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airplane design 5 - component weight estimation - part 6

• Hàng không sân bay được sử dụng cho . • Dịch Vụ Khẩn Cấp • Kết nối cộng đồng nông thôn • Được sử dụng chủ yếu là do thí điểm riêng • Giải trí sử dụng 30 Trung tâm sân bay | 7.1.4 Fighters and Attack Airplanes 7 1 431 GD .-Method For USAF fighters wfc - Kfcf MTO 1-000 0 5 1 7- The constant Kfcf takes on the following values Kf - 106 for airplanes with elevon control r r and no horizontal tail 138 for airplanes with a horizontal tail 168 for airplanes with a variable sweep wing For USN fighters and attack airplanes W- - 2 3.77 W- 1 000 1 7.10 fc TO Note these estimates include the weight of all associated hydraulic and or pneumatic systems. Certain airplanes require a center of gravity control system. This is normally implemented using a fuel transfer system. The extra weight due to a c.g. control system may be estimated from Wjr 23. 3 8 W_ K.p 100 0 442 7.11 fccg p fsp where w is the mission fuel weight in lbs r KfSp 6.55 lbs gal for JP-4 Part V Chapter 7 Page 100 7.2 HYDRAULIC AND OR PNEUMATIC SYSTEM WEIGHT ESTIMATION As seen in Section 7.1 the weight of the hydraulic __ and or pneumatic system needed for powered flight controls is usually included in the flight control system weight prediction. The following weight ratios may be used to determine the hydraulic system weight separately _ For business jets 0.0070 - 0.0150 of WTQ For regional turboprops 0.0060 - 0.0120 of WT0 For commercial transports 0.0060 - 0.0120 of WTQ For military patrol transport and bombers 0.0060 - 0.0120 of WT0 _ For fighters and attack airplanes 0.0050 - 0.0180 of WT0 The reader should consult the detailed weight data in Appendix A for more precise information. 7.3 ELECTRICAL SYSTEM WEIGHT ESTIMATION The reader should consult the detailed weight data in Appendix A for electrical system weights of specific airplanes. 7.3.1 General Aviation Airplanes 7.3.1.1 Cessna Method wels - -0268WTO 7-12 Lt .2 USAF Method w o 426 w. w. l 000 0 51 7.13 els fs iae Note that the electrical system weight In this case is given as a function of the weight of the fuel system plus the weight of Instrumentation avionics and electronics. Part V Chapter 7 Page 101 7.3.1.3 Torenbeek .