phase, with the total length of the journey remaining unchanged.

[0069] Adding the calculated increase in range to the total flight distance Lc yields the second part of the total flight distance Lc, calculated based on stable level flight conditions. 折算 At this flight distance, the force balance equations and motion equations for stable level flight of the aircraft in cruise configuration, at a given cruise altitude and speed are solved. The calculated fuel consumption per kilometer is then integrated to obtain the second part of the fuel consumption, Wf. Lc .

[0070] 5) If there is an airdrop segment in the second part:

[0071] The flight distance of the airdrop segment is not included in the total route distance; only fuel consumption is considered. The fuel consumption of the airdrop configuration is converted to the fuel consumption of the cruise configuration using the following formula:

[0072] Wf airdrop =Wf airdrop_cruise ×K max_cruise / K max_airdrop ;

[0073] Among them, Wf airdrop This refers to the fuel consumption during the airdrop phase; Wf airdrop_cruise K represents the fuel consumption of the cruise configuration during the required airdrop and descent time. max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_airdrop This represents the maximum lift-to-drag ratio for the airdrop / airborne configuration.

[0074] 6) If there is a refueling / receiving section in the second part:

[0075] The flight distance during the refueling / receiving segment is not included in the total route distance; only fuel consumption is considered. The fuel consumption calculation for the refueling / receiving configuration is converted to the fuel consumption calculation for the cruise configuration. The conversion formula is as follows:

[0076] Wf refuel =Wf refuel_cruise ×K max_cruise / K max_airdrop ,

[0077] Among them, Wf refuel Fuel consumption at the refueling / receiving section; Wf cruise Fuel consumption of the cruise configuration during the required refueling / reloading time; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_refuel This represents the maximum lift-to-drag ratio for the oil-feeding / oil-receiving configuration.

[0078] 7) If there is an early warning patrol segment in the second part:

[0079] The flight distance of the early warning patrol segment is not included in the total route distance; only fuel consumption is considered. The fuel consumption calculation for the early warning patrol configuration is converted to that for the cruise configuration, and the conversion formula is as follows:

[0080] Wf patrol =Wf patrol_cruise ×K max_cruise / K max_patrol / cosθ patrol ,

[0081] Among them, Wf patrol Fuel consumption of the early warning patrol segment; Wf lpatrol_cruise This refers to the fuel consumption calculated during the early warning patrol segment in stable level flight configuration during cruise; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_patrol The maximum lift-to-drag ratio for the early warning patrol configuration; θ patrol The average slope angle of the early warning patrol section.

[0082] Part Two: Fuel Consumption Wf Lc Add Wf airdrop Wf refuel Wf patrol .

[0083] 4. Fuel consumption during takeoff (Wf) takeoff Fuel consumption during landing (Wf) land Part Two: Fuel Consumption Wf LcBy summing the results, we obtain the aircraft mission fuel consumption Wf. a =Wf takeoff +Wf takeoff +Wf Lc .

[0084] In a specific embodiment, a transport aircraft performs an airdrop mission. The flight plan mainly includes the takeoff segment, climb and turn segment, cruise segment, airdrop and descent segment, descent segment, and landing segment. Figure 1 is a schematic diagram of the vertical cross-section. Its fuel consumption is calculated as follows:

[0085] I. Takeoff Segment: The fuel consumption calculation for the takeoff segment is shown in Figure 2. The aircraft takeoff weight is W0. Based on the takeoff configuration and takeoff weight W0, the safe takeoff speed V2 at point C is obtained. Based on the engine data, the hourly fuel consumption q is obtained. h-takeoff Convert the horizontal track of the aircraft takeoff and departure procedure into the distance L of AD. AD The takeoff and departure procedure is equivalent to uniform linear flight at V2, and the departure time t is calculated. AD =L AD / V2, then the fuel consumption W f-AD =q h-takeoff ×t AD The aircraft weight at the end of takeoff is W. D =W0-W f-AD ;

[0086] II. Climbing and Turning Section: Section DE is the climbing and turning section, as shown in Figure 3. Calculate the distance of section DE as a circular arc segment. In the figure, DE' is the projection of section DE onto the horizontal plane. Then, the distance L of the circular arc segment is... DE＇ =r DE＇ Ψ DE＇ , where r DE＇ Let Ψ be the radius of arc segment DE'. DE＇ Let DE' be the central angle of the arc segment;

[0087] Decompose segment DE into a straight climb segment and a horizontal turn segment. The horizontal turn segment is shown in Figure 4, with a gradient of θ. The increased distance due to the horizontal turn is ΔL. circle =L DE＇ / cosθ-L DE＇ ;

[0088] The straight climb section is shown in Figure 5. The increased range during the straight climb section is ΔL. climb =△h DE ×K max , where △h DE K represents the increase in height of the DE section during the climb. max This represents the maximum lift-to-drag ratio at the climb rate.

[0089] Therefore, the total distance of the climbing and turning section can be calculated as follows:

[0090] L DE =r DE′ Ψ DE′ +Δh DE ×K max +L DE′ / cosθ-L DE′ .

[0091] III. Cruise and Descent Phases: The aircraft's cruise phase distance is L cruise The descent phase of the aircraft does not consider the effects of altitude loss and turning; it is calculated equivalent to the cruise phase, with a range of L. descent .

[0092] The converted distance of the climb and turn phase in the above two steps is added to the distance of the cruise and descent phases to obtain the total flight distance used for calculating fuel consumption during stable level flight:

[0093] L c折算 =r DE′ Σ DE′ +Δh DE ×K max +L DE′ / cosθ-L DE′ +L cruise +L descent ;

[0094] At this flight distance, the force balance equations and motion equations for stable level flight of the aircraft in cruise configuration, at a given cruise altitude and speed are solved, and the calculated fuel consumption per kilometer is q. c-km Therefore, the fuel consumption of the route is obtained.

[0095] IV. Airdrop Phase: Convert the fuel consumption of the airdrop configuration to the fuel consumption of the cruise configuration. The fuel consumption of the cruise configuration during the required airdrop time is: The conversion formula is as follows:

[0096]

[0097] Among them, W fairdrop This refers to the fuel consumption during the airdrop phase; W fcruise Fuel consumption for the cruise configuration during the required airdrop and descent time; q h-cruise Hourly fuel consumption for cruise configuration; K max-cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max-airdrop This represents the maximum lift-to-drag ratio for the airdrop / airborne configuration.

[0098] Point L is taken as the end point after the second, third, and fourth steps are completed, as shown in Figures 1 and 6. The above three steps are all converted into cruise segment fuel consumption, and the aircraft weight W at the end of the cruise segment is obtained. E =W D -W fLc -W fairdrop .

[0099] V. Landing Phase: The aircraft approach procedure is shown in Figure 6. The horizontal distance corresponding to the horizontal track during the landing phase is L. EH L 折算 =L EH ×K0 / K land This is the converted cruising range, where K0 is the cruising range in V. REF The corresponding lift-to-drag ratio, K land For landing configuration in V REF The corresponding lift-to-drag ratio;

[0100] Landing weight W L Based on engine data, the cruise configuration and V REF_cruise Hourly fuel consumption q h-land , where V REF_cruise The approach reference speed for the cruise configuration is then determined based on the approach and landing time t. land =L LO / V REF_land The fuel consumption W during the landing phase was obtained. f-LAND =q h-land t land ; where V REF_land The approach reference speed for the landing configuration is given by W. Therefore, after approach and landing, the aircraft weight is W. END =W L -W f-LAND ;

[0101] VI. In summary, the total fuel consumption for the flight plan is:

[0102] W f总 =W f-AD +W fLc +W fairdrop +W f-EH .

[0103] The technical solution of this 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 this application is obviously not limited to these specific embodiments. Without departing from the principles of this 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 all fall within the scope of protection of this application.

Claims

1. A method for calculating aircraft mission fuel consumption, characterized in that, include: Step 1: Divide the aircraft's mission flight path into two parts. The first part includes the takeoff and landing segments, consisting of the departure and approach procedures at the takeoff / landing airports. The second part includes the climb, cruise, and descent segments, consisting of a series of waypoints from the end of the departure procedure to the start of the approach procedure, forming vertical and horizontal profiles. This part's track includes a straight climb segment, a straight level flight segment, a horizontal turn segment, an ascending turn segment, a straight descent segment, and a circling descent segment. Step 2: Calculate the fuel consumption for the first part: For the takeoff segment, convert the horizontal track provided by the departure procedure of the expected takeoff airport into a straight distance L. takeoff The flight time required for takeoff is calculated based on the aircraft's expected takeoff configuration, the preset takeoff weight, and the corresponding safe takeoff speed. This flight time is then multiplied by the engine takeoff power state fuel flow rate corresponding to the safe takeoff speed to calculate the fuel consumption Wf for the takeoff segment. takeoff The landing segment fuel consumption calculation converts the horizontal track provided by the approach procedure of the expected landing airport into a straight-line distance L. land Under the expected landing weight, in cruise configuration and the corresponding V REF Flight L calculated based on stable level flight land折算 The fuel consumption required for the distance traveled is used as the fuel consumption Wf for the landing segment. land , where L land折算 =L land ×K0 / K land Where K0 is the cruise configuration in V REF The corresponding lift-to-drag ratio; K land For landing configuration in V REF The corresponding lift-to-drag ratio; Step 3: Calculate the fuel consumption for the second part: Add up the segment distances between each waypoint in the second part to obtain the total flight distance L required. c The distance of the straight line segment is the great circle distance between the two points, and the distance of the arc segment is calculated by multiplying the radius of curvature by the central angle: L circle =r circle .Ψ, where L circle r is the distance of the arc segment. circle Let be the radius of curvature of the arc segment; Ψ be the central angle of the arc segment; for the straight climb, horizontal turn, and ascending turn segments in Part Two, calculate the increase in stable level flight distance: for the straight climb segment, the calculated increase in stable level flight distance is ΔL. climb =Δh climb ×K max , where Δh climb K represents the increase in height during the straight climb section. max This represents the maximum lift-to-drag ratio at the cruise Mach number; for the level turn segment, the increase in stable level flight distance is ΔL. circle =L circle / cosθ-L circle Where θ is the bank angle of the aircraft during a horizontal turn; for the climbing turn segment, it is decomposed into a straight climb segment and a horizontal turn segment, and the stable level flight distance increases by the calculated amount ΔL. cli-circle1 =Δh climb ×K max +L circle / cosθ-L circle The total flight distance L of the aircraft c The increase in stable level flight distance ΔL compared to the straight climb, horizontal turn, and ascending turn sections. climb ΔL circle1 ΔL cli-circle By summing these up, we obtain the second part of the total flight distance Lc, calculated based on fuel consumption during stable level flight. 折算 At this flight distance, the force balance equations and motion equations for stable level flight of the aircraft in cruise configuration, at a given cruise altitude and speed are solved. The calculated fuel consumption per kilometer is then integrated to obtain the second part of the fuel consumption, Wf. Lc Step 4: Calculate the fuel consumption Wf during takeoff. takeoff Fuel consumption during landing (Wf) land Part Two: Fuel Consumption Wf Lc By summing the results, we obtain the aircraft mission fuel consumption Wf. a =Wf takeoff +Wf land +Wf Lc .

2. The method for calculating aircraft mission fuel consumption according to claim 1, characterized in that, If the second part includes an airdrop segment, then the fuel consumption Wf in the second part... Lc Add Wf airdrop =Wf airdrop_cruise ×K max_cruise / K max_airdrop Among them, Wf airdrop This refers to the fuel consumption during the airdrop phase; Wf airdrop_cruise K represents the fuel consumption of the cruise configuration during the required airdrop and descent time. max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_airdrop This represents the maximum lift-to-drag ratio for the airdrop / airborne configuration.

3. The method for calculating aircraft mission fuel consumption according to claim 1, characterized in that, If the second part includes a refueling / receiving section, then the fuel consumption Wf in the second part... Lc Add Wf refuel =Wf refuel_cruise ×K max_cruise / K max_refuel Among them, Wf refuel Fuel consumption at the refueling / receiving section; Wf cruise Fuel consumption of the cruise configuration during the required refueling / reloading time; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_refuel This represents the maximum lift-to-drag ratio for the oil-feeding / oil-receiving configuration.

4. The method for calculating aircraft mission fuel consumption according to claim 1, characterized in that, If the second part includes a warning patrol segment, then the fuel consumption Wf in the second part... Lc Add Wf patrol =Wf patrol_cruise ×K max_cruise / K max_patrol / cosθ patrol Among them, Wf patrol Fuel consumption of the early warning patrol segment; Wf lpatrol_cruise This refers to the fuel consumption calculated during the early warning patrol segment in stable level flight configuration during cruise; K max_cruise K represents the maximum lift-to-drag ratio for the cruise configuration. max_patrol The maximum lift-to-drag ratio for the early warning patrol configuration; θ patrol The average slope angle of the early warning patrol section.

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