Spring parameter value determination method and device, electronic equipment and storage medium

Abstract

The embodiment of the invention provides a spring parameter value determination method and device, electronic equipment and a storage medium, and relates to the technical field of carrier rockets. The method comprises the following steps: determining a change relation between an angular velocity and an overturning angle of a half cover in a fairing separation process based on structural information of the fairing and a parameter value of a spring to be verified; the parameter value of the to-be-verified spring is a parameter value representing the elastic characteristic of the spring, and the overturning angle is the rotating angle of the half cover relative to the central axis of the fairing; determining a target angular velocity corresponding to the target turnover angle based on a change relationship between the angular velocity and the turnover angle; the target turnover angle represents a turnover angle corresponding to the highest point of the centroid of the half cover; and if the target angular velocity is greater than the preset angular velocity, determining the to-be-verified spring parameter value as a target spring parameter value. According to the embodiment of the invention, the parameter value of the spring can be verified, so that the parameter value of the spring which is actually required to be used can be quickly, simply and conveniently determined.

Description

Technical Field

[0001] The present application relates to the technical field of launch vehicles. Specifically, the present application relates to a method, device, electronic device and storage medium for determining spring parameter values. Background Art

[0002] The fairing of the launch vehicle includes two half-covers, namely a first cover body and a second cover body. The fairing can be provided with a separation spring mechanism having a spring. The two ends of the separation spring mechanism can be connected to the first cover body and the second cover body respectively. The elastic force of the spring can promote the separation of the first cover body and the second cover body.

[0003] In actual production practice, the structural information of the weight, size and other parameters of the rocket fairing is often changed according to the launch requirements. Therefore, it is necessary to determine the spring parameter value of the separation spring mechanism according to the actual rocket requirements so as to adapt it in production.

[0004] However, how to determine whether the spring parameter value meets the design requirements so as to use it as the spring parameter value for production so that the spring can achieve separation of the sorting cover requires further research. Summary of the invention

[0005] The embodiments of the present application provide a method, device, electronic device and storage medium for determining spring parameter values, which are used to solve the technical problem of how to verify spring parameter values ​​to obtain spring parameter values ​​that meet design requirements.

[0006] In a first aspect, an embodiment of the present application provides a method for determining a spring parameter value, which is applied to the separation of two half-covers of a fairing, and the method includes: Based on the structural information of the fairing and the spring parameter value to be verified, the changing relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing is determined; the spring parameter value to be verified is a parameter value that characterizes the elastic characteristics of the spring, and the flip angle is the angle at which the half-cover rotates relative to the central axis of the fairing; Based on the changing relationship between the angular velocity and the flip angle, the target angular velocity corresponding to the target flip angle is determined; the target flip angle represents the flip angle corresponding to the centroid of the half mask being at the highest point; If the target angular velocity is greater than the preset angular velocity, the spring parameter value to be verified is determined as the target spring parameter value.

[0007] In a possible implementation, based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half fairing during the fairing separation process includes: Based on the structural information of the fairing and the preset rigid shaft formula, the changing relationship between the coordinates of the center of mass of the half-fairing and the flip angle and the changing relationship between the coordinates of the spring's action points on the two half-fairings and the flip angle are determined; the structural information includes the weight and size of the fairing and the information on the connection position of the spring and the half-fairing, and the half-fairing rotates around the hinge center point where the half-fairing is connected to the rocket body; Based on the spring parameter value to be verified and the preset energy conservation equation, the relationship between the angular velocity and the height change of the center of mass and the length change of the spring is determined; the height change is determined based on the coordinate change of the center of mass, and the length change is determined based on the coordinate change of the spring's action points at the two half-covers; Based on the changing relationship between the coordinates of the center of mass of the half cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half covers and the flip angle, and the changing relationship between the angular velocity and the change in the height of the center of mass and the change in the length of the spring, the changing curves of the angular velocity and the flip angle are determined as the changing relationship between the angular velocity and the flip angle.

[0008] In a possible implementation, based on the structural information of the fairing and a preset rigid shaft formula, the changing relationship between the coordinates of the center of mass of the half fairing and the flip angle and the changing relationship between the coordinates of the spring's action points on the two half fairings and the flip angle are determined, including: Based on the structural information of the fairing, determine the initial coordinates of the center of mass of the two half fairings, the initial coordinates of the points of action of the springs on the two half fairings, and the initial coordinates of the center point of the hinge connecting the two half fairings to the rocket body from the preset coordinate system; For any half-shield, based on the rigid axis formula, the initial coordinates of the center of mass of the half-shield and the initial coordinates of the center point of the hinge connecting the half-shield and the arrow body, determine the relationship between the coordinates of the center of mass of the half-shield and the flip angle; Based on the rigid axis formula, the initial coordinates of the spring's points of action on the two half-shiels, and the initial coordinates of the hinge center points connecting the two half-shiels to the rocket body, the changing relationship between the coordinates of the spring's points of action on the two half-shiels and the flip angle is determined.

[0009] In a possible implementation, based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half fairing during the fairing separation process also includes: Based on the unhooking condition of the fairing, determine the unhooking angular velocity corresponding to the unhooking angle of the fairing; the unhooking condition is used to indicate the condition under which the fairing is separated from the arrow body when the centrifugal acceleration and the overload acceleration of the half-fairing are equal in radial direction, and the unhooking angle is the angle at which the half-fairing is separated from the arrow body; and, Based on the changing relationship between the coordinates of the center of mass of the half-mask and the flip angle, the changing relationship between the coordinates of the spring's action points on the two half-mask and the flip angle, and the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, the changing curve of the angular velocity and the flip angle is determined, including: Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the changing curves of the angular velocity and the flip angle of the half-cover are determined.

[0010] In a possible implementation, before determining the target angular velocity corresponding to the target flip angle based on the change relationship between the angular velocity and the flip angle, the method further includes: Based on the structural information of the fairing, the target flip angle corresponding to the highest point of the center of mass of the half fairing is determined.

[0011] In a possible implementation, the method for determining the spring parameter value further includes: If the target angular velocity is not greater than the preset angular velocity, the spring parameter value to be verified is adjusted to obtain the adjusted spring parameter value, and the adjusted spring parameter value is used as a new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load and working stroke.

[0012] In a possible implementation, adjusting the spring parameter value to be verified to obtain the adjusted spring parameter value includes: In response to a setting operation on the parameter display interface, a current spring parameter value on the parameter display interface is acquired as an adjusted spring parameter value; the parameter display interface includes a parameter setting area, and the parameter setting area is used to set the spring parameter value.

[0013] In a second aspect, an embodiment of the present application provides a device for determining a spring parameter value, which is applied to the separation of two half-covers of a fairing, comprising: The first determination module is used to determine the change relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified; the spring parameter value to be verified is a parameter value characterizing the elastic characteristics of the spring, and the flip angle is the angle at which the half-cover rotates relative to the central axis of the fairing; The second determination module is used to determine the target angular velocity corresponding to the target flip angle based on the change relationship between the angular velocity and the flip angle; the target flip angle represents the flip angle corresponding to the centroid of the half mask being at the highest point; The third determination module is used to determine the spring parameter value to be verified as the target spring parameter value if the target angular velocity is greater than the preset angular velocity.

[0014] In a third aspect, an embodiment of the present application provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory, wherein the processor executes the computer program to implement the steps of the method of the first aspect.

[0015] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon, which implements the steps of the method of the first aspect when the computer program is executed by a processor.

[0016] The beneficial effects of the technical solution provided by the embodiment of the present application are: The embodiment of the present application can determine the changing relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified, and then determine the target angular velocity corresponding to the flip angle corresponding to the center of mass of the half-cover being at the highest point according to the changing relationship between the angular velocity and the flip angle, so that when the target angular velocity is greater than the preset angular velocity, it can be determined that the spring parameter value to be verified meets the design requirements, and the spring parameter value to be verified is determined as the target spring parameter value, which is applied in production and use. The embodiment of the present application can verify the spring parameter value, and determine that the angular velocity of the spring when the center of mass of the half-cover is at the highest point is not lower than the lowest angular velocity, thereby ensuring the separation of the two half-covers. Therefore, the embodiment of the present application can quickly and easily determine the spring parameter value that actually needs to be used by verifying the spring parameter value. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for use in describing the embodiments of the present application.

[0018] Figure 1 This is a flow chart of a method for determining a spring parameter value according to an embodiment of the present application; Figure 2 A flowchart of the steps of determining the changing relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified provided in an embodiment of the present application; Figure 3 A flowchart of another step of determining the relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified provided in an embodiment of the present application; Figure 4 A schematic diagram of a fairing separation process provided in an embodiment of the present application; Figure 5 A schematic diagram of a curve of changes in angular velocity and flip angle of a half mask provided in an embodiment of the present application; Figure 6 A schematic diagram of the structure of a device for determining a spring parameter value provided in an embodiment of the present application; Figure 7 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0019] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0020] It will be understood by those skilled in the art that, unless specifically stated, the singular forms "one", "said", and "the" used herein may also include plural forms. It should be further understood that the terms "including" and "comprising" used in the embodiments of the present application refer to that the corresponding features can be implemented as the presented features, information, data, steps, operations, elements and / or components, but do not exclude the implementation as other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. It should be understood that when we say that an element is "connected" or "coupled" to another element, the one element may be directly connected or coupled to the other element, or it may refer to that the one element and the other element establish a connection relationship through an intermediate element. In addition, the "connection" or "coupling" used herein may include wireless connection or wireless coupling. The term "and / or" used herein indicates at least one of the items defined by the term, for example, "A and / or B" indicates that it is implemented as "A", or is implemented as "A", or is implemented as "A and B".

[0021] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0022] The method for determining the spring parameter value provided in the embodiment of the present application is to determine the parameter value of the spring elastic characteristic. The spring is used in a separation spring mechanism. The separation spring mechanism can be arranged inside the fairing and close to the top of the fairing. The fairing can be divided into a first cover body and a second cover body. The two ends of the separation spring mechanism are respectively connected to the first cover body and the second cover body. The separation spring mechanism may include a coaxially arranged inner sleeve and an outer sleeve. The two ends of the spring are respectively abutted against the inner sleeve and the outer sleeve. The inner sleeve and the outer sleeve can be telescopically connected through the contraction and extension of the spring. When the fairing is opened, the elastic force of the spring can promote the separation of the first cover body and the second cover body.

[0023] As an example, one end of the separation spring mechanism can be rotatably connected to the first cover body, and the other end can be supported by the second cover body. A limit block with a limit hole is arranged in the inner sleeve, and the outer sleeve is connected to a limit rod coaxially arranged therewith. The limit rod passes through the limit hole and the end of the limit rod is provided with a limit boss matching the limit hole. During the separation process of the separation spring mechanism, the limit rod moves with the outer sleeve, and the moving position of the limit boss is limited by the limit hole, so as to prevent the inner sleeve from jumping out of the outer sleeve.

[0024] See also Figure 1 As shown, the present application embodiment provides a flow chart of a method for determining a spring parameter value. Figure 1 As shown, the method for determining the spring parameter value is applied to the separation of two half-covers of a fairing, and the method includes: steps S101 to S103.

[0025] S101. Based on the structural information of the fairing and the spring parameter value to be verified, determine the changing relationship between the angular velocity and the flip angle of the half-fairing during the separation process of the fairing; the spring parameter value to be verified is a parameter value that characterizes the elastic characteristics of the spring, and the flip angle is the angle at which the half-fairing rotates relative to the central axis of the fairing.

[0026] Optionally, the structural information of the fairing is determined based on the known structure of the fairing, which is pre-stored structural information and may include information such as the size, weight, and connection position of the spring of the fairing, so as to facilitate determination of the initial and changed coordinates of known points on the fairing.

[0027] Optionally, the spring parameter value to be verified is a predetermined parameter value that needs to be verified, and can be a reasonable spring parameter value given by a technician based on practical production experience combined with the spatial environment in the fairing. In the method for determining the spring parameter value of each fairing, an initial spring parameter value needs to be verified as the spring parameter value to be verified. If the initial spring parameter value does not meet the design requirements, the initial spring parameter value needs to be adjusted, and then the adjusted spring parameter value is used as the new spring parameter to be verified to perform the steps of the method for determining the spring parameter value of the embodiment of the present application.

[0028] In some embodiments, the method for determining the spring parameter value also includes: if the target angular velocity is not greater than the preset angular velocity, adjusting the spring parameter value to be verified to obtain the adjusted spring parameter value, and using the adjusted spring parameter value as the new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load, working stroke.

[0029] The embodiment of the present application can adjust the spring parameter value, and use the adjusted spring parameter value as the new spring parameter value to be verified to continue the verification process of the spring parameter value to be verified, that is, execute the steps of the method for determining the spring parameter value of the embodiment of the present application until the target spring parameter value that meets the design requirements is obtained.

[0030] In some embodiments, the spring parameter value to be verified is adjusted to obtain the adjusted spring parameter value, including: in response to a setting operation on the parameter display interface, obtaining the current spring parameter value of the parameter display interface as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, and the parameter setting area is used to set the spring parameter value.

[0031] The embodiment of the present application can use manual settings to continuously adjust the spring parameter value in the parameter display interface. The adjustment of the spring parameter value can be determined in combination with the practical experience of the technicians and the space environment inside the fairing.

[0032] S102, based on the changing relationship between the angular velocity and the flip angle, determining a target angular velocity corresponding to a target flip angle; the target flip angle represents a flip angle corresponding to when the center of mass of the half mask is at the highest point.

[0033] Optionally, the target flip angle is a known flip angle that can be determined according to the structure of the fairing.

[0034] In some embodiments, before determining the target angular velocity corresponding to the target flip angle based on the changing relationship between the angular velocity and the flip angle, it also includes: determining the target flip angle corresponding to the center of mass of the half-cover being at the highest point based on the structural information of the fairing.

[0035] In the embodiment of the present application, the target flip angle corresponding to the center of mass of the half-mask being at the highest point can be used to determine the corresponding target angular velocity in the changing relationship between the angular velocity and the flip angle, so as to facilitate subsequent comparison of the target angular velocity.

[0036] S103: If the target angular velocity is greater than the preset angular velocity, the spring parameter value to be verified is determined as the target spring parameter value.

[0037] In the embodiment of the present application, the lowest angular velocity when the center of mass is at the highest point can be used as the preset angular velocity, which is a preset known angular velocity. When the target angular velocity is greater than the preset angular velocity, the separation of the two half fairings can be ensured. The setting of the preset angular velocity can be determined according to the angular velocity determined by the technician in actual production practice.

[0038] Based on the above steps S101 to S103, the embodiment of the present application can determine the changing relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified, and then determine the target angular velocity corresponding to the flip angle corresponding to the center of mass of the half-cover being at the highest point according to the changing relationship between the angular velocity and the flip angle, so that when the target angular velocity is greater than the preset angular velocity, it can be determined that the spring parameter value to be verified meets the design requirements, and the spring parameter value to be verified is determined as the target spring parameter value, which is applied in production and use. The embodiment of the present application can verify the spring parameter value to determine that the angular velocity of the spring when the center of mass of the half-cover is at the highest point is not lower than the lowest angular velocity, thereby ensuring the separation of the two half-covers. Therefore, the embodiment of the present application can quickly and easily determine the spring parameter value that actually needs to be used by verifying the spring parameter value.

[0039] See also Figure 2 As shown, the embodiment of the present application provides a flowchart of the steps of determining the relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified. Figure 2 As shown, this step includes: S201 to S203.

[0040] S201. Based on the structural information of the fairing and the preset rigid axis formula, determine the changing relationship between the coordinates of the center of mass of the half-fairing and the flip angle and the changing relationship between the coordinates of the spring's points of action on the two half-fairings and the flip angle; the structural information includes the weight and size of the fairing and the information on the connection position between the spring and the half-fairing, and the half-fairing rotates around the center point of the hinge connecting the half-fairing and the rocket body.

[0041] In some embodiments, based on the structural information of the fairing and a preset rigid shaft formula, determining the changing relationship between the coordinates of the center of mass of the half-fairing and the flip angle and the changing relationship between the coordinates of the spring's action points on the two half-fairings and the flip angle includes: (1) Based on the structural information of the fairing, determine the initial coordinates of the center of mass of the two half fairings, the initial coordinates of the points of action of the springs on the two half fairings, and the initial coordinates of the center point of the hinge connecting the two half fairings to the rocket body from the preset coordinate system.

[0042] (2) For any half-shield, based on the rigid axis formula, the initial coordinates of the center of mass of the half-shield, and the initial coordinates of the center point of the hinge connecting the half-shield and the rocket body, determine the relationship between the coordinates of the center of mass of the half-shield and the change in the flip angle.

[0043] (3) Based on the rigid axis formula, the initial coordinates of the spring's points of action on the two half-shiels, and the initial coordinates of the hinge center point connecting the two half-shiels to the rocket body, determine the relationship between the coordinates of the spring's points of action on the two half-shiels and the change in the flip angle.

[0044] Based on the structural information of the fairing, the embodiment of the present application determines the initial coordinates of the center of mass of the two half-covers, the initial coordinates of the points of action of the springs at the two half-covers, and the initial coordinates of the center of the hinge connecting the two half-covers to the body of the rocket in a preset coordinate system. As the flip angle changes, the center of mass of the two half-covers and the points of action of the springs at the two half-covers will change. Based on the rigid shaft formula, the relationship between the coordinates of the center of mass of the half-covers and the flip angle, as well as the relationship between the coordinates of the points of action of the springs at the two half-covers and the flip angle can be determined.

[0045] Optionally, the two half covers are symmetrically arranged relative to the central axis of the fairing, and during the separation process of the two half covers, the two half covers are also symmetrically flipped relative to the central axis. Therefore, the movement of one half cover can be selected to determine the change relationship between the coordinates of the center of mass of the half cover and the flip angle.

[0046] Optionally, the rigid axis formula is a preset calculation formula involving the changing relationship between the coordinates of the center of mass of the half-shield and the flip angle, and the changing relationship between the coordinates of the spring's points of action at the two half-shields and the flip angle. By correspondingly substituting the initial coordinates of the center of mass of the two half-shields, the initial coordinates of the spring's points of action at the two half-shields, and the initial coordinates of the hinge center point connecting the two half-shields to the arrow body into the calculation formula, the changing relationship between the coordinates of the center of mass of the half-shield and the flip angle, and the changing relationship between the coordinates of the spring's points of action at the two half-shields and the flip angle can be determined.

[0047] S202. Based on the spring parameter value to be verified and the preset energy conservation equation, determine the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring; the height change is determined based on the coordinate change of the center of mass, and the length change is determined based on the coordinate change of the spring's action points at the two half-covers.

[0048] Optionally, the preset energy conservation equation is a preset calculation formula involving the changing relationship between the angular velocity and the change in height of the center of mass and the change in length of the spring. By substituting the spring parameter value to be verified into the calculation formula, the changing relationship between the angular velocity and the change in height of the center of mass and the change in length of the spring can be obtained.

[0049] S203. Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, and the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, determine the changing curve of the angular velocity and the flip angle as the changing relationship between the angular velocity and the flip angle.

[0050] The embodiment of the present application can draw a curve of changes in angular velocity and flip angle based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, and the changing relationship between the angular velocity and the change in the height of the center of mass and the change in the length of the spring.

[0051] In actual operation, based on the calculation formula of the above-mentioned change relationship of the embodiment of the present application, through some values ​​of the flip angle and the angular velocity, a change curve of the angular velocity and the flip angle can be drawn in a coordinate system with the flip angle as the horizontal coordinate and the angular velocity as the vertical coordinate.

[0052] In some embodiments, based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing also includes: Based on the unhooking condition of the fairing, the unhooking angular velocity corresponding to the unhooking angle of the fairing is determined; the unhooking condition is used to indicate the condition under which the fairing separates from the rocket body when the centrifugal acceleration of the half-fairing and the radial components of the overload acceleration are equal, and the unhooking angle is the angle at which the half-fairing separates from the rocket body.

[0053] Optionally, the unhooking condition is a calculation formula involving the unhooking angle and the unhooking angular velocity. After determining the unhooking angle, the corresponding unhooking angular velocity can be determined based on the unhooking condition, so that it can be used to draw a variation curve of the angular velocity and the flip angle.

[0054] In step S203, based on the changing relationship between the coordinates of the center of mass of the half-mask and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-mask and the flip angle, and the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, the changing curve of the angular velocity and the flip angle is determined, including: Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the changing curves of the angular velocity and the flip angle of the half-cover are determined.

[0055] As an example, the embodiment of the present application provides another flowchart of the steps of determining the relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified. Figure 3 As shown, this step includes: S301 to S304.

[0056] S301. Based on the structural information of the fairing and the preset rigid axis formula, determine the changing relationship between the coordinates of the center of mass of the half-fairing and the flip angle and the changing relationship between the coordinates of the spring's points of action on the two half-fairings and the flip angle; the structural information includes the weight and size of the fairing and the information on the connection position between the spring and the half-fairing, and the half-fairing rotates around the center point of the hinge connecting the half-fairing and the rocket body.

[0057] S302. Based on the spring parameter value to be verified and the preset energy conservation equation, determine the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring; the height change is determined based on the coordinate change of the center of mass, and the length change is determined based on the coordinate change of the spring's action points at the two half-covers.

[0058] S303. Determine the unhooking angular velocity corresponding to the unhooking angle of the fairing based on the unhooking condition of the fairing; the unhooking condition is used to indicate the condition under which the fairing separates from the rocket body when the centrifugal acceleration of the half-fairing and the overload acceleration along the radial direction are equal, and the unhooking angle is the angle at which the half-fairing separates from the rocket body.

[0059] S304, based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, determine the changing curves of the angular velocity and the flip angle of the half-cover.

[0060] The embodiment of the present application can draw a curve of the change of the angular velocity and flip angle of the half mask, so as to conduct simulation tests more quickly and accurately to determine whether the design index requirements are met.

[0061] Based on the above example, see Figure 4 As shown, the present application embodiment provides a schematic diagram of a fairing separation process. Figure 4 As shown in the figure, the relationship between each particle on the fairing and the half-cover flip angle θ is established through the rotation axis formula, and then the relationship between the half-cover rotation angular velocity and the half-cover center of mass coordinates at any time is established through the law of conservation of energy. The specific analysis process is as follows: See also Figure 4 As shown, let the initial center of mass of the left and right half masks be ( x c0 , y c0 )and( x c0 ,- y c0 ); the initial coordinates of the action points of the left and right covers of the separation spring are ( x A0 , y A0 )and( xB0 ,- y B0 ), the initial coordinates of the turning points of the left and right half covers are ( x J , y J )and( x J ,- y J ); at any time, the center of mass of the left half mask is ( x c1 , y c1 ), the center of mass of the right half cover is ( x c1 ,- y c1 ); the coordinates of the action points of the left and right covers of the separation spring are ( x A1 , y A1 )and( x B1 , - y B1 ), the coordinates of the center points of the left and right half covers are ( x J , y J )and( x J ,- y J ); Assuming that the fairing is a pure rigid body motion during the motion process (i.e., the deformation effect is ignored), the relationship between the coordinates of each particle at any time and its initial coordinates can be obtained according to the rigid body rotation axis formula: The coordinates of the centroid of the half mask: (Formula 1) Coordinates of the left action point of the spring: (Formula 2) Coordinates of the right action point of the spring: (Formula 3) According to the energy conservation equation, we have (Formula 4) in, P n —Spring working load, take 7500N; H n —Spring working stroke, take 300mm; R — Radius of gyration from the centroid of the half cover to the hinge center, ; m —Half cover mass, designed to be 160kg; n —Overload factor, take 5.5; η —Spring efficiency coefficient, taking into account the flexible deformation of the fairing and external friction, is conservatively set to 0.8; ω — Half-mask angular velocity.

[0062] J is the rotational inertia of the fairing, and h is the height change of the center of mass, that is, x c1 - x c0 , △l is the length change of the spring, which can be 2*( y A1 - y A0 ).

[0063] Specifically, Pn and H n The value is the parameter value of the spring to be verified, that is, the parameter value of the working load is 7500N, and the parameter value of the working stroke is 300mm.

[0064] When the centrifugal acceleration and overload acceleration of the half-cover are equal in radial direction, the fairing reaches the unhooking condition, then: (Formula 5) in, — fairing unhooking angle, g-gravitational acceleration, radial direction is the vector from the hinge center to the center of mass of the half fairing, with the coordinates of the hinge center as the rotation origin.

[0065] The rigid shaft formula preset in the embodiment of the present application adopts the rigid shaft formula shown in formula (1) to formula (3), the preset energy conservation equation adopts the energy conservation equation shown in formula (4), and the decoupling condition is the decoupling formula shown in formula (5).

[0066] See also Figure 5 As shown, an embodiment of the present application provides a schematic diagram of a change curve of the angular velocity and flip angle of a half mask. Figure 5 By solving formula (1) to formula (5) together, we can obtain the curve of the angular velocity of the half cover changing with the flip angle under the spring design load and working stroke. Figure 5 The flip angle is used as the horizontal coordinate and the angular velocity is used as the vertical coordinate to draw the change curve of the angular velocity and the flip angle.

[0067] Based on the above and Figure 5 From the variation curve of angular velocity and flip angle, the design values ​​of fairing separation characteristic parameters can be obtained, see Table 1.

[0068] Table 1 Design parameters of separation characteristics of finishing hood

[0069] Based on Table 1, we can know that the angular velocity of the fairing (i.e., the target angular velocity) is 53.38 degrees / second, and the preset angular velocity can be 20 degrees / second. Then the spring parameter values ​​to be verified (the parameter value of the working load is 7500N, and the parameter value of the working stroke is 300mm) meet the design requirements and can be used as the target spring parameter values ​​for production application.

[0070] The method based on the embodiment of the present application can determine the required fairing separation characteristic design parameters according to actual needs.

[0071] Moreover, the spring of the embodiment of the present application can be used in the separation spring mechanism, and the inner sleeve and the outer sleeve can be telescopically connected through the elastic force of the spring. In order to prevent the inner sleeve from jumping out of the outer sleeve during the movement of the mechanism, a limit rod structure can be set. Subsequently, the embodiment of the present application carried out a rigid body separation simulation on the fairing to verify the effect of the separation mechanism. The simulation calculation results show that under the action of the separation mechanism, the fairing can smoothly realize the fairing ejection action under large overload conditions, and the target angular velocity of the separation meets the design index requirements.

[0072] The embodiment of the present application can predetermine the parameter value of the spring in a required separation spring mechanism: working load P n , Work schedule H n Etc.; and then obtain the variation curve of the half-mask angular velocity with the half-mask flip angle through simulation to verify the overall scheme, thereby improving the speed and accuracy of scheme verification.

[0073] See also Figure 6 As shown, the present invention provides a schematic diagram of a spring parameter value determination device. The spring parameter value determination device 60 is applied to separate two half fairings, and includes: a first determination module 601, a second determination module 602 and a third determination module 603.

[0074] The first determination module 601 is used to determine the changing relationship between the angular velocity and flip angle of the half-cover during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified; the spring parameter value to be verified is the parameter value that characterizes the elastic characteristics of the spring, and the flip angle is the angle at which the half-cover rotates relative to the central axis of the fairing. The second determination module 602 is used to determine the target angular velocity corresponding to the target flip angle based on the changing relationship between the angular velocity and the flip angle; the target flip angle represents the flip angle corresponding to the centroid of the half mask being at the highest point.

[0075] The third determination module 603 is used to determine the spring parameter value to be verified as the target spring parameter value if the target angular velocity is greater than the preset angular velocity.

[0076] Optionally, the third determination module 603 is used to adjust the spring parameter value to be verified if the target angular velocity is not greater than the preset angular velocity, obtain the adjusted spring parameter value, and use the adjusted spring parameter value as the new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load, working stroke.

[0077] Optionally, the third determination module 603 is used to respond to the setting operation on the parameter display interface, obtain the current spring parameter value of the parameter display interface as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, and the parameter setting area is used to set the spring parameter value.

[0078] Optionally, the first determination module 601 is used to determine the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle and the changing relationship between the coordinates of the spring's points of action at the two half-covers and the flip angle based on the structural information of the fairing and a preset rigid shaft formula; the structural information includes the weight, size and information of the connection position of the spring and the half-cover, and the half-cover rotates around the center point of the hinge connecting the half-cover and the rocket body; based on the spring parameter value to be verified and the preset energy conservation equation, determine the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring; the height change is determined based on the coordinate change of the center of mass, and the length change is determined based on the coordinate change of the spring's points of action at the two half-covers; based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the spring's points of action at the two half-covers and the flip angle, and the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, determine the changing curve of the angular velocity and the flip angle as the changing relationship between the angular velocity and the flip angle.

[0079] Optionally, the first determination module 601 is used to determine the initial coordinates of the center of mass of the two half-shields, the initial coordinates of the points of action of the springs on the two half-shields, and the initial coordinates of the center points of the hinges connecting the two half-shields to the rocket body from a preset coordinate system based on the structural information of the fairing; for any half-shield, based on the rigid axis formula, the initial coordinates of the center of mass of the half-shield, and the initial coordinates of the center point of the hinge connecting the half-shield to the rocket body, determine the changing relationship between the coordinates of the center of mass of the half-shield and the flip angle; based on the rigid axis formula, the initial coordinates of the points of action of the springs on the two half-shields, and the initial coordinates of the center point of the hinge connecting the two half-shields to the rocket body, determine the changing relationship between the coordinates of the points of action of the springs on the two half-shields and the flip angle.

[0080] Optionally, the first determination module 601 is used to determine the unhooking angular velocity corresponding to the unhooking angle of the fairing based on the unhooking condition of the fairing; the unhooking condition is used to indicate the condition under which the fairing is separated from the arrow body when the radial components of the centrifugal acceleration and the overload acceleration of the half-cover are equal, and the unhooking angle is the angle at which the half-cover is separated from the arrow body; based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the spring at the two half-covers and the flip angle, the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the changing curve of the angular velocity and the flip angle of the half-cover is determined.

[0081] Optionally, the second determination module 602 is used to determine a target flip angle corresponding to the centroid of the half fairing being at the highest point based on the structural information of the fairing.

[0082] The device of the embodiments of the present application can execute the method provided by the embodiments of the present application, and the implementation principles are similar. The actions performed by each module in the device of each embodiment of the present application correspond to the steps in the method of each embodiment of the present application. For the detailed functional description of each module of the device, please refer to the description in the corresponding method shown in the previous text, which will not be repeated here.

[0083] Based on the same inventive concept, an embodiment of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory, and the processor executes the computer program to implement the steps of the method of the embodiment of the present application.

[0084] In an alternative embodiment, an electronic device is provided, such as Figure 7 As shown, Figure 7 The electronic device 4000 shown includes: a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, such as through a bus 4002. Optionally, the electronic device 4000 may also include a transceiver 4004, which may be used for data interaction between the electronic device and other electronic devices, such as data transmission and / or data reception. It should be noted that in actual applications, the transceiver 4004 is not limited to one, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of the present application.

[0085] Processor 4001 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array) or other programmable logic devices, transistor logic devices, hardware components or any combination thereof. It may implement or execute various exemplary logic blocks, modules and circuits described in conjunction with the disclosure of this application. Processor 4001 may also be a combination that implements computing functions, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, etc.

[0086] The bus 4002 may include a path to transmit information between the above components. The bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus. The bus 4002 may be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 7 Only one thick line is used in the diagram, but this does not mean that there is only one bus or only one type of bus.

[0087] The memory 4003 may be a ROM (Read Only Memory) or other types of static storage devices that can store static information and instructions, a RAM (Random Access Memory) or other types of dynamic storage devices that can store information and instructions, or an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory) or other optical disk storage, optical disk storage (including compressed optical disk, laser disk, optical disk, digital versatile disk, Blu-ray disk, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium that can be used to carry or store computer programs and can be read by a computer, without limitation herein.

[0088] The memory 4003 is used to store the computer program for executing the embodiment of the present application, and the execution is controlled by the processor 4001. The processor 4001 is used to execute the computer program stored in the memory 4003 to implement the steps shown in the above method embodiment.

[0089] Based on the same inventive concept, an embodiment of the present application provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the steps of the method of the embodiment of the present application are implemented.

[0090] The computer-readable medium of the present application may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0091] In an embodiment of the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, device, or device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, device, or device. The program code contained on a computer-readable medium may be transmitted using any suitable medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination of the above.

[0092] The computer-readable medium of the embodiment of the present application may be included in the electronic device; or may exist independently without being assembled into the electronic device.

[0093] The embodiment of the present application also provides a computer program product, including a computer program, which can implement the steps and corresponding contents of the aforementioned method embodiment when executed by a processor.

[0094] It should be understood that, although each operation step is indicated by arrows in the flowchart of the embodiment of the present application, the implementation order of these steps is not limited to the order indicated by the arrows. Unless clearly stated herein, in some implementation scenarios of the embodiment of the present application, the implementation steps in each flowchart can be performed in other orders according to demand. In addition, some or all of the steps in each flowchart may include multiple sub-steps or multiple stages based on actual implementation scenarios. Some or all of these sub-steps or stages may be executed at the same time, and each sub-step or stage in these sub-steps or stages may also be executed at different times respectively. In different scenarios of execution time, the execution order of these sub-steps or stages may be flexibly configured according to demand, and the embodiment of the present application does not limit this.

[0095] In the embodiments of the present application, the term "module" or "unit" refers to a computer program or a part of a computer program that has a predetermined function and works together with other related parts to achieve a predetermined goal, and can be implemented in whole or in part by using software, hardware (such as processing circuits or memories), or a combination thereof. Similarly, a processor (or multiple processors or memories) can be used to implement one or more modules or units. In addition, each module or unit can be part of an overall module or unit that includes the function of the module or unit.

[0096] The above is only an optional implementation method for some implementation scenarios of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the solution of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A method for determining a spring parameter value, characterized in that: Applied to the separation of two half fairings, the method comprises: Based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing; the spring parameter value to be verified is a parameter value characterizing the elastic characteristics of the spring, and the flip angle is the angle at which the half-cover rotates relative to the central axis of the fairing; Based on the changing relationship between the angular velocity and the flip angle, a target angular velocity corresponding to a target flip angle is determined; the target flip angle represents the flip angle corresponding to the centroid of the half mask being at the highest point; If the target angular velocity is greater than the preset angular velocity, the spring parameter value to be verified is determined as the target spring parameter value.

2. The method for determining spring parameter values ​​according to claim 1, characterized in that: Based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing, including: Based on the structural information of the fairing and a preset rigid shaft formula, the changing relationship between the coordinates of the center of mass of the half-fairing and the flip angle and the changing relationship between the coordinates of the spring's action points on the two half-fairings and the flip angle are determined; the structural information includes the weight and size of the fairing and the information of the connection position between the spring and the half-fairing, and the half-fairing rotates around the hinge center point where the half-fairing is connected to the rocket body; Based on the spring parameter value to be verified and the preset energy conservation equation, determining the relationship between the angular velocity and the height change of the center of mass and the length change of the spring; the height change is determined based on the coordinate change of the center of mass, and the length change is determined based on the coordinate change of the spring's action points at the two half-covers; Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the spring on the two half-covers and the flip angle, and the changing relationship between the angular velocity and the change in height of the center of mass and the change in length of the spring, the changing curve of the angular velocity and the flip angle is determined as the changing relationship between the angular velocity and the flip angle.

3. The method for determining spring parameter values ​​according to claim 2, characterized in that: Based on the structural information of the fairing and the preset rigid shaft formula, the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle and the changing relationship between the coordinates of the spring's action points on the two half-covers and the flip angle are determined, including: Based on the structural information of the fairing, determine the initial coordinates of the center of mass of the two half-fairings, the initial coordinates of the points of action of the springs on the two half-fairings, and the initial coordinates of the center points of the hinges connecting the two half-fairings to the rocket body from a preset coordinate system; For any of the half-shields, based on the rigid axis formula, the initial coordinates of the center of mass of the half-shield and the initial coordinates of the center point of the hinge connecting the half-shield and the arrow body, determine the relationship between the coordinates of the center of mass of the half-shield and the flip angle; Based on the rigid axis formula, the initial coordinates of the spring's points of action on the two half-covers, and the initial coordinates of the hinge center points where the two half-covers are connected to the arrow body, the relationship between the coordinates of the spring's points of action on the two half-covers and the flip angle is determined.

4. The method for determining spring parameter values ​​according to claim 2, characterized in that: Based on the structural information of the fairing and the spring parameter value to be verified, determining the changing relationship between the angular velocity and the flip angle of the half fairing during the separation process of the fairing, further comprising: Based on the unhooking condition of the fairing, determining the unhooking angular velocity corresponding to the unhooking angle of the fairing; the unhooking condition is used to indicate the condition under which the fairing is separated from the arrow body when the centrifugal acceleration and the overload acceleration of the half-fairing are equal in radial direction, and the unhooking angle is the angle at which the half-fairing is separated from the arrow body; and, Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the springs on the two half-covers and the flip angle, and the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, the changing curve of the angular velocity and the flip angle is determined, including: Based on the changing relationship between the coordinates of the center of mass of the half-cover and the flip angle, the changing relationship between the coordinates of the points of action of the spring at the two half-covers and the flip angle, the changing relationship between the angular velocity and the height change of the center of mass and the length change of the spring, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the changing curves of the angular velocity and the flip angle of the half-cover are determined.

5. The method for determining spring parameter values ​​according to claim 1, characterized in that: Before determining the target angular velocity corresponding to the target flip angle based on the change relationship between the angular velocity and the flip angle, the method further includes: Based on the structural information of the fairing, a target flip angle corresponding to the centroid of the half fairing being at the highest point is determined.

6. The method for determining spring parameter values ​​according to claim 1, characterized in that: Also includes: If the target angular velocity is not greater than the preset angular velocity, the spring parameter value to be verified is adjusted to obtain an adjusted spring parameter value, and the adjusted spring parameter value is used as a new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load and working stroke.

7. The method for determining spring parameter values ​​according to claim 6, characterized in that: Adjusting the spring parameter value to be verified to obtain the adjusted spring parameter value includes: In response to a setting operation on a parameter display interface, a current spring parameter value of the parameter display interface is acquired as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, and the parameter setting area is used to set the spring parameter value.

8. A device for determining a spring parameter value, characterized in that: Applied to the separation of the two half fairings, including: A first determination module is used to determine the change relationship between the angular velocity and the flip angle of the half-cover during the separation process of the fairing based on the structural information of the fairing and the spring parameter value to be verified; the spring parameter value to be verified is a parameter value characterizing the elastic characteristics of the spring, and the flip angle is the angle at which the half-cover rotates relative to the central axis of the fairing; A second determination module is used to determine a target angular velocity corresponding to a target flip angle based on a change relationship between the angular velocity and the flip angle; the target flip angle represents a flip angle corresponding to a point where the center of mass of the half mask is at the highest point; The third determination module is used to determine the spring parameter value to be verified as the target spring parameter value if the target angular velocity is greater than the preset angular velocity.

9. An electronic device comprising a memory, a processor and a computer program stored in the memory, characterized in that: The processor executes the computer program to implement the steps of the method according to any one of claims 1 to 7.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 7 are implemented.

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