CN114812292B - Offset side-hanging rocket adapter structure - Google Patents
Offset side-hanging rocket adapter structure Download PDFInfo
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- CN114812292B CN114812292B CN202210574964.1A CN202210574964A CN114812292B CN 114812292 B CN114812292 B CN 114812292B CN 202210574964 A CN202210574964 A CN 202210574964A CN 114812292 B CN114812292 B CN 114812292B
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- bearing
- rocket
- bottom plate
- piece
- supporting rod
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 229910001234 light alloy Inorganic materials 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention relates to the field of aerospace, and discloses a biased side-hung rocket adapter structure, which comprises: the bearing piece is eccentrically arranged relative to the central shaft of the fairing of the rocket; the bearing bottom plate is arranged at one end of the bearing piece; the support connecting piece is used for connecting the bearing piece and the bearing bottom plate; the bearing piece, the bearing bottom plate, the supporting connecting piece and the fairing of the rocket surround to form an envelope space for arranging the effective load of the rocket, and a central shaft of the fairing of the rocket penetrates through the envelope space. By eccentrically arranging the bearing piece, the effective envelope space in the rocket can be enlarged under the condition of not changing the size of the fairing, and the loading of a payload with a single size and a larger size is facilitated. Through the effect of support connecting piece, can improve the intensity of adapter structure, avoid the force load that the bearing member received to surpass the allowed range, can realize the connection of rocket adapter structure and rocket final stage other sections through the load-bearing bottom plate.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a biased side-hung rocket adapter structure.
Background
Rocket adapter structures currently used in the rocket field can be divided into a base-type structure and a side-hanging-type structure according to different installation modes of payloads on rocket adapters. Wherein the base rocket adapter is coupled to and decoupled from the payload in the direction of rocket flight, and the side-mounted rocket adapter is coupled to and decoupled from the payload in a lateral direction.
At present, the structure of the side-hung rocket adapter is mainly a symmetrical structure, and payloads are distributed around the adapter and laterally connected with the adapter. When the space of the carrier rocket is smaller, the loading requirement of the payload cannot be met by adopting the symmetrical side-hanging rocket adapter. Therefore, an offset side-hung rocket adapter structure is urgently needed, and the problem that a carrier rocket with a smaller load space cannot carry a payload with a larger size is solved.
Disclosure of Invention
The invention provides a biased side-hung rocket adapter structure to solve the technical problems.
The offset side-hung rocket adapter structure of the present invention comprises:
The bearing piece is eccentrically arranged relative to the central shaft of the fairing of the rocket;
the bearing bottom plate is arranged at one end of the bearing piece; and
The support connecting piece is used for connecting the bearing piece and the bearing bottom plate;
The bearing piece, the bearing bottom plate, the supporting connecting piece and the fairing of the rocket surround to form an envelope space for arranging the effective load of the rocket, and a central shaft of the fairing of the rocket penetrates through the envelope space.
Further, the bearing piece comprises a bearing cylinder, and the inside of the bearing cylinder is of a hollow structure.
The beneficial effects of the above-mentioned further scheme are: the bearing piece is arranged to be of a hollow structure, so that the cable net is convenient to install and fix.
Further, the bearing piece further comprises a connecting portion, the connecting portion is arranged at the side end of the bearing barrel, and the connecting portion is located in the enveloping space and used for being connected with the effective load.
Further, the support connecting piece comprises support rod systems arranged on two sides of the bearing piece; one end of each supporting rod system is connected with the bearing piece, and the other end of each supporting rod system is connected with the bearing bottom plate.
Further, the center of the bearing bottom plate coincides with the center axis of the fairing, three connection points are arranged on the surface of the bearing bottom plate, connecting lines of the three connection points form isosceles or equilateral triangles, vertical lines of the triangles pass through the center of the bearing bottom plate, and the three connection points are in one-to-one correspondence with one end of the bearing piece and one end of the supporting rod system arranged on two sides of the bearing piece.
The beneficial effects of the above-mentioned further scheme are: through evenly and symmetrically arranging the supporting rod systems, the concentrated force born by the bearing piece and the supporting connecting piece can be evenly dispersed to each connecting point of the rocket final stage connected with the bearing bottom plate.
Further, each supporting rod system comprises a first supporting rod, a second supporting rod and a connecting rod; the first end of the first supporting rod is connected with the bearing piece, and the second end of the first supporting rod is connected with the bearing bottom plate; the first end of the second supporting rod is connected with the bearing piece, and the second end of the second supporting rod is connected with the bearing bottom plate; the connecting rod is connected with the first supporting rod and the second supporting rod.
Further, the first ends of the first support rod and the second support rod are respectively connected with the same position or different positions of the bearing piece; the second ends of the first support rod and the second support rod are respectively connected with the same position or different positions of the bearing bottom plate.
Further, the support connecting piece comprises a rod piece and connectors arranged at two ends of the rod piece, and the rod piece and the connectors are made of high-modulus carbon fiber or light alloy materials.
Further, the length direction of the bearing piece is parallel to the central axis of the fairing of the rocket.
Further, the length direction of the bearing piece is perpendicular to the plate surface of the bearing bottom plate.
The technical scheme provided by the invention has the beneficial effects that: by eccentrically arranging the bearing piece, the effective envelope space in the rocket can be enlarged under the condition of not changing the size of the fairing, and the loading of a payload with a single size and a larger size is facilitated. The strength of the adapter structure can be improved through the action of the supporting connecting piece, the force load borne by the bearing piece is prevented from exceeding the allowable range, and the connection between the rocket adapter structure and other sections of the rocket final stage can be realized through the bearing bottom plate; in addition, the rocket adapter has the advantages of simple integral structure, easy installation and low cost.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic illustration of the structure of an offset side-hung rocket adapter of the present invention.
Fig. 2 is a schematic top view of fig. 1.
In the figure: 1-a force bearing cylinder; a 2-connection; 3-a load floor; 4-support connectors; 41-a first support bar; 42-a second support bar; 43-connecting rod; 5-payload; 6-envelope space.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to the offset side-hung rocket adapter structure shown in FIGS. 1 and 2, comprising: a load bearing member, a load bearing bottom plate 3 and a support connecting member 4.
The bearing piece comprises a bearing cylinder 1, and the inside of the bearing cylinder 1 is of a hollow structure. The cross section of the force-bearing cylinder 1 is not limited to a circle, but may be a square. The hollow bearing cylinder 1 is convenient for wiring and mounting the cable network.
The bearing piece is eccentrically arranged relative to the central shaft of the fairing of the rocket, wherein the fairing of the rocket is a cylindrical structure formed by splicing a plurality of arc plates along the circumferential direction of the rocket, and the central shaft of the cylindrical structure is the central shaft of the fairing of the rocket.
In this embodiment, the length direction of the bearing cylinder 1 of the bearing member is parallel to the central axis of the fairing of the rocket. As shown in fig. 2, the central axis of the bearing cylinder 1 of the bearing member is in the same horizontal plane as the central axis of the fairing, and the horizontal plane passes through the central axis of the fairing. The distance between the central axis of the bearing cylinder 1 of the bearing piece and the central axis of the fairing is the eccentric distance of the bearing piece.
The load-bearing bottom plate 3 is arranged at one end of the load-bearing member. The length direction of the bearing piece is perpendicular to the plate surface of the bearing bottom plate 3. In this embodiment, as shown in fig. 2, the surface of the load-bearing bottom plate 3 is circular, and the center of the load-bearing bottom plate 3 coincides with the center axis of the fairing. The bearing piece is eccentrically arranged relative to the central shaft of the fairing of the rocket, and the bearing cylinder 1 of the bearing piece can also be regarded as being eccentrically arranged relative to the center of the bearing bottom plate 3.
The support connection 4 connects the load bearing member with the load bearing base plate 3.
The bearing piece, the bearing bottom plate 3, the supporting connection piece 4 and the fairing of the rocket surround to form an envelope space 6 for arranging a payload 5 of the rocket, and a central shaft of the fairing of the rocket passes through the envelope space 6. As shown in fig. 2, the cross section of the envelope space 6 of the present embodiment is a sector area having a radius larger than that of the cylindrical structure of the fairing of the rocket. The eccentrically positioned bearings form a larger envelope space 6 than in the conventional manner of positioning the bearings in the centre of the rocket, so that a larger payload 5 can be accommodated without having to change the size of the fairing.
The bearing piece further comprises a connecting part 2, the connecting part 2 is arranged at the side end of the bearing barrel 1, and the connecting part 2 is positioned in the enveloping space 6 and is used for being connected with the effective load 5. Referring to fig. 1, a plurality of connection portions 2 are arranged at intervals along the length direction of the bearing barrel 1 of the bearing member, so as to improve the connection effect with the payload 5.
The supporting connecting piece 4 in the embodiment comprises supporting rod systems arranged at two sides of the bearing piece; one end of each supporting rod system is connected with the bearing piece, and the other end of each supporting rod system is connected with the bearing bottom plate 3.
As shown in fig. 2, the surface of the bearing bottom plate 3 is provided with three connection points, the connection lines of the three connection points form an isosceles or equilateral triangle, the perpendicular lines of the triangle pass through the center of the bearing bottom plate 3, and the three connection points are connected with one end of the bearing barrel 1 of the bearing member and one end of the support rod systems arranged on two sides of the bearing member in a one-to-one correspondence manner. Because the bearing bottom plate 3 is used for realizing connection of the rocket adapter structure and other sections of the rocket final stage, three connecting points uniformly arranged on the bearing bottom plate 3 can uniformly disperse the force born by the bearing cylinder 1 and the supporting rod system to the rocket final stage through the bearing bottom plate 3.
Each of the support bars includes a first support bar 41, a second support bar 42, and a connecting bar 43; the first end of the first supporting rod 41 is connected with the bearing piece, and the second end is connected with the bearing bottom plate 3; the first end of the second supporting rod 42 is connected with the bearing piece, and the second end is connected with the bearing bottom plate 3; the connection rod 43 connects the first support rod 41 and the second support rod 42.
The first ends of the first support bar 41 and the second support bar 42 are respectively connected with the same position or different positions of the bearing piece; the second ends of the first support bar 41 and the second support bar 42 are respectively connected with the same position or different positions of the load-bearing bottom plate 3.
In this embodiment, as shown in fig. 1, the first ends of the first support rod 41 and the second support rod 42 of each support rod system are respectively connected to two different positions of the bearing cylinder 1 of the bearing member, and the two different positions are distributed at intervals along the length direction of the bearing cylinder 1. The second ends of the first support bar 41 and the second support bar 42 of each of the support bar systems are connected to the same location of the load floor 3. As shown in fig. 2, the two support rods are symmetrically arranged with the horizontal plane passing through the central axis of the bearing cylinder 1 as a mirror plane.
In this embodiment, the support connection member 4 includes a rod member and connectors disposed at two ends of the rod member, and the rod member and the connectors are made of high-modulus carbon fiber or light alloy material. Of course, other lightweight materials may be used to effectively reduce the weight of the rocket adapter structure.
By eccentrically arranging the bearing member, the effective envelope space 6 inside the rocket can be enlarged without changing the size of the fairing, and the loading of a payload 5 with a single size and a larger size is facilitated. The strength of the adapter structure can be improved through the action of the supporting connecting piece 4, the force load born by the bearing piece is prevented from exceeding the allowable range, and the connection between the rocket adapter structure and other sections of the rocket final stage can be realized through the bearing bottom plate 3; in addition, the rocket adapter has the advantages of simple integral structure, easy installation and low cost.
In the description of the present invention, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present invention. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
It should be noted that in the present invention, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The foregoing is only a specific embodiment of the invention to enable those skilled in the art to understand or practice the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (6)
1. An offset side-hung rocket adapter structure, comprising:
The bearing piece is eccentrically arranged relative to the central shaft of the fairing of the rocket;
the bearing bottom plate is arranged at one end of the bearing piece; and
The support connecting piece is used for connecting the bearing piece and the bearing bottom plate;
the bearing piece, the bearing bottom plate, the supporting connecting piece and the fairing of the rocket surround to form an envelope space for arranging the effective load of the rocket, and a central shaft of the fairing of the rocket penetrates through the envelope space;
The support connecting piece comprises support rod systems arranged on two sides of the bearing piece; one end of each supporting rod system is connected with the bearing piece, and the other end of each supporting rod system is connected with the bearing bottom plate;
Each supporting rod system comprises a first supporting rod, a second supporting rod and a connecting rod; the first end of the first supporting rod is connected with the bearing piece, and the second end of the first supporting rod is connected with the bearing bottom plate; the first end of the second supporting rod is connected with the bearing piece, and the second end of the second supporting rod is connected with the bearing bottom plate; the connecting rod is connected with the first supporting rod and the second supporting rod;
the first ends of the first support rod and the second support rod are respectively connected with the same position or different positions of the bearing piece; the second ends of the first support rod and the second support rod are respectively connected with the same position or different positions of the bearing bottom plate;
The center of the bearing bottom plate coincides with the center axis of the fairing, three connection points are arranged on the surface of the bearing bottom plate, connecting lines of the three connection points form isosceles or equilateral triangles, vertical lines of the triangles pass through the center of the bearing bottom plate, and the three connection points are in one-to-one correspondence with one end of the bearing piece and one end of the supporting rod system arranged on two sides of the bearing piece.
2. An offset side-hung rocket adapter structure according to claim 1 wherein said bearing comprises a barrel having a hollow interior.
3. A biased side-hung rocket adapter structure according to claim 2, wherein said carriage further comprises a connecting portion disposed at a side end of said carriage, said connecting portion being disposed within said envelope space for connection with said payload.
4. An offset side-hung rocket adapter structure according to claim 1, wherein said support connection comprises a rod and adapters disposed at opposite ends of said rod, said rod and said adapters being made of high modulus carbon fiber or lightweight alloy material.
5. An offset side-hung rocket adapter structure according to claim 1, wherein the length of said carrier is parallel to the central axis of the fairing of said rocket.
6. An offset side-hung rocket adapter structure according to claim 1 wherein the length of said carriage is perpendicular to the plane of said carriage floor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574964.1A CN114812292B (en) | 2022-05-24 | 2022-05-24 | Offset side-hanging rocket adapter structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574964.1A CN114812292B (en) | 2022-05-24 | 2022-05-24 | Offset side-hanging rocket adapter structure |
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| Publication Number | Publication Date |
|---|---|
| CN114812292A CN114812292A (en) | 2022-07-29 |
| CN114812292B true CN114812292B (en) | 2024-08-13 |
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| CN202210574964.1A Active CN114812292B (en) | 2022-05-24 | 2022-05-24 | Offset side-hanging rocket adapter structure |
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| CN (1) | CN114812292B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113562205A (en) * | 2021-08-03 | 2021-10-29 | 湖北航天技术研究院总体设计所 | Satellite and arrow separation method with offset layout and satellite and arrow system |
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| US5199672A (en) * | 1990-05-25 | 1993-04-06 | Orbital Sciences Corporation | Method and apparatus for deploying a satellite network |
| US6761335B2 (en) * | 2001-11-29 | 2004-07-13 | Alliant Techsystems Inc. | Apparatus for load transfer between aerospace vehicle components, aerospace vehicles including same, and method of attachment of aerospace vehicle components |
| RU2265560C1 (en) * | 2005-09-06 | 2005-12-10 | Соломонов Юрий Семенович | Multi-stage space launch vehicle |
| RU2422335C1 (en) * | 2009-12-21 | 2011-06-27 | Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" | Spacehead |
| US8800935B2 (en) * | 2011-03-09 | 2014-08-12 | Space Systems/Loral, Llc | Spacecraft payload positioning with respect to a virtual pivot point |
| US8939409B2 (en) * | 2012-05-07 | 2015-01-27 | The Johns Hopkins University | Adaptor system for deploying small satellites |
| CN102785589B (en) * | 2012-05-09 | 2015-08-26 | 北京鼎昌复合材料有限责任公司 | Insulated contact net suspension gear |
| CN206936749U (en) * | 2017-07-12 | 2018-01-30 | 芜湖宝骐汽车制造有限公司 | Reversible logistic car car door mounting bracket |
| CN108756411B (en) * | 2018-05-30 | 2020-06-16 | 长江大学 | Eccentric supporting structure of tree-shaped column |
| CN113665845B (en) * | 2021-09-10 | 2023-06-09 | 上海卫星工程研究所 | Structural load bearing device for stacked satellites |
| CN114506474B (en) * | 2022-01-14 | 2023-08-18 | 上海卫星工程研究所 | Satellite layout based on multi-type remote sensing instrument joint detection |
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2022
- 2022-05-24 CN CN202210574964.1A patent/CN114812292B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110901964A (en) * | 2019-12-31 | 2020-03-24 | 航天科工火箭技术有限公司 | Load board and satellite adapter device |
| CN113562205A (en) * | 2021-08-03 | 2021-10-29 | 湖北航天技术研究院总体设计所 | Satellite and arrow separation method with offset layout and satellite and arrow system |
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| CN114812292A (en) | 2022-07-29 |
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