A method for designing a control law of a solid engine based on nozzle stroke

Abstract

The application discloses a solid engine control law design method based on nozzle stroke, takes nozzle stroke as a control law independent variable, takes nozzle stroke change rate as a control law dependent variable, and then converts the control law into a nozzle stroke and time change curve, controls the nozzle stroke change rate of an initial point, a terminal point and a process interval, guarantees the nozzle stroke time change curve to be smooth, and thus suppresses the engine overshoot phenomenon.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket motor technology, specifically relating to a design method for solid rocket motor control law based on nozzle stroke. Background Technology

[0002] Solid rocket motors can adjust thrust in real time by regulating the nozzle stroke. However, when adjusting thrust over a wide range, overshoot may occur, meaning the measured performance values ​​differ significantly from the calculated predictions. This negatively impacts the engine's ability to accurately predict and control performance; therefore, it is crucial to suppress overshoot as much as possible during solid rocket motor nozzle control. Summary of the Invention

[0003] To overcome the shortcomings of existing technologies, this invention provides a design method for solid rocket motor control laws based on nozzle stroke. The nozzle stroke is used as the independent variable of the control law, and the rate of change of the nozzle stroke is the dependent variable of the control law. Then, the control law is transformed into a curve of nozzle stroke versus time. By controlling the rate of change of the nozzle stroke at the initial point, the final point, and the process interval, the curve of change of nozzle stroke versus time is kept stable, thereby suppressing engine overshoot.

[0004] The technical solution adopted by this invention to solve its technical problem is as follows: Step 1: Determine the starting and ending points of the engine's dynamic process and its operating status; Step 2: Determine the initial and maximum limits of the engine nozzle stroke change rate; Step 3: Using nozzle stroke as the independent variable of the control law and the nozzle stroke change rate as the dependent variable of the control law, establish the control law of "nozzle stroke change rate - nozzle stroke"; Step 4: Transform the "nozzle stroke change rate - nozzle stroke" control law into the "nozzle stroke - working time" control law.

[0005] Preferably, the operating state includes engine nozzle stroke, engine operating pressure, and engine thrust.

[0006] Preferably, the nozzle stroke at the starting point of the "nozzle stroke change rate - nozzle stroke" control law is the nozzle stroke of the initial thrust adjustment condition, and the nozzle stroke change rate is not greater than the initial maximum limit value of the nozzle stroke change rate; the nozzle stroke at the ending point of the control law is the throat plug formation of the final thrust adjustment condition, and the nozzle stroke change rate is 0; the nozzle stroke change rate during the control law process is not greater than the maximum value of the nozzle stroke change rate during the process.

[0007] An electronic device includes a processor and a memory; the memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory to enable the electronic device to perform the above-described solid rocket motor control law design method.

[0008] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the above-described solid rocket motor control law design method.

[0009] A chip includes a processor for calling and running a computer program from a memory, causing a device equipped with the chip to execute the above-described solid rocket motor control law design method.

[0010] A computer program product includes a computer storage medium storing a computer program, the computer program including instructions executable by at least one processor, which, when executed by the at least one processor, implement the above-described solid rocket motor control law design method.

[0011] The beneficial effects of this invention are as follows: The solid rocket motor control law design method of the present invention can suppress the performance overshoot phenomenon of the engine during nozzle adjustment. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the control law of "nozzle stroke change rate - nozzle stroke" of the solid rocket motor in an embodiment of the present invention. The data in the figure has been normalized.

[0013] Figure 2 This is a schematic diagram of the control law of "nozzle stroke-working time" of the solid rocket motor in an embodiment of the present invention. The data in the figure has been normalized. Detailed Implementation

[0014] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0015] The technical problem solved by this invention is that the control law obtained by the traditional solid rocket motor control law design method has a high frequency of performance overshoot during the engine nozzle adjustment process.

[0016] A method for designing control laws for a solid rocket motor based on nozzle stroke includes the following steps: Step 1: Determine the starting and ending points of the engine's dynamic process, including but not limited to engine nozzle stroke, engine operating pressure, and engine thrust.

[0017] Step 2: Determine the initial and maximum limits of the engine nozzle stroke change rate.

[0018] Step 3: Using nozzle stroke as the independent variable of the control law and the nozzle stroke change rate as the dependent variable, establish a control law of "nozzle stroke change rate - nozzle stroke". The nozzle stroke at the starting point of the control law is the nozzle stroke under the initial thrust regulation condition, and the nozzle stroke change rate should not exceed the initial maximum limit value of the nozzle stroke change rate; the nozzle stroke at the ending point of the control law is the throat block formation under the final thrust regulation condition, and the nozzle stroke change rate is 0; the nozzle stroke change rate during the control law process should not exceed the maximum value of the nozzle stroke change rate during the process.

[0019] Step 4: Transform the "nozzle stroke change rate - nozzle stroke" control law into the "nozzle stroke - working time" control law.

[0020] Example: Step 1: Determine the starting and ending points of the engine's dynamic process, including but not limited to engine nozzle stroke, engine operating pressure, and engine thrust.

[0021] Step 2: Determine the initial and maximum limits of the engine nozzle stroke change rate.

[0022] Step 3: Using nozzle stroke as the independent variable of the control law and the nozzle stroke change rate as the dependent variable, establish a control law of "nozzle stroke change rate - nozzle stroke". The nozzle stroke at the starting point of the control law is the nozzle stroke under the initial thrust regulation condition, and the nozzle stroke change rate should not exceed the initial maximum limit value of the nozzle stroke change rate; the nozzle stroke at the ending point of the control law is the throat block formation under the final thrust regulation condition, and the nozzle stroke change rate is 0; the nozzle stroke change rate during the control law process should not exceed the maximum value of the nozzle stroke change rate during the process.

[0023] Step 4: Transform the "nozzle stroke change rate - nozzle stroke" control law into the "nozzle stroke - working time" control law.

Claims

1. A method for designing control laws for a solid rocket motor based on nozzle stroke, characterized in that, Includes the following steps: Step 1: Determine the starting and ending points of the engine's dynamic process and its operating status; Step 2: Determine the initial and maximum limits of the engine nozzle stroke change rate; Step 3: Using nozzle stroke as the independent variable of the control law and the nozzle stroke change rate as the dependent variable of the control law, establish the control law of "nozzle stroke change rate - nozzle stroke"; Step 4: Transform the "nozzle stroke change rate - nozzle stroke" control law into the "nozzle stroke - working time" control law.

2. The method for designing control laws for a solid rocket motor based on nozzle stroke according to claim 1, characterized in that, The operating states include engine nozzle stroke, engine operating pressure, and engine thrust.

3. The method for designing control laws for a solid rocket motor based on nozzle stroke according to claim 1, characterized in that, The nozzle stroke at the starting point of the "nozzle stroke change rate - nozzle stroke" control law is the nozzle stroke under the initial thrust adjustment condition, and the nozzle stroke change rate is not greater than the initial maximum limit of the nozzle stroke change rate; the nozzle stroke at the ending point of the control law is the throat block formation under the final thrust adjustment condition, and the nozzle stroke change rate is 0; the nozzle stroke change rate during the control law process is not greater than the maximum value of the nozzle stroke change rate during the process.

4. An electronic device, characterized in that, include: Processor and memory; The memory is used to store a computer program, and the processor is used to execute the computer program stored in the memory to cause the electronic device to perform the method as described in any one of claims 1 to 3.

5. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the method as described in any one of claims 1 to 3.

6. A chip, characterized in that, include: A processor for retrieving and running a computer program from memory, causing a device on which the chip is mounted to perform the method as described in any one of claims 1 to 3.

7. A computer program product, characterized in that, The computer program product includes a computer storage medium storing a computer program, the computer program including instructions executable by at least one processor, which, when executed by the at least one processor, implement the method as described in any one of claims 1 to 3.

Images