A method for moving the burning surface of a solid rocket engine charge

Abstract

The application discloses a solid rocket engine charge burning surface moving method, which is based on three-dimensional model design software, and divides a solid rocket engine charge model into an outer contour model and a core model. According to the symmetry of the charge shape, the outer contour model is divided, and the core model is modified. Then, the "offset" function in the three-dimensional model design software is used to obtain the burning surface moving result. The solid rocket engine charge burning surface moving method can overcome the low success rate of the traditional solid rocket engine charge burning surface moving method based on the three-dimensional model design software.

Description

Technical Field

[0001] This invention belongs to the field of rocket technology, specifically relating to a method for shifting the propellant burning surface in a solid rocket engine. Background Technology

[0002] As the propulsion system of missiles, obtaining the combustion surface of solid rocket motors during combustion is crucial for internal ballistic design. Traditional methods often involve "offsetting" the internal surface of the propellant in 3D modeling software to move the combustion surface. This method can cause geometric distortion of the propellant during the moving process, leading to moving failure. Simplification and modification of the geometry are necessary for successful moving, which in turn reduces the accuracy of the combustion surface moving results. To improve the success rate of high-precision combustion surface moving of engine propellants, the solid rocket motor propellant can be divided into an outer contour model and a core model. Based on the symmetry of the propellant shape, the outer contour model is subdivided, and the core model is modified. The "offset" function in 3D modeling software is then used to obtain the combustion surface moving results. Summary of the Invention

[0003] To overcome the shortcomings of existing technologies, this invention provides a method for moving the burning surface of a solid rocket motor propellant. Based on 3D model design software, the solid rocket motor propellant model is divided into an outer contour model and a core model. According to the symmetry of the propellant type, the outer contour model is subdivided, and the core model is modified. Then, the "offset" function in the 3D model design software is used to obtain the burning surface moving result. Applying this method can overcome the low success rate of traditional solid rocket motor propellant burning surface moving methods based on 3D model design software.

[0004] The technical solution adopted by this invention to solve its technical problem includes the following steps:

[0005] Step 1: In the 3D modeling software, establish the outer contour model of the solid rocket motor propellant and the core model of the propellant respectively, and obtain the symmetry number n of the propellant geometry according to the propellant design scheme;

[0006] Step 2: Divide the outer contour model of the charge into 1 / n models according to the symmetry of the charge;

[0007] Step 3: Divide the charge core model into 1 / n models according to the charge symmetry. Using the symmetrical boundary contours on both sides of the 1 / n charge core model as the rotation curve and the axis of rotation of the 1 / n core model as the rotation axis, rotate it in the normal direction to the outside of the symmetry plane of the 1 / n core model. The rotation angle β satisfies the following formula:

[0008]

[0009] Step 4: Use the offset function of the 3D modeling software to offset the outer contour surface of the charge core model, and trim the outer contour model of the charge using the offset charge core model to obtain the charge model after the burning surface is shifted.

[0010] Preferably, n = 18.

[0011] The beneficial effects of this invention are as follows:

[0012] The method of this invention overcomes the low success rate of traditional solid rocket engine propellant burning surface shifting methods based on three-dimensional model design software. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the method flow of the present invention.

[0014] Figure 2 This is a solid rocket engine propellant core model of the single rear wing sprue propellant burning surface shift embodiment of the present invention.

[0015] Figure 3 This is a model of the outer contour of the propellant charge of a solid rocket engine in the embodiment of the single rear wing stylist propellant charge combustion surface shifting of the present invention.

[0016] Figure 4 This is a 1 / 18 scale model of the outer contour of the propellant charge of a solid rocket engine in the single rear wing stylist propellant burner surface shifting embodiment of the present invention.

[0017] Figure 5 This is a 1 / 18 scale model of the propellant core mold of a solid rocket engine in the embodiment of the single rear wing sprue propellant burning surface shifting of the present invention.

[0018] Figure 6 This is a 1 / 18 scale modified model of the solid rocket motor propellant core mold of the single embodiment of the present invention, which is a rear wing column propellant burning surface shifting embodiment.

[0019] Figure 7 This is the propellant burning surface shifting process of a solid rocket engine in a single embodiment of the present invention, which is a rear wing post propellant burning surface shifting embodiment. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0021] The technical problem solved by this invention is that the traditional method for high-precision propulsion of the propellant burning surface in solid rocket engines based on 3D model design software has a low success rate.

[0022] like Figure 1 As shown, the technical solution of the present invention is: a method for propelling the combustion surface of a solid rocket engine, comprising the following steps:

[0023] Step 1: In the 3D modeling software, establish the outer contour model and core model of the solid rocket motor propellant, and obtain the symmetry number n of the propellant geometry according to the propellant design scheme.

[0024] Step 2: Divide the outer contour model of the charge into 1 / n models according to the symmetry of the charge.

[0025] Step 3: Divide the charge core model into 1 / n models according to the symmetry of the charge. Using the symmetrical boundary contours on both sides of the 1 / n charge core model as the rotation curve and the axis of rotation of the 1 / n core model as the rotation axis, rotate it in the normal direction to the outside of the symmetry plane of the 1 / n core model. The rotation angle should satisfy the following formula:

[0026]

[0027] Step 4: Use 3D modeling software to "offset" the outer contour surface of the charge core model, and then trim the outer contour model of the charge using the offset charge core model to obtain the charge model after the burning surface has been shifted.

[0028] Example:

[0029] Step 1: In 3D modeling software, create the outer contour model and core model of the propellant charge for a single rear wing styloft solid rocket motor, such as... Figure 2 and Figure 3 As shown, the symmetry number of the charge geometry is 18 according to the charge design scheme.

[0030] Step 2: Divide the outer contour model of the charge into 1 / 18 scale models according to the symmetry of the charge, such as... Figure 4 As shown.

[0031] Step 3: Divide the charge core model into 1 / 18 scale models according to the symmetry of the charge, such as... Figure 5 As shown, using the symmetrical boundary contours on both sides of the 1 / 18 scale mandrel model as the rotation curve, and the axis of the 1 / 18 scale mandrel model as the rotation axis, the model rotates in the normal direction to the outside of the symmetrical plane of the 1 / 18 scale mandrel model, with a rotation angle of 120°. Figure 6 As shown.

[0032] Step 4: Using 3D modeling software, the outer contour surface of the charge core mold model is "offset". The offset charge core mold model is then used to trim the outer contour model of the charge, thus obtaining the charge model after the burning surface has been shifted. Figure 7 As shown.

Claims

1. A method for shifting the propellant combustion surface in a solid rocket motor, characterized in that, Includes the following steps: Step 1: In the 3D modeling software, establish the outer contour model of the solid rocket motor propellant and the core model of the propellant respectively, and obtain the symmetry number n of the propellant geometry according to the propellant design scheme; Step 2: Divide the outer contour model of the charge into 1 / n models according to the symmetry of the charge; Step 3: Divide the charge core model into 1 / n models according to the charge symmetry. Using the symmetrical boundary contours on both sides of the 1 / n charge core model as the rotation curve and the axis of rotation of the 1 / n core model as the rotation axis, rotate it in the normal direction to the outside of the symmetry plane of the 1 / n core model. The rotation angle β satisfies the following formula: Step 4: Use the offset function of the 3D modeling software to offset the outer contour surface of the charge core model, and trim the outer contour model of the charge using the offset charge core model to obtain the charge model after the burning surface is shifted.

2. The method for shifting the propellant burning surface of a solid rocket motor according to claim 1, characterized in that, The n = 18.

Images