CN110334410B - High-speed aircraft and integrated design method of rear body tail nozzle thereof - Google Patents
High-speed aircraft and integrated design method of rear body tail nozzle thereof Download PDFInfo
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Abstract
The invention provides a high-speed aircraft rear body tail nozzle integrated design method and a high-speed aircraft, wherein the method comprises the following steps: 1. tail nozzle profile design, including: acquiring a plurality of tail pipe molded lines based on the same nozzle inlet conditions and expected nozzle outlet conditions; determining a required tail pipe molded line, wherein the net thrust of the tail pipe is maximum under the molded line; 2. based on the desired nozzle profile, an initial integrated design of the aircraft aft body/nozzle is performed, including: determining the expansion ratio and the outlet area of the tail nozzle; acquiring a three-dimensional tail pipe molded surface according to the outlet area and a required tail pipe molded line; designing the thickness of the post-structure; 3. based on the initial design results, the final integrated design of the aircraft aft body/nozzle is performed: and adjusting the offset height of the thrust center line of the tail nozzle and the aspect ratio of the tail nozzle. The invention can solve the technical problems of mismatching of push resistance performance, incapability of meeting the performance requirement of an aircraft and the like caused by lower integration degree in the aspect of the design of the existing rear body/tail nozzle.
Description
Technical Field
The invention relates to the technical field of high-speed aircraft design, in particular to a high-speed aircraft rear body tail nozzle integrated design method and a high-speed aircraft.
Background
For a high-speed aircraft adopting an air suction type engine, the integrated design of the aircraft and a propulsion system is an important design concept of pneumatic appearance design, and the requirements of each specialty of engines, pneumatic, overall and structural are comprehensively considered in the design process, so that the integrated design of a rear body/tail nozzle is one of important matters. From the viewpoint of aircraft design, the requirements for the engine body and the engine are different: the engine design requires that the loading space of the rear body of the aircraft is enough, the cross section area is as small as possible, the bottom resistance is small, and the engine design requires the tail nozzle to have enough area expansion ratio to generate enough thrust.
The present high speed aircraft has a low degree of integration in the aft body/tail nozzle design due to: on one hand, for the current machine body and tail nozzle design, the designs are divided into different professions, and the individual performances of the machine body and the tail nozzle can be guaranteed, so that the total effect after superposition is greatly reduced; on the other hand, in the two designs, the related design parameters are more and complex, and as the matching design of the two designs is not simple superposition and compromise, the matching relation of each key design parameter needs to be comprehensively balanced, so that the difficulty is increased. Because the integration degree in the aspect of the design of the current post body/tail nozzle is lower, the high-speed aircraft has the technical problems that the push resistance is not matched, the overall performance of the aircraft cannot meet the requirements and the like, and the development of the aircraft is limited. Based on this background, it is highly desirable to establish a post body/tail nozzle integrated matching design method suitable for high-speed aircraft.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, provides a high-speed aircraft aft-body tail nozzle integrated design method and a high-speed aircraft, and can solve the technical problems that in the prior art, the high-speed aircraft is low in integration degree in the aspect of aft-body/tail nozzle design, the push resistance performance is not matched, the aircraft performance requirement cannot be met, and the like.
The technical scheme of the invention is as follows:
according to one aspect, there is provided a method of integrated design of a high-speed aircraft aft body/tail nozzle, the method comprising the steps of:
step 1, designing a tail nozzle molded line, which comprises the following steps:
1.1, acquiring a plurality of tail nozzle molded lines based on the same nozzle inlet conditions and expected nozzle outlet conditions;
1.2, selecting one of a plurality of tail pipe molded lines as a required tail pipe molded line, wherein the net thrust of the tail pipe is maximum under the required tail pipe molded line;
2.1 determining the expansion ratio and the outlet area of the tail pipe;
2.3, obtaining a three-dimensional tail pipe molded surface according to the outlet area and the required tail pipe molded surface;
2.4 designing the thickness of the post-body structure based on the outlet area of the tail nozzle;
and adjusting the offset height of the thrust center line of the tail nozzle and the aspect ratio of the tail nozzle.
Further, in the step 1, the nozzle profile design is based on a full wall expansion nozzle.
Further, the same nozzle inlet conditions include: mach number and pressure of the gas flow at the nozzle inlet; the desired nozzle outlet condition is a desired Mach number of the gas stream at the nozzle outlet.
Further, the step 1.2 includes:
based on Mach numbers and pressures of airflow at the inlet and expected Mach numbers of airflow at the outlet of the jet pipes corresponding to each tail jet pipe molded line, acquiring the tail jet pipe net thrust corresponding to each tail jet pipe molded line by adopting a numerical simulation method;
the tail pipe molded line corresponding to the maximum tail pipe net thrust is the required tail pipe molded line.
Further, the outlet area s2=nozzle inlet area s1×nozzle expansion ratio of the nozzle;
further, the expansion ratio of the tail nozzle and the thickness of the rear body structure are determined by the following steps:
taking the expansion ratio of the tail pipe and the thickness of the rear body structure as input conditions according to flight suggestion requirements;
under the input condition, a numerical simulation method is adopted to obtain the corresponding expansion ratio of the tail nozzle and the thickness of the rear body structure when the thrust resistance characteristics of the aircraft are optimal.
Further, the adjusting the nozzle thrust centerline offset height and the nozzle aspect ratio includes:
obtaining a theoretical value of the thrust central line deviation height of the tail nozzle;
and taking the theoretical value and the aspect ratio of the tail nozzle required by the flight proposal as input conditions, and acquiring the corresponding deviation height and the aspect ratio of the tail nozzle when the front moment and the rear moment of the aircraft are balanced by adopting a numerical simulation method.
Further, the theoretical value of the deviation height is obtained by adopting the following formula:
further, the expansion ratio and the thickness of the rear body structure of the tail nozzle required by the flight proposal are respectively as follows: 3-7, and 50-100mm; the aspect ratio of the tail nozzle required by the flight proposal is as follows: 1-3.
According to another aspect, a high speed aircraft is provided, the aircraft comprising an aircraft aft body and a tail nozzle, the aircraft aft body and the tail nozzle being integrally designed according to the above method.
By the technical scheme, the invention provides a high-speed aircraft aft-body/tail nozzle integrated design method, key parameters are extracted from a plurality of complex design parameters to carry out collaborative design and design steps are reasonably arranged, namely, the tail nozzle molded line is designed firstly, and key parameters extracted from the expansion ratio, the outlet area, the aft-body structure thickness, the thrust central line deviation height of the tail nozzle, the tail nozzle aspect ratio and the like of the tail nozzle are designed in a collaborative manner, so that the aft-body/tail nozzle integrated process is simplified, the net thrust of the tail nozzle and the thrust resistance characteristic of the aircraft are guaranteed to be excellent, the moment of the aircraft is balanced, and the overall performance of the aircraft is greatly improved. The invention solves the problems of contradiction of push resistance and safety control of the high-speed aircraft, realizes the optimal overall performance of the aircraft on the basis of ensuring feasibility through wind tunnel test and numerical simulation effectiveness verification, and supports the design of the aircraft scheme.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 shows a schematic cross-sectional view of a tail pipe with a symmetrical nozzle;
FIG. 2 illustrates a profile axial view of a tail pipe;
FIG. 3 illustrates a schematic diagram of an aircraft isometric view provided in accordance with an embodiment of the present invention;
FIG. 4 illustrates a schematic cross-sectional view of an aircraft aft-body, tail nozzle, provided in accordance with an embodiment of the present disclosure;
FIG. 5 illustrates nozzle profiles at different exit Mach numbers provided in accordance with an embodiment of the present invention;
FIG. 6 is a flow diagram of a method for integrated design of a high-speed aircraft aft body/tail nozzle according to an embodiment of the present disclosure;
wherein the above figures include the following reference numerals:
the method comprises the steps of 1, taking the inlet airflow of the tail pipe as a reference, 2, taking the outlet airflow of the tail pipe as a reference, 3, taking the profile of the symmetrical surface of the tail pipe as a reference, 4, taking the profile of the tail pipe as a reference, 5, taking the thickness of the bottom structure of the rear body as a reference, 7, taking the thrust center line of the tail pipe as a reference, deviating from the y-direction center of mass of the aircraft, and 8, taking the thrust center line of the tail pipe as a reference, and taking the thrust center line of the tail pipe as a reference, namely the front body of the aircraft.
Detailed Description
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments in accordance with the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
1-5, according to an embodiment of the present invention, there is provided a method for integrally designing a rear body nozzle of a high-speed aircraft, the method including the steps of:
step 1, designing a tail nozzle molded line, which comprises the following steps:
1.1, acquiring a plurality of tail nozzle molded lines based on the same nozzle inlet conditions and expected nozzle outlet conditions;
1.2, selecting one of a plurality of tail pipe molded lines as a required tail pipe molded line, wherein the net thrust of the tail pipe is maximum under the required tail pipe molded line;
2.1 determining the expansion ratio and the outlet area of the tail pipe;
2.3, obtaining a three-dimensional tail pipe molded surface according to the outlet area and the required tail pipe molded surface;
2.4 designing the thickness of the post-body structure based on the outlet area of the tail nozzle;
and adjusting the offset height of the thrust center line of the tail nozzle and the aspect ratio of the tail nozzle.
By adopting the configuration mode, the integrated design method of the rear body/tail nozzle of the high-speed aircraft is provided, key parameters are extracted from a plurality of complex design parameters to carry out collaborative design and design steps are reasonably arranged, namely, the tail nozzle molded line is designed firstly, the expansion ratio and the outlet area of the tail nozzle, the thickness of the rear body structure, the thrust central line deviation height of the tail nozzle, the aspect ratio of the tail nozzle and other extracted key parameters are designed in a collaborative manner, the integrated process of the rear body/tail nozzle is simplified, the net thrust of the tail nozzle and the thrust resistance characteristic of the aircraft are guaranteed to be excellent, the moment of the aircraft is balanced, and the overall performance of the aircraft is greatly improved. The invention solves the problems of contradiction of push resistance and safety control of the high-speed aircraft, realizes the optimal overall performance of the aircraft on the basis of ensuring feasibility through wind tunnel test and numerical simulation effectiveness verification, and supports the design of the aircraft scheme.
Further, in the present invention, in order to ensure aerodynamic performance and safety control of the aircraft, in the step 1, the nozzle profile design is performed based on a full-wall expansion nozzle.
In the embodiment of the present invention, the tail nozzles are generally divided into two types: the reason why the full-wall expansion spray pipe is selected is that: the single-wall expansion spray pipe can generate a 'propulsion lift force' and a cold-hot moment difference for the aircraft due to asymmetry, so that the influence on the aerodynamic performance of the aircraft is great; and for the problem of interstage separation of the serial booster on the tail end face of the single-shot and bullet-used scale aircraft, the angle of the tail end face is inclined due to the single-wall expansion spray pipe, which is not beneficial to separation safety.
Further, to obtain a jet tail line, the same jet inlet conditions include: mach number and pressure of the gas flow at the nozzle inlet; the desired nozzle outlet condition is a desired Mach number of the gas stream at the nozzle outlet.
In the embodiment of the invention, in the design process, according to Mach number and pressure information of the air flow 1 at the nozzle inlet and Mach number of the air flow 2 at the expected nozzle outlet, as input conditions of a supersonic nozzle characteristic line design method, a simple wave or a Pradat-Meyer expansion fan with central expansion is generated through the acute angle of the nozzle inlet, and the boundary shape of the nozzle, namely the tail nozzle molded line 3, can be determined by absorbing or eliminating each characteristic line reached to the wall by utilizing the change of the slope and the sign with equal size.
Further, in the present invention, in order to obtain the desired nozzle profile, the step 1.2 includes:
based on Mach numbers and pressures of airflow at the inlet and expected Mach numbers of airflow at the outlet of the jet pipes corresponding to each tail jet pipe molded line, acquiring the tail jet pipe net thrust corresponding to each tail jet pipe molded line by adopting a numerical simulation method;
the tail pipe molded line corresponding to the maximum tail pipe net thrust is the required tail pipe molded line.
In the embodiment of the present invention, the numerical simulation method is a technology known in the art, and the specific implementation process thereof is not described in detail herein.
As a specific embodiment of the invention, as shown in FIG. 5, based on the same nozzle inlet condition and design method, 11 tail nozzle molded lines with nozzle outlet Mach numbers of 3.0-4.0 at equal intervals are constructed, and the influence rule of the nozzle Mach numbers on the aircraft resistance and the nozzle thrust is obtained by a numerical calculation method as follows:
(1) the Mach number of the outlet of the tail nozzle is increased, the line length of the tail nozzle is increased, the height of the tail nozzle is increased, the area of the outlet is increased, and the resistance of the aircraft is increased;
(2) the thrust of the tail nozzle is increased and then decreased along with the increase of the Mach number at the outlet of the tail nozzle;
according to the scheme provided by the embodiment of the invention, the jet pipe outlet Mach number is an important parameter affecting the thrust performance of the tail jet pipe, and the net thrust of the tail jet pipe has a maximum value under different outlet Mach numbers. In view of this, the example of the embodiment of the present invention proposes to select the nozzle profile generated by the exit mach number 3.5 as the optimal profile, i.e. the desired nozzle. According to the embodiment of the invention, the tail nozzle is designed according to the tail nozzle molded line, and the tail nozzle molded line selection method is determined, so that the tail nozzle has better thrust performance, and a foundation is laid for the design of the thrust resistance performance of the aircraft.
Further, in the present invention, to obtain the nozzle exit area, the nozzle exit area s2=nozzle entrance area s1 is the nozzle expansion ratio;
further, in the present invention, in order to obtain a suitable expansion ratio of the tail pipe and thickness of the aft-body structure, the expansion ratio of the tail pipe and thickness of the aft-body structure are determined by:
taking the expansion ratio of the tail pipe and the thickness of the rear body structure as input conditions according to flight suggestion requirements;
under the input condition, a numerical simulation method is adopted to obtain the corresponding expansion ratio of the tail nozzle and the thickness of the rear body structure when the thrust resistance characteristics of the aircraft are optimal.
In the embodiment of the invention, on the basis of the required tail nozzle molded line, the expansion ratio of the tail nozzle and the thickness of the rear body structure are selected to perform the initial integrated design of the tail nozzle/the rear body, and the step is a key step for ensuring the solving of the thrust resistance contradiction of the aircraft, and the design principle of the embodiment of the invention is as follows:
as can be seen from the above formula, the outlet area S2 of the nozzle is related to the expansion ratio of the nozzle, the thrust of the engine is generally proportional to the outlet area S2 of the tail nozzle, and for a single-shot, missile-based high-speed aircraft, the outlet area S2 of the nozzle and the thickness 6 of the rear body bottom structure directly determine the rear body cross-sectional area S3 of the aircraft, so that the resistance of the hull increases nonlinearly with the area of the nozzle, and the increase amplitude is larger and larger; with the same structure thickness, the bottom area of the rear body is increased along with the increase of the outlet area S2 of the spray pipe, the bottom resistance of the aircraft is increased, and the maximum push resistance allowance can be ensured by a proper spray pipe expansion ratio from the aspect of push resistance allowance, so the spray pipe expansion ratio is used as a parameter designed in the embodiment of the invention. The design of the aircraft aft-body 5 requires that the aft-body structural thickness 6 is selected to reduce the aircraft drag by taking into account the space requirements of the aft-body structural thickness 6 and the aircraft aft-cabin equipment (steering engines, separation mechanisms, etc.) on the basis of the outlet area S2 of the tail nozzle.
In the embodiment of the invention, the expansion ratio and the thickness of the rear body structure of the tail nozzle required by the flight proposal are respectively as follows: 3-7, and 50-100mm; the thrust resistance characteristics of the aircraft can be evaluated by using the thrust resistance characteristics as input conditions and adopting a numerical simulation method, so that the proper nozzle outlet area S2, the thickness 6 of the rear body bottom structure, the nozzle outlet area and the like can be obtained.
Furthermore, the nozzle profile 3 determined in step one may be given a three-dimensional nozzle profile 4 by adding lateral expansion designs, rotation, etc. depending on the determined nozzle exit area.
Further, in the present invention, based on the above-mentioned guarantee of the thrust performance of the aircraft, to further optimize the performance of the aircraft, obtaining the thrust centerline deviation height of the tail nozzle and the tail nozzle aspect ratio includes:
obtaining a theoretical value of the thrust central line deviation height of the tail nozzle;
and taking the theoretical value and the aspect ratio of the tail nozzle required by the flight proposal as input conditions, and acquiring the corresponding deviation height and the aspect ratio of the tail nozzle when the front moment and the rear moment of the aircraft are balanced by adopting a numerical simulation method.
In the embodiment of the invention, on the basis of ensuring the push resistance performance of the aircraft, the design principle of the embodiment is as follows:
according to the embodiment of the invention, the fore-and-aft moment of the aircraft is balanced through the further optimized design of the aft-body/tail nozzle, and the good stability of operation is maintained. The design parameters of the embodiments of the present invention are selected from the nozzle thrust centerline offset height and nozzle aspect ratio, as follows: the general aircraft front body 8 generates head-up moment and the aircraft rear body 5 generates low head moment, and the low head moment of the rear body can be adjusted on the basis of keeping the optimal energy of the front body/air inlet channel by adjusting the offset height of the thrust center line of the tail nozzle, namely the offset height 7 of the thrust center line of the tail nozzle from the y-direction center of mass of the aircraft and the aspect ratio of the tail nozzle, so that the pitching moment balance design of the aircraft is realized: the thrust center line of the tail nozzle deviates from the positive height (namely, the center line is positioned above the y-direction centroid) so that the thrust of the tail nozzle generates low head moment; the increase of the aspect ratio of the tail nozzle increases the area of the longitudinal lifting surface of the rear body, increases the moment of low head, increases the longitudinal stability of the aircraft and gives consideration to the resistance characteristic of the aircraft.
Specific determination of the thrust centerline off-height and aspect ratio of the nozzle: the aspect ratio of the jet nozzle required by flight advice is: 1-3. The offset height may be expressed as:
the method is characterized in that a theoretical value is obtained through calculation, on the basis, the moment characteristics of the aircraft can be confirmed and adjusted through calculation of the whole aircraft performance by a numerical simulation method, iterative optimization is carried out according to an optimization target, the variation range of pitching moment differences under different working conditions of an engine is ensured to be small, the aircraft has good stability characteristics, and the safety of flight control is ensured.
According to a further embodiment of the invention, there is also provided a high-speed aircraft comprising an aircraft aft-body and a nozzle, the aircraft aft-body and nozzle being integrally designed according to the above-described method.
In the embodiment of the invention, based on the integrated design method of the rear body and the tail nozzle of the aircraft, the comprehensive performance of the aircraft can be greatly improved.
In conclusion, by adopting the method for integrally matching and designing the rear body/tail nozzle of the high-speed aircraft, provided by the embodiment of the invention, the net thrust of the tail nozzle is ensured to be better, the moment balance design of the aircraft is realized, the problems of contradiction between push resistance of the high-speed aircraft and safety control of the aircraft are solved, the comprehensive performance of the aircraft is ensured to be optimal on the basis of ensuring feasibility, and the design of the scheme of the high-speed aircraft is supported through wind tunnel test and numerical simulation effectiveness verification.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The integrated design method for the aft body tail nozzle of the high-speed aircraft is characterized by comprising the following steps of:
step 1, designing a tail nozzle molded line, which comprises the following steps:
1.1, acquiring a plurality of tail nozzle molded lines based on the same nozzle inlet conditions and expected nozzle outlet conditions;
1.2, selecting one of a plurality of tail pipe molded lines as a required tail pipe molded line, wherein the net thrust of the tail pipe is maximum under the required tail pipe molded line;
step 2, based on the required tail nozzle molded line, performing initial integrated design of an aircraft tail body/tail nozzle, including:
2.1 determining the expansion ratio and the outlet area of the tail pipe;
2.3, obtaining a three-dimensional tail pipe molded surface according to the outlet area and the required tail pipe molded surface;
2.4 designing the thickness of the post-body structure based on the outlet area of the tail nozzle;
step 3, based on the initial design result obtained in the step 2, performing final integrated design of the aircraft afterbody/tail nozzle, including:
adjusting the offset height of the thrust center line of the tail nozzle and the aspect ratio of the tail nozzle;
outlet area of the tail nozzle = nozzle inlet area S1 tail nozzle expansion ratio;
the method for determining the expansion ratio and the thickness of the rear body structure of the tail jet pipe comprises the following steps:
taking the expansion ratio of the tail pipe and the thickness of the rear body structure as input conditions according to flight suggestion requirements;
under the input condition, a numerical simulation method is adopted to obtain the corresponding expansion ratio of the tail nozzle and the thickness of the rear body structure when the thrust resistance characteristics of the aircraft are optimal.
2. The method of claim 1, wherein in step 1, the nozzle profile design is based on a full wall expansion nozzle.
3. The method of claim 1, wherein the same nozzle inlet conditions comprise: mach number and pressure of the gas flow at the nozzle inlet; the desired nozzle outlet condition is a desired Mach number of the gas stream at the nozzle outlet.
4. A method according to claim 3, wherein said step 1.2 comprises:
based on Mach numbers and pressures of airflow at the inlet and expected Mach numbers of airflow at the outlet of the jet pipes corresponding to each tail jet pipe molded line, acquiring the tail jet pipe net thrust corresponding to each tail jet pipe molded line by adopting a numerical simulation method;
the tail pipe molded line corresponding to the maximum tail pipe net thrust is the required tail pipe molded line.
5. The method of any of claims 1-4, wherein adjusting the nozzle thrust centerline offset height and the nozzle aspect ratio comprises:
obtaining a theoretical value of the thrust central line deviation height of the tail nozzle;
and taking the theoretical value and the aspect ratio of the tail nozzle required by the flight proposal as input conditions, and acquiring the corresponding deviation height and the aspect ratio of the tail nozzle when the front moment and the rear moment of the aircraft are balanced by adopting a numerical simulation method.
6. The method of claim 5, wherein the theoretical value of the deflection height is obtained using the following equation:
7. the method of claim 5, wherein the flight recommended required expansion ratio and aft-body structure thickness of the jet nozzle are each: 3-7, and 50-100mm; the aspect ratio of the tail nozzle required by the flight proposal is as follows: 1-3.
8. A high-speed aircraft comprising an aircraft aft body and a tail nozzle, characterized in that the aircraft aft body and the tail nozzle are integrally designed according to the method of any one of claims 1-7.
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