Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN Table 7.Cabin Seat Parameters. Class Seating Seat Aisle Seat Arrangementwidth(mm) width(mm) pitch(mm) Business 2-2-2 625 625 930 Economy 2-4-2 500(505) 495 840 Then main geometry parameters can be got according to Table 6 and 7. Table 8.Geometry parameters. Fuselage Fuselage Fuselage fineness Width(m) length(m) ratio PIS-413 6.517 53.03 8.1372 A330 5.64 63.65 11.29 Fuselage Follow Aft fuselage structures fuselage fineness ratio thickness(mm) fineness ratio PIS-413 120 2.0 3.0 Estimation of Fuselage Width: Wr Na+N'a'+8 (5.1) Where 'N is number of seats,N is number of aisles,'a'is the seat width,and a'is the aisle width. Estimation of Fuselage Length: Lc=20(P%)1.052 (5.2) 16.8Na Where P'is seat pitch,Np is the number of passengers,and 'Na'is the number of seats abreast.) Fuselage fineness ratio: fitess ratio=÷ (5.3) whereLe'is the length of fuselage,and 'W is the width of the fuselage. A thickness of 12omm is added to accommodate fuselage structures,internal decoration,soundproofing panels.Choose fitness ratio 2.0 for forward fuselage and 3.0 for rear fuselage by experience
Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN 11 Table 7. Cabin Seat Parameters. Class Seating Arrangement Seat width(mm) Aisle width(mm) Seat pitch(mm) Business 2-2-2 625 625 930 Economy 2-4-2 500(505) 495 840 Then main geometry parameters can be got according to Table 6 and 7. Table 8. Geometry parameters. Fuselage Width(m) Fuselage length(m) Fuselage fineness ratio PIS-413 6.517 53.03 8.1372 A330 5.64 63.65 11.29 Estimation of Fuselage Width: 𝑊𝑓 = 𝑁𝑎 + 𝑁 ′𝑎 ′ + 𝛿 (5.1) Where ‘N’ is number of seats, N’ is number of aisles, ‘a’ is the seat width, and a’ is the aisle width. Estimation of Fuselage Length: 𝐿𝑐 = 20( 𝑃𝑁𝑝 16.8𝑁𝑎 ) 1.052 (5.2) Where ‘P’ is seat pitch, NP is the number of passengers, and ‘Na’ is the number of seats abreast.) Fuselage fineness ratio: fitness ratio = 𝐿𝑐 𝑊𝑓 (5.3) where ‘Lc’ is the length of fuselage, and ‘Wf’ is the width of the fuselage. A thickness of 120mm is added to accommodate fuselage structures, internal decoration, soundproofing panels. Choose fitness ratio 2.0 for forward fuselage and 3.0 for rear fuselage by experience. Fuselage structures thickness(mm) Follow fuselage fineness ratio Aft fuselage fineness ratio PIS-413 120 2.0 3.0
Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN 5.3 Design of Forward and Aft Fuselage 5.3.1 Forward Fuselage Design The cockpit is located in the front of the fuselage.Main requirements about design is as follows: (1)Streamlined to reduce drag (2)Accommodate pilot of 5%-95%percentile male (1.66-1.86 m) (3)External vision requirements-window layout (4)Length/diameter between 1.5 and 2.0 To design a cockpit,the following factors should be considered: The aerodynamic drag of the shape,adequate space to house the radar equipment, satisfy the airworthiness regulation of drivers'vision and landing gear space.The interior space of cockpit is supposed to satisfy driver's operation requirements.The main factors to consider in the design of the cockpit include airworthiness requirements,human factors,and integrated system. The vision requirement for the fuselage is that pilot can see the distance of the ground in 15 to 20 m,and be able to see the wing tips of wings.In climbing process, the pilot should be able to see the horizon more than 10.In landing progress,the pilot should has enough field of vision to see the ground.And in level flight,view angle should be upwards 20 and downward 17 at least. 5.3.2 Aft Fuselage Design In general,dihedral angle is one of the main parameters in the design of the aft fuselage.Because in takeoff and landing process,the plane at a large angle of attack position not brushing the ground is important.Other considerations including the cargo door of aft fuselage and the layout of the tail. (1)Dihedral angle is the factor to decide the ability of taking off and landing process.As a matter of experience,we set to be 14 degree. (2)Contraction angle.It's the most important factor to influence the drag of the tail.This angle is usually at 12 degree to 15 degree.The large contraction angle will lead the separation of the air,which will increase the drag.In PIS-413 12
Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN 12 5.3 Design of Forward and Aft Fuselage 5.3.1 Forward Fuselage Design The cockpit is located in the front of the fuselage. Main requirements about design is as follows: (1) Streamlined to reduce drag (2) Accommodate pilot of 5%-95% percentile male (1.66-1.86 m) (3) External vision requirements –window layout (4) Length/diameter between 1.5 and 2.0 To design a cockpit, the following factors should be considered: The aerodynamic drag of the shape, adequate space to house the radar equipment, satisfy the airworthiness regulation of drivers' vision and landing gear space. The interior space of cockpit is supposed to satisfy driver's operation requirements. The main factors to consider in the design of the cockpit include airworthiness requirements, human factors, and integrated system. The vision requirement for the fuselage is that pilot can see the distance of the ground in 15 to 20 m, and be able to see the wing tips of wings. In climbing process, the pilot should be able to see the horizon more than 10 °. In landing progress, the pilot should has enough field of vision to see the ground. And in level flight, view angle should be upwards 20°and downward 17°at least. 5.3.2 Aft Fuselage Design In general, dihedral angle is one of the main parameters in the design of the aft fuselage. Because in takeoff and landing process, the plane at a large angle of attack position not brushing the ground is important. Other considerations including the cargo door of aft fuselage and the layout of the tail. (1) Dihedral angle is the factor to decide the ability of taking off and landing process. As a matter of experience, we set to be 14 degree. (2) Contraction angle. It’s the most important factor to influence the drag of the tail. This angle is usually at 12 degree to 15 degree. The large contraction angle will lead the separation of the air, which will increase the drag. In PIS-413
Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN design,the contraction angle is set to be 15 degree. 5.4 Airworthiness Related to Cabin Design (1)Crashworthiness Crashworthiness refers to which can make the crew on board the maximum protected,as far as possible to reduce casualties in case of emergency events.In this part,we mainly should consider aft-facing seats,avoid seating passengers over areas with stiff understructure,fire and smoke resistant interior design,energy absorbent structure design,seat design to withstand crash loading. (2)Evacuation PIS-413 should satisfy FAA 9o-second rule and pay attention to the minimum number and type of emergency exits. (3)Passenger Comfort Factors In this part,oxygen,humidity level,temperature,air flow,and rate of change are important factors.Seat arrangement and in-flight entertainment system should also be considered. 5.5 Fuselage Cross Section The design of cross section based mainly on the considerations as follows: (1)Structural requirements for pressurization (2)Passenger comfort and configuration flexibility (3)Freight and baggage considerations (4)Airworthiness regulations Finally,we choose interconnection circular (multi-arc)sections and hypothesize every passenger carry 0.125 m3 luggage.Choose 120 mm to add to accommodate fuselage structures,internal decoration,soundproofing panels. 13
Conceptual Design of the Wide-Body PIS-413 FUSELAGE DESIGN 13 design, the contraction angle is set to be 15 degree. 5.4 Airworthiness Related to Cabin Design (1) Crashworthiness Crashworthiness refers to which can make the crew on board the maximum protected, as far as possible to reduce casualties in case of emergency events. In this part, we mainly should consider aft-facing seats, avoid seating passengers over areas with stiff understructure, fire and smoke resistant interior design, energy absorbent structure design, seat design to withstand crash loading. (2)Evacuation PIS-413 should satisfy FAA 90-second rule and pay attention to the minimum number and type of emergency exits. (3)Passenger Comfort Factors In this part, oxygen, humidity level, temperature, air flow, and rate of change are important factors. Seat arrangement and in-flight entertainment system should also be considered. 5.5 Fuselage Cross Section The design of cross section based mainly on the considerations as follows: (1) Structural requirements for pressurization (2) Passenger comfort and configuration flexibility (3) Freight and baggage considerations (4) Airworthiness regulations Finally, we choose interconnection circular (multi-arc) sections and hypothesize every passenger carry 0.125 m3 luggage. Choose 120 mm to add to accommodate fuselage structures, internal decoration, soundproofing panels
Conceptual Design of the Wide-Body PIS-413 CABIN AND CARGO DESIGN 6 Cabin and Cargo Design 6.1 Cabin Design 6.1.1 Considerations Cabin design should meet the airworthiness,industry standards,human factors,such as requirements,comfortable travel environment for passengers. The comfort feeling of passengers is not only affected by the physical space design,also the influence of psychological factors.In the cabin environment design,consider the following three factors: (1)Spatial layout (2)The physical environment (climate) (3)The psychological factor Factors that affect the cabin layout design include:voyage,seating,structure, pneumatic,man-machine engineering and regulatory requirements. 6.1.2 Cross Section Design Circular is ideal for pressurized cabin.Figure 1 shows the cross section of PIS- 413's fuselage which use multi-arc to make up.The landscape orientation,also the diameter is 6.517 m,longitudinal distance is about 4.187m. (a) (b) Figure 1.Cross section of fuselage.(a)First design.(b)Second design. 14
Conceptual Design of the Wide-Body PIS-413 CABIN AND CARGO DESIGN 14 6 Cabin and Cargo Design 6.1 Cabin Design 6.1.1 Considerations Cabin design should meet the airworthiness, industry standards, human factors, such as requirements, comfortable travel environment for passengers. The comfort feeling of passengers is not only affected by the physical space design, also the influence of psychological factors. In the cabin environment design, consider the following three factors: (1) Spatial layout (2) The physical environment (climate) (3) The psychological factor Factors that affect the cabin layout design include: voyage, seating, structure, pneumatic, man-machine engineering and regulatory requirements. 6.1.2 Cross Section Design Circular is ideal for pressurized cabin. Figure 1 shows the cross section of PIS- 413’s fuselage which use multi-arc to make up. The landscape orientation, also the diameter is 6.517 m, longitudinal distance is about 4.187 m. (a) (b) Figure 1. Cross section of fuselage. (a) First design. (b) Second design
Conceptual Design of the Wide-Body PIS-413 CABIN AND CARGO DESIGN Table 9.First design parameters. Fuselage Width (m) Longitudinal distance(m) 5.24 5.49 Table 10.Second design parameters. Fuselage Width(m) Longitudinal distance(m) 6.517 4.187 Compared with the first design,cargo of the second one is smaller.Because it's short flight,passengers usually won't bring much luggage.And this innovative design will save place on the two sides.What's more,we can make conveyor belt on the two sides to help distribute food or other things.When combined with wings, cross section of the plane is just like an airfoil,which can produce more lift force. 6.1.3 Arrangement of Toilets and Kitchen (1)Kitchen: The number of toilets and kitchens should match with the number of passengers and the air range.Use the function as follow to measure area of kitchen. Sk=(0.050.1)N (6.1) N represents number of passengers.After calculating,our design of kitchen is 15m2. (2)Toilet: Table 11.Number of toilets. All economic Economic Item class First/Business class Passengers per toilet ≤75 ≤75 ≤20 Table 12.Geometry parameters of toilet. Item Size Minimum volume (in3) 2.7*107 Minimum length/width (in) 737 Minimum distance between each toilet seat(in) 661 15
Conceptual Design of the Wide-Body PIS-413 CABIN AND CARGO DESIGN 15 Table 9. First design parameters. Fuselage Width (m) Longitudinal distance (m) 5.24 5.49 Table 10. Second design parameters. Fuselage Width(m) Longitudinal distance (m) 6.517 4.187 Compared with the first design, cargo of the second one is smaller. Because it's short flight, passengers usually won't bring much luggage. And this innovative design will save place on the two sides. What’s more, we can make conveyor belt on the two sides to help distribute food or other things. When combined with wings, cross section of the plane is just like an airfoil, which can produce more lift force. 6.1.3 Arrangement of Toilets and Kitchen (1) Kitchen: The number of toilets and kitchens should match with the number of passengers and the air range. Use the function as follow to measure area of kitchen. 𝑆𝑘 = (0.05~0.1)N (6.1) N represents number of passengers. After calculating, our design of kitchen is 15 m2. (2) Toilet: Table 11. Number of toilets. Item All economic class Economic class First/Business Passengers per toilet ≤75 ≤75 ≤20 Table 12. Geometry parameters of toilet. Item Size Minimum volume（in3） 2.7*107 Minimum length/width（in） 737 Minimum distance between each toilet seat（in） 661