RU2403175C2 - Fuselage nose compartment - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Fuselage nose compartment is made in the form of shell the external surface of which is faired with fuselage nose compartment contours in lateral view and plan views. Ordinates and applicates of contour points are calculated by ratios with regard to maximum contour deviation from aircraft reference plane. External surface of windshield glasing is made as single curvature surface formed by straight segments and two arcs superimposed on external surface of fuselage nose compartment.

EFFECT: noise abatement in flight deck and accommodation of sizeable radiolocator.

3 cl, 10 dwg, 4 tbl

Description

The claimed technical solution relates to aeronautical engineering, namely to the solutions of the nose compartments of the fuselages of passenger aircraft, during the design of which, along with the traditional tasks of designing the outer surfaces of aircraft, to reduce aerodynamic drag and optimize the layout of the cockpit, taking into account favorable conditions for the work of aircraft pilots, it is necessary to solve the problems of ensuring optimal division of the fuselage with technological joints on separate compartments.

The technical solution of the nose compartment of the fuselage of an aircraft is known (see Engineering. Encyclopedia. Volume IV-21, part 1, p. 97, M .: Engineering, 2002), in which the shape of the nose compartment of the fuselage and, accordingly, the coordinates of the points of the contours of the nose compartment of the fuselage in the lateral and planned projections are selected in accordance with the ratio:

in which D _f , L is the diameter of the fuselage of the aircraft and the length of the nose compartment of the fuselage, x is the coordinate from the nose of the fuselage, while the value of the coefficient m is selected from the range 0.54 ... 0.95. The construction of the outer contours of the nose compartment of the fuselage in accordance with this technical solution leads to convex contours along the entire length of the new compartment in the side and planar projections. The obtained contours of the bow compartment are suitable for theoretical aerodynamic calculations and do not take into account the layout of the cockpit and the need to include in the outer contours of the bow compartment of the fuselage the frontal glazing of the cockpit, which provides the necessary overview and requirements to ensure favorable working conditions for pilots.

The solution of the nose section of the fuselage is known (see S.M. Eger. Aircraft Design. M .: Mashinostroenie, 1983, pp. 215-219), including a skin made in the form of a shape narrowing towards the tip of the nose section, and frontal glazing. Frontal glazing is made in the form of flat surfaces. Inside the bow compartment there are 2 pilot seats. The implementation of the frontal glazing in the form of flat surfaces worsens the flow around the nose compartment with an oncoming flow, which increases the noise level in the cockpit.

Known technical solution of the nose compartment of the fuselage of the aircraft (see certificate for utility model of the Russian Federation No. 13647, IPC V64C 1/00, publ. 2000.05.10). The theoretical profile of the nasal compartment of this technical solution in the lateral and planned projection is given by the coordinates of the contour points in tabular form. The coordinates of the points in the upper and lower contours of the outer surface of the skin of the nose section of the fuselage are plotted from the horizontal of the fuselage, the coordinates of the contour in the outer surface of the skin of the nose section of the fuselage are plotted from the plane of symmetry of the aircraft (from the center section axis). The nose compartment is equipped with two seats located next to each other and is covered by windshields, the surfaces of which are included in the outer contours of the nose compartment of the fuselage. In addition, in this technical solution in the nose compartment of the fuselage is placed a power plant (engine with a pulling screw).

The closest analogue of the claimed technical solution is the solution given in the certificate for a utility model of the Russian Federation No. 19814 (IPC B64C 1/00, publ. 2001.10.10). As in the above analogue, in this technical solution, the coordinates of the points of the contours of the outer surface of the nose of the fuselage in the side and planar projections are set. The technical solutions stated in this certificate provide for the implementation of the nose section of the aircraft fuselage in the form of a shape tapering to the nose of the aircraft, while the cabin with 2 ... 4 seats for accommodating the pilot and passengers is built into the nose section and is equipped with a windshield, the surface of which is included in the outer contours of the nose fuselage compartment.

Solving the problem of reducing the overall dimensions of the aircraft while maintaining high aerodynamic qualities for light two-four-seat aircraft, mainly for agricultural purposes or local airlines, these solutions are not suitable for designing the nose compartments of the fuselages of passenger aircraft.

The technical problem solved by the claimed invention is the development of the nose compartment of the fuselage of the aircraft, providing favorable conditions for pilots to work in conjunction with the fulfillment of the necessary review requirements for two pilots, the convenience of layout of equipment in the nose compartment and the optimal placement of the technological junction of the nose compartment with the subsequent fuselage compartment.

The technical task is solved as follows.

Known nose compartment of the fuselage, including skin and windshield. The coordinates of the points of the outer surfaces of the skin and the frontal glazing are set in a rectangular coordinate system, the abscissa axis of which is aligned with the construction horizontal of the fuselage, the ordinate axis is placed in the plane of symmetry of the plane, and the applicate axis is perpendicular to it.

In the known solution of the nasal compartment, the new one is that the lower contour of the fuselage nose compartment in the side projection and the contour of the fuselage nose compartment in the plan view are made of successive curves. The curves of the lower contour of the outer surface of the casing in the lateral projection are given by the parameters given in table 1.

Table 1

0 0.0001 -0.29 0 -one -1.174 0.161 0 0.0001 0.003 -0.29 -0.235 -one 0 0.121 -0.0000004 0.003 0.166 -0.29 0,069 -one -0.033 0.146 -0.00000004 0.166 0.951 -0.29 0,069 -one -0.033 0.146 0.000005 0.951 one -0.294 0,067 -one -0.032 0.142 -0.0012

The curves of the contours of the outer surface of the casing in the planned projection are given by the parameters given in table 2.

table 2

C ^B

0 0.003 0 3,134 one -21.0 0.186 0 0.003 0.166 0.000002 0,077 one -0.0001 0.268 -0.0000001 0.166 0.272 -0.482 -0.52 one 0 1,954 0,304 0.272 0.453 -0.473 -0.495 one -0.031 1,891 0.293 0.453 0.951 -1.22 -1,366 one 1,407 6,428 1,687 0.951 one 0.113 0.001 one -0.085 0.271 -0.037

In the claimed solution, the upper contour of the nose compartment of the fuselage in the lateral projection is made of two groups of curves, each of which is composed of successively placed curves, while the curves of the first group are given by the parameters shown in table 3.

Table 3

FROM

0 0.0001 -0.289 0 one -1.174 0.161 0 0.0001 0.003 -0,291 -0.152 one 0 0.219 0.00001 0.003 0.166 -0.289 0.285 one -0.0000004 0.175 -0.00000005 0.166 0.302 -0.289 0.285 one -0.00007 0.175 -0.000003 0.302 0.337 -0.118 0.521 -one -0.001 -0.003 0.001

The curves of the second group of the upper contour of the nose compartment of the fuselage in the lateral projection are given by the parameters shown in table 4.

Table 4

FROM

0.555 0.667 0.113 0.109 one 0.00005 0.124 -0.063 0.667 0.951 0.178 0.789 -one 0.586 -0.601 0.282 0.951 one 0.019 -0.185 one -0.189 0.894 -0.326

The first and second groups of curves of the upper contour of the nasal compartment in the lateral projection are connected by a base segment, the ordinates of the points of which are calculated by the ratio:

The lower end of the base segment is docked with the first group, and the upper with the second group of curves of the upper contour of the nasal compartment in lateral projection.

In the claimed solution, the ordinates of the points of the upper and lower contours of the nose compartment of the fuselage in the lateral projection and the applicates of the points of the outline of the fuselage in the planned projection are calculated by the ratios:

the coordinates of the ends of the curves along the abscissa are calculated by the relations:

А₀ ^K, A₁ ^K, С^K, В₂ ^K, B₁ ^K, B₀ ^K - параметры, значения которых приведены в таблицах 1-4, к - индекс контура,

- относительная продольная координата, рассчитанная по соотношению:Where

A ₀ ^K , A ₁ ^K , C ^K , B ₂ ^K , B ₁ ^K , B ₀ ^K - parameters, the values of which are given in tables 1-4, k is the loop index,

- relative longitudinal coordinate calculated by the ratio:

where x is the longitudinal coordinate counted from the projection of the tip of the fuselage nose compartment to the building horizontal, L _nose is the length of the fuselage nose compartment, and Y _con , Z _con is the distance between the ends of the upper and lower contours of the fuselage nose compartment in the lateral projection and the distance between the ends of the contours the fuselage nose compartment in a planned projection, respectively, ΔY, ΔZ - values whose values do not exceed 5 mm.

In the claimed solution, the said outer surface of the frontal glazing is made in the form of a surface of a single curvature. This surface is formed by segments, including the mentioned base segment, and lower and upper arcs. The lower and upper arches are combined with the outer surface of the skin of the nose compartment of the fuselage, and their vertices are located at the lower and upper ends of the base segment, respectively. The applicates of the points of the lower arc are calculated by the ratio

and the applicants of the points of the upper arc in the ratio:

The ends of the indicated segments are placed at the points of the lower and upper arcs, corresponding to the equal ratio of their applicate to half the length of the corresponding chord, tightening the ends of the lower and upper arcs.

In addition, in the claimed solution, the length of the nose compartment of the fuselage can be selected from the range of 3575 ... 3775 mm, and the distance between the ends of the upper and lower contours in the side projection and the ends of the contours in the planned projection are selected from the ranges of 3385 ... 3400 mm, 3210 ... 3225, respectively.

In addition, in the claimed solution, the planes of the arcs of the outer surface of the frontal glazing can be turned upward relative to their peaks, the lower arc can be rotated at an angle of 2 ... 3 degrees, and the upper one at an angle of 1 ... 1.5 degrees.

The technical result from the use of the proposed technical solution is to enable the development and manufacture on its basis of the nose compartment of the fuselage, providing a comprehensive solution to a number of problems.

So, the totality of the parameters of the nose compartment of the fuselage, given in Tables 1-4, allows not only to improve the aerodynamic characteristics of the aircraft as a whole, but also to provide comfortable conditions for the flight crew to work, as it allows to reduce the noise level in the cockpit as a result of achieving a smooth (continuous ) flow around the upper part of the nose compartment of the fuselage. This is achieved by performing the outer surface of the frontal glazing of the cockpit in the form of a single curvature surface in accordance with its claimed parameters and smoothly interfacing it with the skin in the upper part of the fuselage nose compartment, which is ensured by the claimed combination of the parameters of the upper contour of the nose fuselage projection in lateral projection. In addition, the implementation of the frontal glazing of the cockpit in the form of a surface of a single curvature reduces the possibility of distortion. A turn of the planes of the arches of the outer surface of the frontal glazing relative to their vertices by a small angle further improves the aerodynamic characteristics of the nasal compartment.

The resulting set of parameters of the bow compartment allows you to meet the requirements of AP-25 (OST 1 02721-91) for the review for two pilots placed in the cockpit. In addition, the obtained theoretical contours of the nasal compartment allow you to place all the necessary equipment.

It is most preferable to use the claimed solution for airplanes with a fuselage diameter of 3 ... 4.2 m, and the specified set of distances between the ends of the upper and lower contours in the lateral projection and the ends of the contours in the planned projection provides an opportunity for designers to choose the most successful layout solutions when placing equipment and a cabin pilots in the bow compartment of the fuselage. In addition, the choice of the length of the nose compartment from the range of 3575 ... 3775 mm makes it possible to rationally place the technological joint between the nose compartment and the subsequent fuselage compartment. The prevailing typical layout schemes of modern passenger aircraft include a door located along the fuselage between the cockpit and the wing of the aircraft. A shorter nose section makes it difficult to fit the cockpit; a longer nose section makes it difficult to position the door in the fuselage.

Frontal glazing in the claimed solution is a surface of single curvature - i.e. the line is selected as the generatrix. However, the surface is not expandable - since the generators in their extreme positions are not intersecting straight lines, but intersecting. This solution does not affect the optical properties of the glass and the technology of its production, eliminates additional stresses in the glass, allows you to increase the internal free volume in the pilot’s temple area (the proximity of the inner lining of the cockpit does not “pressure” the pilot).

The claimed solution to the nose compartment of the fuselage is illustrated by the following drawings:

figure 1 - axonometric image of the nose compartment of the fuselage,

figure 2 is a side view of the nose compartment of the fuselage,

figure 3 is a view of the nose compartment of the fuselage in plan,

4 is a diagram of the formation of the surface of the frontal glazing of the nose compartment of the fuselage,

5 is a perspective view of the contours of the nose compartment of the fuselage and the surface of the single curvature of the windshield,

6 is a diagram of the review (for the right pilot),

Fig.7 - viewing angles for the left pilot in a lateral projection,

Fig - viewing angles for the left pilot in a planned projection,

Fig.9 is a diagram of the division of the fuselage, side view,

figure 10 - diagram of the relative position of the upper and lower arches of the outer surface of the windshield relative to the horizontal construction of the aircraft.

The inventive nose compartment 37 of the fuselage is made in the form of a smoothly rounded to the point of the nose shape. The nose compartment of the fuselage includes a lining made of aluminum alloys, and glazing of the cockpit, which includes, as a rule, frontal glazing 1, window 2 and side glazing 3.

In the claimed solution, the outer surface of the skin of the nose compartment of the fuselage and the outer surface of the frontal glazing are specified in a rectangular coordinate system, the abscissa axis of which (X) is aligned with the construction horizontal of the fuselage, the ordinate axis (Y) is located in the plane of symmetry of the plane, and the applicate axis (Z) is perpendicular.

In the claimed solution, the nose compartment of the fuselage is given by the coordinates of the points of the contours in the side and plan projections (see Fig. 2, 3, 5).

The lower contour 29 of the nose compartment of the fuselage (see FIG. 1) in a side projection and the outline 28 (see FIG. 1) of the nose compartment of the fuselage in a plan view are made of successively placed second-order curves, the coordinates of which are calculated by the ratio:

- относительная абсцисса точки контура, А₀ ^K, A₁ ^K, С^K, В₂ ^K, В₁ ^K, В₀ ^K - заявляемые числовые параметры, W_макс - нормирующий множитель, ΔW - дополнительный параметр, учитывающий различного рода погрешности. Относительная координата вдоль оси абсцисс рассчитывается по соотношению:in which w is the desired ordinate or applicate of the contour point,

is the relative abscissa of the contour point, A ₀ ^K , A ₁ ^K , C ^K , B ₂ ^K , B ₁ ^K , B ₀ ^K are the claimed numerical parameters, W _max is the normalizing factor, ΔW is an additional parameter that takes into account various errors. The relative coordinate along the abscissa axis is calculated by the ratio:

in which x is the coordinate of the contour point of the nasal compartment, L _nose is the length of the nasal compartment.

The curves of the lower contour 29 of the outer surface of the skin in the side projection are defined by five curves, the parameters of which are given above in table 1. In accordance with this table, the lower contour is composed of five successive curves of the second order. Figure 2 shows the third 4, fourth 5 and fifth 6 curves. The first and second curves of the lower contour of the outer skin of the fuselage are not conventionally shown in the drawings. The coordinates of the points of the lower contour of the outer surface of the fuselage skin in the lateral projection for all six curves are calculated by the ratio:

in which the parameters A ₀ ^H , A ₁ ^H , C ^H , B ₂ ^H , B ₁ ^H , B ₀ ^H are shown in table 1. The same table also shows the boundaries (in relative values) between the lower contour curves along the fuselage horizontal . So, on the segment from X = 0.166 to X = 0.951 (fourth curve 5 of the lower contour of the skin of the nose compartment of the fuselage in the lateral projection) the ordinates of the lower contour of the nose compartment in the lateral projection are calculated by the ratio:

where Y _con is the distance between the ends 34 of the upper and lower contours of the nose compartment of the fuselage in the lateral projection, ΔY is a value whose value does not exceed 5 mm.

The coordinates of the contour points of the outer surface of the skin in a plan view (see figure 3) are calculated by the ratio:

и конца которых

в относительных единицах также приведены выше в таблице 2. Так, на отрезке, ограниченном относительными координатами

и

кривая задается соотношением:in which A ₀ ^B , A ₁ ^B , C ^B , B ₂ ^B , B ₁ ^B , B ₀ ^B are the parameters shown in Table 2 above, Z _con is the distance between the ends of the 35 contours of the nose compartment of the fuselage in the plan view of the aircraft, ΔZ - a value whose value does not exceed 5 mm. In the claimed solution, the contour of the outer skin of the nose compartment of the fuselage in a plan view is made symmetrical with respect to the plane of symmetry of the aircraft in the form of two branches, each of which is composed of six curves placed in series. Figure 3 shows the location of the second 8, third 9, fourth 10, fifth 11 and sixth 12 curves. The first curve of the contour of the outer skin of the fuselage in a plan view in figure 3 is not conventionally shown. Boundary start points

and the end of which

in relative units are also given above in table 2. So, on a segment bounded by relative coordinates

and

the curve is defined by the ratio:

На фиг.2 показаны вторая 13, третья 14 и четвертая 15 кривые первой группы кривых верхнего контура наружной обшивки фюзеляжа в боковой проекции. Первая и пятая кривые этой группы на фиг.2 условно не показаны. Вторая группа кривых составлена из трех кривых 16, 17, 18 (см. фиг.2 и табл.3) и размещена вдоль оси абсцисс от точки по оси абсцисс с относительной координатой

до плоскости стыка 36 носового отсека с последующим отсеком фюзеляжа 38. Первая и вторая группа кривых верхнего контура носового отсека в боковой проекции соединены наклонным базовым отрезком 19, нижний конец 20 которого с относительной координатой по оси абсцисс

состыкован с первой группой кривых, а верхний конец 21 с относительной координатой по оси абсцисс

состыкован со второй группой кривых верхнего контура носового отсека фюзеляжа в боковой проекции.The upper contour of the nose compartment of the fuselage in the lateral projection is composed of two groups of curves. The first group of curves is composed of five curves (see table 3) and is placed along the abscissa from the nose point of the compartment to a point along the abscissa with a relative coordinate

Figure 2 shows the second 13, third 14 and fourth 15 curves of the first group of curves of the upper contour of the outer fuselage skin in a lateral projection. The first and fifth curves of this group are not conventionally shown in FIG. 2. The second group of curves is composed of three curves 16, 17, 18 (see figure 2 and table 3) and is placed along the abscissa from a point along the abscissa with a relative coordinate

to the junction plane 36 of the nasal compartment with the subsequent fuselage compartment 38. The first and second groups of curves of the upper contour of the nasal compartment in the lateral projection are connected by an inclined base segment 19, the lower end of which 20 with a relative coordinate along the abscissa axis

docked with the first group of curves, and the upper end 21 with a relative coordinate along the abscissa

docked with the second group of curves of the upper contour of the nose compartment of the fuselage in the lateral projection.

The ordinates of the upper contour of the nose compartment of the fuselage in the lateral projection in the areas corresponding to the first and second groups of curves are calculated by the ratio:

in which A ₀ ^B , A ₁ ^B , C ^B , B ₂ ^V , B ₁ ^B , B ₀ ^B are the parameters shown in table 3 for the first group of curves, which includes 5 curves, and in table 4 for the second group of curves which includes three curves. The value of Y _con - the distance between the ends 34 of the upper and lower contours of the nose compartment of the fuselage in the lateral projection (see figure 2), ΔY is a value whose value does not exceed 5 mm

The ordinates of the points of the base segment 19 are calculated by the ratio:

и верхним концом 21 базового отрезка 19

in which X is the relative coordinate of the points along the abscissa axis in the interval between the lower end 20 of the base segment

and the upper end 21 of the base segment 19

до

зализом - последней кривой из первой группы кривых - обеспечивает гладкий переход от кривых первой группы базовому отрезку.The claimed parameters of the first and second groups of curves and the parameters of the base segment are selected so that without kinks and steps to complete the entire upper contour of the nose compartment of the fuselage in the lateral projection in the form of a smooth curve. The presence of the base segment 19 in combination with a small length along the abscissa from

before

Zaliz - the last curve from the first group of curves - provides a smooth transition from the curves of the first group to the base line.

The frontal glazing of the cockpit is inscribed in the casing of the nose compartment of the fuselage in the claimed technical solution. Its outer surface is made in the form of a surface of single curvature, which is formed by a combination of segments 22, the ends of which are placed on two forming arcs: the upper 23 and lower 24. The upper 23 and lower 24 arches are laid on the outer surface of the skin of the nose compartment of the fuselage and are symmetrical with respect to the plane of symmetry the plane. The vertices of the lower 23 and upper 24 arcs are located in the lower 20 and upper 21 ends of the base segment 19, respectively, while the applications of the points of the lower arc are calculated by the ratio

and the applicants of the points of the upper arc in the ratio:

The set of segments that form the outer surface of the frontal glazing of the nose compartment of the fuselage includes the mentioned base segment 19. In addition to this segment includes segments 22 (see FIGS. 3 and 4), the ends of which are located on the lower 24 and upper 23 arches. In this case, the ends of each of the segments are placed at points with an equal ratio of their applicate Z _bi , Z _ni ; to Z _square , Z _kn - half the distance between the ends 42 and 41 of the upper and lower arcs, which is illustrated in figure 4: the ratio of the applicates of the lower end 25 of the forming segment 22 Z _ni to the distance Z _kn is selected equal to the ratio of the applicates of the upper end 26 of the forming segment 22 Z _bi to the distance Z _kb , where Z _kn and Z _{kb are} half the length of the chords that tighten the ends 41 and 42 of the corresponding arcs.

For narrow-body aircraft designed to carry from 90 to 115 passengers, the indicated values of Z _kn and Z _kv can be selected from the ranges 1800 ... 2000 mm and 1450 ... 1600 mm, respectively.

The nose compartment of the fuselage of the aircraft, made in accordance with the claimed technical solution, allows to ensure compliance with the review requirements for pilots. From the review diagram shown in Fig.6, it is seen that the claimed solution to the windshield surface in combination with the parameters of the outer surface of the skin of the nose compartment of the fuselage provides the viewing requirements for passenger aircraft: curves corresponding to the field of view of the left 32 and right 33 eyes of the right pilots, cover with a margin a broken line 31, corresponding to the aviation rules for the review. In addition, the claimed solution provides sufficient visibility in the direction directly in front of the pilot (see Fig. 7) and in the lateral direction (see Fig. 8). The implementation of the nose compartment of the fuselage of the aircraft in accordance with the claimed solution also provides noise reduction in the cockpit and placement in the nose compartment of the radar 30 of significant dimensions.

It is most advisable to use the claimed solution of the bow compartment for narrow-body aircraft designed to carry from 70 to 115 passengers. At the same time, it is advisable to choose the overall dimensions of the fuselage in the cross section from the range from 3 to 4.2 m, and the length of the nose compartment from the range of 3575 ... 3775 mm. This allows you to rationally place the technological junction 36 (see Fig.9) between the nose compartment 37 and the subsequent fuselage compartment 38, taking into account the placement of the fuselage door 39 (see Fig.9).

To improve the aerodynamic characteristics of the nasal compartment, it is advisable to unfold the plane of the arches of the frontal glazing surface, as shown in Fig. 10, at small angles α and β (see Fig. 10) relative to their vertices 20 and 21 upwards from the horizontal of the fuselage. In this case, it is advisable to deploy the lower arc of the outer surface of the frontal glazing at an angle of 2 ... 3 degrees, and the upper arc of the outer surface of the frontal glazing at an angle of 1 ... 1.5 degrees.

Claims (3)

1. The nose compartment of the fuselage, including skin and frontal glazing, the coordinates of the points of the outer surfaces of which in the side and plan projections are specified in a rectangular coordinate system, the abscissa axis of which is aligned with the construction horizontal of the fuselage, the ordinate axis is located in the plane of symmetry of the aircraft, and the applicate axis is perpendicular to it while the lower contour of the nose compartment of the fuselage in the lateral projection and the outline of the nose compartment of the fuselage in the plan view are made of successive curves, the curves of the lower contour aruzhnoy plating surface in lateral projection set parameters:

the contour curves of the outer surface of the skin in a plan view are given by the parameters:

the upper contour of the nose compartment of the fuselage in the lateral projection is made of two groups of curves, each of which is composed of successively placed curves, while the curves of the first group are specified by parameters

the curves of the second group are given by the parameters:

the first and second groups of curves of the upper contour of the nasal compartment in the lateral projection are connected by a base segment, the ordinates of the points of which are calculated by the ratio:

while its lower end is docked with the first group, and the upper - with the second group of curves of the upper contour, the ordinates of the points of the upper and lower contours of the nose compartment of the fuselage in the lateral projection and the applicates of the points of the fuselage contour in the planned projection are calculated by the relations:

the coordinates of the ends of the curves along the abscissa are calculated by the relations:

Where

,

, A ₀ ^K , A ₁ ^K , C ^K , B ₂ ^K , B ₁ ^K , B ₀ ^K - parameters whose values are given in the tables; k is the contour index;

- relative longitudinal coordinate calculated by the ratio:

,
where x is the longitudinal coordinate counted from the projection of the fuselage nose tip to the construction horizontal; L _nose - the length of the nose compartment of the fuselage; Y _con , Z _con - the distance between the ends of the upper and lower contours of the nose section of the fuselage in the lateral projection and the distance between the ends of the contours of the nose section of the fuselage in the plan view, respectively, a ΔY, ΔZ - values whose values do not exceed 5 mm, while the outer surface of the frontal glazing is made in the form of a single curvature surface formed by segments, which include the mentioned base segment, and lower and upper arches, combined with the outer surface of the nasal skin Single fuselage whose vertices are located in the lower and upper ends of the base segment, respectively, wherein the bottom arc applicate points calculated from the ratio

and the applicants of the points of the upper arc in the ratio:

moreover, the ends of these segments are placed at the points of the lower and upper arcs corresponding to the equal ratios of their applicate to half the lengths of the chords, tightening the ends of the corresponding arcs. 2. The nose compartment of the fuselage according to claim 1, characterized in that its length is selected from the range of 3575 ... 3775 mm, and the distance between the ends of the upper and lower contours in the side projection and the ends of the contours in the planned projection are selected from the ranges of 3385 ... 3400 mm and 3210 ... 3225 mm, respectively. 3. The nose compartment of the fuselage according to claim 2, characterized in that the planes of the arcs of the outer surface of the frontal glazing are deployed upward relative to the vertices of the arches, with the lower arc rotated at an angle of 2 ... 3 °, and the upper one at an angle of 1 ... 1.5 °.

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