Cg location
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This document discusses the importance and effects of center of gravity (CG) location in aircraft design. It notes that CG affects longitudinal stability, horizontal tail angle selection, and maneuverability. Ideal CG locations are described as forward (high stability but low maneuverability), at the neutral point (balanced stability and control), and aft (unstable but maneuverable). The factors involved in calculating the neutral point are also summarized. Guidelines for CG ranges and component weight placement are provided to achieve proper balance and control.
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2开始安排制作毕业证成绩单电子图；
3毕业证成绩单电子版做好以后发送给您确认；
4毕业证成绩单电子版您确认信息无误之后安排制作成品；
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6快递给客户（国内顺丰国外DHLUPS等快读邮寄）。我们的亲人生我养我的父母您们的年迈的苍老换来了我们新一代的新鲜与活力无论我们在哪里父母对我们的爱和思念为我们的生命增加了光彩给予我们自由追求的力量生活的力量我们也不忘感恩正因为这股感恩的线牵着我们使我们在一年的结束时刻义无反顾的踏上了回家的旅途人们常说父母恩最难回报愿我能以当年爸爸妈妈对待小时候的我们那样耐心温柔地对待我将渐渐老去的父母体谅他们以反哺之心奉敬父母以感恩之心孝顺父母哪怕只为父母换洗的
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留信网认证的作用:
1:该专业认证可证明留学生真实身份
2:同时对留学生所学专业登记给予评定
3:国家专业人才认证中心颁发入库证书
4:这个认证书并且可以归档倒地方
5:凡事获得留信网入网的信息将会逐步更新到个人身份内，将在公安局网内查询个人身份证信息后，同步读取人才网入库信息
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Cg location
- 1. CG LOCATION
- 2. WHY WE NEED TO LOCATE CG? LONGITUDINAL STABILITY SELECTION OF HORIZONTAL TAIL’S ANGLE OF INCIDENCE MODEL AIRCRAFT’S MANEUVERABILTY
- 3. STEEL BALL AND SAUCER THEORY
- 4. FORWARD CG Position of CG in front of aerodynamic centre. Extent of this position depends upon downward lifting capability of horizontal tail. In the designing of swift, the tail download ,tail download needed to offset its wing airfoil’s pitching moment was calculated at 15.4 ounces at 60mph level flight. At 5% of MAC , a CG revs up the tail download.
- 5. Results of surged tail download Increases the weight the airplane’s wing must support. Plunges the horizontal tail’s manoeuvrability. This limited capacity makes achieving a full stall attitude difficult.
- 6. Ebbs and flow of forward CG High longituidinal stability. Good recovery from pitch disturbances. Easy to fly but not highly manoeuverability.
- 7. Neutral point and rear CG Point where the total lift (and drag) forces of two airfoil’s(wing &tail) effectively act. NP lies between the aerodynamic centre of two airfoils. Any perturbance in pitch causes the AoA of both airfoils to change , resulting in change in lift(and drag) forces at NP. Nose up disturbance increasing lift
- 8. Static margin Degree of inherent longitudinal stability governed by distance between CG and NP aft of it. For given NP , moving CG aft would reduce inherent stability. CG and NP coincide to give neutral stability. Moving CG aft of NP would cause serious instability.
- 9. Factors involving complex calculation of NP Tail plain efficiency. Areas of wing and tailplane. Distance between aero dynamic centres of wing and tail. Slopes of respective airfoil’s lift curve. Fuselage area distribution in plan view. Downwash variations Propeller’s rotation
- 10. Is the stability margin restricted.....? Yes , at least a 5%margin is needed. Should not cross the NP.
- 11. Does the fuel consumption related to lower bound of 5%......? Yes, as the fuel content gets low CG gets shifted to right and might cross over NP if it is too nearer(5%) and causes serious pitch instability to the aircraft. Pattern ship designers recognised this and position their fuel tanks on model’s CG.
- 12. Use of ballast to correct CG Add ballast up front for tail-heaviness. Add it aft for nose-heaviness. However adding much weight doesn’t improve the model’s performace.
- 13. Suggestions for installation of control components Position the servo’s wirings as far away from the receiver and antenna. Keep the antenna away from control cables. Position engine , rudder and elevator servos close behind the tank. Position servos for ailerons and flaps in the open wing centre section, between the main and aft spar. Receiver’s battery should be easily accessible. All in fuselage and wing equipment should be easily accessible.
- 14. Weight analysis in CG Power components and fuel. Control components. Landing-gear components. These are the items over which designer has no weight control.
- 15. Position the CG’s of the variable weight items Wings with flaps-50% MAC. Wings without flaps-40% MAC. Horizontal tail-40% MAC. Vertical tail-eyeball the CG. Fuselage-normally 40%of the distance from bulkhead to rudder post.