CN111080777A - Three-dimensional rapid modeling method for spacecraft thermal control product - Google Patents
Three-dimensional rapid modeling method for spacecraft thermal control product Download PDFInfo
- Publication number
- CN111080777A CN111080777A CN201911329258.5A CN201911329258A CN111080777A CN 111080777 A CN111080777 A CN 111080777A CN 201911329258 A CN201911329258 A CN 201911329258A CN 111080777 A CN111080777 A CN 111080777A
- Authority
- CN
- China
- Prior art keywords
- heater
- model
- thermal control
- template
- establishing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06T—IMAGE DATA PROCESSING OR GENERATION, IN GENERAL
- G06T17/00—Three dimensional [3D] modelling, e.g. data description of 3D objects
Abstract
The invention relates to a three-dimensional rapid modeling method of a spacecraft thermal control product, which comprises the steps of firstly, applying a parametric modeling method to establish a universal template of a heater; secondly, editing size variables in the template to quickly create different types of heater models, automatically creating an installation coordinate system and bending a heater according to a specific installation position and the contour type of an installation surface by adopting a method of assembling according to the coordinate system, and automatically and completely attaching and assembling the heater and the installation surface; and finally, establishing a loop skeleton model, defining a logic connection relation among the heaters, calculating the resistance value and the power of the heaters, renaming the heaters in batches and setting the figure number parameters of the heaters. According to the method, all design elements of the thermal control product are quickly reflected to the three-dimensional model, and the holographic three-dimensional model of the thermal control product is established, so that the thermal control design process is simplified, the design result is visualized, the follow-up production of designers is reduced, and the design efficiency of the thermal control product of the spacecraft is greatly improved.
Description
Technical Field
The invention belongs to the technical field of spacecraft thermal control systems, and relates to a three-dimensional rapid modeling method for a spacecraft thermal control product.
Background
The digitalized design based on the three-dimensional model is applied in China for more than 20 years, the structural components of the spacecraft are completely three-dimensional digitalized design at present, the operation of designing the thermal control product of the spacecraft by applying the existing mainstream three-dimensional design software is complex, the workload is large, the two-dimensional design is still taken as the main point, and the Pro/E-based three-dimensional rapid design aspect is not reported.
The space remote sensor is used as a load subsystem of a spacecraft, the structure appearance is complex due to index requirements such as the realized functional performance and the like, the heater is mostly arranged on the surface of a more critical structure, and the surfaces are mostly curved surfaces, the space layout is complex, the types and the scale of the heater are multiple, although the Pro/E standard function can realize the curved surface assembly of the heater, the operation is complicated, and the efficiency is low; in addition, the design of the thermal control loop and the calculation of the resistance value of the loop cannot be expressed in Pro/E, so that the design of the remote sensor thermal control product still uses the traditional two-dimensional graph mode. The development efficiency of remote sensor thermal control products is limited to a certain extent, the development period of the whole remote sensor is influenced to a certain extent, and the full three-dimensional design technology of the thermal control products is imperative along with the requirements of higher and higher complexity and shorter development period of the remote sensor products.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method overcomes the defects of the prior art, provides a three-dimensional rapid modeling method for a thermal control product of a spacecraft, realizes rapid generation of heater models with various geometric shapes according to a template and automatic assembly to surfaces of various structures, realizes thermal control loop design and resistance power automatic calculation based on the models, rapidly establishes a holographic model of the thermal control product, solves the problems of complex operation, low efficiency and low accuracy of three-dimensional modeling of the thermal control product of a remote sensor, and improves the comprehensive efficiency of design of the thermal control product.
The technical scheme of the invention is as follows:
a three-dimensional rapid modeling method for a spacecraft thermal control product comprises the following specific steps:
(1) establishing a spacecraft structure model, and carrying out contraction envelope processing on the structure model to form a structure contraction envelope model, wherein the surface geometry of the structure contraction envelope model comprises a plane, a cylindrical surface and a dome surface;
(2) establishing a spacecraft thermal control assembly empty model, establishing a thermal control framework model, and assembling a structural shrinkage envelope model into the thermal control assembly empty model in a default mode to form a preliminary thermal control assembly model;
(3) establishing heater templates in three forms of a plane, a cylindrical surface and a conical surface according to the surface geometry of the structural contraction envelope model, and setting a size variable as a variable parameter under each template; establishing a X, Y axis coordinate system which is positioned on the mounting surface and a Z axis is vertical to the mounting surface by taking the central position of the mounting surface as a coordinate origin;
(4) selecting a heater template, setting a size variable, and generating heater middle models with different geometric shapes; establishing a main backup lead coordinate system on a side plane of a heater middle model, wherein a Z axis points to the lead direction, drawing long curve segments in batches at the established lead coordinate system, and the long curve segments are perpendicular to the side plane and overlapped with the Z axis;
(5) selecting different structure surfaces under a preliminary thermal control assembly model, acquiring geometrical information of the selected structure surfaces, if the structure surfaces are planes, creating X, Y coordinate systems with axes on the structure surfaces and Z axes vertical to the structure surfaces at the assembly positions, and automatically assembling the heater on the planes by utilizing a coordinate system superposition assembly mode;
if the structure surface is a cylindrical surface or a conical surface, obtaining the distance S from the assembly position to the central axis and the included angle theta between the structure surface and the central axis, respectively assigning the values of S and theta to two parameters of LY _ BENDR and LY _ BENDWA, setting the rotation angle A of the heater on the structure surface, generating a solid heater with the same curvature as the structure surface, and simultaneously creating a coordinate system on the assembly position, wherein X, Y is the axis on the structure surface, the Z axis is vertical to the structure surface, and automatically assembling the heater on the cylindrical surface or the conical surface by using a coordinate system superposition assembly mode.
(6) Repeating the steps (3) to (5) until all heater models are created and assembled;
(7) under a preliminary thermal control assembly model, sequentially selecting heater models to be included in a loop, determining a series-parallel connection relation, creating a loop skeleton model in a skeleton model mode, and recording the heaters and the series-parallel connection relation included in the loop skeleton model;
(8) according to the serial number requirement of the thermal control integral model, a model name is allocated to the heater with the same geometric shape, lead position, resistance value, power and paint spraying requirement, the model name of the heater is modified in batch, the number of a heater graph is set, the number of the heater graph is written into the parameters of the heater model, and the thermal control assembly model and the heater model are established.
Preferably, the steps (1) and (2) are respectively used for constructing a spacecraft structure model, forming a structure shrinkage envelope model, establishing a thermal control assembly empty model, and assembling the structure shrinkage envelope model.
Preferably, in the step (3), the parameterized modeling of the curved heater is realized by combining four modeling characteristics of rotation, flattening, stretch cutting and bending for the curved heater template of the cylindrical surface and the conical surface.
Preferably, the steps (4) to (6) are implemented by modifying the size variable of the heater template by using parametric modeling to create a heater model; and the geometric dimension of the installation surface is automatically identified, the radian adjustment of the heater is driven, and the complete fitting assembly of the self-adaptive installation surface of the heater is realized by adopting a coordinate system assembly method and automatically establishing an installation coordinate system at the selected position.
Preferably, in the steps (7) and (8), a loop skeleton model is automatically created in a skeleton model mode, the resistance value and the power of the heater are automatically calculated, model numbers and figure numbers are automatically distributed to the heater according to the naming rule of the thermal control assembly model, and a holographic model of the thermal control product is established.
Preferably, the structural contraction envelope model surface geometry comprises a plane, a cylinder and a dome surface.
Preferably, the planar heater directly establishes five types of heater templates with triangular, parallelogram, trapezoid, circle and fan-shaped cross sections, and the thicknesses of the heater templates are all parameters H.
Preferably, an installation coordinate system is established in the right center of each template, and the Z axis is vertical to the installation surface; the size variables of the triangular template comprise two sides L1, L2 and an included angle theta 1, the size variables of the parallelogram template comprise two adjacent sides L, W and an included angle theta 2, the size variables of the trapezoid template comprise L3, L4, L5, an included angle theta 3 between L3 and L4, the size variable of the circular template is set to be a radius R, and the size variables of the fan template are set to be radii R1, R2 and an apex angle theta 4.
Preferably, the method of creating the cylindrical and conical heater templates is:
establishing a sketch line segment, generating a 359-degree rotating curved surface as a heater prototype template, establishing a mounting point and a mounting coordinate system at the midpoint of the sketch line segment, wherein the Z axis is vertical to the mounting surface, the distance from the mounting point to the rotating shaft is S, the included angle between the sketch line segment and the rotating shaft is-theta, and the included angle between the heater curved surface and the rotating shaft is A;
defining model-specific dimensions and parametric relationships: S-LY _ BENDR, θ -LY _ BENDWA, and a-LY _ BENDWA for the cylindrical form θ 0, where the parameter LY _ BENDWA is the mounting point rotation radius, LY _ BENDWA is the sketch line segment included angle with the rotation axis, and LY _ BENDWA is the heater rotation angle;
and flattening the prototype template by taking the mounting coordinate system as a reference point, establishing five types of geometric templates of triangle, parallelogram, trapezoid, circle and fan shape on a display plane by taking the mounting coordinate system as a central reference, setting the dimensional variables of the templates to be consistent with the planar heater, driving the longest edge of the heater to be not more than the length of a rotating line, and generating the heater template for the cylindrical surface or the conical surface by utilizing the entity bending according to LY _ BENDR and LY _ BENDWA parameters of the prototype template.
Preferably, in step (7), a loop voltage U and a loop power P are given, and a resistance value and a power of each heater are automatically calculated by using R ═ U)/P, Rn ═ Sn (R/S) × Sn and Pn ═ Sn (P/S) × Sn, where R is a loop resistance value, U is a loop voltage, P is a loop power, S is a total area of all heaters in the loop, Rn is a resistance value of an nth heater, Sn is an area of an nth heater, and Pn is a power of an nth heater.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention adopts a parametric modeling method, establishes a heater template applied to curved surfaces such as a cylindrical surface, a conical surface and the like by four modeling modes of rotation, flattening, stretching and bending, and completes the rapid construction of heater models with different geometric shapes by setting dimension variables;
(2) the method comprises the steps of automatically creating an installation coordinate system on an assembly surface, obtaining specific geometric information of the installation surface, assigning the specific geometric information to specific parameters, and driving the automatic deformation and fast and completely fitting assembly of a curved surface heater model to a specified structure surface position;
(3) according to the invention, thermal control loop design, heater resistance value calculation, thermal control product naming rules and methods are solidified into Pro/E, and thermal control loop design, automatic calculation of heater resistance value and power and batch naming of heater models based on a three-dimensional model are realized;
(4) the method can conveniently and rapidly construct the holographic model of the thermal control product, effectively improve the design efficiency of the thermal control product of the spacecraft, and provide the thermal control assembly model for the construction of the digital prototype of the spacecraft.
Drawings
FIG. 1 is a three-dimensional modeling flow chart of a thermal control product of a spacecraft of the invention.
Detailed Description
The invention is further described by the following specific embodiments in conjunction with the drawings of the specification.
A three-dimensional rapid modeling method for a spacecraft thermal control product is shown in figure 1, and comprises the following specific steps:
(1) establishing a spacecraft structure model, and carrying out contraction enveloping processing on the structure model to form a structure contraction enveloping model;
(2) establishing a spacecraft thermal control assembly empty model, establishing a thermal control framework model, and assembling a structural shrinkage envelope model into the thermal control assembly empty model in a default mode to form a preliminary thermal control assembly model;
(3) establishing heater templates in three forms of a plane, a cylindrical surface and a conical surface according to the surface geometry of the structural contraction envelope model, and setting a size variable as a variable parameter under each template; establishing a X, Y axis coordinate system which is positioned on the mounting surface and a Z axis is vertical to the mounting surface by taking the central position of the mounting surface as a coordinate origin;
(4) selecting a heater template, setting a size variable, and generating heater middle models with different geometric shapes; establishing a main backup lead coordinate system on a side plane of a heater middle model, wherein a Z axis points to the lead direction, drawing long curve segments in batches at the established lead coordinate system, and the long curve segments are perpendicular to the side plane and overlapped with the Z axis;
(5) selecting different structure surfaces under a preliminary thermal control assembly model, acquiring geometrical information of the selected structure surfaces, if the structure surfaces are planes, creating X, Y coordinate systems with axes on the structure surfaces and Z axes vertical to the structure surfaces at the assembly positions, and automatically assembling the heater on the planes by utilizing a coordinate system superposition assembly mode;
if the structure surface is a cylindrical surface or a conical surface, obtaining the distance S from the assembly position to the central axis and the included angle theta between the structure surface and the central axis, respectively assigning the values of S and theta to two parameters of LY _ BENDR and LY _ BENDWA, setting the rotation angle A of the heater on the structure surface, generating a solid heater with the same curvature as the structure surface, and simultaneously creating a coordinate system on the assembly position, wherein X, Y is the axis on the structure surface, the Z axis is vertical to the structure surface, and automatically assembling the heater on the cylindrical surface or the conical surface by using a coordinate system superposition assembly mode.
(6) Repeating the steps (3) to (5) until all heater models are created and assembled;
(7) under a preliminary thermal control assembly model, sequentially selecting heater models to be included in a loop, determining a series-parallel connection relation, creating a loop skeleton model in a skeleton model mode, and recording the heaters and the series-parallel connection relation included in the loop skeleton model;
(8) according to the serial number requirement of the thermal control integral model, a model name is allocated to the heater with the same geometric shape, lead position, resistance value, power and paint spraying requirement, the model name of the heater is modified in batch, the number of a heater graph is set, the number of the heater graph is written into the parameters of the heater model, and the thermal control assembly model and the heater model are established.
And (3) respectively constructing a spacecraft structure model in the steps (1) and (2), forming a structure shrinkage envelope model, establishing a thermal control assembly empty model, and assembling the structure shrinkage envelope model.
In the step (3), the parameterized modeling of the curved surface heater is realized by combining four modeling characteristics of rotation, flattening, stretch cutting and bending for the curved surface heater templates of the cylindrical surface and the conical surface.
The steps (4) - (6) are implemented by modifying the size variable of the heater template by using parametric modeling, and creating a heater model; and the geometric dimension of the installation surface is automatically identified, the radian adjustment of the heater is driven, and the complete fitting assembly of the self-adaptive installation surface of the heater is realized by adopting a coordinate system assembly method and automatically establishing an installation coordinate system at the selected position.
And (7) and (8) automatically creating a loop skeleton model in a skeleton model mode, automatically calculating the resistance value and the power of the heater, automatically distributing model numbers and figure numbers to the heater according to the naming rule of the thermal control assembly model, and establishing a holographic model of the thermal control product.
The planar heater directly establishes five heater templates with triangular, parallelogram, trapezoidal, circular and fan-shaped cross sections, and the thicknesses of the heater templates are all parameters H. Establishing an installation coordinate system in the right center of each template, wherein the Z axis is vertical to the installation surface; the size variables of the triangular template comprise two sides L1, L2 and an included angle theta 1, the size variables of the parallelogram template comprise two adjacent sides L, W and an included angle theta 2, the size variables of the trapezoid template comprise L3, L4, L5, an included angle theta 3 between L3 and L4, the size variable of the circular template is set to be a radius R, and the size variables of the fan template are set to be radii R1, R2 and an apex angle theta 4.
The method for establishing the cylindrical surface and conical surface type heater template comprises the following steps:
establishing a sketch line segment, generating a 359-degree rotating curved surface as a heater prototype template, establishing a mounting point and a mounting coordinate system at the midpoint of the sketch line segment, wherein the Z axis is vertical to the mounting surface, the distance from the mounting point to the rotating shaft is S, the included angle between the sketch line segment and the rotating shaft is-theta, and the included angle between the heater curved surface and the rotating shaft is A;
defining model-specific dimensions and parametric relationships: S-LY _ BENDR, θ -LY _ BENDWA, and a-LY _ BENDWA for the cylindrical form θ 0, where the parameter LY _ BENDWA is the mounting point rotation radius, LY _ BENDWA is the sketch line segment included angle with the rotation axis, and LY _ BENDWA is the heater rotation angle;
and flattening the prototype template by taking the mounting coordinate system as a reference point, establishing five types of geometric templates of triangle, parallelogram, trapezoid, circle and fan shape on a display plane by taking the mounting coordinate system as a central reference, setting the dimensional variables of the templates to be consistent with the planar heater, driving the longest edge of the heater to be not more than the length of a rotating line, and generating the heater template for the cylindrical surface or the conical surface by utilizing the entity bending according to LY _ BENDR and LY _ BENDWA parameters of the prototype template.
In the step (7), a loop voltage U and a loop power P are given, and the resistance value and the power of each heater are automatically calculated by using R ═ U)/P, Rn ═ R/S ═ Sn and Pn ═ P/S ═ Sn, where R is the loop resistance value, U is the loop voltage, P is the loop power, S is the total area of all heaters in the loop, Rn is the resistance value of the nth heater, Sn is the area of the nth heater, and Pn is the power of the nth heater.
Taking the example that a thermal control product model is created on the basis of a long-wave lens barrel structure model created by Pro/E, the long-wave lens barrel structure has three types of planes, cylindrical surfaces and a circular table top, according to the layout condition and requirements of the structure surface, triangular and trapezoidal heaters with different sizes are required to be installed on the planes, rectangular and circular heaters with different sizes are required to be installed on the cylindrical surfaces, and rectangular and fan-shaped heaters with different sizes are required to be installed on the circular table top.
As shown in FIG. 1, the method for rapidly constructing a spacecraft thermal control product model by packaging a Pro/E open interface Pro/Toolkit comprises the following steps:
step S10, Pro/E is started, a long-wave lens barrel structure component model is built, and a structure contraction enveloping model is formed.
Step S20, creating a long-wave lens barrel thermal control assembly model, building a thermal control framework model under the long-wave lens barrel thermal control assembly model, and building a reference coordinate system in the framework model, wherein the framework model is used for collecting geometrical information of the installation surface in the subsequent steps; and assembling the structural shrinkage envelope model under the thermal control component model by using a default assembling mode.
Step S30, establishing a three-dimensional heater template; in this embodiment, a triangular heater template for planar assembly, a rectangular heater template for cylindrical assembly, and a sector heater template for mesa assembly are established. For the triangular heat collector template, the triangular heat collector template is laid out on a plane in the embodiment, firstly, a triangular sketch cross section is established, the side length L1 is 1000mm, the side length L2 is 1000mm, and the included angle theta is 60, then, a stretching characteristic mode is used, the thickness H is set to be 2mm, two sides L1 and L2 of the triangular heat collector template and the included angle theta are set as dimension variables, an installation coordinate system is established at the center of an installation surface, and the Z axis is perpendicular to the installation plane. For a rectangular heater template, in this embodiment, the rectangular heater template is laid out on a cylindrical surface, a prototype template needs to be established first, a 1000mm long sketch line segment is established first, the line segment is parallel to a rotating shaft, the distance S from the rotating shaft to the rotating shaft is 500mm, a 359 ° rotating curved surface is generated as the prototype template, a mounting point and a mounting coordinate system are established at the midpoint of the sketch line segment, a Z-axis vertical mounting surface is established, and a model specific size and parameter relationship is defined in the relationship: setting LY _ BENDR as the rotation radius of the installation point and setting LY _ BENDRA as the rotation angle of the heater in the parameters; the original template is flattened by taking the mounting point as a datum point, a rectangular solid is formed on an unfolding plane by taking a mounting coordinate system as a central datum in a stretching and cutting mode, the thickness H is 2mm, the length L of the rectangle is 1000mm, the width W of the rectangle is 800mm, the included angle theta 1 is 90 degrees, the rectangular heater template for the curved surface is generated by bending the solid according to the S value, and S, A, L, W and theta are set as size variables.
For the fan-shaped heater template, which is laid out on the circular table surface in the embodiment, a prototype template needs to be established according to the rectangular heater prototype template construction method, wherein the included angle θ between the sketched line segment and the rotating shaft is-60 °, other parameters are the same as those of the rectangular heater prototype template, and the specific size and parameter relationship of the model is defined in the relationship: setting LY _ BENDR as the rotation radius of the installation point, setting LY _ BENDWA as the included angle between the sketch line segment and the rotation axis, and setting LY _ BENDRA as the rotation angle of the heater; flattening the original template by taking the mounting point as a reference point, forming a fan-shaped entity on an unfolding plane by taking a mounting coordinate system as a central reference in a stretching and cutting mode, wherein the thickness H is 2mm, the fan-shaped inner diameter R1 is 500mm, the inner diameter R2 is 800mm, the included angle theta 1 is 120 degrees, bending the entity according to S and theta to generate a fan-shaped heater template for a curved surface, and taking S, theta, A, R1, R2 and theta 1 as size variables.
The template is only required to be constructed once, and the template can be reused to derive a specific heater model subsequently.
Step S40, setting heater size variables, such as a triangular heater L1 being 20mm, an L2 being 30mm, and an included angle θ 1 being 60 ° according to the three types of heater templates established in step S30 and according to the structural surface space and temperature control requirements, and automatically generating heater intermediate models with different geometric shapes according to the set sizes; the method comprises the steps of establishing a main backup lead coordinate system on a side plane of a middle model of a heater, wherein a Z axis points to the lead direction, and all heaters used in the embodiment are four main backup leads, so that four outgoing line coordinate systems are established on each heater, automatically drawing 20mm long curve sections in batches at the positions of the established lead coordinate systems after the setting is completed, and enabling the sections to be perpendicular to the side plane and coincide with the Z axis.
In step S50, a heater model is assembled under the thermal control assembly model. In the embodiment, after the triangular heater model is generated, a certain position on the installation plane is selected, an installation coordinate system is automatically created at the position, and the heater assembly is automatically completed in a coordinate system overlapping mode. After the rectangular heater model is generated, a certain cylindrical surface is selected as an installation surface, the distance S from the selected cylindrical surface to a rotating shaft is automatically acquired to be 2400mm, the distance S is automatically given to a heater model parameter LY _ BENDR through the relation, the deformation that the radian of the rectangular heater is the same as that of the cylindrical surface is realized, the rotating angle A of the heater is set to be 60 degrees, and the rectangular heater model is automatically completely attached and assembled to a specified position. After the sector heater model is generated, a certain circular table surface position is selected as an installation surface, the distance S between the selected circular table surface and a rotating shaft is 3500mm, the included angle theta between the circular table surface and the rotating shaft is 45 degrees, the parameters LY _ BENDR and LY _ BENDWA are automatically given to the heater model through the relation, the deformation that the radian of the sector heater is the same as that of the circular table surface is realized, the rotating angle A of the heater is set to be 0, and the sector heater model is automatically and completely attached to a specified position.
And step S60, repeating the steps 4-5 until all heater models are created and assembled.
And step S70, under the thermal control assembly model, creating a loop skeleton model, and calculating the resistance value and the power of the heater. In the embodiment, 3 loop skeleton models are created, heaters are distributed to each loop, the series-parallel connection relation among the heaters is established, loop voltage U and loop power P are given, the resistance value and the power of each heater are calculated according to a formula, and the values of the resistance value and the power are automatically recorded in model parameters R and P.
And step S80, calling a Pro/E renaming function, completing batch renaming of all heaters under the thermal control component model according to the numbering requirements of the thermal control overall model, setting heater figure numbers in batches, writing the heater figure numbers into heater model parameters, and completing quick creation of the thermal control assembly model and elements.
The invention adopts a parametric modeling method, establishes a heater template applied to curved surfaces such as a cylindrical surface, a conical surface and the like by four modeling modes of rotation, flattening, stretching and bending, and completes the rapid construction of heater models with different geometric shapes by setting dimension variables;
the method comprises the steps of automatically creating an installation coordinate system on an assembly surface, obtaining specific geometric information of the installation surface, assigning the specific geometric information to specific parameters, and driving the automatic deformation and fast and completely fitting assembly of a curved surface heater model to a specified structure surface position;
according to the invention, thermal control loop design, heater resistance value calculation, thermal control product naming rules and methods are solidified into Pro/E, and thermal control loop design, automatic calculation of heater resistance value and power and batch naming of heater models based on a three-dimensional model are realized;
the invention provides a three-dimensional rapid modeling method for a spacecraft thermal control product, which can conveniently construct a holographic model of the thermal control product, effectively improve the design efficiency of the spacecraft thermal control product and provide a thermal control assembly model for the construction of a spacecraft digital prototype.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A three-dimensional rapid modeling method for a spacecraft thermal control product is characterized by comprising the following specific steps:
(1) establishing a spacecraft structure model, and carrying out contraction enveloping processing on the structure model to form a structure contraction enveloping model;
(2) establishing a spacecraft thermal control assembly empty model, establishing a thermal control framework model, and assembling a structural shrinkage envelope model into the thermal control assembly empty model in a default mode to form a preliminary thermal control assembly model;
(3) establishing heater templates in three forms of a plane, a cylindrical surface and a conical surface according to the surface geometry of the structural contraction envelope model, and setting a size variable as a variable parameter under each template; establishing a X, Y axis coordinate system which is positioned on the mounting surface and a Z axis is vertical to the mounting surface by taking the central position of the mounting surface as a coordinate origin;
(4) selecting a heater template, setting a size variable, and generating heater middle models with different geometric shapes; establishing a main backup lead coordinate system on a side plane of a heater middle model, wherein a Z axis points to the lead direction, drawing long curve segments in batches at the established lead coordinate system, and the long curve segments are perpendicular to the side plane and overlapped with the Z axis;
(5) selecting different structure surfaces under a preliminary thermal control assembly model, acquiring geometrical information of the selected structure surfaces, if the structure surfaces are planes, creating X, Y coordinate systems with axes on the structure surfaces and Z axes vertical to the structure surfaces at the assembly positions, and automatically assembling the heater on the planes by utilizing a coordinate system superposition assembly mode;
if the structure surface is a cylindrical surface or a conical surface, obtaining the distance S from the assembly position to the central axis and the included angle theta between the structure surface and the central axis, respectively assigning the values of S and theta to two parameters of LY _ BENDR and LY _ BENDWA, setting the rotation angle A of the heater on the structure surface, generating a solid heater with the same curvature as the structure surface, and simultaneously creating a coordinate system on the assembly position, wherein X, Y is the axis on the structure surface, the Z axis is vertical to the structure surface, and automatically assembling the heater on the cylindrical surface or the conical surface by using a coordinate system superposition assembly mode.
(6) Repeating the steps (3) to (5) until all heater models are created and assembled;
(7) under a preliminary thermal control assembly model, sequentially selecting heater models to be included in a loop, determining a series-parallel connection relation, creating a loop skeleton model in a skeleton model mode, and recording the heaters and the series-parallel connection relation included in the loop skeleton model;
(8) according to the serial number requirement of the thermal control integral model, a model name is allocated to the heater with the same geometric shape, lead position, resistance value, power and paint spraying requirement, the model name of the heater is modified in batch, the number of a heater graph is set, the number of the heater graph is written into the parameters of the heater model, and the thermal control assembly model and the heater model are established.
2. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: and (3) respectively constructing a spacecraft structure model in the steps (1) and (2), forming a structure shrinkage envelope model, establishing a thermal control assembly empty model, and assembling the structure shrinkage envelope model.
3. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: in the step (3), the parameterized modeling of the curved surface heater is realized by combining four modeling characteristics of rotation, flattening, stretch cutting and bending for the curved surface heater templates of the cylindrical surface and the conical surface.
4. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: the steps (4) - (6) are implemented by modifying the size variable of the heater template by using parametric modeling, and creating a heater model; and the geometric dimension of the installation surface is automatically identified, the radian adjustment of the heater is driven, and the complete fitting assembly of the self-adaptive installation surface of the heater is realized by adopting a coordinate system assembly method and automatically establishing an installation coordinate system at the selected position.
5. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: and (7) and (8) automatically creating a loop skeleton model in a skeleton model mode, automatically calculating the resistance value and the power of the heater, automatically distributing model numbers and figure numbers to the heater according to the naming rule of the thermal control assembly model, and establishing a holographic model of the thermal control product.
6. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: the structural contraction envelope model surface geometry includes a plane, a cylinder, and a dome surface.
7. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: the planar heater directly establishes five heater templates with triangular, parallelogram, trapezoidal, circular and fan-shaped cross sections, and the thicknesses of the heater templates are all parameters H.
8. The three-dimensional rapid modeling method for the thermal control product of the spacecraft of claim 7, characterized in that: establishing an installation coordinate system in the right center of each template, wherein the Z axis is vertical to the installation surface; the size variables of the triangular template comprise two sides L1, L2 and an included angle theta 1, the size variables of the parallelogram template comprise two adjacent sides L, W and an included angle theta 2, the size variables of the trapezoid template comprise L3, L4, L5, an included angle theta 3 between L3 and L4, the size variable of the circular template is set to be a radius R, and the size variables of the fan template are set to be radii R1, R2 and an apex angle theta 4.
9. The three-dimensional rapid modeling method for the thermal control product of the spacecraft of claim 1 or 3, characterized in that: the method for establishing the cylindrical surface and conical surface type heater template comprises the following steps:
establishing a sketch line segment, generating a 359-degree rotating curved surface as a heater prototype template, establishing a mounting point and a mounting coordinate system at the midpoint of the sketch line segment, wherein the Z axis is vertical to the mounting surface, the distance from the mounting point to the rotating shaft is S, the included angle between the sketch line segment and the rotating shaft is-theta, and the included angle between the heater curved surface and the rotating shaft is A;
defining model-specific dimensions and parametric relationships: S-LY _ BENDR, θ -LY _ BENDWA, and a-LY _ BENDWA for the cylindrical form θ 0, where the parameter LY _ BENDWA is the mounting point rotation radius, LY _ BENDWA is the sketch line segment included angle with the rotation axis, and LY _ BENDWA is the heater rotation angle;
and flattening the prototype template by taking the mounting coordinate system as a reference point, establishing five types of geometric templates of triangle, parallelogram, trapezoid, circle and fan shape on a display plane by taking the mounting coordinate system as a central reference, setting the dimensional variables of the templates to be consistent with the planar heater, driving the longest edge of the heater to be not more than the length of a rotating line, and generating the heater template for the cylindrical surface or the conical surface by utilizing the entity bending according to LY _ BENDR and LY _ BENDWA parameters of the prototype template.
10. The three-dimensional rapid modeling method for the thermal control product of the spacecraft according to claim 1, characterized in that: in the step (7), a loop voltage U and a loop power P are given, and the resistance value and the power of each heater are automatically calculated by using R ═ U)/P, Rn ═ R/S ═ Sn and Pn ═ P/S ═ Sn, where R is the loop resistance value, U is the loop voltage, P is the loop power, S is the total area of all heaters in the loop, Rn is the resistance value of the nth heater, Sn is the area of the nth heater, and Pn is the power of the nth heater.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911329258.5A CN111080777B (en) | 2019-12-20 | 2019-12-20 | Three-dimensional rapid modeling method for spacecraft thermal control product |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911329258.5A CN111080777B (en) | 2019-12-20 | 2019-12-20 | Three-dimensional rapid modeling method for spacecraft thermal control product |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111080777A true CN111080777A (en) | 2020-04-28 |
| CN111080777B CN111080777B (en) | 2021-08-10 |
Family
ID=70316399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911329258.5A Active CN111080777B (en) | 2019-12-20 | 2019-12-20 | Three-dimensional rapid modeling method for spacecraft thermal control product |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111080777B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112015139A (en) * | 2020-09-01 | 2020-12-01 | 北京卫星环境工程研究所 | Method, device, equipment and storage medium for automatically manufacturing thermal control multilayer of spacecraft |
| CN112465953A (en) * | 2020-12-02 | 2021-03-09 | 杭州群核信息技术有限公司 | Rapid parameterization modeling method based on template |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110148865A1 (en) * | 2009-12-18 | 2011-06-23 | Electronics And Telecommunications Research Institute | Method for automatic rigging and shape surface transfer of 3d standard mesh model based on muscle and nurbs by using parametric control |
| CN102708249A (en) * | 2012-05-10 | 2012-10-03 | 三一集团有限公司 | Method and system for product modular configuration |
| CN104217057A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Three-dimensional collaborative design method for spacecraft final assembly and thermal design |
| CN104217048A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Method for managing complex spacecraft three-dimensional model |
| CN105488242A (en) * | 2015-09-30 | 2016-04-13 | 郑州大学 | Skeleton and template-based earth-rock dam three-dimensional prototype building method |
| CN106446460A (en) * | 2016-10-26 | 2017-02-22 | 北京宇航系统工程研究所 | Lightweight method of super-large three-dimensional model of carrier rocket |
| US20170093483A1 (en) * | 2015-09-24 | 2017-03-30 | Lockheed Martin Corporation | Hybrid communications assembly for spacecraft |
| CN106570301A (en) * | 2016-11-17 | 2017-04-19 | 上海卫星工程研究所 | Satellite distributed type collaborative design method based on three-dimensional environment |
| CN106777575A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Satellite collaborative design method based on the transmission of ProE matrix parameters |
| CN107256009A (en) * | 2017-06-30 | 2017-10-17 | 武汉理工大学 | A kind of Digital product model Intelligent assembly system based on deep learning |
| CN107885922A (en) * | 2017-10-27 | 2018-04-06 | 北京空间技术研制试验中心 | Spacecraft modeling information management method |
| CN108416177A (en) * | 2018-04-28 | 2018-08-17 | 北京空间飞行器总体设计部 | A kind of satellite totality, structure, thermal control Digital Collaborative Design Method and system |
-
2019
- 2019-12-20 CN CN201911329258.5A patent/CN111080777B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110148865A1 (en) * | 2009-12-18 | 2011-06-23 | Electronics And Telecommunications Research Institute | Method for automatic rigging and shape surface transfer of 3d standard mesh model based on muscle and nurbs by using parametric control |
| CN102708249A (en) * | 2012-05-10 | 2012-10-03 | 三一集团有限公司 | Method and system for product modular configuration |
| CN104217057A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Three-dimensional collaborative design method for spacecraft final assembly and thermal design |
| CN104217048A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Method for managing complex spacecraft three-dimensional model |
| US20170093483A1 (en) * | 2015-09-24 | 2017-03-30 | Lockheed Martin Corporation | Hybrid communications assembly for spacecraft |
| CN105488242A (en) * | 2015-09-30 | 2016-04-13 | 郑州大学 | Skeleton and template-based earth-rock dam three-dimensional prototype building method |
| CN106446460A (en) * | 2016-10-26 | 2017-02-22 | 北京宇航系统工程研究所 | Lightweight method of super-large three-dimensional model of carrier rocket |
| CN106570301A (en) * | 2016-11-17 | 2017-04-19 | 上海卫星工程研究所 | Satellite distributed type collaborative design method based on three-dimensional environment |
| CN106777575A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Satellite collaborative design method based on the transmission of ProE matrix parameters |
| CN107256009A (en) * | 2017-06-30 | 2017-10-17 | 武汉理工大学 | A kind of Digital product model Intelligent assembly system based on deep learning |
| CN107885922A (en) * | 2017-10-27 | 2018-04-06 | 北京空间技术研制试验中心 | Spacecraft modeling information management method |
| CN108416177A (en) * | 2018-04-28 | 2018-08-17 | 北京空间飞行器总体设计部 | A kind of satellite totality, structure, thermal control Digital Collaborative Design Method and system |
Non-Patent Citations (3)
| Title |
|---|
| DEREK HENGEVELD,ET AL: "Hot and Cold-Case Orbits for Robust Thermal Control", 《JOURNAL OF SPACECRAFT AND ROCKETS》 * |
| 万毕乐 等: "面向航天器总体装配的工艺数字样机可视化自动构建方法及系统", 《计算机集成制造系统》 * |
| 张婕 等: "平板式石英灯加热器参数化设计", 《机械制造》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112015139A (en) * | 2020-09-01 | 2020-12-01 | 北京卫星环境工程研究所 | Method, device, equipment and storage medium for automatically manufacturing thermal control multilayer of spacecraft |
| CN112465953A (en) * | 2020-12-02 | 2021-03-09 | 杭州群核信息技术有限公司 | Rapid parameterization modeling method based on template |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111080777B (en) | 2021-08-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110516388B (en) | Harmonic mapping-based curved surface discrete point cloud model circular cutter path generation method | |
| EP1881458B1 (en) | Computer-implemented process for creating a parametric surface | |
| CN111080777B (en) | Three-dimensional rapid modeling method for spacecraft thermal control product | |
| CN105739440A (en) | Adaptive machining method of wide-chord hollow fan blade | |
| JPH07234888A (en) | Method for operation of system so as to manufacture three-dimensional structure and manufacturing apparatus of three-dimensional structure | |
| CN107067471B (en) | Self-adaptive scanning speed method for improving forming quality of pendant model | |
| WO2022036591A1 (en) | Method and device for formulating printing process in additive manufacturing | |
| Zheng et al. | Optimization of STL model and layer shape for laser cladding forming | |
| JP3557839B2 (en) | How to create mesh data on a curved surface | |
| CN210848792U (en) | Three-dimensional five-axis laser cutting machine tool | |
| CN109977526B (en) | Method for adjusting finite element model of wing based on three-dimensional CST technology | |
| CN107066644A (en) | A kind of special-shaped furred ceiling automatic modeling method | |
| Li et al. | Five-axis trochoidal sweep scanning path planning for free-form surface inspection | |
| CN115366568B (en) | Self-adaptive olive pit conformal carving method and system | |
| CN116330706A (en) | Process path generation system for automatically laying composite material | |
| Gibson et al. | Software for additive manufacturing | |
| CN110796735A (en) | NURBS curved surface finite element plate shell mesh division method and computer implementation system | |
| Du et al. | Wire arc additive manufacturing from the perspective of remanufacturing: A review of data processing | |
| EP4092557A1 (en) | Parameterization of digital irregular freeform geometries | |
| CN113408042B (en) | BIM-based shield segment parameterization drawing generation method and system | |
| Zhang et al. | Support Generation for Robot-Assisted 3D Printing with Curved Layers | |
| CN104345686B (en) | The two-way dexel blank modeling method of two dimension and machining simulation method thereof | |
| Weir et al. | Wrap-around B-spline surface fitting to digitized data with applications to reverse engineering | |
| JPH07302356A (en) | Method and device for preparing free curved surface | |
| Gao et al. | Cavity vertex regeneration through optimal energy model for restoration of worn parts |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |