CN114812292A - Offset side-hanging rocket adapter structure - Google Patents
Offset side-hanging rocket adapter structure Download PDFInfo
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- CN114812292A CN114812292A CN202210574964.1A CN202210574964A CN114812292A CN 114812292 A CN114812292 A CN 114812292A CN 202210574964 A CN202210574964 A CN 202210574964A CN 114812292 A CN114812292 A CN 114812292A
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- bearing
- rocket
- bottom plate
- load
- adapter structure
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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 2
- 230000000694 effects Effects 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 229910001234 light alloy Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 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
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Classifications
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- 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 aviation, and discloses a bias side-hanging rocket adapter structure, which comprises: the force 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 supporting connecting piece is used for connecting the bearing piece and the bearing bottom plate; the force bearing part, the load bearing bottom plate, the supporting connecting part 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. Through the eccentric arrangement of the bearing part, the effective enveloping space in the rocket can be enlarged under the condition that the size of the fairing is not changed, and the carrying of a single effective load with larger size is facilitated. Through the effect of supporting the connecting piece, can improve the intensity of adapter structure, avoid the power load that the load-bearing piece received to exceed the allowed range, can realize the connection of rocket adapter structure and other sections of rocket final stage through the load-bearing bottom plate.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a bias side-hanging rocket adapter structure.
Background
The existing rocket adapter structures applied in the rocket field can be divided into a base type structure and a side hanging type structure according to different installation modes of effective loads on the rocket adapter. Wherein the base rocket adapter is attached to and detached from the payload in a rocket flight direction, and the side-hung rocket adapter is attached to and detached from the payload in a lateral direction.
At present, the side-hung rocket adapter structure is mainly a symmetrical structure, and effective loads are distributed on the periphery of the adapter and are laterally connected with the adapter. When the load space of the carrier rocket is small, the carrying requirement of the effective load can not be met by adopting the symmetrical side-hung rocket adapter. Therefore, an offset side-hanging rocket adapter structure is urgently needed, so that the problem that a carrier rocket with a smaller load space cannot carry a payload with a larger volume is solved.
Disclosure of Invention
The invention provides an offset side-hanging rocket adapter structure, which aims to solve the technical problem.
The invention discloses a bias side-hanging rocket adapter structure, which comprises:
the force 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 supporting connecting piece is used for connecting the bearing piece and the bearing bottom plate;
the force 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 payload of the rocket, and a central shaft of the fairing of the rocket penetrates through the envelope space.
Further, the bearing part comprises a bearing cylinder, and the inside of the bearing cylinder is of a hollow structure.
The beneficial effects of the further scheme are as follows: the force bearing piece is arranged to be of a hollow structure, so that the cable net can be conveniently installed and fixed.
Further, the bearing part further comprises a connecting part, the connecting part is arranged at the side end of the bearing cylinder, and the connecting part is located in the enveloping space and is 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 support rod system is connected with the bearing piece, and the other end of each support rod system is connected with the bearing bottom plate.
Furthermore, the center of the bearing bottom plate coincides with the central axis of the fairing, three connection points are arranged on the surface of the bearing bottom plate, the connecting lines of the three connection points form an isosceles or equilateral triangle, the vertical line of the triangle passes 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 part and one end of the support rod system arranged on two sides of the bearing part.
The beneficial effects of the further scheme are as follows: the supporting rod systems are uniformly and symmetrically arranged, so that concentrated force borne by the bearing parts and the supporting connecting parts can be uniformly dispersed to each connecting point of the rocket final stage connected with the bearing bottom plate.
Further, each support rod system comprises a first support rod, a second support rod and a connecting rod; the first end of the first supporting rod is connected with the force bearing part, 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 force bearing part, 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.
Furthermore, the first ends of the first supporting rod and the second supporting rod are respectively connected with the same position or different positions of the force bearing piece; the second ends of the first supporting rod and the second supporting 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 adapters arranged at two ends of the rod piece, and the rod piece and the adapters are made of high-modulus carbon fibers 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 part is vertical to the plate surface of the bearing bottom plate.
The technical scheme provided by the invention has the beneficial effects that: through the eccentric arrangement of the bearing part, the effective enveloping space in the rocket can be enlarged under the condition that the size of the fairing is not changed, and the carrying of a single effective load with 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 force 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 structure of the invention has simple integral structure, easy installation and low cost.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of an offset side-hung rocket adapter structure according to the present invention.
Fig. 2 is a schematic top view of the structure of fig. 1.
In the figure: 1-bearing cylinder; 2-a connecting part; 3-carrying the bottom plate; 4-a support connection; 41-a first support bar; 42-a second support bar; 43-connecting rod; 5-payload; 6-envelope space.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Referring to fig. 1 and 2, the offset side-hung rocket adapter structure comprises: bearing member, bearing bottom plate 3 and supporting connection 4.
The bearing part comprises a bearing cylinder 1, and the inside of the bearing cylinder 1 is of a hollow structure. The cross section of the bearing cylinder 1 is not limited to a circle, and can also be a square. The bearing cylinder 1 with a hollow structure is convenient for routing and installing cable network lines.
The force bearing part is eccentrically arranged relative to the central shaft of the fairing of the rocket, wherein the fairing of the rocket is usually a cylindrical structure formed by splicing a plurality of arc-shaped 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 part and the central axis of the fairing are in the same horizontal plane, 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 part and the central axis of the fairing is the eccentric distance of the bearing part.
The bearing bottom plate 3 is arranged at one end of the bearing piece. The length direction of the bearing part is vertical to the plate surface of the bearing bottom plate 3. In this embodiment, as shown in fig. 2, the plate surface of the load floor 3 is circular, and the center of the load floor 3 coincides with the central axis of the cowling. The bearing part is eccentrically arranged relative to the central shaft of the fairing of the rocket, and the bearing cylinder 1 of the bearing part can also be regarded as being eccentrically arranged relative to the center of the bearing bottom plate 3.
And the supporting connecting piece 4 is connected with the bearing piece and the bearing bottom plate 3.
The force bearing piece, the bearing bottom plate 3, the supporting connecting 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 penetrates 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 cowling of the rocket. Compared with the traditional mode that the force bearing part is arranged at the center of the rocket, the envelope space 6 formed by the force bearing part arranged eccentrically is larger, so that the payload 5 with larger size can be accommodated, and the size of the fairing does not need to be changed.
The force bearing part further comprises a connecting part 2, the connecting part 2 is arranged at the side end of the force bearing cylinder 1, and the connecting part 2 is located in the enveloping space 6 and is used for being connected with the effective load 5. Referring to fig. 1, a plurality of connecting parts 2 are arranged at intervals along the length direction of the bearing cylinder 1 of the bearing part to improve the connecting effect with the payload 5.
The supporting connecting piece 4 in the embodiment comprises supporting rod systems arranged on two sides of the bearing piece; one end of each support rod system is connected with the bearing part, and the other end of each support rod system is connected with the bearing bottom plate 3.
As shown in fig. 2, three connection points are arranged on the surface of the bearing bottom plate 3, the connection line of the three connection points forms an isosceles or equilateral triangle, the perpendicular line of the triangle passes through the center of the bearing bottom plate 3, and the three connection points are connected with one end of the bearing cylinder 1 of the bearing part and one end of the support rod system arranged on both sides of the bearing part in a one-to-one correspondence manner. Because the bearing bottom plate 3 is used for realizing the connection of the rocket adapter structure and other sections of the rocket final stage, three connecting point positions are uniformly arranged on the bearing bottom plate 3, and the force borne by the bearing cylinder 1 and the support rod system can be uniformly dispersed to the rocket final stage through the bearing bottom plate 3.
Each support rod system comprises a first support rod 41, a second support rod 42 and a connecting rod 43; the first end of the first supporting rod 41 is connected with the force bearing part, 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 force bearing part, 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 rod 41 and the second support rod 42 are respectively connected with the same position or different positions of the bearing part; 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 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 with two different positions of the force bearing cylinder 1 of the force bearing member, and the two different positions are distributed at intervals along the length direction of the force bearing cylinder 1. The second ends of the first support bar 41 and the second support bar 42 of each support bar series are connected to the same position of the load-bearing floor 3. As shown in fig. 2, the two support rods are symmetrically arranged by taking the horizontal plane of the central axis of the overstress cylinder 1 as a mirror image plane.
In this embodiment, the supporting and connecting member 4 includes a rod and adapters disposed at two ends of the rod, and the rod and the adapters 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 piece, the effective enveloping space 6 in the rocket can be enlarged under the condition of not changing the size of the fairing, and the carrying of a single effective load 5 with 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 borne by the force 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 structure of the invention has simple integral structure, easy installation and low cost.
In the description of the present invention, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present invention. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
It is to 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. Also, 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 an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present 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 (10)
1. An offset side-hung rocket adapter structure, comprising:
the force 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 supporting connecting piece is used for connecting the bearing piece and the bearing bottom plate;
the force 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 payload of the rocket, and a central shaft of the fairing of the rocket penetrates through the envelope space.
2. A biased side-hung rocket adapter structure as recited in claim 1, wherein said bearing member comprises a bearing cylinder, and the interior of said bearing cylinder is hollow.
3. An offset side-hung rocket adapter structure as recited in claim 2, wherein said messenger further comprises attachment portions disposed at lateral ends of said messenger, said attachment portions being located within said envelope space for attachment to said payload.
4. An offset side-hung rocket adapter structure as recited in claim 1, wherein said support links comprise a series of support rods disposed on either side of said carrier; one end of each support rod system is connected with the bearing piece, and the other end of each support rod system is connected with the bearing bottom plate.
5. An offset side-hung rocket adapter structure as recited in claim 4, wherein the center of said load-bearing base plate coincides with the central axis of said fairing, three connection points are provided on the surface of said load-bearing base plate, the connecting lines of said three connection points form an isosceles or equilateral triangle, the perpendicular line of said triangle passes through the center of said load-bearing base plate, and said three connection points are connected with one end of said load-bearing member and one end of said support rod system disposed on both sides of said load-bearing member in a one-to-one correspondence.
6. An offset side-hung rocket adapter structure as recited in claim 4, wherein each of said support linkages comprises a first support rod, a second support rod, and a connecting rod; the first end of the first supporting rod is connected with the force bearing part, 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 force bearing part, 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.
7. An offset side-hung rocket adapter structure as recited in claim 6, wherein said first ends of said first support rod and said second support rod are connected to said load-bearing member at the same position or at different positions, respectively; the second ends of the first supporting rod and the second supporting rod are respectively connected with the same position or different positions of the bearing bottom plate.
8. An offset side-hung rocket adapter structure as recited in claim 1, wherein said support links comprise rods and adapters disposed at both ends of said rods, said rods and said adapters being made of high modulus carbon fiber or light weight alloy material.
9. An offset side-hung rocket adapter structure as recited in claim 1, wherein said carrier has a length direction parallel to a central axis of a fairing of said rocket.
10. The structure of an offset side-hung rocket adapter according to claim 1 wherein the length direction of said force-bearing member is perpendicular to the surface of said load-bearing base plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574964.1A CN114812292A (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 CN114812292A (en) | 2022-05-24 | 2022-05-24 | Offset side-hanging rocket adapter structure |
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| Publication Number | Publication Date |
|---|---|
| CN114812292A true CN114812292A (en) | 2022-07-29 |
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| CN202210574964.1A Pending CN114812292A (en) | 2022-05-24 | 2022-05-24 | Offset side-hanging rocket adapter structure |
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| CN (1) | CN114812292A (en) |
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| US20030098396A1 (en) * | 2001-11-29 | 2003-05-29 | Goodro Jerry B. | Apparatus for load transfer between aerospace vehicle components, aerospace vehicles including same, and method of attachment of aerospace vehicle components |
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| US20120228436A1 (en) * | 2011-03-09 | 2012-09-13 | Space Systems/Loral, Inc. | Spacecraft payload positioning with respect to a virtual pivot point |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| 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 |
| 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 |
| CN113665845A (en) * | 2021-09-10 | 2021-11-19 | 上海卫星工程研究所 | Structural bearing device for stacked satellites |
| CN114506474A (en) * | 2022-01-14 | 2022-05-17 | 上海卫星工程研究所 | Satellite layout based on joint detection of multiple types of remote sensing instruments |
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2022
- 2022-05-24 CN CN202210574964.1A patent/CN114812292A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5199672A (en) * | 1990-05-25 | 1993-04-06 | Orbital Sciences Corporation | Method and apparatus for deploying a satellite network |
| US20030098396A1 (en) * | 2001-11-29 | 2003-05-29 | Goodro Jerry B. | 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 |
| US20120228436A1 (en) * | 2011-03-09 | 2012-09-13 | Space Systems/Loral, Inc. | Spacecraft payload positioning with respect to a virtual pivot point |
| US20140131521A1 (en) * | 2012-05-07 | 2014-05-15 | The Johns Hopkins University | Adaptor System for Deploying Small Satellites |
| 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 |
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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 |
| CN113665845A (en) * | 2021-09-10 | 2021-11-19 | 上海卫星工程研究所 | Structural bearing device for stacked satellites |
| CN114506474A (en) * | 2022-01-14 | 2022-05-17 | 上海卫星工程研究所 | Satellite layout based on joint detection of multiple types of remote sensing instruments |
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