Stability Principle of Pneumatic Gyro Rudder and Utilization of Decommissioned Gyro Xue Xiaozhong 0糜志浩1 Wei Jingwei Dian Lixin 1 Shen Jianping Pan Yongping, School of Power Engineering, Nanjing University of Science and Technology, Nanjing 210094 Aviation Ammunition Service Institute, Nanjing 210037, the balance speed of the rudder, to solve a certain When the missile is retired, the re-use of its parts and components asks for improvement measures.
According to the spirit of the relevant state departments, the father-type missile has reached the end of its service life and will be retired from the army. However, the multi-component material of this type of missile has excellent processing precision and good performance. It can still be applied to similar or other weapons and equipment. Valuable resource wealth. Re-use of retired equipment parts should be given the attention of the leadership department and the weapons design department.
The missile uses two channels of pitch and yaw control, and the pneumatic gyro and its grandson characteristics are installed on the roll circuit at the rear edge of the wing. The test cabinet is applied to the guidance system of a weapon.
1 The stability principle of the pneumatic gyro rudder is only for the rudder surface, and each pair of rudder surfaces can only be deflected in the same direction, but cannot be differential. This can be used for pitch and yaw motion of the steerable missile, but it cannot control the roll of the missile. When the missile moves in the air, the aerodynamic shape caused by the error in the manufacture and distribution of the missile is asymmetrical, or the external disturbance causes the missile to roll. This roll motion has the potential to interfere with pitch and yaw control. Therefore, it is necessary to control the magnitude of the angular velocity of the missile. At the time of design, a pneumatic gyro rudder was installed at the rear edge of the missile wing.
When the missile is moving in the air, the pneumatic gyro rudder is rotated by the oncoming airflow, and the speed can be as high as 3,44, 1.1. The gyroscopic rudder is part of the empennage, and the rudder surface 4 is parallel. When the missile rolls when it is disturbed. According to the precession of the top. The rotating shaft of the gyro is precessed in the direction of the rolling angular velocity 7 under the action of the gyro torque. The pneumatic gyro rudder surface is forced to deflect about the axis and is at an angle to the empennage. After the deflection of the rudder surface, the gyro damping torque is formed. On the other hand, the pneumatic hinge torque is generated. When the gyro moment is balanced with the pneumatic hinge torque, the yaw deflection of the gyro is obtained. The direction of the moment is opposite to the direction of the roll angular velocity 7 of the missile. Therefore, it is the damping torque of the damper missile rolling, which plays a stabilizing role in the rolling circuit.
Set the polar moment of inertia of the parent gyro's pneumatic gyro rudder. , the gyro moment is the direction of the forward sagittal product, y790, the distance from the center of the pneumatic gyro rudder to the rudder axis is 6, when the gyro moment is privately balanced with the hinge torque field, the lift of the single pneumatic gyro rudder The following four lifts of the pneumatic gyro rudder are used to take the moment of the elastic shaft, and the gyro damping torque is obtained. The gyro damping torque seems to have the following approximate type. When the pneumatic gyro rudder rotates and swings at the same time, due to the change of the flow field near the gyro surface, Magnus forces and moments are generated. The 4 nunu break type is the diameter of the gyro, and the brother is the area of ​​the gyro rudder. The Magnus torque direction is perpendicular to the rudder shaft.
The moment of the Magnus torque of the four pneumatic gyro rudders on the spring axis is the gyro Magnus damping torque, the gyro Magnus damping torque has the following approximation, and the characteristics of the 2 rolling motion of the missile are in the pneumatic gyroscope. In the case of rudder damping, the missile roll motion equation is due to 锾. Far from small. , and, so the equation can be simplified to a simplified form of the missile roll motion equation.
Solution, you can get 7 = rush, 5, æ¡•. Under normal circumstances. In the case of the above formula, under the action of the pneumatic gyro rudder, the horizontal rotation speed of the missile after being disturbed is rapidly attenuated. The attenuation speed depends on the total expansion length of 1%, which is inversely proportional to the missile's polar moment of inertia. The higher the speed, the faster the attenuation; the gyro navigation knows from the above analysis that the speed of the pneumatic gyro rudder plays a crucial role in the attenuation of the missile's horizontal speed.
Then, how to mention 1 and which marriages to play 4, we from the establishment of the pneumatic gyro, the 7-way Yin to discuss its nature.
The speed equation of the pneumatic gyro rudder can be as follows, from the state = 57 catch 012 =, 1. out. 1.1 The aerodynamic conduction torque coefficient 1 is the damper torque coefficient of the gyro rudder. Solving the equation can be obtained if 5=0, =00, then the integral constant is =0 female. = Substituting it into 12 with time and ballistic arc length, plus, the pneumatic gyro will reach the equilibrium speed. The balance speed depends on the speed of the missile rudder and will be limited to a certain range, and cannot be increased indefinitely. The higher the flight speed of the missile, the re-use of the resilience-type missile of the pneumatic gyro rudder 3 scrapped resources has been retired from the army, and the 1 resource is scrapped. The components of the mountain control rudder and the rudder surface, the pneumatic gyro rudder and the like are designed to be light in weight, small in size and excellent in performance. If these scrap resources are reused, it will be a good thing to save materials and save money.
It is envisaged to apply the steering gear tail and the pneumatic gyro rudder of this type of missile to the modification of a weapon. Then each of the bombs can be transformed into wood to save the near force. For a large number of weapons transformation, it has been a small number. Like the extreme moment of inertia of a weapon, it turns bigger. Its polar moment of inertia is about twice that of a missile. It can be seen from the attenuation factor that when the structural motion characteristics of the pneumatic gyro snake are constant, the reduction will be reduced. This will greatly weaken the roll stability of this type of weapon.
In order not to affect the stability of the roll after the transformation of a weapon, this paper proposes an improvement measure to change the material of the pneumatic gyro from the original alloy to the alloy steel; it is the extension of the pneumatic gyro rudder, 1.1 Given the mass of the weapon, the length of the gyro, the length of the gyro, the length of the gyro, the ykgDm attenuation factor ※ ※ missile ※ ※ transformation of the weapon can be seen from the 1, the modified attenuation factor is close to the prototype missile, it is expected that the transformation weapon will also have Better roll stability.
1 Pufa. External ballistics. Beijing National Defense Industry Press, 1989
Steam Trap,Flange Drain Primer Valve,Floating Ball Drain Valve,Floating Ball Steam Trap
Chongqing Xingjida Import and Export Trade Co., Ltd. , https://www.xjdvalve.com