Methods, devices, electronic equipment, and storage media for determining spring parameter values

Abstract

This application provides a method, apparatus, electronic device, and storage medium for determining spring parameter values, relating to the technical field of launch vehicles. The method includes: determining the relationship between the angular velocity and flip angle of the half-fairing during the fairing separation process based on the fairing's structural information and the spring parameter values ​​to be verified; the spring parameter values ​​to be verified are parameters characterizing the elasticity of the spring, and the flip angle is the angle of rotation of the half-fairing relative to the fairing's central axis; determining the target angular velocity corresponding to the target flip angle based on the relationship between the angular velocity and the flip angle; the target flip angle represents the flip angle corresponding to the half-fairing's center of mass being at its highest point; if the target angular velocity is greater than a preset angular velocity, then the spring parameter value to be verified is determined as the target spring parameter value. This application embodiment can quickly and easily determine the spring parameter values ​​actually needed by verifying the spring parameter values.

Description

Technical Field

[0001] This application relates to the technical field of launch vehicles, and more specifically, to a method, apparatus, electronic device, and storage medium for determining spring parameter values. Background Technology

[0002] The fairing of a launch vehicle consists of two halves, namely the first fairing and the second fairing. The fairing may be equipped with a separation spring mechanism, the two ends of which can be connected to the first fairing and the second fairing respectively. The spring force can push the first fairing and the second fairing to separate.

[0003] In actual production practice, the structural information of rocket fairing parameters such as weight and dimensions is often modified according to launch requirements. Therefore, it is necessary to determine the spring parameter values ​​of the separation spring mechanism based on the actual rocket requirements, so as to adapt them in production.

[0004] However, further research is needed to determine whether the spring parameter values ​​meet the design requirements for use in production, so that the spring can separate the finishing cover. Summary of the Invention

[0005] This application provides a method, apparatus, electronic device, and storage medium for determining spring parameter values, which solves the technical problem of how to verify spring parameter values ​​to obtain spring parameter values ​​that meet design requirements.

[0006] In a first aspect, embodiments of this application provide a method for determining spring parameter values, applied to the separation of the two halves of a fairing, the method comprising:

[0007] Based on the structural information of the fairing and the spring parameter values ​​to be verified, the relationship between the angular velocity and the flip angle of the half-fairing during the fairing separation process is determined; the spring parameter values ​​to be verified are parameters characterizing the elastic characteristics of the spring, and the flip angle is the angle of rotation of the half-fairing relative to the central axis of the fairing.

[0008] Based on the relationship between angular velocity and 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 highest point of the half-mask's center of mass.

[0009] If the target angular velocity is greater than the preset angular velocity, then the spring parameter value to be verified is determined as the target spring parameter value.

[0010] In one possible implementation, based on the fairing's structural information and the spring parameter values ​​to be verified, the relationship between the changes in the angular velocity and flip angle of the half-fairing during the fairing separation process is determined, including:

[0011] Based on the structural information of the fairing and the preset rigid rotation axis formula, the relationship between the coordinates of the center of mass of the half-fairing and the change of the flip angle, and the relationship between the coordinates of the spring at the action points of the two half-fairings and the change of the flip angle are determined. The structural information includes the weight and size of the fairing and the connection position of the spring and the half-fairing. The half-fairing rotates around the hinge center point connecting the half-fairing and the rocket body.

[0012] Based on the spring parameter values ​​to be verified and the preset energy conservation equation, the relationship between angular velocity and the changes in the height of the center of mass and the changes in the length of the spring is determined; the change in height is determined based on the coordinate changes of the center of mass, and the change in length is determined based on the coordinate changes of the spring at the two points of action of the two half-covers.

[0013] Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, and the 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 curves of the change of angular velocity and the flip angle are determined as the relationship between the change of angular velocity and the flip angle.

[0014] In one possible implementation, based on the structural information of the fairing and a preset rigid pivot formula, the relationship between the coordinates of the center of mass of the half-fairing and the change in the flip angle, and the relationship between the coordinates of the springs at their respective points of action on the two half-fairings and the change in the flip angle, are determined, including:

[0015] Based on the structural information of the fairing, the initial coordinates of the center of mass of the two half-fairings, the initial coordinates of the springs at the points of action of the two half-fairings, and the initial coordinates of the hinge center points connecting the two half-fairings to the rocket body are determined from the preset coordinate system.

[0016] For any half of the shield, based on the rigid rotation axis formula, the initial coordinates of the center of mass of the half shield, and the initial coordinates of the hinge center point connecting the half shield to the rocket body, the relationship between the coordinates of the center of mass of the half shield and the change of the flip angle is determined.

[0017] Based on the rigid shaft formula, the initial coordinates of the spring at the two half-covers' points of action, and the initial coordinates of the hinge center points connecting the two half-covers to the arrow body, the relationship between the spring's coordinates at the two half-covers' points of action and the change in the flip angle is determined.

[0018] In one possible implementation, based on the structural information of the fairing and the spring parameter values ​​to be verified, the relationship between the changes in the angular velocity and the flip angle of the half-fairing during the fairing separation process is determined, and the method further includes:

[0019] Based on the fairing's disengagement conditions, the disengagement angular velocity corresponding to the fairing's disengagement angle is determined; the disengagement condition represents the condition under which the fairing detaches from the rocket body when the radial components of the half-fairing's centrifugal acceleration and overload acceleration are equal; the disengagement angle is the angle at which the half-fairing separates from the rocket body; and,

[0020] Based on the relationship between the coordinates of the center of mass of the half-cover and the change in the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change in the flip angle, and the relationship between the angular velocity and the changes in the height of the center of mass and the changes in the length of the spring, the curves of the change in angular velocity and the flip angle are determined, including:

[0021] Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, the 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, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the curves of the change of angular velocity and flip angle of the half-cover are determined.

[0022] In one possible implementation, before determining the target angular velocity corresponding to the target flip angle based on the relationship between the angular velocity and the flip angle, the following steps are also included:

[0023] Based on the structural information of the fairing, the target flip angle corresponding to the center of mass of the half-fairing being at its highest point is determined.

[0024] In one possible implementation, the method for determining the spring parameter values ​​also includes:

[0025] 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 the new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load and working stroke.

[0026] In one possible implementation, the spring parameter values ​​to be verified are adjusted to obtain adjusted spring parameter values, including:

[0027] In response to the setting operation in the parameter display interface, the current spring parameter value in the parameter display interface is obtained as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, which is used to set the spring parameter value.

[0028] Secondly, embodiments of this application provide a device for determining spring parameter values, applied to the separation of the two halves of a fairing, comprising:

[0029] The first determining module is used to determine the relationship between the angular velocity and the flip angle of the half-shell during the fairing separation process, based on the fairing's structural information and the spring parameter values ​​to be verified. The spring parameter values ​​to be verified are parameters characterizing the elasticity of the spring, and the flip angle is the angle of rotation of the half-shell relative to the fairing's central axis.

[0030] The second determining module is used to determine the target angular velocity corresponding to the target flip angle based on the relationship between the changes in angular velocity and flip angle; the target flip angle represents the flip angle corresponding to the highest point of the center of mass of the half-mask;

[0031] The third determining 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.

[0032] Thirdly, embodiments of this application provide an electronic device, including 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.

[0033] Fourthly, embodiments of this application provide a computer-readable storage medium having a computer program stored thereon, wherein the computer program, when executed by a processor, implements the steps of the method of the first aspect.

[0034] The beneficial effects of the technical solutions provided in this application are:

[0035] This application embodiment can determine the relationship between the angular velocity and flip angle of the half-shell during the fairing separation process based on the fairing's structural information and the spring parameter values ​​to be verified. Then, based on the relationship between the angular velocity and flip angle, it determines the target angular velocity corresponding to the flip angle at the highest point of the half-shell's center of mass. Thus, when the target angular velocity is greater than a preset angular velocity, it can be determined that the spring parameter values ​​to be verified meet the design requirements, and these spring parameter values ​​are determined as the target spring parameter values ​​for application in production. This application embodiment can verify the spring parameter values ​​to ensure that the angular velocity of the spring at the highest point of the half-shell's center of mass is not lower than the minimum angular velocity, thereby guaranteeing the separation of the two half-shells. Therefore, this application embodiment can quickly and easily determine the actual required spring parameter values ​​by verifying the spring parameter values. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments of this application will be briefly introduced below.

[0037] Figure 1 This is a flowchart illustrating a method for determining spring parameter values ​​according to an embodiment of this application;

[0038] Figure 2 A flowchart illustrating the steps for determining the relationship between the angular velocity and flip angle of the half-fair during fairing separation based on fairing structural information and spring parameter values ​​to be verified, as provided in this application embodiment;

[0039] Figure 3 A flowchart illustrating another step for determining the relationship between the angular velocity and flip angle of the half-fairing during the fairing separation process, based on the fairing's structural information and the spring parameter values ​​to be verified, as provided in this application embodiment;

[0040] Figure 4 A schematic diagram of a fairing separation process provided in an embodiment of this application;

[0041] Figure 5 A schematic diagram showing the variation curves of the angular velocity and flip angle of a half-cover provided in an embodiment of this application;

[0042] Figure 6 A schematic diagram of a device for determining spring parameter values ​​provided in an embodiment of this application;

[0043] Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0044] The embodiments of this application are described below with reference to the accompanying drawings. It should be understood that the embodiments described below with reference to the accompanying drawings are exemplary descriptions for explaining the technical solutions of the embodiments of this application, and do not constitute a limitation on the technical solutions of the embodiments of this application.

[0045] Those skilled in the art will understand that, unless otherwise stated, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the terms “comprising” and “including” as used in embodiments of this application mean that the corresponding feature can be implemented as the presented feature, information, data, step, operation, element, and / or component, but do not exclude implementation as other features, information, data, step, operation, element, component, and / or combinations thereof supported by the art. It should be understood that when we say that an element is “connected” or “coupled” to another element, the one element can be directly connected or coupled to the other element, or it can mean that the one element and the other element establish a connection relationship through an intermediate element. Furthermore, “connected” or “coupled” as used herein can include wireless connection or wireless coupling. The term “and / or” as used herein indicates at least one of the items defined by the term; for example, “A and / or B” indicates implementation as “A,” or implementation as “A,” or implementation as “A and B.”

[0046] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0047] The method for determining the spring parameter values ​​provided in this application embodiment is the determination of the parameter values ​​of the spring's elastic characteristics. This spring is applied in a separation spring mechanism, which can be located inside the fairing and near the top of the fairing. The fairing can be divided into two parts: a first cover and a second cover. The two ends of the separation spring mechanism are connected to the first cover and the second cover, respectively. The separation spring mechanism can include an inner sleeve and an outer sleeve arranged coaxially. The two ends of the spring abut against the inner sleeve and the outer sleeve, respectively. The inner sleeve and the outer sleeve can be telescopically connected by the spring's contraction and extension. When the fairing is opened, the spring force can push the first cover and the second cover to separate.

[0048] As an example, one end of the separation spring mechanism can be rotatably connected to the first cover, and the other end can be held against the second cover. A limiting block with a limiting hole is provided in the inner sleeve, and a limiting rod is connected to the outer sleeve and is coaxially arranged therewith. The limiting rod passes through the limiting hole and the end of the limiting rod is provided with a limiting boss that matches the limiting hole. During the separation process of the separation spring mechanism, the limiting rod moves with the outer sleeve. The limiting hole restricts the movement position of the limiting boss, which can prevent the inner sleeve from popping out of the outer sleeve.

[0049] See Figure 1 As shown, this application provides a flowchart of a method for determining spring parameter values. Figure 1 As shown, the method for determining the spring parameter value is applied to the separation of the two halves of the fairing, and the method includes steps S101 to S103.

[0050] S101. Based on the structural information of the fairing and the spring parameter values ​​to be verified, determine the relationship between the angular velocity and the flip angle of the half-fairing during the fairing separation process; the spring parameter values ​​to be verified are parameter values ​​characterizing the elastic characteristics of the spring, and the flip angle is the angle of rotation of the half-fairing relative to the central axis of the fairing.

[0051] Optionally, the structural information of the fairing is determined based on the known structure of the fairing. It is pre-stored structural information and may include information such as the size and weight of the fairing and the connection position of the springs, which facilitates the determination of the initial and changing coordinates of known points on the fairing.

[0052] Optionally, the spring parameter value to be verified is a predetermined parameter value that needs to be verified. It can be a reasonable spring parameter value given by technicians based on practical production experience and the spatial environment inside the fairing. In the method for determining the spring parameter value of each fairing, an initial spring parameter value needs to be used 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 in the steps of the spring parameter value determination method of this application embodiment.

[0053] In some embodiments, the method for determining the spring parameter value further 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 and working stroke.

[0054] The embodiments of this application can adjust the spring parameter values, and use the adjusted spring parameter values ​​as new spring parameter values ​​to be verified to continue the verification process of the spring parameter values ​​to be verified, that is, to execute the steps of the spring parameter value determination method of the embodiments of this application until the target spring parameter values ​​that meet the design requirements are obtained.

[0055] In some embodiments, 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, obtaining the current spring parameter value on the parameter display interface as the adjusted spring parameter value; the parameter display interface includes a parameter setting area for setting the spring parameter value.

[0056] In this embodiment, the spring parameter value can be continuously adjusted manually on the parameter display interface. The adjustment of the spring parameter value can be determined by combining the practical experience of technicians and the spatial environment inside the fairing.

[0057] S102. Based on the relationship between angular velocity and flip angle, determine the target angular velocity corresponding to the target flip angle; the target flip angle represents the flip angle corresponding to the center of mass of the half-mask being at its highest point.

[0058] Alternatively, the target flip angle can be a known flip angle that can be determined based on the structure of the fairing.

[0059] In some embodiments, before determining the target angular velocity corresponding to the target flip angle based on the relationship between the angular velocity and the flip angle, the method further includes: determining the target flip angle corresponding to the center of mass of the half-cover being at its highest point based on the structural information of the fairing.

[0060] According to the embodiments of this application, the target angular velocity can be determined based on the target flip angle corresponding to the highest point of the half-mask, in the relationship between the change of angular velocity and flip angle, so as to facilitate the subsequent comparison of the target angular velocity.

[0061] S103. If the target angular velocity is greater than the preset angular velocity, then the spring parameter value to be verified is determined as the target spring parameter value.

[0062] In this embodiment, the minimum angular velocity at the highest point of the center of mass can be used as the preset angular velocity. This is a preset, known angular velocity, and when the target angular velocity is greater than the preset angular velocity, the separation of the two halves of the fairing can be guaranteed. The preset angular velocity can be determined based on the angular velocity determined by technicians in actual production practice.

[0063] Based on the above steps S101 to S103, this embodiment of the application can determine the relationship between the angular velocity and flip angle of the half-shell during the fairing separation process based on the fairing's structural information and the spring parameter values ​​to be verified. Then, according to the relationship between the angular velocity and flip angle, the target angular velocity corresponding to the flip angle at the highest point of the half-shell's center of mass can be determined. Thus, when the target angular velocity is greater than a preset angular velocity, it can be determined that the spring parameter values ​​to be verified meet the design requirements, and the spring parameter values ​​to be verified can be determined as the target spring parameter values ​​for application in production. This embodiment of the application can verify the spring parameter values ​​to determine that the angular velocity of the spring at the highest point of the half-shell's center of mass is not lower than the minimum angular velocity, thereby ensuring the separation of the two half-shells. Therefore, this embodiment of the application can quickly and easily determine the spring parameter values ​​actually needed by verifying the spring parameter values.

[0064] See Figure 2 As shown, this application embodiment provides a flowchart of the steps for determining the relationship between the angular velocity and flip angle of the half-fairing during the fairing separation process based on the fairing's structural information and the spring parameter values ​​to be verified. Figure 2 As shown, this step includes: S201 to S203.

[0065] S201. Based on the structural information of the fairing and the preset rigid rotation axis formula, determine the relationship between the coordinates of the center of mass of the half-fairing and the change of the flip angle, and the relationship between the coordinates of the spring at the action points of the two half-fairings and the change of the flip angle; the structural information includes the weight and size of the fairing and the connection position of the spring and the half-fairing, and the half-fairing rotates around the hinge center point connecting the half-fairing and the rocket body.

[0066] In some embodiments, based on the structural information of the fairing and a preset rigid pivot formula, the relationship between the coordinates of the center of mass of the half-fairing and the change in the flip angle, and the relationship between the coordinates of the springs at their respective points of action on the two half-fairings and the change in the flip angle, are determined, including:

[0067] (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 springs at the action points of the two half fairings, and the initial coordinates of the hinge center points connecting the two half fairings to the rocket body from the preset coordinate system.

[0068] (2) For any half of the shield, based on the rigid rotation axis formula, the initial coordinates of the center of mass of the half shield and the initial coordinates of the hinge center point 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 of the flip angle.

[0069] (3) Based on the rigid shaft formula, the initial coordinates of the spring at the action points of the two half-covers, and the initial coordinates of the hinge center points connecting the two half-covers to the arrow body, determine the relationship between the coordinates of the spring at the action points of the two half-covers and the change of the flip angle.

[0070] Based on the structural information of the fairing, this embodiment determines the initial coordinates of the centers of mass of the two fairing halves, the initial coordinates of the springs at their respective points of action on the two fairing halves, and the initial coordinates of the hinge centers connecting the two fairing halves to the rocket body in a preset coordinate system. As the rotation angle changes, the centers of mass of the two fairing halves and the points of action of the springs at their respective points of action on the two fairing halves will all change. Based on the rigid rotation axis formula, the relationship between the coordinates of the centers of mass of the fairing halves and the change in the rotation angle, as well as the relationship between the coordinates of the springs at their respective points of action on the two fairing halves and the change in the rotation angle, can be determined.

[0071] Optionally, the two half-covers are symmetrically arranged with respect to the central axis of the fairing, and during the separation process, the two half-covers also rotate symmetrically with respect to the central axis. Therefore, the motion of one half-cover can be selected to determine the relationship between the coordinates of the half-cover's center of mass and the change in the rotation angle.

[0072] Optionally, the rigid pivot formula is a pre-defined calculation formula involving the relationship between the coordinates of the center of mass of the two half-covers and the rotation angle, as well as the relationship between the coordinates of the spring at the points of action of the two half-covers and the rotation angle. By substituting the initial coordinates of the centers of mass of the two half-covers, the initial coordinates of the spring at the points of action of the two half-covers, and the initial coordinates of the hinge center points connecting the two half-covers to the arrow body into the calculation formula, the relationship between the coordinates of the center of mass of the half-covers and the rotation angle, as well as the relationship between the coordinates of the spring at the points of action of the two half-covers and the rotation angle, can be determined.

[0073] S202. Based on the spring parameter values ​​to be verified and the preset energy conservation equation, determine the relationship between the angular velocity and the changes in the height of the center of mass and the changes in the length of the spring; the change in height is determined based on the coordinate changes of the center of mass, and the change in length is determined based on the coordinate changes of the spring at the two half-covers respectively.

[0074] Optionally, the preset energy conservation equation is a preset calculation formula involving the relationship between angular velocity and the change in the height of the center of mass and the change in the length of the spring. By substituting the spring parameter values ​​to be verified into this calculation formula, the relationship between angular velocity and the change in the height of the center of mass and the change in the length of the spring can be obtained.

[0075] S203. Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, and the 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, determine the curves of the change of angular velocity and the flip angle as the relationship between the change of angular velocity and the flip angle.

[0076] The embodiments of this application can plot the curves of angular velocity and flip angle based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, and the 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.

[0077] In actual operation, based on the calculation formula of the above-mentioned change relationship in the embodiments of this application, by taking some values ​​of the flip angle and the angular velocity, the change curve of the angular velocity and the flip angle can be plotted in a coordinate system with the flip angle as the abscissa and the angular velocity as the ordinate.

[0078] In some embodiments, based on the structural information of the fairing and the spring parameter values ​​to be verified, determining the relationship between the changes in the angular velocity and the flip angle of the half-fairing during the fairing separation process further includes:

[0079] Based on the fairing's disengagement conditions, the disengagement angular velocity corresponding to the fairing's disengagement angle is determined. The disengagement conditions are used to indicate the conditions under which the fairing detaches from the rocket body when the radial components of the half-fairing's centrifugal acceleration and overload acceleration are equal. The disengagement angle is the angle at which the half-fairing detaches from the rocket body.

[0080] Optionally, the unhooking condition involves the calculation formulas for 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, which can then be used to plot the curves of the change in angular velocity and flip angle.

[0081] In step S203, based on the relationship between the coordinates of the center of mass of the half-cover and the change in the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change in the flip angle, and the 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 curves of the change in angular velocity and the change in flip angle are determined, including:

[0082] Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, the 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, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the curves of the change of angular velocity and flip angle of the half-cover are determined.

[0083] As an example, this application provides a flowchart of another step for determining the relationship between the angular velocity and flip angle of the half-fairing during the fairing separation process, based on the fairing's structural information and the spring parameter values ​​to be verified. Figure 3 As shown, this step includes: S301 to S304.

[0084] S301. Based on the structural information of the fairing and the preset rigid rotation axis formula, determine the relationship between the coordinates of the center of mass of the half-fairing and the change of the flip angle, and the relationship between the coordinates of the spring at the action points of the two half-fairings and the change of the flip angle; the structural information includes the weight and size of the fairing and the connection position of the spring and the half-fairing, and the half-fairing rotates around the hinge center point connecting the half-fairing and the rocket body.

[0085] S302. Based on the spring parameter values ​​to be verified and the preset energy conservation equation, determine the relationship between the angular velocity and the changes in the height of the center of mass and the changes in the length of the spring; the change in height is determined based on the coordinate changes of the center of mass, and the change in length is determined based on the coordinate changes of the spring at the two half-covers respectively.

[0086] S303. Based on the fairing's disengagement conditions, determine the disengagement angular velocity corresponding to the fairing's disengagement angle; the disengagement conditions are used to represent the conditions under which the fairing detaches from the rocket body when the radial components of the half-fairing's centrifugal acceleration and overload acceleration are equal, and the disengagement angle is the angle at which the half-fairing detaches from the rocket body.

[0087] S304. Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, the 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, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, determine the curves of the change in angular velocity and flip angle of the half-cover.

[0088] The embodiments of this application can plot the curves of the angular velocity and flip angle of the half-cover, thereby enabling faster and more accurate simulation experiments to determine whether the design requirements are met.

[0089] Based on the above example, see Figure 4 As shown in the diagram, this application provides a schematic diagram of a fairing separation process. Figure 4 As shown, the relationship between each mass point on the fairing and the half-fairing rotation angle θ is established using the rotation axis formula. Then, the relationship between the half-fairing rotation angular velocity and the half-fairing center of mass coordinates at any time is established using the law of conservation of energy. The specific analysis process is as follows:

[0090] See Figure 4 As shown, let the initial centroids of the left and right halves of the shield be ( ) at the initial moment. x c0 , y c0 )and(x c0 , - y c0 The initial coordinates of the action points inside the left and right covers of the separating spring are ( x A0 , y A0 )and( x B0 , - y B0 The initial coordinates of each rotation point in the left and right halves of the shield are ( x J , y J )and( x J , - y J Then at any given time, the centroid of the left half of the cover is ( x c1 , y c1 The centroid of the right half of the cover is ( ). x c1 , - y c1 ); The coordinates of the points of action inside the left and right covers of the separating spring are ( x A1 , y A1 )and( x B1 , - y B1 The coordinates of the center points of the hinges of the left and right halves of the cover are ( x J , y J )and( x J , - y J );

[0091] Assuming the fairing undergoes pure rigid body motion (i.e., neglecting deformation), then according to the rigid body rotation formula, the relationship between the coordinates of each mass point at any given time and its initial coordinates can be obtained:

[0092] The centroid coordinates of the semi-mask: (Formula 1)

[0093] Coordinates of the left point of application of the spring: (Formula 2)

[0094] Coordinates of the right point of application of the spring:

[0095] (Formula 3)

[0096] According to the law of conservation of energy, we have

[0097] (Formula 4)

[0098] in, P n —Spring working load, taken as 7500N;

[0099] H n —The working stroke of the spring is 300mm;

[0100] R —Radius of rotation from the center of mass of the half-cover to the center of the hinge, ;

[0101] m —The weight of the half-coverage is designed to be 160kg;

[0102] n —Overload factor, taken as 5.5;

[0103] η —The spring efficiency coefficient, taking into account the flexible deformation of the fairing and external friction, is conservatively taken as 0.8;

[0104] ω — Half-cover angular velocity.

[0105] J is the moment of inertia of the fairing, and h is the change in height of the center of mass, i.e. x c1 - x c0 Δl is the change in the length of the spring, which can be 2*( y A1 - y A0 ).

[0106] Specifically, Pn and H n The values ​​are the spring parameters to be verified, namely, the working load parameter value is 7500N and the working stroke parameter value is 300mm.

[0107] When the radial components of the centrifugal acceleration and overload acceleration of the half-fairing are equal, the fairing reaches the uncoupling condition, and thus: (Formula 5)

[0108] in, — Fairing decoupling angle, g-gravitational acceleration, radial direction is the vector from the center of the hinge to the center of mass of the half-fairing, with the coordinates of the hinge center as the origin of rotation.

[0109] The rigid shaft formula preset in this application embodiment is the rigid shaft formula shown in formulas (1) to (3), the energy conservation equation preset is the energy conservation equation shown in formula (4), and the decoupling condition is the decoupling formula shown in formula (5).

[0110] See Figure 5 As shown in the figure, this application embodiment provides a schematic diagram of the variation curves of the angular velocity and flip angle of a half-cover. Figure 5 By solving equations (1) to (5) simultaneously, 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 curves showing the changes in angular velocity and flip angle are plotted with the flip angle as the x-axis and angular velocity as the y-axis.

[0111] Based on the above content and Figure 5 The curves showing the changes in angular velocity and flip angle can be used to obtain the design values ​​of the fairing separation characteristic parameters, as shown in Table 1.

[0112] Table 1 Design parameters for the separation characteristics of the hood

[0113]

[0114] Based on Table 1, we know that the angular velocity of the fairing over the top (i.e., the target angular velocity) is 53.38 degrees / second, and the preset angular velocity can be 20 degrees / second. Therefore, the spring parameter values ​​to be verified (the working load parameter value is 7500N, and the working stroke parameter value is 300mm) meet the design requirements and can be used as the target spring parameter values ​​for production application.

[0115] The method based on the embodiments of this application can determine the required fairing separation characteristic design parameters according to actual needs.

[0116] Furthermore, the spring in this embodiment can be used in the separation spring mechanism, allowing the inner sleeve and outer sleeve to be telescopically connected through the spring force. To prevent the inner sleeve from slipping out of the outer sleeve during the mechanism's movement, a limiting rod structure can be provided. Subsequently, this embodiment performed a rigid body separation simulation on the fairing to verify the effectiveness of the separation mechanism. The simulation results show that under the action of the separation mechanism, the fairing can successfully achieve the fairing ejection action under high overload conditions, and the target angular velocity of the separation meets the design requirements.

[0117] The embodiments of this application can predetermine the parameter values ​​of the spring in a desired separation spring mechanism: working load. P n Work schedule H n Then, the curve of the half-cover angular velocity changing with the half-cover flip angle is obtained through simulation, which is used to verify the overall scheme, thereby improving the speed and accuracy of scheme verification.

[0118] See Figure 6 As shown in the diagram, this application provides a schematic diagram of a device for determining spring parameter values. This spring parameter value determining device 60 is used for separating the two halves of a fairing and includes: a first determining module 601, a second determining module 602, and a third determining module 603.

[0119] The first determining module 601 is used to determine the relationship between the angular velocity and the flip angle of the half-cover during the fairing separation process based on the structural information of the fairing and the spring parameter values ​​to be verified; the spring parameter values ​​to be verified are parameter values ​​that characterize the elastic characteristics of the spring, and the flip angle is the angle of rotation of the half-cover relative to the central axis of the fairing.

[0120] The second determining module 602 is used to determine the target angular velocity corresponding to the target flip angle based on the relationship between the angular velocity and the flip angle; the target flip angle represents the flip angle corresponding to the center of mass of the half-mask being at its highest point.

[0121] The third determining 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.

[0122] Optionally, the third determining 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, to obtain the adjusted spring parameter value, and to 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 and working stroke.

[0123] Optionally, the third determining module 603 is used to obtain the current spring parameter value of the parameter display interface in response to the setting operation on the parameter display interface, and use it as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, which is used to set the spring parameter value.

[0124] Optionally, the first determining module 601 is used to determine the relationship between the coordinates of the center of mass of the half-shell and the rotation angle, and the relationship between the coordinates of the springs at the points of action of the two half-shells and the rotation angle, based on the structural information of the fairing and a preset rigid shaft formula. The structural information includes the weight and dimensions of the fairing, as well as the connection position between the springs and the half-shells. The half-shells rotate around the hinge center point connecting the half-shells and the rocket body. Based on the spring parameter values ​​to be verified and a preset energy conservation equation, the module determines the 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 change in height is determined based on the change in the coordinates of the center of mass, and the change in length is determined based on the change in the coordinates of the springs at the points of action of the two half-shells. Based on the relationship between the coordinates of the center of mass of the half-shell and the rotation angle, the relationship between the coordinates of the springs at the points of action of the two half-shells and the rotation angle, and the 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 module determines the curves of the change in angular velocity and the rotation angle, which serve as the relationship between the change in angular velocity and the rotation angle.

[0125] Optionally, the first determining module 601 is used to determine, based on the structural information of the fairing, the initial coordinates of the center of mass of the two half-fairings, the initial coordinates of the springs at their respective points of action on the two half-fairings, and the initial coordinates of the hinge center points connecting the two half-fairings to the rocket body from a preset coordinate system; for any half-fairing, based on the rigid rotation axis formula, the initial coordinates of the center of mass of the half-fairing, and the initial coordinates of the hinge center points connecting the half-fairing to the rocket body, the relationship between the coordinates of the center of mass of the half-fairing and the rotation angle is determined; based on the rigid rotation axis formula, the initial coordinates of the springs at their respective points of action on the two half-fairings, and the initial coordinates of the hinge center points connecting the two half-fairings to the rocket body, the relationship between the coordinates of the springs at their respective points of action on the two half-fairings and the rotation angle is determined.

[0126] Optionally, the first determining 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 represent the condition when the radial components of the centrifugal acceleration and overload acceleration of the half-fairing are equal, and the unhooking angle is the angle at which the half-fairing separates from the rocket body; based on the relationship between the coordinates of the half-fairing's center of mass and the flip angle, the relationship between the coordinates of the spring at the two half-fairings' points of action and the flip angle, the 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, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the angular velocity and flip angle change curves of the half-fairing are determined.

[0127] Optionally, the second determining module 602 is used to determine the target flip angle corresponding to the highest point of the half-cover's center of mass based on the fairing's structural information.

[0128] The apparatus in this application embodiment can execute the method provided in this application embodiment, and the implementation principle is similar. The actions performed by each module in the apparatus of each embodiment of this application correspond to the steps in the method of each embodiment of this application. For detailed functional descriptions of each module of the apparatus, please refer to the descriptions in the corresponding methods shown above, which will not be repeated here.

[0129] Based on the same inventive concept, embodiments of this application provide an electronic device, including 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 embodiments of this application.

[0130] In one alternative embodiment, an electronic device is provided, such as Figure 7 As shown, Figure 7 The illustrated electronic device 4000 includes a processor 4001 and a memory 4003. The processor 4001 and the memory 4003 are connected, for example, via a bus 4002. Optionally, the electronic device 4000 may further include a transceiver 4004, which can be used for data interaction between the electronic device and other electronic devices, such as sending and / or receiving data. It should be noted that in practical applications, the transceiver 4004 is not limited to one type, and the structure of the electronic device 4000 does not constitute a limitation on the embodiments of this application.

[0131] 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 can implement or execute the 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 computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0132] Bus 4002 may include a pathway for transmitting information between the aforementioned components. Bus 4002 may be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Bus 4002 can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 7 The bus is represented by a single thick line, but this does not mean that there is only one bus or one type of bus.

[0133] The memory 4003 may be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or EEPROM (Electrically Erasable Programmable Read Only Memory), CD-ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed optical discs, laser discs, optical discs, digital universal optical discs, Blu-ray discs, etc.), magnetic disk storage media, other magnetic storage devices, or any other medium capable of carrying or storing computer programs and capable of being read by a computer, without limitation herein.

[0134] The memory 4003 stores computer programs that execute embodiments of this application, and its execution is controlled by the processor 4001. The processor 4001 executes the computer programs stored in the memory 4003 to implement the steps shown in the foregoing method embodiments.

[0135] Based on the same inventive concept, embodiments of this application provide a computer-readable storage medium storing a computer program thereon, wherein the computer program, when executed by a processor, implements the steps of the method of embodiments of this application.

[0136] The computer-readable medium of this application may be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof.

[0137] In this application embodiment, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can also be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical cables, RF (radio frequency), etc., or any suitable combination thereof.

[0138] The computer-readable medium in the embodiments of this application may be included in an electronic device; or it may exist separately and not assembled into an electronic device.

[0139] This application also provides a computer program product, including a computer program that, when executed by a processor, can implement the steps and corresponding content of the aforementioned method embodiments.

[0140] It should be understood that although arrows indicate various operation steps in the flowcharts of this application's embodiments, the order in which these steps are implemented is not limited to the order indicated by the arrows. Unless explicitly stated herein, in some implementation scenarios of this application's embodiments, the implementation steps in each flowchart can be executed in other orders as required. Furthermore, some or all steps in each flowchart, based on the actual implementation scenario, may include multiple sub-steps or multiple stages. Some or all of these sub-steps or stages can be executed at the same time, and each sub-step or stage can also be executed at different times. In scenarios where execution times differ, the execution order of these sub-steps or stages can be flexibly configured according to requirements, and this application's embodiments do not limit this.

[0141] In the embodiments of this application, the terms "module" or "unit" refer to a computer program or part of a computer program that has a predetermined function and works with other related parts to achieve a predetermined goal, and can be implemented wholly or partially using software, hardware (such as processing circuitry or memory), or a combination thereof. Similarly, a processor (or multiple processors or memory) can be used to implement one or more modules or units. Furthermore, each module or unit can be part of an overall module or unit that includes the functionality of that module or unit.

[0142] The above description is only an optional implementation method for some implementation scenarios of this application. It should be noted that for those skilled in the art, other similar implementation methods based on the technical concept of this application without departing from the technical concept of this application also fall within the protection scope of the embodiments of this application.

Claims

1. A method for determining spring parameter values, characterized in that, The method for separating the two halves of the fairing includes: Based on the structural information of the fairing and the parameter values ​​of the spring to be verified, the relationship between the angular velocity and the flip angle of the half-fairing during the fairing separation process is determined, including: based on the structural information of the fairing and a preset rigid shaft formula, determining the relationship between the coordinates of the center of mass of the half-fairing and the flip angle, and the relationship between the coordinates of the spring at the points of action of the two half-fairings and the flip angle; the structural information includes the weight and dimensions of the fairing, and the connection position of the spring and the half-fairing, with the half-fairing rotating around the hinge center point connecting the half-fairing to the rocket body; based on the parameter values ​​of the spring to be verified and a preset energy conservation equation, determining the angular velocity and the change in the height of the center of mass, and the relationship between the spring and the height of the half-fairing. The relationship between the length change and 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 at the two points of action of the two half-covers. Based on the relationship between the coordinates of the center of mass of the half-cover and the flip angle, the relationship between the coordinates of the spring at the two points of action of the two half-covers and the flip angle, and the relationship between the angular velocity and the height change of the center of mass and the length change of the spring, the curves of the angular velocity and the flip angle are determined as the relationship between the angular velocity and the flip angle. 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 of rotation of the half-cover relative to the central axis of the fairing. Based on the 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 highest point of the center of mass of the half-mask. If the target angular velocity is greater than the preset angular velocity, then 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 preset rigid pivot formula, the relationship between the coordinates of the center of mass of the half-fairing and the rotation angle, and the relationship between the coordinates of the spring at the points of action of the two half-fairings and the rotation angle are determined, including: Based on the structural information of the fairing, the initial coordinates of the centroids of the two half-fairings, the initial coordinates of the springs at the points of action of the two half-fairings, and the initial coordinates of the hinge center points connecting the two half-fairings to the rocket body are determined from the preset coordinate system. For any of the half-covers, based on the rigid rotation axis formula, the initial coordinates of the center of mass of the half-cover, and the initial coordinates of the hinge center point connecting the half-cover to the arrow body, the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle is determined. Based on the rigid shaft formula, the initial coordinates of the spring at the two points of action of the two half-covers, and the initial coordinates of the hinge center points connecting the two half-covers to the arrow body, the relationship between the coordinates of the spring at the two points of action of the two half-covers and the change of the flip angle is determined.

3. 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 values ​​to be verified, the relationship between the changes in the angular velocity and the flip angle of the half-fairing during the fairing separation process is determined, which also includes: Based on the fairing's disengagement conditions, the disengagement angular velocity corresponding to the fairing's disengagement angle is determined; the disengagement conditions represent the condition under which the fairing detaches from the rocket body when the radial components of the half-fairing's centrifugal acceleration and overload acceleration are equal; the disengagement angle is the angle at which the half-fairing separates from the rocket body; and, Based on the relationship between the coordinates of the center of mass of the half-cover and the rotation angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the rotation angle, and the relationship between the angular velocity and the changes in the height of the center of mass and the length of the spring, the curves of the changes in angular velocity and rotation angle are determined, including: Based on the relationship between the coordinates of the center of mass of the half-cover and the change of the flip angle, the relationship between the coordinates of the spring at the two points of action of the half-cover and the change of the flip angle, the 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, and the unhooking angular velocity corresponding to the unhooking angle of the fairing, the curves of the change of angular velocity and flip angle of the half-cover are determined.

4. 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 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 half-fairing's center of mass is determined.

5. 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 the adjusted spring parameter value, and the adjusted spring parameter value is used as the new spring parameter value to be verified; the spring parameter value includes at least one of the following: working load and working stroke.

6. The method for determining spring parameter values ​​according to claim 5, characterized in that, The spring parameter values ​​to be verified are adjusted to obtain the adjusted spring parameter values, including: In response to a setting operation on the parameter display interface, the current spring parameter value of the parameter display interface is obtained as the adjusted spring parameter value; the parameter display interface includes a parameter setting area, which is used to set the spring parameter value.

7. A device for determining spring parameter values, characterized in that, The separation of the two halves of the fairing, applied to the fairing, includes: The first determining module is used to determine the relationship between the angular velocity and the flip angle of the half-shell during the separation process of the fairing, based on the structural information of the fairing and the parameter values ​​of the spring to be verified. This includes: determining the relationship between the coordinates of the center of mass of the half-shell and the flip angle, and the relationship between the coordinates of the spring at the points of action of the two half-shells and the flip angle, based on the structural information of the fairing and a preset rigid shaft formula; the structural information includes the weight and dimensions of the fairing, and the connection position between the spring and the half-shell, with the half-shell rotating around the hinge center point connecting the half-shell to the rocket body; and determining the relationship between the angular velocity and the change in height of the center of mass, based on the parameter values ​​of the spring to be verified and a preset energy conservation equation. The relationship between the change in the length of the spring; the change in height is determined based on the coordinate change of the center of mass, and the change in length is determined based on the coordinate changes of the spring at the two points of action of the two half-covers; based on the relationship between the coordinates of the center of mass of the half-covers and the rotation angle, the relationship between the coordinates of the spring at the two points of action of the two half-covers and the rotation angle, and the 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 curves of the change in angular velocity and the rotation angle are determined as the relationship between the change in angular velocity and the rotation angle; the spring parameter value to be verified is a parameter value characterizing the elastic characteristics of the spring, and the rotation angle is the angle of rotation of the half-cover relative to the central axis of the fairing; The second determining module is used to determine the target angular velocity corresponding to the target flip angle based on the relationship between the angular velocity and the flip angle; the target flip angle represents the flip angle corresponding to the highest point of the center of mass of the half-mask; The third determining 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.

8. 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 1-6.

9. 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 steps of the method according to any one of claims 1-6.

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