Satellite hanging beam design method and satellite hanging beam

Abstract

The present invention relates to a satellite hanging beam design method and a satellite hanging beam, comprising the following steps: step S1, determining the hanging point spacing on the horizontal plane according to the top load avoidance area of ​​the satellite and the minimum safe distance of the satellite body; step S2, determining the position of the mechanical interface for installing the hanging beam on the satellite according to the setting principle of the mechanical interface for installing the hanging beam; step S3, designing the hanging beam; step S4, performing structural mechanics analysis on the hanging beam designed in step S3, establishing a finite element model, calculating the overload imposed by inertial release, analyzing the maximum stress on the satellite structure skin, and confirming that the safety margin meets the requirements. The present invention clarifies the method for designing a hanging beam when a satellite universal sling cannot meet the hoisting requirements, provides a design method and problem-solving ideas for similar hoisting designs, and has good versatility.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite assembly design, and in particular to a satellite suspension beam design method and a satellite suspension beam. Background Art

[0002] Satellites usually need to be hoisted multiple times during the development process according to the requirements of final assembly and test status. Generally, the satellite is installed with lifting lugs on the satellite surface structure and lifted vertically by a universal cross-beam hoist. The advantage of this method is that the design is simple, and the structure is only subjected to vertical tension during the hoisting process, avoiding bending moment on the structure caused by oblique tension.

[0003] Due to the limitation of satellite's star chart equipment and other conditions, some satellites cannot be hoisted with general hoisting equipment, and specially designed hoisting beams are required to transfer the satellite hoisting point to the outside of the satellite's horizontal envelope. At this time, the structure will inevitably introduce bending moment introduced by the hoisting point offset, which places high requirements on the hoisting design, and the general hoisting form is more complicated.

[0004] Therefore, it is particularly important to plan a reasonable and effective satellite crane beam design method that meets the lifting needs. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a satellite lifting beam design method and a satellite lifting beam, sort out the issues that need to be paid attention to in the satellite lifting design process, summarize the design methods, and provide design methods and problem-solving ideas for similar lifting designs.

[0006] To achieve the above-mentioned object of the invention, the present invention provides a satellite suspension beam design method, comprising the following steps:

[0007] Step S1, determining the satellite suspension point spacing on the horizontal plane according to the satellite's top load avoidance area and the satellite's minimum body safety distance;

[0008] Step S2, determining the position of the suspension beam installation mechanical interface on the satellite according to the suspension beam installation mechanical interface setting principle and the satellite suspension point spacing;

[0009] Step S3, designing a hanging beam;

[0010] Step S4, perform structural mechanics analysis on the suspension beam designed in step S3, establish a finite element model, perform calculations on the overload applied by inertial release, analyze the maximum stress on the satellite structure skin, and confirm that the safety margin meets the requirements.

[0011] According to a technical solution of the present invention, the setting principle of the mechanical interface of the hanging beam installation is:

[0012] Under the premise of ensuring that the installation of the hanging beam does not interfere with the final assembly process, the mechanical interface for installing the hanging beam is set on the satellite structure top plate and the satellite structure bottom plate;

[0013] In the case where it is not possible to set the mechanical interface for installing the hanging beam on the top plate and the bottom plate of the satellite structure, the mechanical interface for installing the hanging beam is set on the side plate of the satellite structure;

[0014] When the suspension beam installation mechanical interface is arranged on the satellite structure side panel, the satellite suspension point and the installation surface of the satellite structure side panel are located on the same plane.

[0015] According to a technical solution of the present invention, in step S3, it specifically includes:

[0016] Step S31, determining the safety level and safety factor of the hanging beam according to the structural strength and rigidity of the beam body, and determining the main body form of the hanging beam by considering the dynamic load coefficient of the crane;

[0017] Step S32, estimating the weight of the suspension beam, confirming the center of gravity position of the satellite and the suspension beam after installation, performing overturning calculation, and determining the position of the satellite suspension point in the height direction;

[0018] Step S33, designing a satellite connection mechanical interface on the suspension beam;

[0019] Step S34, designing the number and positions of the observation holes on the suspension beam;

[0020] Step S35, designing the position of the protective tooling on the hanging beam;

[0021] Step S36, setting the suspension point of the suspension beam according to the weight of the suspension beam and the centroid of the suspension beam;

[0022] Step S37: design the support beam structure.

[0023] According to one aspect of the present invention, a satellite suspension beam is provided, which is implemented based on the above suspension beam design method, and includes:

[0024] Two suspension beam bodies arranged in parallel are fixedly connected to the satellite structure side panels; the length of the suspension beam bodies is greater than the length of the satellite structure side panels;

[0025] Lifting ears are arranged and fixedly disposed at both ends of the lifting beam body; satellite lifting points and lifting beam lifting points are arranged on the lifting ears;

[0026] Two connecting beams are arranged between the two hanging beam bodies, and two ends of the connecting beams are respectively connected to the hanging beam bodies.

[0027] According to a technical solution of the present invention, the distance between the lifting ear and the satellite body and the distance between the connecting beam and the satellite body are both greater than the safety distance.

[0028] According to a technical solution of the present invention, a protective tooling is provided between the suspension beam body and the satellite structure side panel, and the protective tooling is a satellite protection block.

[0029] According to a technical solution of the present invention, the suspension beam body comprises:

[0030] The C-shaped beam comprises a parallel upper beam plate and a lower beam plate and a side beam plate arranged between the upper beam plate and the lower beam plate, wherein the side beam plate is provided with a satellite connection mechanical interface for fixedly connecting with the satellite structure side plate;

[0031] A plurality of supporting ribs are arranged between the upper beam plate and the lower beam plate, distributed along the length direction of the side beam plate, and are welded and fixed to the upper beam plate, the lower beam plate and the side beam plate.

[0032] According to a technical solution of the present invention, the satellite connection mechanical interface comprises:

[0033] The first interface, the second interface and the third interface are arranged in parallel, the first interface, the second interface and the third interface are respectively arranged in the horizontal direction, and the straight lines where the first interface, the second interface and the third interface are located are parallel, the number of the first interfaces is the same as the number of the second interfaces, the number of the third interfaces is less than the number of the first interfaces, and the third interface is provided with a notch at the corner of the second interface where the mechanical interface of the suspension beam is installed.

[0034] According to a technical solution of the present invention, the satellite hanging point is arranged at the upper end of the hanging ear, and the height of the satellite hanging point is lower than the height of the center of mass position of the combination of the satellite and the hanging beam.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] The present invention proposes a satellite hanging beam design method and a satellite hanging beam. The satellite hanging beam design method clarifies the method of hanging beam design when the satellite general hanging device cannot meet the lifting requirements, and provides a design method and problem-solving ideas for similar lifting designs. The satellite hanging beam can be used as a reference for the subsequent satellite hanging beam design and has good versatility. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0038] Figure 1 Schematically showing a flow chart of a satellite suspension beam design method provided in an embodiment of the present invention;

[0039] Figure 2 A schematic plan view schematically showing the positional relationship between a satellite payload envelope and a satellite suspension point according to an embodiment of the present invention;

[0040] Figure 3 A schematic diagram of the structure of the suspension beam body according to an embodiment of the present invention is shown;

[0041] Figure 4 A schematic diagram schematically shows the positional relationship between the satellite centroid and the satellite hanging point according to an embodiment of the present invention;

[0042] Figure 5 Schematically showing a structural diagram of a mechanical interface for installing a hanging beam according to an embodiment of the present invention;

[0043] Figure 6 A schematic diagram schematically shows the positional relationship between the suspension beam and the satellite structure side plate according to an embodiment of the present invention;

[0044] Figure 7 Schematically showing a schematic diagram of the structure of a satellite suspension beam according to an embodiment of the present invention;

[0045] Figure 8 Schematically showing the structure of the suspension beam body and the suspension ears according to an embodiment of the present invention;

[0046] Fig. 9 A schematic diagram of the structure of the observation hole on the hanging beam according to an embodiment of the present invention is schematically shown;

[0047] Fig.10 A schematic diagram of a finite element model of a satellite suspension beam according to an embodiment of the present invention is schematically shown;

[0048] Fig.11 A schematic diagram schematically shows the stress distribution results of the static analysis of the satellite suspension beam according to an embodiment of the present invention;

[0049] Fig.12 A schematic diagram schematically shows a stress distribution result of a static analysis at a mechanical interface of a satellite connection according to an embodiment of the present invention;

[0050] Fig.13The figure schematically shows the stress distribution result of the mechanical analysis of the satellite suspension beam structure according to the embodiment of the present invention.

[0051] The corresponding relationship between the component names and the reference numerals is as follows:

[0052] 1. Hanging beam; 2. Satellite body;

[0053] 11. Lifting beam body; 12. Lifting lugs; 13. Connecting beam; 14. Protective tooling;

[0054] 111. Satellite connection mechanical interface; 112. Support ribs; 113. Observation hole;

[0055] 121. Satellite hanging point; 122. Beam hanging point;

[0056] 21. Satellite structure side panel; 22. Satellite structure top load; 23. Center of mass of satellite and suspension beam assembly; 24. Suspension beam installation mechanical interface. DETAILED DESCRIPTION

[0057] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0058] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0059] like Figure 1 As shown, a satellite suspension beam design method of the present invention comprises the following steps:

[0060] Step S1, determining the satellite suspension point spacing on the horizontal plane according to the satellite's top load avoidance area and the satellite's minimum body safety distance;

[0061] The spacing of the satellite hanging points 121 on the horizontal plane is determined by taking into account avoiding the top load and the minimum safe distance from the satellite body. To avoid additional bending moments introduced by the offset, the satellite hanging points 121 should be as close to the center of mass as possible and as symmetrical as possible relative to the center of mass.

[0062] Step S2, determining the position of the suspension beam installation mechanical interface on the satellite according to the suspension beam installation mechanical interface setting principle and the satellite suspension point spacing;

[0063] The principles for setting the mechanical interface of the hanging beam installation are as follows:

[0064] Under the premise of ensuring that the installation of the hanging beam 1 does not interfere during the general assembly process, the hanging beam installation mechanical interface is set on the satellite structure top plate and the satellite structure bottom plate to ensure that the structure is not subject to lateral bending moment during the vertical lifting process, has better load-bearing, and has the advantage of easy structural design;

[0065] In the case where it is not possible to set the mechanical interface for installing the hanging beam 1 on the satellite structure top plate and the satellite structure bottom plate, it is selected to set the mechanical interface for installing the hanging beam on the satellite structure side plate 21;

[0066] When the mechanical interface for mounting the hanging beam is arranged on the satellite structure side panel 21, the satellite hanging point 121 and the mounting surface of the satellite structure side panel 21 are located on the same plane, thereby preventing the structure from being subjected to additional lateral bending moment.

[0067] Step S3, designing the hanging beam 1;

[0068] Step S4, perform structural mechanics analysis on the suspension beam 1 designed in step S3, establish a finite element model, perform calculations on the overload applied by inertial release, analyze the maximum stress on the satellite structure skin, and confirm that the safety margin meets the requirements.

[0069] In step S3, it specifically includes:

[0070] Step S31, determining the safety level and safety factor of the hanging beam 1 according to the structural strength and rigidity of the beam body, and determining the form of the hanging beam body 11 by considering the dynamic load coefficient of the crane;

[0071] Step S32, estimating the weight of the suspension beam 1, confirming the center of gravity position of the satellite and the suspension beam 1 after installation, performing overturning calculation, and determining the position of the satellite suspension point 121 in the height direction;

[0072] Step S33, designing the satellite connection mechanical interface 111 on the suspension beam 1;

[0073] In the design process of the satellite connection mechanical interface 111, the stress concentration and strength failure risk problems that may exist during the satellite structure processing should be considered, so as to increase the number of connection screws as much as possible.

[0074] Step S34, designing the number and positions of the observation holes 113 on the suspension beam 1;

[0075] During the installation of the hanging beam 1, due to the need to avoid the star chart equipment, there may be a problem of blind spots during the installation process. In this case, it is necessary to add an observation hole 113, such as Fig. 9 As shown, component a in the figure represents a mounting nut on the star chart device that is blocked by the suspension beam 1. The mounting nut can be observed through the observation hole 113 provided on the suspension beam 1 to avoid affecting the star chart device during the installation of the suspension beam.

[0076] Step S35, designing the position of the protective tooling 14 on the hanging beam 1;

[0077] During the installation process of connecting the suspension beam 1 to the satellite structure, considering the risk of collision with the structure, it is necessary to add protective tooling 14 at the contact position.

[0078] Step S36, setting the suspension point of the suspension beam according to the weight of the suspension beam and the centroid of the suspension beam;

[0079] The weight of the hanging beam 1 itself is heavy. When it needs to be lifted, the lifting point position of the hanging beam 1 itself needs to consider the center of mass of the hanging beam to avoid docking with the satellite structure when the hanging beam itself is tilted.

[0080] Step S37: design the support beam structure.

[0081] The structural stability of the lifting beam 1 during the lifting process needs to be considered, and measures such as adding support beams should be taken when necessary.

[0082] The present invention is further described in detail below with reference to the accompanying drawings and specific examples:

[0083] like Figure 2 As shown, the top load 22 of the satellite structure of a certain satellite is relatively large. Considering the limitation of the carrying envelope, the main structure of the satellite cannot protrude the load envelope in the horizontal direction, and the bottom of the satellite cannot be installed with a hanging beam due to the limitation of assembly. Therefore, the side panel 21 of the satellite structure is selected to install the hanging beam 1 for lifting. At this time, considering the minimum safe distance of 100mm from the satellite body 2 during the lifting process, and to avoid the additional bending moment introduced by the asymmetry of the lifting point compared to the center of mass position, the length of the hanging beam 1 is designed to be 3300.4mm.

[0084] Considering the processing convenience and reliability, the channel steel and the supporting rib welding are selected as the main structure of the hanging beam body 11 while meeting the strength and rigidity of the beam structure. Figure 3 shown.

[0085] The hanging beam 1 is made of steel, and the weight of a single hanging beam is about 370kg. Considering that the height of the center of mass 23 of the satellite and the hanging beam combination is about 1300mm, in order to prevent the satellite from tipping over during the lifting process, the height of the hanging point is designed to be 1130mm. Figure 4 shown.

[0086] Considering the satellite lifting weight and structural safety, the designed mechanical interface 24 for the lifting beam installation is as follows: Figure 5 As shown, it is connected by 22 M10 screws.

[0087] In order to avoid interference with the satellite equipment, the safety distance between the suspension beam body 11 and the satellite body 2 is 50 mm. In order to prevent the structure from being subjected to additional lateral bending moment, the satellite suspension point 121 on the suspension beam 1 is on the same plane as the installation surface of the satellite structure side plate 21, and a protective tooling 14 (i.e., a satellite protection block) is added to avoid the risk of collision with the satellite during the installation of the suspension beam. Figure 6 shown.

[0088] Since the lifting is completed by two hanging beams 1, considering the structural stability requirements, the hanging beam 1 is increased in its own torsion resistance, and two connecting beams 13 are added, such as Figure 7 shown.

[0089] Due to the requirement that the main body of the hanging beam 11 is far away from the satellite body 2, the center of mass of the hanging beam 1 is offset from the hanging point position, and the hanging beam 1 needs to be lifted during the installation process, so the hanging beam hanging point 122 is added, such as Figure 8 shown.

[0090] The finite element model of the suspension beam 1 is created using tetrahedral solid mesh elements, and the structural material is steel. The suspension beam body 11 and the connecting beam 13, and the suspension beam body 11 and the satellite body 2 are connected using MPC elements. Fig. 9 shown.

[0091] In the static analysis of the hanging beam, the four hanging points are subjected to a vertical upward load of 1 t, and the connection point between the hanging beam and the satellite structure is constrained by displacement. The stress distribution results of the hanging beam are as follows: Fig.10 shown.

[0092] According to the mechanical analysis results, the maximum stress of the suspension beam 1 is 68.1Mpa, which is located near the structural connection screws with the satellite body 2. According to the yield limit of carbon steel material is not less than 200Mpa, the design safety margin of the suspension beam is 1.93, and the strength meets the requirements.

[0093] According to the finite element model of the hoist, the calculation is carried out by applying an overload of 2.6g through inertial release. The maximum stress of the satellite hoist is 106MPa, the safety margin is 3.8, and the strength meets the requirements. The analysis results are as follows Fig.11 and Fig.12 shown.

[0094] Through the above steps, the satellite hoisting design was carried out, and the strength of the hoisting beam was analyzed to meet the hoisting requirements of the satellite during the assembly process. The satellite hoisting beam realized based on the above hoisting beam design method includes:

[0095] Two parallel suspension beam bodies 11 are fixedly connected to the satellite structure side panels 21; the length of the suspension beam body 11 is greater than the length of the satellite structure side panels 21;

[0096] The lifting ears 12 are fixedly arranged at both ends of the suspension beam body 11; the satellite suspension points 121 and the suspension beam 1 suspension points are arranged on the lifting ears 12; the distance between the lifting ears 12 and the satellite body 2 and the distance between the connecting beam 13 and the satellite body 2 are both greater than the safety distance.

[0097] Two connecting beams 13 are arranged between the two suspension beam bodies 11 , and two ends thereof are connected to the suspension beam bodies 11 respectively.

[0098] A protective tooling 14 is provided between the suspension beam body 11 and the satellite structure side plate 21 , and the protective tooling 14 is a satellite protection block.

[0099] The hanging beam body 11 comprises:

[0100] The C-shaped beam comprises a parallel upper beam plate and a lower beam plate and a side beam plate arranged between the upper beam plate and the lower beam plate, and the side beam plate is provided with a satellite connection mechanical interface 111 for fixedly connecting with the satellite structure side plate 21;

[0101] A plurality of support ribs 112 are disposed between the upper beam plate and the lower beam plate, distributed along the length direction of the side beam plate, and are welded and fixed to the upper beam plate, the lower beam plate and the side beam plate.

[0102] The satellite connection mechanical interface 111 includes:

[0103] The first interface, the second interface and the third interface are arranged in parallel, and the first interface, the second interface and the third interface are respectively arranged in the horizontal direction, and the straight lines where the first interface, the second interface and the third interface are located are parallel. The number of the first interfaces is the same as the number of the second interfaces, and the number of the third interfaces is less than the number of the first interfaces. The third interface has a notch at the corner of the second interface where the mechanical interface for installing the suspension beam is arranged.

[0104] The satellite hanging point 121 is arranged at the upper end of the hanging ear 12 , and the height of the satellite hanging point 121 is lower than the height of the center of mass of the combination of the satellite and the hanging beam 1 .

[0105] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A satellite suspension beam design method, characterized in that: The following steps are involved: Step S1, determining the satellite suspension point spacing on the horizontal plane according to the satellite's top load avoidance area and the satellite's minimum body safety distance; Step S2, determining the position of the suspension beam installation mechanical interface on the satellite according to the suspension beam installation mechanical interface setting principle and the satellite suspension point spacing; Step S3, designing a hanging beam; Step S4, perform structural mechanics analysis on the suspension beam designed in step S3, establish a finite element model, perform calculations on the overload applied by inertial release, analyze the maximum stress on the satellite structure skin, and confirm that the safety margin meets the requirements.

2. The design method according to claim 1, characterized in that: The setting principle of the mechanical interface of the hanging beam installation is: Under the premise of ensuring that the installation of the hanging beam does not interfere with the final assembly process, the mechanical interface for installing the hanging beam is set on the satellite structure top plate and the satellite structure bottom plate; In the case where it is not possible to set the mechanical interface for installing the hanging beam on the top plate and the bottom plate of the satellite structure, the mechanical interface for installing the hanging beam is set on the side plate of the satellite structure; When the suspension beam installation mechanical interface is arranged on the satellite structure side panel, the satellite suspension point and the installation surface of the satellite structure side panel are located on the same plane.

3. The design method according to claim 2, characterized in that: In the step S3, it specifically includes: Step S31, determining the safety level and safety factor of the hanging beam according to the structural strength and rigidity of the beam body, and determining the main body form of the hanging beam by considering the dynamic load coefficient of the crane; Step S32, estimating the weight of the suspension beam, confirming the center of gravity position of the satellite and the suspension beam after installation, performing overturning calculation, and determining the position of the satellite suspension point in the height direction; Step S33, designing a satellite connection mechanical interface on the suspension beam; Step S34, designing the number and positions of the observation holes on the suspension beam; Step S35, designing the position of the protective tooling on the hanging beam; Step S36, setting the suspension point of the suspension beam according to the weight of the suspension beam and the centroid of the suspension beam; Step S37: design the support beam structure.

4. A satellite suspension beam, characterized in that: The method for designing a suspension beam according to any one of claims 1 to 3 is implemented, comprising: Two suspension beam bodies arranged in parallel are fixedly connected to the satellite structure side panels; the length of the suspension beam bodies is greater than the length of the satellite structure side panels; Lifting ears are arranged and fixedly disposed at both ends of the lifting beam body; satellite lifting points and lifting beam lifting points are arranged on the lifting ears; Two connecting beams are arranged between the two hanging beam bodies, and two ends of the connecting beams are respectively connected to the hanging beam bodies.

5. The satellite suspension beam according to claim 4, characterized in that: The distance between the lifting lug and the satellite body and the distance between the connecting beam and the satellite body are both greater than the safety distance.

6. The satellite suspension beam according to claim 4, characterized in that: A protective tooling is provided between the suspension beam body and the satellite structure side plate, and the protective tooling is a satellite protection block.

7. The satellite suspension beam according to claim 4, characterized in that: The hanging beam body comprises: The C-shaped beam comprises a parallel upper beam plate and a lower beam plate and a side beam plate arranged between the upper beam plate and the lower beam plate, wherein the side beam plate is provided with a satellite connection mechanical interface for fixedly connecting with the satellite structure side plate; A plurality of supporting ribs are arranged between the upper beam plate and the lower beam plate, distributed along the length direction of the side beam plate, and are welded and fixed to the upper beam plate, the lower beam plate and the side beam plate.

8. The satellite suspension beam according to claim 4, characterized in that: The satellite connection mechanical interface comprises: The first interface, the second interface and the third interface are arranged in parallel, the first interface, the second interface and the third interface are respectively arranged in the horizontal direction, and the straight lines where the first interface, the second interface and the third interface are located are parallel, the number of the first interfaces is the same as the number of the second interfaces, the number of the third interfaces is less than the number of the first interfaces, and the third interface is provided with a notch at the corner of the second interface where the mechanical interface of the suspension beam is installed.

9. The satellite suspension beam according to claim 4, characterized in that: The satellite hanging point is arranged at the upper end of the hanging ear, and the height of the satellite hanging point is lower than the height of the center of mass position of the combination of the satellite and the hanging beam.

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