Small liquid/solid rocket thrust vectoring nozzle servo control system and method

A servo control system, solid rocket technology, applied in the direction of rocket engine device, jet propulsion device, machine/engine, etc., can solve the problem of no control system and control method, and achieve the reduction of volume and weight, good real-time performance, dynamic Responsive effect

Active Publication Date: 2017-02-01
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

However, there is no corresponding control system and control method

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  • Small liquid/solid rocket thrust vectoring nozzle servo control system and method
  • Small liquid/solid rocket thrust vectoring nozzle servo control system and method
  • Small liquid/solid rocket thrust vectoring nozzle servo control system and method

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Embodiment Construction

[0023] A small liquid / solid rocket vector nozzle servo control system and method proposed by the present invention will be described in detail below in conjunction with the accompanying drawings.

[0024] Such as figure 1 As shown, a small liquid / solid rocket vector nozzle servo control system of the present invention includes two parts: a servo mechanism and a servo controller. Such as figure 2 As shown, the servo mechanism includes two servo actuators, a cross cardan mechanism, an angle encoder and a limit switch. Servo actuators include servo motors, couplings, ball screws, and push rods. The two servo actuators are respectively installed on the X-axis surface and the Y-axis surface of the nozzle. The two servo actuators are connected to the rocket engine frame and the nozzle through fish-eye bearings. The nozzle is connected with the engine frame through a cross universal mechanism. The servo controller controls the rotation speed and rotation angle of the servo moto...

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Abstract

The invention discloses a small liquid/solid rocket thrust vectoring nozzle servo control system. The system comprises a servo mechanism and a servo controller; the servo mechanism comprises two servo actuators, a cross-shaped omnidirectional mechanism, angle encoders and travel switches; the two servo actuators are respectively mounted on an X-axis surface and a Y-axis surface of a thrust vectoring nozzle; each travel switch is mounted in the middle of a push rod of the corresponding servo actuator; the angle encoders are mounted at shaft ends of two shafts, which are perpendicular to each other, of the cross-shaped omnidirectional mechanism; the servo controller comprises a core board and an interface extension board; and a CPU soft core is quickly established for the core board by an FPGA chip. By the control system and method, the size and the weight of the servo mechanism are greatly reduced because a mode of directly driving a lead screw by a motor is adopted, and reliability of the servo mechanism is improved; the FPGA-based core board and the peripheral interface extension board are adopted, instantaneity is good, computing efficiency is high, and extensibility is also high; and the servo mechanism and the servo controller are integrated, so that integration level is high, dynamic response is quick, and control precision is high.

Description

technical field [0001] The invention belongs to the technical field of rocket control, in particular to a small liquid / solid rocket vector nozzle servo control system and method. Background technique [0002] During the entire flight of the rocket, it mainly operates in the atmosphere. Due to the complex environment of the atmosphere and the greater influence of the weather, ideal weather conditions must be selected for general rocket launches. To improve the rocket's adaptability to harsh environments, it is necessary to improve the maneuverability of the rocket, and thrust vector control is an effective measure. [0003] The thrust direction adjustment of the rocket engine changes the thrust direction according to the control command by manipulating the servo mechanism, thereby generating the moment to control the attitude of the rocket. The thrust direction adjustment methods mainly include: (1) Swing the main engine: manipulate the main engine to swing around the axis ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/80F02K9/88F02K9/72
CPCF02K9/72F02K9/805F02K9/88
Inventor 吴云华秦远田许蕾陈志明华冰郁丰
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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