A method for determining the oil storage capacity of a squeeze servo system for a launch vehicle
An extrusion servo and servo system technology, which is applied in the field of aerospace servo system parameter design, can solve the problems of whether the flight success or failure has no effect on success or failure, there is no solution, and the oil cannot be recycled.
Active Publication Date: 2018-05-22
BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS +1
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Problems solved by technology
[0003] The existing servo systems on the arrows all use pump energy, and the energy medium can be recycled. The energy storage capacity mainly considers the influence of temperature, which has no impact on the success of the flight.
The fuel tank of the squeeze servo system is a high-pressure open fuel tank, and the oil cannot be recycled; in addition, due to the weight control requirements of the space vehicle, the rocket cannot carry too much oil during flight. Therefore, the squeeze servo system The determination of the oil storage capacity of the system oil tank is a crucial parameter in the design of the servo system, but there is no relevant solution for the traditional pump energy servo system
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[0040] See attached figure 1 , the squeeze servo system is mainly composed of 2 servo actuators 1, 2 roll control servo actuators 2, 1 servo high-pressure helium source 3, squeeze oil tank 4, servo valve controller 5 and 2 horns The displacement sensor measuring device 6 constitutes a set of extrusion servo system.
[0041] The servo actuator is a combination of hydraulic, mechanical, electronic, electromagnetic and feedback control technologies. The control command is converted inside the servo actuator through command current-electromagnetic torque-hydraulic power amplification-mechanical displacement and other output conversions, and is sprayed by the swing engine. The main engine nozzle 7 and the rolling control engine 8 nozzles change the thrust vector direction of the engine, thereby changing the flight attitude of the launch vehicle.
[0042] Since the servo valve of the hydraulic system cannot achieve absolute sealing, there is internal leakage during the working proc...
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The invention discloses a method for determining the fuel storage capacity of a squeeze servo system for a launch vehicle, and provides a method for determining the fuel storage capacity of a squeeze servo system under the premise of considering the influence of static consumption on the fuel storage capacity of a fuel tank . Creatively defined "within the specified flight mission time t, the cumulative sum of the absolute value of the swing angle variation of any servo actuator adjacent to the control cycle dt is the mission swing angle Sk of the actuator to complete the flight mission" , using the task swing angle Sk to calculate the oil storage capacity of the servo system. The method for determining the amount of fuel storage is successfully applied to solid launch vehicles, and the flight weight of the rockets is effectively and accurately controlled.
Description
technical field [0001] The invention relates to the parameter design field of an aerospace servo system used in a thrust vector control system of a large solid rocket. Background technique [0002] The extrusion servo system has the "open" feature that the energy medium does work at one time. The high-power cold air extrusion servo system developed on the solid launch vehicle is the first application in China. [0003] The existing servo systems on arrows all use pump energy, and the energy medium can be recycled. The energy storage capacity mainly considers the influence of temperature, which has no influence on the success or failure of the flight. The fuel tank of the squeeze servo system is a high-pressure open fuel tank, and the oil cannot be recycled; in addition, due to the weight control requirements of the space vehicle, the rocket cannot carry too much oil during flight. Therefore, the squeeze servo system The determination of the oil storage capacity of the syste...
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IPC IPC(8): G06F17/50
Inventor 陈安平邓涛彭昆雅李俊岩李冬成兆义高健倪永健陈海波
Owner BEIJING RES INST OF PRECISE MECHATRONICS CONTROLS