CN114662343A - Method for calculating cruise oil consumption of airplane - Google Patents
Method for calculating cruise oil consumption of airplane Download PDFInfo
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- CN114662343A CN114662343A CN202210543908.1A CN202210543908A CN114662343A CN 114662343 A CN114662343 A CN 114662343A CN 202210543908 A CN202210543908 A CN 202210543908A CN 114662343 A CN114662343 A CN 114662343A
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Abstract
The embodiment of the disclosure relates to a method for calculating the cruise oil consumption of an airplane stair. The method comprises the following steps: determining the gravitational potential energy added by the airplane in the climbing section by utilizing the height added by the climbing section during the airplane ladder cruising; determining the work done by the thrust of an aircraft engine according to the stable plane flight of the aircraft to a preset distance; according to the conservation of energy, the gravitational potential energy added by the airplane is equal to the fuel energy consumed by the climbing section due to the increase of the gravitational potential energy, and the fuel energy consumed by the climbing section due to the increase of the gravitational potential energy is approximately equal to the work done by the thrust of an engine of the airplane when the airplane stably and flatly flies to a preset distance. According to the embodiment of the invention, the performance of the climbing section in the airplane ladder cruising process can be estimated by adopting an energy conservation method, the height increased by the climbing section in the airplane ladder cruising process is converted into the increment of the voyage, the calculation of the total fuel consumption of the airplane ladder cruising process is realized, the complexity of the calculation process is reduced, and the calculation efficiency and the calculation precision are improved.
Description
Technical Field
The embodiment of the disclosure relates to the technical field of aerocraft flight mechanics, in particular to a method for calculating the cruise oil consumption of an airplane stair.
Background
The flight weight of the airplane is reduced along with the consumption of fuel in the actual cruising flight process, so that the cruising altitude is increased, and when fuel planning is carried out in a mission planning system, in order to reduce the fuel consumption as much as possible under a certain cruising distance, the flight requirement of cruising with variable altitude is required to be considered, and a step cruising mode is often adopted. The conventional method for calculating the fuel consumption is to introduce the performance calculation of the climbing section in the performance calculation process of the cruising section through a motion equation and a balance equation, and count the calculation result into the cruising distance to obtain the stepped cruising fuel consumption when the cruising distance is R. In actual calculation, due to the introduction of a climbing performance calculation process, the conventional oil consumption method can cause the complexity and the calculation amount of the calculation process to be increased seriously, the consumed calculation time is greatly increased, and the formulation efficiency of a flight plan is influenced.
Accordingly, there is a need to ameliorate one or more of the problems with the related art solutions described above.
It is noted that this section is intended to provide a background or context to the disclosure as recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
Disclosure of Invention
An object of the disclosed embodiments is to provide a method for calculating an aircraft cruise oil consumption, thereby overcoming, at least to some extent, one or more of the problems due to the limitations and disadvantages of the related art.
The embodiment of the disclosure provides a method for calculating the cruise oil consumption of an airplane at steps, which comprises the following steps:
determining the gravitational potential energy added by the airplane in the climbing section by utilizing the height added by the climbing section when the airplane is cruising in the ladder;
determining the work done by the thrust of the aircraft engine according to the stable flat flight of the aircraft to a preset distance;
according to energy conservation, the gravitational potential energy added by the aircraft is equal to the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy, and the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy is approximately equal to the work done by the thrust of the aircraft engine when the aircraft stably and flatly flies to the preset distance;
based on the conservation of the energy, converting the increased height of the climbing section in the airplane step cruise into the increased amount of the voyage according to the relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the airplane stably flies flat, and obtaining the total cruise distance in the airplane step cruise process;
and calculating the total fuel consumption of the airplane during the step cruise according to the total cruise distance.
In an embodiment of the present disclosure, the gravitational potential energy added by the aircraft is:
Ep=migΔhi （1）
wherein m isiThe real-time quality of the airplane at the ith climbing section of the airplane ladder cruising,
is the acceleration of gravity,. DELTA.hiAnd increasing the height of the ith climbing section of the airplane step cruise, wherein i is a positive integer.
In an embodiment of the present disclosure, the thrust of the aircraft engine does:
W=FΔRi （2）
wherein F is the thrust of the engine when the aircraft is stably level flying, and Delta RiThe increment of the voyage of the ith climbing section of the airplane ladder cruising.
In an embodiment of the present disclosure, a relationship between gravitational potential energy added by the aircraft and work performed by thrust of the aircraft engine when the aircraft steadily flies to the preset distance is as follows:
migΔhi≈FΔRi （3）。
in an embodiment of the disclosure, the step of converting the increased height of the climbing section in the airplane ladder cruising process into the increased amount of the voyage according to the relationship between equal thrust and resistance and equal lift and gravity when the airplane stably flies based on the conservation relationship between the energies comprises:
introducing an average lift-drag ratio to obtain a relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the aircraft stably flies flat:
wherein D is the resistance when the airplane stably flies flat, Y is the lift when the airplane stably flies flat, K is the average lift-drag ratio,
is the aircraft weight.
In an embodiment of the present disclosure, the step of converting the increased height of the climbing section in the airplane ladder cruising process into the increased amount of the voyage according to the relationship between equal thrust and resistance and equal lift and gravity when the airplane stably flies in a flat manner based on the energy conservation to obtain the total cruising distance in the airplane ladder cruising process includes:
the increased height of the climbing section in the airplane step cruise is converted into the increased amount of the voyage:
ΔRi=Δhi·K （5）。
in an embodiment of the present disclosure, the step of converting the increased height of the climbing section in the airplane ladder cruising process into the increased amount of the voyage according to the relationship between equal thrust and resistance and equal lift and gravity when the airplane stably flies based on the conservation of energy includes:
according to the increment of the voyage and the actual distance of the aircraft during stable level flight cruising, the total cruising distance obtained in the process of cruising at the aircraft ladder is as follows:
Rconversion calculation=R+ΔR1+ΔR2+···+ΔRi+···+ΔRn （6）
Wherein the content of the first and second substances,
for the aircraft to stabilize the actual distance during flat flight cruise, RConversion calculationThe total cruising distance of the airplane during the cruising at the stairs.
In an embodiment of the disclosure, the step of calculating the total fuel consumption of the aircraft during the step cruising according to the total cruising distance includes:
converting the height increased by the climbing section in the airplane step cruising into the increment of the voyage and the kilometer oil consumption of the climbing section in the airplane step cruising, and obtaining the fuel consumption of the climbing section in the airplane step cruising, which is required by the height increase, as follows:
Δmwi=ΔRi·qkmi=Δhi·K·qkmi （7）
wherein, Δ mwiThe fuel consumption of the ith climbing section during the step cruise of the airplane, qkmiAnd the kilometer oil consumption of the ith climbing section during the stair cruise of the airplane.
In an embodiment of the disclosure, the step of calculating the total fuel consumption of the aircraft during the step cruising according to the total cruising distance includes:
the total fuel consumption of the airplane during the step cruise is obtained by the kilometer fuel consumption of the airplane during the stable level flight cruise, the actual distance of the airplane during the stable level flight cruise and the fuel consumption of the climbing section of the airplane during the step cruise, which is required by the increase of the height:
mw=R·q+ΔR1·qkm1+ΔR2·qkm2+···+ΔRi·qkmi+···+ΔRn·qkmn （8）
wherein q is the kilometer oil consumption of the aircraft during stable level flight cruising, mwAnd the total fuel consumption of the airplane during the step cruise.
The technical scheme provided by the embodiment of the disclosure can have the following beneficial effects:
in the embodiment of the disclosure, by the method for calculating the fuel consumption of the airplane ladder cruising, when fuel oil planning is performed in a mission planning system or a flight management system of the airplane, the performance of a climbing section in the process of the airplane ladder cruising is estimated by adopting an energy conservation method, the height increased by the climbing section in the process of the airplane ladder cruising is converted into the increment of a voyage, namely, the calculation of the climbing process is converted into the calculation of the cruising process of stable level flight, so that the calculation of the total fuel consumption in the process of the airplane ladder cruising is realized, the complexity of the calculation process is reduced, the calculation complexity is greatly reduced within the allowable range of engineering calculation errors, and the calculation efficiency and the calculation precision are improved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the disclosure. It is to be understood that the drawings in the following description are merely exemplary of the disclosure, and that other drawings may be derived from those drawings by one of ordinary skill in the art without the exercise of inventive faculty.
FIG. 1 illustrates a flow chart of a method of calculating aircraft cruise fuel consumption in an exemplary embodiment of the present disclosure;
FIG. 2 illustrates a schematic diagram of a conventional computational method for cruise flight of an aircraft in an exemplary embodiment of the disclosure;
FIG. 3 shows a schematic diagram of an aircraft step cruise calculation method in an exemplary embodiment of the disclosure.
Detailed Description
Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many different forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
Furthermore, the drawings are merely schematic illustrations of embodiments of the disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repetitive description will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
FIG. 2 is a schematic diagram of a conventional calculation method for cruising flight of an aircraft, wherein the conventional fuel consumption calculation method is to introduce climbing section performance calculation in the cruise section performance calculation process through a motion equation and a balance equation, and count the calculation result into the cruise distance to obtain the stepped cruise fuel consumption when the cruise distance is R. In actual calculation, due to the introduction of a climbing performance calculation process, the conventional oil consumption method can cause the complexity and the calculation amount of the calculation process to be increased seriously, the consumed calculation time is greatly increased, and the formulation efficiency of a flight plan is influenced.
In the exemplary embodiment, a method for calculating an aircraft step cruise fuel consumption is provided. Referring to fig. 1, the method includes:
determining the gravitational potential energy added by the airplane in the climbing section by utilizing the height added by the climbing section when the airplane is cruising in the ladder;
determining the work done by the thrust of the aircraft engine according to the stable flat flight of the aircraft to a preset distance;
according to energy conservation, the gravitational potential energy added by the aircraft is equal to the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy, and the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy is approximately equal to the work done by the thrust of the aircraft engine when the aircraft stably and flatly flies to the preset distance;
based on the conservation of the energy, converting the increased height of the climbing section in the airplane step cruise into the increased amount of the voyage according to the relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the airplane stably flies flat, and obtaining the total cruise distance in the airplane step cruise process;
and calculating the total fuel consumption of the airplane during the step cruise according to the total cruise distance.
By the method for calculating the fuel consumption of the airplane during the step cruise, when fuel oil planning is performed on the airplane in a task planning system or a flight management system of the airplane, the performance of a climbing section in the step cruise process of the airplane is estimated by adopting an energy conservation method, the height increased by the climbing section during the step cruise of the airplane is converted into the increment of a voyage, namely, the calculation of the climbing process is converted into the calculation of the cruise process of stable level flight, and the calculation of the total fuel consumption during the step cruise of the airplane is realized, so that the complexity of the calculation process is reduced, the calculation complexity is greatly reduced within the allowable range of engineering calculation errors, and the calculation efficiency and the calculation precision are improved.
Next, the respective steps of the above-described method for calculating the aircraft step cruise fuel consumption in the present exemplary embodiment will be described in more detail with reference to fig. 1 and 3.
In step S101, the increased gravitational potential energy of the aircraft in the climbing section is determined by the increased height of the climbing section during the aircraft ladder cruising.
Optionally, in some embodiments, the added gravitational potential energy of the aircraft is:
Ep=migΔhi （1）
wherein m isiThe real-time quality of the airplane at the ith climbing section of the airplane ladder cruising,
is the acceleration of gravity,. DELTA.hiAnd increasing the height of the ith climbing section of the airplane step cruise, wherein i is a positive integer.
Specifically, according to energy conservation, the increase of the height of the climbing section of the aircraft in the stair cruising process is the gravitational potential energy increase process, and the process needs to consume more fuel oil to increase the gravitational potential energy. Based on the method, the gravitational potential energy added by the airplane in the climbing section can be determined according to the height added by the climbing section when the airplane is in the step cruise, and the additional fuel consumed by the climbing section can be conveniently calculated subsequently.
In step S102, the work performed by the thrust of the aircraft engine is determined according to the stable level flight of the aircraft to a preset distance.
Optionally, in some embodiments, the work performed by the thrust of the aircraft engine is:
W=FΔRi （2）
wherein F is the thrust of the engine when the aircraft is stably level flying, and Delta RiThe increment of the voyage of the ith climbing section of the airplane ladder cruising.
Specifically, based on energy conservation, the fuel energy consumed by the climbing section of the aircraft in the cruising process due to the increase of gravitational potential energy can be converted into the work done by the thrust of an engine of the aircraft when the aircraft stably flies for a preset distance. The preset distance is a voyage increment converted from the height increased by the climbing section.
In step S103, according to energy conservation, the gravitational potential energy added by the aircraft is equal to the fuel energy consumed by the climbing section due to the increase of the gravitational potential energy, and the fuel energy consumed by the climbing section due to the increase of the gravitational potential energy is approximately equal to the work performed by the thrust of the aircraft engine when the aircraft steadily flies to the preset distance.
Optionally, in some embodiments, the relationship between the gravitational potential energy added by the aircraft and the work performed by the thrust of the aircraft engine when the aircraft steadily flies to the preset distance is as follows:
migΔhi≈FΔRi （3）。
specifically, based on the fact that the gravitational potential energy increased by the climbing section in the aircraft ladder cruising process is equal to the fuel energy consumed by the height increase of the climbing section, as shown in formula (1), and the fuel energy consumed by the height increase of the climbing section is converted into the work done by the thrust of the aircraft engine when the aircraft stably and flatly flies to the preset distance, as shown in formula (2), the gravitational potential energy increased by the climbing section in the aircraft ladder cruising process is obtained to be approximately equal to the work done by the thrust of the aircraft engine when the aircraft stably and flatly flies to the preset distance, as shown in formula (3). That is, the formula (3) is obtained based on the relationship of the formulas (1) and (2).
In step S104, based on the conservation of energy, according to the relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the aircraft is stably flying flat, the increased height of the climbing section in the aircraft ladder cruising process is converted into the increased amount of the voyage, so as to obtain the total cruising distance in the aircraft ladder cruising process.
Optionally, in some embodiments, the step of converting the increased height of the climbing section in the airplane ladder cruising process into the increment of the voyage according to the relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the airplane stably flies flat based on the conservation relationship of the energy includes:
introducing an average lift-drag ratio to obtain a relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the aircraft stably flies flat:
wherein D is the resistance when the airplane stably flies flat, Y is the lift when the airplane stably flies flat, K is the average lift-drag ratio,
is the aircraft weight.
Specifically, when the aircraft stably flies flatly, the thrust and the resistance are equal, the lift and the gravity are equal, the average lift-drag ratio is introduced, and the increase of the height of a climbing section in the aircraft ladder cruising is converted into the increment of the voyage for calculation.
Optionally, in some embodiments, the step of converting a climbing section in the aircraft ladder cruising process into an increment of a voyage according to a relationship between equal thrust and resistance and equal lift and gravity when the aircraft is stably flying flat based on the conservation of energy includes:
the increased height of the climbing section in the airplane step cruise is converted into the increased amount of the voyage:
ΔRi=Δhi·K （5）。
specifically, based on the formulas (1), (2), (3) and (4), the increment of the height of the climbing section in the airplane ladder cruising is converted into the increment of the voyage, and the increment of the height of the climbing section in the airplane ladder cruising is converted into the increment of the voyage as shown in the formula (5).
Optionally, in some embodiments, the step of converting the increased height of the climbing section in the aircraft ladder cruising process into the increased amount of the voyage according to the relationship between equal thrust and resistance and equal lift and gravity when the aircraft is stably flying flat based on the conservation of energy includes:
according to the increment of the voyage and the actual distance of the aircraft during stable level flight cruising, the total cruising distance obtained in the process of cruising at the aircraft ladder is as follows:
Rconversion calculation=R+ΔR1+ΔR2+···+ΔRi+···+ΔRn （6）
Wherein the content of the first and second substances,
for the aircraft to stabilize the actual distance during flat flight cruise, RConversion calculationThe total cruising distance of the airplane during the cruising at the stairs.
Specifically, the actual distance of the aircraft during stable level flight cruising and the increment of the height of a climbing section in the aircraft step cruising process are converted into the increment of the range, so that the actual total cruising distance in the aircraft step cruising process is obtained.
In step S105, the total fuel consumption of the aircraft during the step cruising is calculated according to the total cruising distance.
Optionally, in some embodiments, the step of calculating the total fuel consumption of the aircraft during the step cruising according to the total cruising distance includes:
converting the height increased by the climbing section in the airplane step cruising into the increment of the voyage and the kilometer oil consumption of the climbing section in the airplane step cruising, and obtaining the fuel consumption of the climbing section in the airplane step cruising due to the height increase as follows:
Δmwi=ΔRi·qkmi=Δhi·K·qkmi （7）
wherein, Δ mwiThe fuel consumption of the ith climbing section during the step cruise of the airplane, qkmiAnd the kilometer oil consumption of the ith climbing section during the stair cruise of the airplane.
Specifically, the fuel consumption of the climbing section when the airplane steps cruise is obtained according to the relation between the kilometer fuel consumption of the climbing section when the airplane steps cruise and the increment of the voyage, wherein the kilometer fuel consumption of the climbing section when the airplane steps cruise approximately adopts the kilometer fuel consumption when the airplane steps cruise.
Optionally, in some embodiments, the step of calculating the total fuel consumption of the aircraft during the step cruising according to the total cruising distance includes:
the total fuel consumption of the airplane during the step cruise is obtained by the kilometer fuel consumption of the airplane during the stable level flight cruise, the actual distance of the airplane during the stable level flight cruise and the fuel consumption of the climbing section of the airplane during the step cruise, which is required by the increase of the height:
mw=R·q+ΔR1·qkm1+ΔR2·qkm2+···+ΔRi·qkmi+···+ΔRn·qkmn （8）
wherein q is the kilometer oil consumption of the aircraft during stable level flight cruising, mwAnd the total fuel consumption of the airplane during the step cruise.
Specifically, the fuel consumption of the aircraft during stable level flight and cruise and the fuel consumption of the climbing section during step flight and cruise of the aircraft are added to obtain the total actual fuel consumption of the aircraft during step flight and cruise.
By the method for calculating the fuel consumption of the airplane during the step cruise, when fuel oil planning is performed on the airplane in a task planning system or a flight management system of the airplane, the performance of a climbing section in the step cruise process of the airplane is estimated by adopting an energy conservation method, the height increased by the climbing section during the step cruise of the airplane is converted into the increment of a voyage, namely, the calculation of the climbing process is converted into the calculation of the cruise process of stable level flight, and the calculation of the total fuel consumption during the step cruise of the airplane is realized, so that the complexity of the calculation process is reduced, the calculation complexity is greatly reduced within the allowable range of engineering calculation errors, and the calculation efficiency and the calculation precision are improved.
The above process is further illustrated by the following examples.
Example 1: given that the cruising speed of the airplane is 800km/h and the initial cruising weight is 200t, the fuel consumption required by the airplane for cruising and flying for 3000km by adopting a step cruising mode is calculated, wherein the cruising weight, the height division, the average lift-drag ratio and the kilometer fuel consumption data of the step cruising are shown in a table 1.
TABLE 1 average lift-drag ratio and kilometer fuel consumption for cruise section
(1) At the height of 9000m, the kilometer oil consumption is 10kg/km when the weight is 200t, and the kilometer oil consumption is 9.7kg/km when the weight is 190t, so that the flat flight distance obtained when the aircraft consumes 10t of fuel oil is as follows:
10×1000/（10/2+9.7/2）=1015km；
(2) the increase in height from 8900m to 9500m translates into a horizontal distance:
△h×K=（9500-8900）/1000×20=12km
the increase in height from 8900m to 9600m translates into fuel consumption:
10×（10+9.7）/2=99kg=0.118t
the reduced oil consumption consumed by the aircraft in the first cruise segment is as follows: 10+0.118=10.118t
The weight of the aircraft at the end of the first cruise section climbing to a height of 9600m is 200-10.118=189.882t
(3) The initial weight of the aircraft starting the second cruise section at the height of 9500m is 189.882t, the kilometer oil consumption is about 9.6kg/km, the kilometer oil consumption is 9.2kg/km when the aircraft starts the second cruise section at the height of 180t, and therefore the flat flight distance obtained when the aircraft consumes 189.882-180=9.882t of fuel oil is equal to
9.882×1000/（9.6/2+9.2/2）=1051km；
The cruising distance at this moment is cumulatively: 1015+1051=2066km
(4) The aircraft climbs from 9500m to 10100m in height at the end of the second cruise section, and the horizontal distance is converted into:
△h×K=（10100-9500）/1000×21=12.6km
the increase in height from 8900m to 9600m translates into fuel consumption: 12.6 × (9.6/2 + 9.2/2) =94kg =0.094t
The reduced oil consumption of the aircraft in the second cruise segment is as follows: 9.882+0.118=10t
The weight of the aircraft at this time is: 189.882-10=179.882t
(5) The initial cruising weight of the airplane at the beginning of the third cruising segment at the height of 10100m is 179.882t, the kilometer oil consumption at the moment is about 9.2kg/km, the distance from the cruising end point is 3000-plus 2066=934km, and if the weight at the end of cruising is about 170t, the corresponding kilometer oil consumption is 9.2kg/km, and the oil consumption required by the cruising distance 934km is as follows:
934*（9.2/2+8.8/2）=8406kg=8.406t
(6) and finally, calculating the total oil consumption required by the cruise distance of 3000km for performing the step cruise according to the requirement as follows:
10.118+10+8.406=28.524t
example 2: the known conditions of 500km/h of airplane patrol speed, 8900-11300 m of patrol height, 30t of initial patrol weight, 10t of patrol task fuel quantity, the division of patrol sections, the average lift-drag ratio of each section obtained through calculation, the average hour oil consumption and the like are shown in the following table 2. And solving the patrol time of the airplane.
TABLE 2 average lift-drag ratio and average hourly fuel consumption for patrol section
The solving steps are as follows:
(1) the climbing height from the 1 st patrol section to the 2 nd patrol section is as follows: 9500-:
（9500-8900）/1000*（15.5+16）/2=9.45km
the oil consumption required for flying the distance at a patrol speed of 500 km/h: 9.45/500 x 1.3=0.025t
The 1 st patrol section effective patrol fuel oil is as follows: 30-28-0.025=1.975 t;
the patrol time of the 1 st patrol section is as follows: 1.975/1.3=1.519 h;
(2) climbing height from the 2 nd patrol section to the 3 rd patrol section: 10100-:
（10100-9500）/1000*（16+15.7）/2=9.51km
the oil consumption required for flying the distance at a patrol speed of 500 km/h: 9.51/500 x 1.24=0.024t
The 2 nd patrol section effectively patrols fuel oil as follows: 28-26-0.024=1.976 t;
the period of the 2 nd patrol period is as follows: 1.976/1.24=1.594 h;
(3) according to the steps in (1) and (2), the cruise time of the 3 rd section and the cruise time of the 4 th section are respectively obtained as follows: 1.706h, 1.834 h;
(4) the patrol section of the 5 th section does not comprise a climbing section, and the patrol time is (22-20)/0.98 =2.041 h;
(5) the total patrol time is: 1.519+1.594+1.706+1.834+2.041=8.694 h.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by one skilled in the art.
Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. This application is intended to cover any variations, uses, or adaptations of the disclosure following, in general, the principles of the disclosure and including such departures from the present disclosure as come within known or customary practice within the art to which the disclosure pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.
Claims (9)
1. A method for calculating the cruise oil consumption of an aircraft, the method comprising:
determining the gravitational potential energy added by the airplane in the climbing section by utilizing the height added by the climbing section when the airplane is cruising in the ladder;
determining the work done by the thrust of the aircraft engine according to the stable flat flight of the aircraft to a preset distance;
according to energy conservation, the gravitational potential energy added by the aircraft is equal to the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy, and the fuel oil energy consumed by the climbing section due to the increase of the gravitational potential energy is approximately equal to the work done by the thrust of the aircraft engine when the aircraft stably and flatly flies to the preset distance;
based on the energy conservation, according to the relationship that when the aircraft stably and flatly flies, the thrust is equal to the resistance, and the lift is equal to the gravity, the increased height of the climbing section in the airplane ladder cruising process is converted into the increased amount of the voyage, and the total cruising distance of the airplane ladder cruising process is obtained;
and calculating the total fuel consumption of the airplane during the step cruise according to the total cruise distance.
2. The method for calculating the aircraft cruise oil consumption according to claim 1, wherein the added gravitational potential energy of the aircraft is as follows:
Ep=migΔhi （1）
wherein m isiThe real-time quality of the airplane at the ith climbing section of the airplane ladder cruising,
is the acceleration of gravity,. DELTA.hiAnd increasing the height of the ith climbing section of the airplane step cruise, wherein i is a positive integer.
3. The method for calculating the aircraft cruise oil consumption according to claim 2, wherein the thrust of the aircraft engine does the following work:
W=FΔRi （2）
wherein F is the thrust of the engine when the aircraft is stably level flying, and Delta RiThe increment of the voyage of the ith climbing section of the airplane ladder cruising.
4. The method for calculating the aircraft cruise oil consumption according to claim 3, wherein the relationship between the gravitational potential energy added by the aircraft and the work done by the thrust of the aircraft engine when the aircraft steadily flies to the preset distance is as follows:
migΔhi≈FΔRi （3）。
5. the method for calculating the cruising oil consumption of the airplane as claimed in claim 4, wherein the step of converting the increase of the altitude of the climbing section in the cruising of the airplane ladder into the increase of the voyage according to the relationship between the equal thrust and the equal resistance and the equal lift and the equal gravity when the airplane stably flies based on the conservation of energy comprises the following steps:
introducing an average lift-drag ratio to obtain a relationship that the thrust is equal to the resistance and the lift is equal to the gravity when the aircraft stably flies flat:
wherein D is the resistance when the airplane stably flies flat, Y is the lift when the airplane stably flies flat, K is the average lift-drag ratio,
is the aircraft weight.
6. The method for calculating the cruising oil consumption of the airplane as claimed in claim 5, wherein the step of converting the increased height of the climbing section in the cruising of the airplane ladder into the increased amount of the voyage according to the relationship between the equal thrust and the equal resistance and the equal lift and the equal gravity when the airplane stably flies based on the conservation of energy comprises the following steps:
the increased height of the climbing section in the airplane step cruise is converted into the increased amount of the voyage:
ΔRi=Δhi·K （5）。
7. the method for calculating the cruising oil consumption of the airplane as claimed in claim 6, wherein the step of converting the increased height of the climbing section in the cruising of the airplane ladder into the increased amount of the voyage according to the relationship between the equal thrust and resistance and the equal lift and gravity when the airplane stably flies in the ladder based on the conservation of energy comprises the following steps:
according to the increment of the voyage and the actual distance of the aircraft during stable level flight cruising, the total cruising distance obtained in the process of cruising at the aircraft ladder is as follows:
Rconversion calculation=R+ΔR1+ΔR2+···+ΔRi+···+ΔRn （6）
Wherein the content of the first and second substances,
for the aircraft to stabilize the actual distance during flat flight cruise, RConversion calculationThe total cruising distance of the airplane during the cruising at the stairs.
8. The method for calculating the cruise fuel consumption of an aircraft according to claim 7, wherein said step of calculating the total fuel consumption of said aircraft during a step cruise based on said total cruise distance comprises:
converting the increased height of the climbing section in the airplane ladder cruising into the increment of the voyage and the kilometer oil consumption of the climbing section in the airplane ladder cruising process to obtain the fuel consumption required by the climbing section in the airplane ladder cruising process due to the increased height as follows:
Δmwi=ΔRi·qkmi=Δhi·K·qkmi （7）
wherein, Δ mwiThe fuel consumption of the ith climbing section during the step cruise of the airplane, qkmiAnd the kilometer oil consumption of the ith climbing section during the stair cruise of the airplane.
9. The method for calculating the cruise fuel consumption of an aircraft according to claim 8, wherein said step of calculating the total fuel consumption of said aircraft during step cruising according to said total cruising distance comprises:
the total fuel consumption of the airplane during the step cruise is obtained by the kilometer fuel consumption of the airplane during the stable level flight cruise, the actual distance of the airplane during the stable level flight cruise and the fuel consumption of the climbing section of the airplane during the step cruise, which is required by the increase of the height:
mw=R·q+ΔR1·qkm1+ΔR2·qkm2+···+ΔRi·qkmi+···+ΔRn·qkmn （8）
wherein q is the kilometer oil consumption of the aircraft during stable level flight cruising, mwAnd the total fuel consumption of the airplane during the step cruise.
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