歼十的英文简介

20120002 （12级陈赓2班）2012051302 Michael Huang黄浩

The airframe of J-10

The airframe is constructed from metal alloys (金属合金）and composite materials（复合材料）for high strength and low weight.The airframe's aerodynamic layout（气动布局）adopts a tail-less canard delta wing （无尾三角鸭翼）configuration（配置）. A large delta wing is mid-mounted towards the rear （后部）of the fuselage(机身）, while a pair of canards（鸭翼）are mounted higher up and towards the front of the fuselage, behind and below the cockpit（驾驶舱）. This configuration provides very high agility（机动性）, especially at low speeds, and also reduces stall speed（失速速度）. A large vertical tail is present on top of the fuselage and small ventral fins （腹鳍）underneath the fuselage provide further stability..

A rectangular air intake (进风口)is located underneath the fuselage, providing the air supply to the engine. Also under the fuselage and wings are 11 hardpoints（挂载点）, used for carrying various types of weaponry（武器）and drop tanks（副油箱）containing extra fuel.

The retractable undercarriage（伸缩式起落架）comprises a steerable pair of nose wheels (前轮）underneath the air intake and two main gear wheels（齿轮)towards the rear of the fuselage. The cockpit is covered by a two-piece bubble canopy(泡状座舱罩）providing 360 degrees of visual coverage for the pilot. The Controls （操纵系统）takes the form of a conventional centre stick（中心操纵杆）and a throttle stick（节流操纵杆）located to the left of the pilot. These also incorporate（包含）"hands on throttle and stick(HOTAS)（单手操纵与油门控制）" controls.A zero-zero ejection seat（弹射座椅）is provided for the pilot, permitting safe ejection in an emergency even at zero altitude and zero speed.

Due to the J-10's aerodynamically unstable design, a digital quadruplex-redundant(四重冗余的）fly-by-wire(FBW电传操纵)flight control system (FCS飞行控制系统) aids the pilot in flying the aircraft. The FCS typically monitors pilot control inputs, preventing the pilot from accidentally exiting the flight envelope（飞行包线）and applying too much control input during high performance flight situations. This is critical in canard wing aircraft, as they are capable of turning in a much tighter radius (半径）than conventional aircraft.

机身是由金属合金和复合材料制成，以提高飞机的强度并减轻飞机重量。机身的气动布局采用无尾三角鸭翼形式。一个中置的大三角翼安装在机身后部，而一副鸭翼被安装在相对较高的机身前部位于驾驶舱后下方的地方。这种配置使飞机拥有很高的机动性，特别是在飞机低速飞行的时候。这一配置还能达到降低飞机的失速速度的效果。一个大垂直尾翼被安置在机身顶部，为进一步增强机身的稳固性，机身下方还特地安装了几个小腹鳍。在机身下方有一个矩形进风口，它可以为发动机提供源源不断的空气。用于携带各种武器和装有备用燃料的副油箱的11个挂载点也位于机身和机翼下方。伸缩式起落架由一副位于进风口下方的双前轮和两个位于机身后部的主齿轮组成。驾驶舱被一块两件式的泡状座舱罩覆盖，这一设计给驾驶员提供了360度的视野范围。操纵系统采用了一个传统的中心操纵杆加一个位于飞行员左侧的节流操纵杆的形式。这也包括了单手操控与油门控制系统。一旦发生危急情况，甚至是零高度零速度的极限情况，弹射座椅都可以保证将飞行员安全弹出。由于歼10的气动不稳定设计，数字四重冗余电传操纵飞行控制系统可以协助飞行员驾驶飞机。飞行控制系统监视着飞行员控制输入，防止飞行员意外退出飞行包线以及在高性能飞行状况下施加过多控制输入。这对鸭翼飞行器来说是至关重要的，因为它们被要求相对于传统飞机能够转更急的弯。