CN111232249A - Support structure suitable for satellite orbital transfer engine - Google Patents
Support structure suitable for satellite orbital transfer engine Download PDFInfo
- Publication number
- CN111232249A CN111232249A CN202010037944.1A CN202010037944A CN111232249A CN 111232249 A CN111232249 A CN 111232249A CN 202010037944 A CN202010037944 A CN 202010037944A CN 111232249 A CN111232249 A CN 111232249A
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- Prior art keywords
- engine
- support
- mounting flange
- orbital transfer
- satellite orbital
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- 238000012546 transfer Methods 0.000 title claims abstract description 26
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 17
- 239000004917 carbon fiber Substances 0.000 claims description 17
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 17
- 239000000463 material Substances 0.000 claims description 15
- 239000002131 composite material Substances 0.000 claims description 10
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 239000004643 cyanate ester Substances 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 7
- 238000004519 manufacturing process Methods 0.000 abstract description 4
- 238000009434 installation Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 238000004804 winding Methods 0.000 description 4
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
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- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
-
- 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
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
Abstract
The invention provides a support structure suitable for a satellite orbital transfer engine, which comprises an engine mounting flange, a support stay bar assembly and a fastener, wherein the support stay bar assembly comprises a joint and a support bar, a stay bar lug is arranged at one end of the support bar, the other end of the support bar is connected with the joint, and the stay bar lug of the support bar is connected with the engine mounting flange through the fastener. The invention has simple structure and simple and convenient operation, realizes light weight design, lightens the structural weight, reduces the production cost, has good heat resistance, moisture resistance, structural rigidity and strength, and can realize the installation of the engine by repairing and matching the flange plate when the position of the engine is changed.
Description
Technical Field
The invention relates to the field of structural design of large satellite platforms, in particular to a support structure suitable for a satellite orbital transfer engine, and particularly relates to a light-weight support structure suitable for a high-orbit satellite orbital transfer engine.
Background
Satellite orbital transfer is mostly dependent on a high thrust engine installed in the satellite. At present, politics, economy, national defense and the like put forward higher and higher requirements on satellites, so that the satellites develop towards high stability, high precision and high resolution, which puts forward higher performance requirements on large satellite engines and also puts forward more rigorous requirements on support structures for engines. Because the high-orbit satellite orbit transfer process needs larger thrust, the mounting bracket needs to be capable of bearing severe high-temperature load and acceleration load when the engine is ignited, and extremely high requirements are provided for the rigidity, the strength, the heat resistance, the mounting precision and the like of the structure. In addition, the titanium alloy material adopted by the current engine bracket has the problem of large weight, and further lightweight design is needed for the structure.
Therefore, aiming at the satellite orbital transfer engine, the problem to be solved urgently is to design an engine support structure with light weight, high rigidity, high strength and high temperature resistance.
Patent document with publication number CN208962860U discloses an engine suspension bracket, which comprises a cylindrical bracket body, and is characterized in that the left side of the bracket body is connected with a first bracket, the right side of the bracket body is connected with a second bracket, the first bracket is provided with a nut, the second bracket is provided with a screw, and a clamping device for clamping the screw is arranged beside the screw. The invention solves the problem that the traditional engine rear suspension bracket in the prior art is easy to generate strong vibration with an engine in the driving process of an automobile, so that the service life of the engine rear suspension bracket is short. The invention has the advantages of convenient installation, high stability, high safety, long service life and the like. However, this device is complicated in structure and cannot be designed to be light in weight.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a support structure suitable for a satellite orbital transfer engine.
The support structure suitable for the satellite orbital transfer engine comprises an engine mounting flange, a support stay bar assembly and a fastener, wherein the support stay bar assembly comprises a joint and a support bar, a stay bar lug is arranged at one end of the support bar, the other end of the support bar is connected with the joint, and the stay bar lug of the support bar is connected with the engine mounting flange through the fastener.
Preferably, an engine mounting interface is arranged on one side of the engine mounting flange, a bracket stay bar assembly mounting interface is arranged on the other side of the engine mounting flange, the engine is mounted on the engine mounting flange through the engine mounting interface, and the bracket stay bar assembly is mounted on the engine mounting flange through the bracket stay bar assembly mounting interface.
Preferably, the bracket strut assembly mounting interface is located closer to the edge on the engine mounting flange than the engine mounting interface is located on the engine mounting flange.
Preferably, an included angle is formed between the support rod lug and the support rod.
Preferably, the brace ear is integrally formed with the brace.
Preferably, the support rods have a circular cross-section.
Preferably, the number of bracing piece is three at least, a plurality of bracing pieces evenly set up along engine mounting flange circumference to have the contained angle in engine mounting flange place plane.
Preferably, the joint comprises a pipe sleeve and a connecting lug which are connected with each other, the pipe sleeve is connected with the supporting rod, and the connecting lug is connected with the satellite.
Preferably, the sleeves of the joint are connected to the support bar by gluing and/or riveting.
Preferably, the material of the lug connection of the support rod and the support rod is M55J carbon fiber/cyanate ester composite material, the material of the engine mounting flange is titanium alloy, and the material of the joint is T700 carbon fiber composite material.
Compared with the prior art, the invention has the following beneficial effects:
1. the engine support is simple and compact in structure, and can realize light weight, high rigidity, high strength and high temperature resistance of the engine support.
2. According to the invention, the ear connection of the support rod and the support rod is made of M55J carbon fiber/cyanate composite material, and the joint is made of T700 carbon fiber composite material, so that the light weight design is realized, the structural weight is reduced, and the production cost is reduced.
3. The invention adopts the preparation method that the support rod and the stay rod lug are integrally formed, and the engine mounting flange is directly connected with the support rod through the screw, thereby enhancing the heat resistance of the structure.
4. The support rod is made of the M55J carbon fiber material, so that the structural rigidity and the strength are improved.
5. According to the invention, a certain mounting space is reserved between the engine mounting interface on the engine mounting flange and the mounting interface of the support strut assembly, and when the position of the engine is changed, the engine can be mounted by repairing and matching the flange plate.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a stent strut assembly of the present invention;
FIG. 3 is a schematic cross-sectional view of a strut according to the present invention;
FIG. 4 is a schematic cross-sectional view of a joint according to the present invention;
fig. 5 is a schematic view of the shape of the engine mounting flange according to the present invention.
The figures show that:
1-engine mounting flange 4-support rod
2- -Stent strut Assembly 5- -fastener
3- -joint
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do 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 invention provides a support structure suitable for a satellite orbital transfer engine, which comprises an engine mounting flange 1 and a support stay bar assembly 2; the bracket brace rod assembly 2 and the engine are respectively arranged on two mounting surfaces in opposite directions of the engine mounting flange 1; the bracket support rod assembly 2 comprises a support rod 4 and a joint 3; the support rod 4 is connected with the engine mounting flange 1 in a threaded connection mode. The invention provides a structural design scheme of a lightweight and high-temperature-resistant engine support, which has the advantages of simple structure, simplicity and convenience in operation, realization of lightweight design, reduction of structural weight, reduction of production cost, and good heat resistance, moisture resistance, structural rigidity and strength.
The support structure suitable for the satellite orbital transfer engine, provided by the invention, comprises an engine mounting flange 1, a support stay bar assembly 2 and a fastener 5, wherein the support stay bar assembly 2 comprises a joint 3 and a support bar 4, one end of the support bar 4 is provided with a stay bar lug, the other end of the support bar 4 is connected with the joint 3, and the stay bar lug of the support bar 4 is connected with the engine mounting flange 1 through the fastener 5. Preferably, the stay bar lug of the stay bar 4 is connected with the engine mounting flange 1 in a threaded manner.
As shown in fig. 1 and 5, an engine mounting interface is arranged on one side of an engine mounting flange 1, a bracket stay bar assembly 2 mounting interface is arranged on the other side of the engine mounting flange 1, the engine is mounted on the engine mounting flange 1 through the engine mounting interface, and the bracket stay bar assembly 2 is mounted on the engine mounting flange 1 through the bracket stay bar assembly 2 mounting interface; the position of the mounting interface of the support brace rod assembly 2 on the engine mounting flange 1 is close to the edge compared with the position of the mounting interface of the engine on the engine mounting flange 1, a certain adjusting space is reserved on the engine mounting flange 1, when the position of the engine changes, the engine can be mounted by repairing a flange plate, namely, a larger space is reserved between the mounting interface provided for the engine in the engine mounting flange 1 and the mounting interface of the support assembly 2, and coordinated mounting is facilitated.
As shown in fig. 1 to 3, an included angle is formed between the support rod lug and the support rod 4; the support rod lug is integrally formed with the support rod 4, and preferably, the support rod lug part and the support rod main body part are processed by a winding and integral forming process; the section of the support rod 4 is an annular section; the quantity of bracing piece 4 is three at least, a plurality of bracing pieces 4 evenly set up along 1 circumference of engine mounting flange to have the contained angle in 1 plane in the engine mounting flange. Preferably, the number of the support brace component 2 is at least three, so as to ensure the connection rigidity of the support and the star body, the position precision of the flange and the stability under the action of load.
As shown in fig. 2 and 4, the joint 3 comprises a pipe sleeve and a connecting lug which are connected with each other, the pipe sleeve is connected with a support rod 4, and the connecting lug is connected with a satellite; the pipe sleeves of the joints 3 are connected with the support rods 4 by gluing and/or riveting. Preferably, the support rod 4 is connected with the joint 3 through high-strength glue and rivets.
The material that bracing piece 4 and bracing piece ear connect is M55J carbon fiber/cyanate composite to lighten structure weight, improve rigidity, the material of engine mounting flange 1 is the titanium alloy, the material that connects 3 is T700 carbon fiber composite.
The invention provides an engine mounting bracket structure with high rigidity, high strength, high temperature resistance and light weight, which adopts a carbon fiber support rod to provide mounting precision and support rigidity and reduce the whole weight. The traditional engine support is prepared from high-temperature-resistant carbon fiber composite materials or titanium alloys, the common carbon fiber materials are used in the engine support, tests and calculations show that the engine support can completely meet the use requirements, the structural weight is reduced, and the production cost is reduced. The two ends of the supporting rod of the traditional engine support are connected with the joints through glue joint, the joints are connected with the flanges through screws, and the glue joint part has poor high-temperature resistance, so that the whole heat resistance is limited. The carbon fiber support rod is manufactured by adopting a method of integrally forming the carbon fiber support rod main body and the lug connection winding, and the engine mounting flange is directly connected with the support rod through the screw, so that the use of adhesive joint is reduced, and the heat resistance of the structure is enhanced. In the traditional engine support, when the position of an engine changes, a flange or a support rod needs to be prepared again, so that more labor hour and cost are consumed. The engine support rod adopts the M55J carbon fiber material, and the matrix material is cyanate ester, so that the engine support rod has good moisture resistance, and has higher structural rigidity and strength. The high-power orbital transfer engine capable of bearing the satellite can bear higher temperature load and acceleration load, can provide better supporting rigidity and mounting precision, and is suitable for the supporting requirement of a large-scale satellite orbital transfer engine.
Example 1:
as shown in fig. 1, in this embodiment, four support strut assemblies 2 are taken, the total thickness of the engine mounting flange 1 is 4mm, the shape is 295.48mm × 295.48mm square, the corners of the engine mounting flange are chamfered R85, the material is TC4 titanium alloy, and a Φ 6.5 through hole is reserved on the circumference of a Φ 162 central portion of the engine mounting flange 1 as an engine mounting interface. As shown in fig. 2 and 3, the diameter of the main body part of the support rod 4 is phi 40, the thickness of the main body part is 2mm, the thickness of the ear-connection part of the support rod is 2mm, a phi 6.5 through hole is reserved on the main body part to serve as a connection interface with an engine mounting flange 1, the two parts of the support rod assembly 2 of the bracket are processed and prepared by a winding and integral forming process, and an M55J carbon fiber material (a matrix material is cyanate) is adopted; as shown in figure 4, the wall thickness of the upper joint is 2mm, pin holes are reserved on the pipe sleeve part for positioning, phi 6.5 through holes are reserved on the connecting lugs for connecting with a star body, the material is T700 carbon fiber composite material, and a winding forming processing technology is adopted. The support structure is tested under common working conditions, such as normal temperature, high temperature static force, modal, frequency response, impact and the like, and test results prove that the support structure can adapt to various working conditions faced by a satellite, meets requirements and is reliable in quality. The invention provides a better satellite orbital transfer engine bearing scheme, which improves the performance index of the whole satellite to a certain extent.
In conclusion, the invention provides a novel support structure suitable for a satellite orbital transfer engine, which has the advantages of light weight, high rigidity, high strength, high temperature resistance and the like, can meet the requirement of the current satellite development, and has wide application prospect.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The support structure suitable for the satellite orbital transfer engine is characterized by comprising an engine mounting flange (1), a support stay bar assembly (2) and a fastener (5), wherein the support stay bar assembly (2) comprises a joint (3) and a support bar (4), a stay bar lug is arranged at one end of the support bar (4), the other end of the support bar (4) is connected with the joint (3), and the stay bar lug of the support bar (4) is connected with the engine mounting flange (1) through the fastener (5).
2. The support structure suitable for the satellite orbital transfer engine is characterized in that an engine mounting interface is arranged on one side of the engine mounting flange (1), a support stay rod assembly (2) mounting interface is arranged on the other side of the engine mounting flange (1), the engine is mounted on the engine mounting flange (1) through the engine mounting interface, and the support stay rod assembly (2) is mounted on the engine mounting flange (1) through the support stay rod assembly (2) mounting interface.
3. The bracket structure suitable for the satellite orbital transfer engine according to claim 2, wherein the position of the mounting interface of the bracket stay assembly (2) on the engine mounting flange (1) is close to the edge compared with the position of the mounting interface of the engine on the engine mounting flange (1).
4. The mounting structure for a satellite orbital transfer engine according to claim 1, characterized in that said brace lug has an angle with said brace bar (4).
5. The mounting structure for a satellite orbital transfer engine according to claim 1, characterized in that said brace lug is integral with said brace (4).
6. The support structure suitable for a satellite orbital transfer engine according to claim 1, characterized in that the section of the supporting rod (4) is a circular section.
7. The support structure suitable for the satellite orbital transfer engine is characterized in that the number of the support rods (4) is at least three, the support rods (4) are uniformly arranged along the circumferential direction of the engine mounting flange (1), and included angles are formed in the plane of the engine mounting flange (1).
8. The mounting structure for a satellite orbital transfer engine according to claim 1, characterized in that said joint (3) comprises a socket and an ear connected to each other, said socket connecting the support bar (4), said ear connecting the satellite.
9. Support structure suitable for a satellite orbital transfer engine according to claim 1, characterized in that the sleeves of said joints (3) are connected to the supporting rods (4) by gluing and/or riveting.
10. The bracket structure suitable for the satellite orbital transfer engine according to claim 1, wherein the material of the support rod (4) and the support rod lug is M55J carbon fiber/cyanate ester composite material, the material of the engine mounting flange (1) is titanium alloy, and the material of the joint (3) is T700 carbon fiber composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010037944.1A CN111232249A (en) | 2020-01-14 | 2020-01-14 | Support structure suitable for satellite orbital transfer engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010037944.1A CN111232249A (en) | 2020-01-14 | 2020-01-14 | Support structure suitable for satellite orbital transfer engine |
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| Publication Number | Publication Date |
|---|---|
| CN111232249A true CN111232249A (en) | 2020-06-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010037944.1A Pending CN111232249A (en) | 2020-01-14 | 2020-01-14 | Support structure suitable for satellite orbital transfer engine |
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| Country | Link |
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| CN (1) | CN111232249A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476145A (en) * | 2022-01-18 | 2022-05-13 | 大连理工大学 | Satellite isolation/vibration reduction support made of short carbon fiber reinforced thermoplastic composite material |
-
2020
- 2020-01-14 CN CN202010037944.1A patent/CN111232249A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114476145A (en) * | 2022-01-18 | 2022-05-13 | 大连理工大学 | Satellite isolation/vibration reduction support made of short carbon fiber reinforced thermoplastic composite material |
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Application publication date: 20200605 |
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