CN112550761B - Integrated truss type minisatellite main bearing structure and design optimization method - Google Patents

Integrated truss type minisatellite main bearing structure and design optimization method Download PDF

Info

Publication number
CN112550761B
CN112550761B CN202011516069.1A CN202011516069A CN112550761B CN 112550761 B CN112550761 B CN 112550761B CN 202011516069 A CN202011516069 A CN 202011516069A CN 112550761 B CN112550761 B CN 112550761B
Authority
CN
China
Prior art keywords
truss
bottom plate
satellite
main bearing
middle plate
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.)
Active
Application number
CN202011516069.1A
Other languages
Chinese (zh)
Other versions
CN112550761A (en
Inventor
罗青
李东旭
范才智
王杰
周国华
周利霖
屠永刚
韩明芬
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
National University of Defense Technology
Original Assignee
National University of Defense Technology
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by National University of Defense Technology filed Critical National University of Defense Technology
Priority to CN202011516069.1A priority Critical patent/CN112550761B/en
Publication of CN112550761A publication Critical patent/CN112550761A/en
Application granted granted Critical
Publication of CN112550761B publication Critical patent/CN112550761B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M13/00—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
    • F16M13/02—Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16M—FRAMES, CASINGS OR BEDS OF ENGINES, MACHINES OR APPARATUS, NOT SPECIFIC TO ENGINES, MACHINES OR APPARATUS PROVIDED FOR ELSEWHERE; STANDS; SUPPORTS
    • F16M7/00—Details of attaching or adjusting engine beds, frames, or supporting-legs on foundation or base; Attaching non-moving engine parts, e.g. cylinder blocks
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Remote Sensing (AREA)
  • Evolutionary Computation (AREA)
  • Computer Hardware Design (AREA)
  • Mechanical Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Accessories Of Cameras (AREA)
  • Bridges Or Land Bridges (AREA)

Abstract

The invention belongs to the technical field of spacecraft structural design, and discloses an integrated truss type minisatellite main bearing structure and a design optimization method. Compared with the traditional small satellite main bearing structure, the satellite main bearing structure has the advantages that the integral supporting rigidity of the satellite structure is improved, the structural stability is improved, the mass of a structural system is reduced, the internal space volume of the small satellite is increased, and the internal space utilization efficiency of the satellite is improved. In addition, the invention can also provide good installation supporting points to adapt to the requirements of the satellite final assembly and the complex routing of the whole satellite cable on the installation points.

Description

Integrated truss type minisatellite main bearing structure and design optimization method
Technical Field
The invention belongs to the structural design of a spacecraft, and particularly relates to an integrated truss type minisatellite main bearing structure and a design optimization method.
Background
The main bearing structure is used for bearing the main load of the whole satellite and providing sufficient transverse, longitudinal and torsional rigidity for the satellite. On one hand, installation interfaces are provided for relevant equipment of a camera load and attitude control subsystem and the like, and the requirement of sufficient installation precision is ensured; in another aspect, a mechanical interface to interface with a launch vehicle is provided down.
The main bearing structure of the existing satellite platform is generally in the form of a bearing cylinder, a box plate or a combination of the bearing cylinder and the box plate. The number of the small satellite single-machine equipment is relatively large, and under the limiting conditions of the mass and the volume of the whole satellite and the like, if the existing main bearing structure form is directly used, the whole mass of the satellite is larger, the quality requirement of the satellite for carrying cannot be met, the available space in the satellite is seriously insufficient, and the on-satellite equipment cannot be reasonably arranged and installed. Therefore, a novel satellite main bearing structure design is needed to be established, stable support and good installation characteristics are provided for sensitive equipment such as camera loads, the space utilization efficiency in the satellite can be improved, and the installation requirements of other satellite equipment such as a propellant storage box and a satellite computer are met.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the integrated truss type minisatellite main bearing structure and the design optimization method can fully utilize the hollow structural characteristics of the truss type supporting structure on the premise of ensuring the enough supporting rigidity of the whole satellite, effectively improve the utilization rate of the mounting space of the equipment in the satellite, and meet the requirements of the equipment mounting on the satellite, the cable routing assembly on the satellite, the quality limitation of the whole satellite and the like.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
the utility model provides an integration truss-like moonlet owner load-carrying structure, includes medium plate, truss-like bearing structure and bottom plate, both parallel arrangement of medium plate and bottom plate are as the installation of satellite load and bear the weight of the mechanism each other, link to each other through truss-like bearing structure between medium plate and the bottom plate, one side that truss-like bearing structure was kept away from to the bottom plate is equipped with the docking mechanism who is used for connecting and carrier rocket butt joint.
Optionally, the middle portions of the middle plate and the bottom plate are both provided with a central through hole which is coaxially arranged, the truss-like support structure comprises a plurality of groups of support units, and the plurality of groups of support units are arranged between the middle plate and the bottom plate in a central symmetry manner around the central through hole.
Optionally, each group of support units of the truss-type support structure includes a group of truss rods arranged obliquely, one end of each group of truss rods is connected with each other and fixed with the bottom plate, and the other end of each group of truss rods is respectively connected and fixed with different connection points on the middle plate.
Optionally, a plurality of bottom plate embedded parts are arranged in the bottom plates, one ends of the bottom plate embedded parts are connected with each group of truss rods together, and the other ends of the bottom plate embedded parts are connected with the docking mechanism.
Optionally, an embedded reinforced annular frame and a plurality of middle plate embedded parts are arranged in the middle plate, and the truss rods in each group of truss rods are respectively connected with the embedded reinforced annular frame or the plurality of middle plate embedded parts.
Optionally, the docking mechanism is a conical tubular structure, and the outside aperture is larger than the inside aperture.
Optionally, the propellant storage tank in the satellite load is mounted on the bottom plate and located inside the truss-type supporting structure, and the satellite-borne computer, the magnetic suspension flywheel, the route management unit and the power management unit in the satellite load are respectively mounted at four corners of the bottom plate and located outside the truss-type supporting structure; and the fiber-optic gyroscope, the camera load and the star sensor in the satellite load are arranged on the middle plate.
Optionally, the fiber-optic gyroscope, the camera load and the star sensor are respectively mounted on the pre-embedded reinforced annular frame.
The invention also provides a satellite which comprises a satellite load and a main bearing structure which are connected with each other, wherein the main bearing structure is the integrated truss type minisatellite main bearing structure.
The invention also provides a design optimization method of the integrated truss type minisatellite main bearing structure, which comprises the following steps:
s1) determining the optimization parameters to be designed, including: height h and inverted cone angle alpha of butt joint mechanism, length l of truss rod, and outer diameter r of truss rodiAnd inner diameter ro(ii) a Setting constraint conditions, wherein the constraint conditions comprise the length range of the truss rod, the stress and the strain at the connecting point of the embedded part of the bottom plate and the stress and the strain at the connecting point of the butting mechanism;
s2) generating a plurality of groups of optimized parameters to be designed within the length range of the truss rod;
s3), aiming at each group of optimized parameters to be designed, establishing a functional expression of a structural analysis model of a docking mechanism, a bottom plate, a truss rod and a middle plate in the main bearing structure by using a finite element method, wherein the functional expression is shown as the following formula:
Figure 913067DEST_PATH_IMAGE001
in the above formula, the first and second carbon atoms are,
Figure 581946DEST_PATH_IMAGE002
is a quality matrix of an integrated truss type minisatellite main bearing structure,
Figure 575310DEST_PATH_IMAGE003
is a rigidity matrix of an integrated truss type minisatellite main bearing structure,
Figure 329639DEST_PATH_IMAGE004
in order to accelerate the elastic deformation of the structure,
Figure 375306DEST_PATH_IMAGE005
in order to increase the elastic deformation speed of the structure,
Figure 898691DEST_PATH_IMAGE006
is the elastic deformation displacement of the structure;x 1 ～x n respectively represent the finite element model 1 st to EnElastic deformation displacement of the structure with one degree of freedom; respectively calculating the stress and strain distribution of the connecting point of the bottom plate embedded part, the connecting point of the butt joint mechanism, the middle plate and the truss of the integrated truss type minisatellite main bearing structure under the given external static load conditionStress distribution at the frame joints, and the natural frequencies of the structure in transverse, longitudinal, and torsional directions; wherein:
Figure 328535DEST_PATH_IMAGE007
wherein the subscriptnRepresenting the number of degrees of freedom of the finite element model; general formula (VII)m ij For elements in the mass matrix, the representation is such that the system produces a unit acceleration only at the jth coordinate and corresponds to the jth coordinateiThe force required to be applied at each coordinate; general formula (VII)k ij For elements in the stiffness matrix, the representation is such that the system is only in the first placejProducing unit displacement on each coordinate corresponding to the secondiThe force required to be applied at each coordinate;
s4), under the constraint conditions of the strength of the connecting point of the embedded part of the bottom plate, the strength of the connecting point of the butt joint mechanism and the strength of the connecting point of the middle plate and the truss, selecting a group of parameters to be designed and optimized with optimal natural frequency, and outputting the parameters as an optimal design scheme.
Compared with the prior art, the technical scheme of the invention has the beneficial effects that:
according to the invention, the plate and the bottom plate are arranged in parallel to each other to serve as a mounting and bearing mechanism of a satellite load, the middle plate and the bottom plate are connected through the truss type supporting structure, and the side, away from the truss type supporting structure, of the bottom plate is provided with the butt joint mechanism for connecting and butting with a carrier rocket.
Secondly, the invention realizes the installation requirements of the propellant storage tank, the large-mass single machine and other various devices under the limited space in the star under the premise of meeting the requirement of carrying on the envelope size of the whole star through the truss type supporting structure.
Thirdly, the invention provides a wiring channel and a fixed installation point for the cable layout of the equipment in the satellite by utilizing the characteristic of the hollow structure of the truss type supporting structure, thereby improving the convenience of the final assembly operation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is a schematic front view of an embodiment of the present invention.
Fig. 2 is a schematic perspective exploded view of an embodiment of the present invention.
Fig. 3 is a schematic perspective exploded view of a satellite load according to an embodiment of the present invention.
Fig. 4 is a diagram showing an installation layout of a satellite load on a base plate according to an embodiment of the present invention.
Fig. 5 is a diagram of an installation layout of a satellite load on a midplane in an embodiment of the invention.
Fig. 6 is a schematic connection perspective view of the truss-like support structure and the docking mechanism according to the embodiment of the invention.
Fig. 7 is a partial sectional structural view of the connection between the truss-like support structure and the docking mechanism according to an embodiment of the present invention.
Fig. 8 is a schematic connection perspective view of the truss-like support structure and the pre-buried reinforcing annular frame according to the embodiment of the present invention.
Fig. 9 is a schematic view of a partial cross-sectional structure of a connection between an embedded reinforcing ring frame and a camera load according to an embodiment of the present invention.
FIG. 10 is a diagram illustrating related parameter labeling according to an embodiment of the present invention.
Fig. 11 is a top view of the topology of the main messenger when the number of satellite side deck boards is 4.
Fig. 12 is a top view of the topology of the main messenger when the number of satellite side deck boards is 5.
Fig. 13 is a top view of the topology of the main messenger when the number of satellite side deck boards is 6.
Fig. 14 is a stress distribution cloud chart of the satellite main bearing structure in the embodiment of the invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and fig. 2, the integrated truss type minisatellite main bearing structure of the embodiment includes a middle plate 1, a truss type supporting structure 3 and a bottom plate 5, the middle plate 1 and the bottom plate 5 are arranged in parallel to each other as a mounting and carrying mechanism of a satellite load, the middle plate 1 and the bottom plate 5 are connected through the truss type supporting structure 3, and a docking mechanism 6 for connecting with a launch vehicle in a docking manner is arranged on one side of the bottom plate 5 away from the truss type supporting structure 3.
In this embodiment, the middle plate 1 is an aluminum panel aluminum honeycomb core plate structure.
As shown in fig. 1 and 2, each group of support units of the truss-type support structure 3 includes a group of truss rods arranged obliquely, one end of each group of truss rods is connected with each other and fixed with the bottom plate 5, and the other end of each group of truss rods is respectively connected with different connection points on the middle plate 1. The truss type supporting structure 3 of the embodiment comprises 4 groups of supporting units and 12 truss rods in total, wherein the truss rods are made of carbon fiber composite materials, the lower ends of the truss rods are connected with a bottom plate 5, and the upper ends of the truss rods are connected with a middle plate 1; as an alternative embodiment, the truss rods of the truss-type supporting structure 3 are made of carbon fiber composite material, are wound and formed by carbon fiber composite material M55J/epoxy resin, have an outer diameter of phi 30mm and a wall thickness of 2mm, have high strength and high rigidity, and are hollow inside to reduce the weight.
As shown in fig. 1 and 2, the middle portions of the middle plate 1 and the bottom plate 5 are provided with a central through hole coaxially arranged, and the truss-type supporting structure 3 includes a plurality of groups of supporting units which are arranged between the middle plate 1 and the bottom plate 5 in a central symmetry manner around the central through hole. The central through hole can reduce the weight and simultaneously provide a wiring channel for the arrangement of the intra-satellite equipment in the intra-satellite cable.
As shown in fig. 3, the middle plate 1 in this embodiment is a rectangular plate.
As shown in fig. 3, the bottom plate 5 in this embodiment is a rectangular plate.
As shown in fig. 3, 4 and 5, the propellant tanks 11 in the satellite load are installed on the bottom plate 5 and located inside the truss-type supporting structure 3, and the satellite computer 7, the magnetic levitation flywheel 8, the route management unit 9 and the power management unit 10 in the satellite load are respectively installed at four corners of the bottom plate 5 and located outside the truss-type supporting structure 3; and the optical fiber gyroscope 13, the camera load 14 and the star sensor in the satellite load are arranged on the middle plate 1. Referring to fig. 5, as an alternative implementation, the star sensors in the embodiment respectively include the first star sensor 12, the second star sensor 15 and the third star sensor 16, and the number of the star sensors may be set according to requirements. In this embodiment, some of the equipment cables such as the satellite computer 7 and the propellant storage tank 11 are fixedly installed on the truss rods of the truss-type supporting structure 3.
As shown in fig. 3, 6 and 7, a plurality of bottom plate embedded parts 4 are arranged in the bottom plate 5, one end of each bottom plate embedded part 4 is connected with each group of truss rods, and the other end is connected with the docking mechanism 6, so that the requirements of rigidity, strength, stability support and the like are met, and the truss type supporting structure 3 and the docking mechanism 6 can be mounted stably. Furthermore, a pre-buried reinforced annular frame 2 and a plurality of middle plate embedded parts are arranged in the middle plate 1, and the truss rods in each group of truss rods are respectively connected with the pre-buried reinforced annular frame 2 or the plurality of middle plate embedded parts.
In this embodiment, the bottom plate 5 is an aluminum panel aluminum honeycomb core flat plate structure; the bottom plate embedded parts 4 are made of aluminum alloy, the number of the bottom plate embedded parts is 4 in total, and the bottom plate embedded parts 4 are respectively provided with a connecting hole of the butt joint ring 6 and a connecting hole of the truss 3. As an optional implementation manner, the floor embedded part 4 adopts a plurality of separate joint design forms, the reference circle size of the plane of the floor 5 is the same as that of the upper end interface of the docking mechanism 6, and a screw mounting hole is designed below the joint to realize the fixed connection between the floor embedded part 4 and the docking mechanism 6; and a screw mounting hole is designed above the joint so as to realize the fixed connection of the bottom plate embedded part 4 and a truss rod of the truss type supporting structure 3.
As shown in fig. 3, 8 and 9, the middle plate 1 is provided with the embedded reinforced annular frame 2, the fiber optic gyroscope 13, the camera load 14 and the star sensor are respectively connected with the embedded reinforced annular frame 2, and meanwhile, the requirements on rigidity, strength, stability support and the like are met, and the high-stability installation of sensitive equipment such as the fiber optic gyroscope 13, the camera load 14 and the star sensor is realized. The material of annular frame 2 strengthens in this embodiment is the aluminum alloy, and the quantity is 1 totally, is located the geometric centre position of medium plate 1, strengthens annular frame 2 and has truss-like bearing structure 3's connecting hole above the design respectively, and the below design has the connecting hole of camera load 14.
As shown in fig. 8, the truss-like support structure 3 is connected to the embedded reinforced annular frame 2 and the body of the middle plate 1, respectively. In this embodiment, 8 of 12 truss rods are connected to the pre-buried reinforcing ring frame 2, and the remaining 4 truss rods are connected to the body of the middle plate 1. As an optional implementation mode, the pre-embedded reinforced annular frame 2 is an integrated annular aluminum frame designed in a light weight mode, and has the characteristics of good integrity, good structural deformation consistency and the like, and a screw mounting hole is designed above the pre-embedded reinforced annular frame to provide a mounting surface for a camera load sensitive to structural deformation; the embedded reinforcing annular frame 2 and the bottom plate embedded part 4 are both provided with screw mounting holes so as to realize the fixed connection with the joint of the truss type supporting structure 3; the design has the screw mounting hole all around the medium plate 1, provides the installation interface for the curb plate.
As shown in fig. 3, 7 and 8, the docking mechanism 6 has a conical tubular structure, and the outside diameter is larger than the inside diameter. In the embodiment, the docking mechanism 6 is made of high-strength hard aluminum alloy, is arranged on the bottom plate 5, is positioned on the outer side of the satellite body, and is a mechanical interface for docking the satellite and the carrier rocket; the outer side caliber of the docking mechanism 6 is 660mm, and is the size of a 660-type docking ring interface of the international standard; the inner side caliber is 470mm in outer diameter, and can be connected with a bottom plate embedded part 4 in a bottom plate 5;
the envelope size of the main bearing structure of the embodiment is 1192mm × 966mm × 1397mm, different designs of the material and the structure size of the truss type supporting structure 3 are adopted to adapt to different bearing requirements, and the bearing capacity is 1 t.
In addition, this embodiment still provides a satellite, including interconnect's satellite load and main load-carrying structure, this main load-carrying structure is aforementioned integrated truss-like little satellite main load-carrying structure.
In the embodiment, the number of embedded parts on the bottom plate 5 is connected with the butting mechanism 6, the number of the connection points is N, N is generally 3-6, and is generally determined according to the number of actual side deck boards of the satellite configuration, so that each connection point can provide a support point connected with the side deck boards; as shown in FIG. 10, the reference circle radius of the embedded parts on the bottom plate 5 is R, and is related to the height h and the inverted cone angle alpha of the docking mechanism 6, wherein the height h of the docking mechanism 6 is more than or equal to 70mm and less than or equal to 120mm, the angle alpha is more than or equal to 15 degrees and less than or equal to 15 degrees, and N embedded parts of the bottom plate 5 are uniformly distributed on the reference circle R; according to the principle of continuity of a bearing structure, the butt joint mechanism 6 is a standard interface, the radius of the interface at the lower end is Rs, and then R = Rs-h tan alpha. According to the principle of continuity of a bearing structure, the radius of the middle embedded reinforcing ring frame is r and is the same as the radius of the mounting surface of the camera load; the number of the connection points arranged on the middle pre-buried reinforcing ring frame is consistent with that of the connection points of the butting mechanism 6, the number is N, the radius of a reference circle is r, the N connection points are uniformly distributed on the reinforcing ring frame and are connected with the embedded part of the bottom plate 5, and the angular phase difference of the N connection points and the embedded part of the bottom plate is beta = pi/N. Fig. 11 is a top view of the topological configuration of the main messenger when the number of satellite side deck boards is 4, when N = 4; fig. 12 is a top view of the topological configuration of the main messenger when the number of satellite side deck boards is 5, when N = 5; fig. 13 is a top view of the topological configuration of the main messenger when the number of satellite side deck boards is 6, when N = 6. The number of the support rods arranged at each connecting point is M, M is larger than or equal to 3, generally M =3, and the total number of the support rods of the truss structure is N multiplied by M.
In order to ensure the continuity of the bearing structure, the butt joint mechanism 6, the bottom plate embedded part 4 of the bottom plate 5, the truss rod and the middle plate 1 embedded part are required to be directly connected in a physical structure. Therefore, according to this principle, the present embodiment further provides a design optimization method for a primary load-bearing structure of an integrated truss-type minisatellite, including:
s1), determining optimization parameters to be designed, including: the height h and the inverted cone angle alpha of the docking mechanism 6, the rod length l of the truss rod and the outer diameter r of the rodiAnd inner diameter roSee fig. 10; setting constraint conditions, including the length range of the truss rod, the stress and the strain at the connecting point of the bottom plate embedded part 4 and the stress and the strain at the connecting point of the butting mechanism 6;
s2) generating a plurality of groups of optimized parameters to be designed within the length range of the truss rod;
s3) aiming at each group of optimized parameters to be designed, establishing a functional expression of a structural analysis model of the docking mechanism 6, the bottom plate 5, the truss rod and the middle plate 1 in the main bearing structure by using a finite element method, wherein the functional expression is as follows:
Figure 632478DEST_PATH_IMAGE001
in the above formula, the first and second carbon atoms are,
Figure 455071DEST_PATH_IMAGE002
is a quality matrix of an integrated truss type minisatellite main bearing structure,
Figure 98542DEST_PATH_IMAGE003
is a rigidity matrix of an integrated truss type minisatellite main bearing structure,
Figure 433709DEST_PATH_IMAGE004
in order to accelerate the elastic deformation of the structure,
Figure 162630DEST_PATH_IMAGE005
in order to increase the elastic deformation speed of the structure,
Figure 241445DEST_PATH_IMAGE006
is structural elasticityDeformation displacement;x 1 ～x n respectively represent the finite element model 1 st to EnElastic deformation displacement of the structure with one degree of freedom; respectively calculating stress and strain distribution at a connecting point of a bottom plate embedded part 4, a connecting point of a butting mechanism 6, a connecting point of a middle plate and a truss and inherent frequencies of transverse, longitudinal and torsion of the structure of the integrated truss type minisatellite main bearing structure under a given external static load condition; wherein:
Figure 801739DEST_PATH_IMAGE007
wherein the subscriptnRepresenting the number of degrees of freedom of the finite element model; general formula (VII)m ij For elements in the mass matrix, the representation is such that the system produces a unit acceleration only at the jth coordinate and corresponds to the jth coordinateiThe force required to be applied at each coordinate; general formula (VII)k ij For elements in the stiffness matrix, the representation is such that the system is only in the first placejProducing unit displacement on each coordinate corresponding to the secondiThe force required to be applied at each coordinate;
s4), under the constraint conditions of the strength of the connecting point of the bottom plate embedded part 4, the strength of the connecting point of the butting mechanism 6 and the strength of the connecting point of the middle plate and the truss, selecting a group of parameters to be designed and optimized with optimal natural frequency to be output as an optimal design scheme.
The integrated truss type minisatellite main bearing structure determines the integral rigidity and natural frequency of the whole satellite, and the integral rigidity and natural frequency define the optimization target as the rigidity and natural frequency of the main bearing structure in the design of the satellite structure; the constraint conditions take into account the strength at the connecting point, the connecting strength at the docking mechanism 6, and the range of the rod length limited by the height H between the middle plate 1 and the bottom plate 5; respectively calculating the stress distribution of the structure under the given external static load condition and the transverse, longitudinal and torsional natural frequencies of the structure by using a structure analysis model; analyzing whether the strength requirement is met or not according to the stress conditions at the connecting point of the embedded part of the bottom plate and the butting mechanism 6; meet the strength requirementOn the premise of (1), the height h, the inverted cone angle alpha, the rod length l and the outer diameter r of the rod of the butt joint mechanism 6 are obtained by an optimal calculation methodiAnd inner diameter roThe higher the natural frequency of the system is, the smaller the mass of the main bearing structure of the integrated truss type small satellite is. As shown in fig. 14, the stress distribution diagram of the main load-carrying structure under the condition of the overload acceleration of 10g, where the stress at the joint of the embedded part is 3.90MPa, the stress at the joint of the butt structure is 4.03MPa, and the stress at the joint of the middle plate is 20.5MPa, meets the design requirements.
It should be noted that, in the description of the present application, it should be understood that the terms "upper", "lower", "around", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, which is only for convenience of describing the present application and simplifying the description, but does not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims (1)

1. A design optimization method of an integrated truss type minisatellite main bearing structure is characterized in that the integrated truss type minisatellite main bearing structure comprises a middle plate (1), a truss type supporting structure (3) and a bottom plate (5), the middle plate (1) and the bottom plate (5) are arranged in parallel to serve as a mounting and bearing mechanism of a satellite load, the middle plate (1) and the bottom plate (5) are connected through the truss type supporting structure (3), one side of the bottom plate (5) far away from the truss type supporting structure (3) is provided with a butt joint mechanism (6) used for connecting and carrying rockets, the middle parts of the middle plate (1) and the bottom plate (5) are provided with coaxially arranged central through holes, the truss type supporting structure (3) comprises a plurality of groups of supporting units, and the plurality of groups of supporting units are arranged between the middle plate (1) and the bottom plate (5) in a central symmetry manner around the central through holes, each group of supporting units comprises a group of obliquely arranged truss rods, one ends of the group of truss rods are connected with each other and fixedly connected with a bottom plate (5), the other ends of the group of truss rods are respectively fixedly connected with different connection points on a middle plate (1), a plurality of bottom plate embedded parts (4) are arranged in the bottom plate (5), one ends of the bottom plate embedded parts (4) are jointly connected with each group of truss rods, the other ends of the bottom plate embedded parts are connected with a docking mechanism (6), a pre-embedded reinforced annular frame (2) and a plurality of middle plate embedded parts are arranged in the middle plate (1), the truss rods in each group of truss rods are respectively connected with the pre-embedded reinforced annular frame (2) or the plurality of middle plate embedded parts, the docking mechanism (6) is of a conical tubular structure, the outside aperture is larger than the inside aperture, and the design optimization method of the integrated truss type small satellite main bearing structure comprises the following steps:
s1), determining optimization parameters to be designed, including: the height h and the inverted cone angle alpha of the docking mechanism (6), the rod length l of the truss rod and the outer diameter r of the rodiAnd inner diameter ro(ii) a Setting constraint conditions, wherein the constraint conditions comprise the length range of the truss rod, the strength of the connecting point of the bottom plate embedded part (4), the strength of the connecting part of the butting mechanism (6) and the strength of the connecting point of the middle plate and the truss;
s2) generating a plurality of groups of optimized parameters to be designed within the length range of the truss rod;
s3) aiming at each group of optimized parameters to be designed, establishing a functional expression of a structural analysis model of the butt joint mechanism (6), the bottom plate (5), the truss rod and the middle plate (1) in the main bearing structure by using a finite element method, wherein the functional expression is shown as the following formula:
Figure FDA0003215893910000011
in the above formula, M is the mass matrix of the main bearing structure of the integrated truss type minisatellite, K is the rigidity matrix of the main bearing structure of the integrated truss type minisatellite,
Figure FDA0003215893910000012
in order to accelerate the elastic deformation of the structure,
Figure FDA0003215893910000013
for the elastic deformation speed of the structure, X ═ X1 x2 x3 … xn]TElastic deformation and displacement of the structure; x is the number of1～xnRespectively representing the structure elastic deformation displacement of the 1 st to n th degrees of freedom of the finite element model; respectively calculating stress and strain distribution at a connecting point of a bottom plate embedded part (4), a connecting point of a butting mechanism (6), a connecting point of a middle plate and a truss and inherent frequencies of transverse, longitudinal and torsion of the structure of the integrated truss type minisatellite main bearing structure under a given external static load condition; wherein:
Figure FDA0003215893910000021
Figure FDA0003215893910000022
wherein the subscript n represents the number of degrees of freedom of the finite element model; general formula mijThe elements in the mass matrix represent the force required to be applied to cause the system to produce a unit acceleration at the jth coordinate only and correspond to the ith coordinate; general formula kijIs an element in the stiffness matrix representing the force required to be applied to cause the system to produce a unit displacement at the jth coordinate only, corresponding to the ith coordinate;
s4), under the constraint conditions of the strength of the connecting point of the bottom plate embedded part (4), the strength of the connecting point of the butt joint mechanism (6) and the strength of the connecting point of the middle plate and the truss, selecting a group of parameters to be designed and optimized with optimal natural frequency to be output as an optimal design scheme.
CN202011516069.1A 2020-12-21 2020-12-21 Integrated truss type minisatellite main bearing structure and design optimization method Active CN112550761B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011516069.1A CN112550761B (en) 2020-12-21 2020-12-21 Integrated truss type minisatellite main bearing structure and design optimization method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011516069.1A CN112550761B (en) 2020-12-21 2020-12-21 Integrated truss type minisatellite main bearing structure and design optimization method

Publications (2)

Publication Number Publication Date
CN112550761A CN112550761A (en) 2021-03-26
CN112550761B true CN112550761B (en) 2021-09-21

Family

ID=75031069

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011516069.1A Active CN112550761B (en) 2020-12-21 2020-12-21 Integrated truss type minisatellite main bearing structure and design optimization method

Country Status (1)

Country Link
CN (1) CN112550761B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113607403B (en) * 2021-09-06 2022-04-29 北京空间机电研究所 Height-adjustable spacecraft storage box simulation loading static test device and method

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106564619B (en) * 2016-10-28 2018-09-18 航天东方红卫星有限公司 A kind of Commercial Remote Sensing Satellites configuration layouts
CN106428651A (en) * 2016-11-29 2017-02-22 上海卫星工程研究所 Space-based large-diameter multi-constrained extrasolar terrestrial planet detector structure
CN107804485B (en) * 2017-09-27 2020-04-07 北京空间飞行器总体设计部 Support between all-carbon fiber composite material device
CN108438253A (en) * 2018-03-06 2018-08-24 航天东方红卫星有限公司 A kind of microsatellite structure suitable for optics load
RU2694487C1 (en) * 2018-10-05 2019-07-15 Акционерное общество "Научно-производственное объединение им. С.А. Лавочкина" Double start system and support assembly
CN110065653B (en) * 2019-05-23 2020-08-04 上海微小卫星工程中心 Main framework of small high-orbit satellite common platform

Also Published As

Publication number Publication date
CN112550761A (en) 2021-03-26

Similar Documents

Publication Publication Date Title
CN106564619B (en) A kind of Commercial Remote Sensing Satellites configuration layouts
CN108674692B (en) Remote sensing microsatellite
CN107140233B (en) Ground simulation satellite and the rocket integrated multi-functional structural aircraft
EA031358B1 (en) Modular central structure for a dual launch of space aircrafts
CN112550761B (en) Integrated truss type minisatellite main bearing structure and design optimization method
CN111703592B (en) Large commercial remote sensing satellite platform configuration and assembly method
CN108897239B (en) Spacecraft two-stage attitude control simulation system
CN107792399A (en) Tank test formula satellite platform structure
CN110450983A (en) Quick satellite configuration
CN112357118B (en) Manned lunar surface lander based on truss structure
CN109911246A (en) Spacecraft composite structure is connected suitable for point type
CN112298607A (en) Modularized satellite platform for realizing high agility maneuvering capability
CN111891386B (en) Three-dimensional modular structure for supporting multiple loads
CN110155313A (en) A kind of more rotor manned aircraft
CN104290918B (en) Miniaturization track towboat satellite configuration and layout design method
CN114435627A (en) Satellite structure and satellite assembly method
Heard Jr et al. Structural sizing considerations for large space platforms
CN115817860A (en) Small satellite platform structure carrying a large amount of propellant and separated by point connection
CN107192522A (en) Major diameter strap-on vehicle Spatial Coupling mode exciting method for arranging
JPH11208596A (en) Satellite structure
CN112298605B (en) Plate-and-bar type satellite main structure
Adler et al. Novel phased array antenna structure design
Dorsey Structural performance of orthogonal tetrahedral truss Space-Station configurations
Safak Structural design and analysis of a solar array substrate for a GEO satellite
Bush et al. Deployable and erectable concepts for large spacecraft

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