CN114812290A - Integrated structure of fairing and rocket adapter and carrier rocket - Google Patents
Integrated structure of fairing and rocket adapter and carrier rocket Download PDFInfo
- Publication number
- CN114812290A CN114812290A CN202210574959.0A CN202210574959A CN114812290A CN 114812290 A CN114812290 A CN 114812290A CN 202210574959 A CN202210574959 A CN 202210574959A CN 114812290 A CN114812290 A CN 114812290A
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- Prior art keywords
- adapter
- fairing
- rocket
- reinforcing
- integrated structure
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- 230000007246 mechanism Effects 0.000 claims abstract description 41
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 40
- 238000000926 separation method Methods 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims 2
- 238000010168 coupling process Methods 0.000 claims 2
- 238000005859 coupling reaction Methods 0.000 claims 2
- 238000000034 method Methods 0.000 description 6
- 230000002787 reinforcement Effects 0.000 description 6
- 230000009471 action Effects 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/48—Range-reducing, destabilising or braking arrangements, e.g. impact-braking arrangements; Fall-retarding means, e.g. balloons, rockets for braking or fall-retarding
-
- 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)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention relates to the field of aerospace and aviation, and discloses a fairing and rocket adapter integrated structure and a carrier rocket, wherein the integrated structure comprises: an adapter body including an adapter frame and a plurality of reinforcing ribs; the plurality of reinforcing ribs are arranged at intervals along the circumferential direction of the adapter frame; the fairing body is arranged on the periphery of the adapter body and comprises a plurality of fairing plates which are sequentially spliced along the circumferential direction, and each fairing plate is connected with at least one reinforcing rib plate through a first connecting unlocking mechanism. The reinforcing rib plates are arranged in the circumferential direction of the adapter frame, the reinforcing rib plates are connected with the fairing body through the first connecting unlocking mechanism, the bearing capacity of the adapter frame is dispersed to the reinforcing rib plates and the fairing body, the structural strength and the bearing capacity of the adapter body are effectively improved under the condition that the overall dimension is not required to be increased, and the weight of the whole rocket structure of the carrier rocket is greatly reduced.
Description
Technical Field
The invention relates to the field of space flight and aviation, in particular to a fairing and rocket adapter integrated structure and a carrier rocket.
Background
At present, the final-stage structure of the carrier rocket at home and abroad is positioned inside the fairing, the rocket adapter is positioned on the final-stage structure, and the effective load is arranged on the rocket adapter. The fairing primarily functions to maintain the aerodynamic shape of the launch vehicle and provide the necessary environment for the final internal structure. Whereas rocket adapters rely primarily on the last stage structure for load carrying.
As the payload increases, on the one hand the fairing increases in physical size and structural weight, but does not provide additional structural support for the rocket adapter; on the other hand, because only one end of the rocket adapter is connected, the rocket adapter is of a cantilever beam structure as a whole, the increase of the external dimension of the rocket adapter leads to the increase of the weight of the rocket adapter and the reduction of the rigidity of the rocket adapter.
Disclosure of Invention
The invention provides a fairing and rocket adapter integrated structure and a carrier rocket, and aims to solve the technical problems.
In a first aspect, the present invention provides a fairing and rocket adapter integrated structure, comprising:
an adapter body including an adapter frame and a plurality of reinforcing ribs; a plurality of the reinforcing floor plates are arranged at intervals along the circumference of the adapter frame;
the fairing body is arranged on the periphery of the adapter body and comprises a plurality of fairing plates which are sequentially spliced along the circumferential direction, and each fairing plate is connected with at least one reinforcing rib plate through a first connecting and unlocking mechanism to realize connection and separation of the fairing plate and the reinforcing rib plate.
Further, the adapter body further comprises a reinforcing ring, the reinforcing ring is arranged at one end of the adapter frame, and the reinforcing ring is connected with the plurality of reinforcing ribs.
Furthermore, one end of the adapter frame is provided with a second connecting and unlocking mechanism and is connected with and separated from a nose cone section structure of the rocket through the second connecting and unlocking mechanism, and the other end of the adapter frame is provided with a third connecting and unlocking mechanism and is connected with and separated from a final stage structure of the rocket through the third connecting and unlocking mechanism.
Further, the cowling panel includes the arc, the polylith encloses along the cowling panel that circumference concatenation in proper order and closes formation cylindric structure the cowling body.
Further, a central axis of the fairing body coincides with a central axis of the adapter body.
Further, the adapter frame comprises a bearing cylinder with a hollow inner part.
In a second aspect, the invention provides a launch vehicle, which comprises the fairing and rocket adapter integrated structure, and further comprises a nose cone section structure and a final stage structure which are respectively arranged at two ends of the integrated structure.
Furthermore, the plurality of reinforcing ribs of the integrated structure are uniformly arranged at intervals along the circumferential direction of the adapter frame, one rectifying plate is arranged between every two circumferentially adjacent reinforcing ribs, and an enveloping space is formed by the rectifying plates and the adapter frame between the two reinforcing ribs.
Furthermore, a fourth connecting and unlocking mechanism and a payload are arranged in each enveloping space, and the payload is connected with and separated from the adapter body through the fourth connecting and unlocking mechanism.
Further, a plurality of payloads are arranged in each envelope space at intervals along the length direction of the adapter body.
The technical scheme provided by the invention has the beneficial effects that: the reinforcing rib plates are arranged in the circumferential direction of the adapter frame, the reinforcing rib plates are connected with the fairing body through the first connecting unlocking mechanism, the bearing capacity of the adapter frame is dispersed to the reinforcing rib plates and the fairing body, the structural strength and the bearing capacity of the adapter body are effectively improved under the condition that the overall dimension is not required to be increased, and the weight of the whole rocket structure of the carrier rocket is greatly reduced.
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 perspective view of a launch vehicle with a fairing and rocket adapter integrated structure according to the present invention.
In the figure: 1-an adapter body; 11-a dispenser frame; 12-a reinforcing floor; 13-a reinforcement ring; 2-final stage structure; 3-a conical section structure; 4-payload; 5-a fairing; 51-rectifying plate.
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, the launch vehicle includes a fairing 5 and rocket adapter integrated structure, and further includes a nose cone segment structure 3 and a final stage structure 2 respectively disposed at both ends of the fairing 5 and rocket adapter integrated structure.
The fairing 5 and rocket adapter integrated structure comprises an adapter body 1 and a fairing 5 body.
The adapter body 1 includes an adapter frame 11 and a plurality of reinforcing ribs 12.
One end of the adapter frame 11 is provided with a second connection unlocking mechanism and is connected with and separated from the nose cone structure 3 of the rocket through the second connection unlocking mechanism, and the other end of the adapter frame 11 is provided with a third connection unlocking mechanism and is connected with and separated from the final stage structure 2 of the rocket through the third connection unlocking mechanism.
The adapter frame 11 comprises a hollow bearing cylinder, and the bearing cylinder with the hollow structure is convenient for arranging cables and reducing the weight.
The plurality of reinforcement ribs 12 are provided at intervals in the circumferential direction of the adapter frame 11.
The fairing 5 body is arranged on the periphery of the adapter body 1, the fairing 5 body comprises a plurality of fairing plates 51 which are sequentially spliced along the circumferential direction, each fairing plate 51 is connected with at least one reinforcing rib plate 12 through a first connecting and unlocking mechanism, and the connection and the separation of the fairing plates 51 and the reinforcing rib plates 12 are realized.
The fairing 5 body is connected with the adapter body 1 through a plurality of first connecting and unlocking mechanisms to form an integrated structure. The fairing 5 body provides additional structural support for the integrated structure, and the effect of improving the structural bearing capacity is achieved.
The cowling 51 includes the arc, the polylith encloses along the cowling 51 that circumference concatenation in proper order and closes formation cylindric structure 5 bodies of cowling.
The adapter body 1 further comprises a reinforcement ring 13, the reinforcement ring 13 being arranged at one end of the adapter frame 11, and the reinforcement ring 13 being connected to the plurality of reinforcement ribs 12.
The central axis of the fairing 5 body coincides with the central axis of the adapter body 1. In this embodiment, the reinforcing ring 13 is annular and has a central axis which also coincides with the central axis of the body of the fairing 5.
The fairing 5 body and the adapter body 1 are connected to maintain the aerodynamic shape of the launch vehicle.
The plurality of reinforcing ribs 12 are uniformly spaced along the circumferential direction of the adapter frame 11, one rectifying plate 51 is arranged between every two circumferentially adjacent reinforcing ribs 12, and an enveloping space is formed by the rectifying plates and the adapter frame 11 between the two reinforcing ribs 12.
And a fourth connecting and unlocking mechanism and a payload 4 are arranged in each enveloping space, and the payload 4 is connected with and separated from the adapter body 1 through the fourth connecting and unlocking mechanism.
A plurality of payloads 4 are arranged in each envelope space at intervals along the length direction of the adapter body 1. In this embodiment, two payloads 4 are provided in each of the envelope spaces, and the two payloads 4 are spaced apart from each other in the length direction of the adapter frame 11 of the adapter body 1. The payload 4 comprises a satellite.
The first connecting and unlocking mechanism, the second connecting and unlocking mechanism, the third connecting and unlocking mechanism and the fourth connecting and unlocking mechanism can all adopt explosive bolts.
The carrier rocket further comprises a controller, wherein the controller is in communication connection with the first connecting unlocking mechanism, the second connecting unlocking mechanism, the third connecting unlocking mechanism and the fourth connecting unlocking mechanism and is used for sending a control command, and the control command comprises an unlocking command. And when the first connection unlocking mechanism, the second connection unlocking mechanism, the third connection unlocking mechanism or the fourth connection unlocking mechanism receives an unlocking instruction sent by the controller, executing the unlocking instruction.
After the first connecting unlocking mechanism executes the unlocking command, the rectifying plate 51 is separated from the reinforcing rib plate 12. After the second connection unlocking mechanism executes the unlocking command, the adapter frame 11 is separated from the nose cone structure 3 of the rocket. After the third connection unlocking mechanism executes the unlocking command, the adapter frame 11 is detached from the final stage structure 2 of the rocket. When the fourth connection unlocking mechanism executes the unlocking instruction, the payload 4 is separated from the adapter frame 11.
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 by those skilled in the art according to specific situations.
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. A fairing and rocket adapter integrated structure, comprising:
an adapter body including an adapter frame and a plurality of reinforcing ribs; a plurality of the reinforcing floor plates are arranged at intervals along the circumference of the adapter frame;
the fairing body is arranged on the periphery of the adapter body and comprises a plurality of fairing plates which are sequentially spliced along the circumferential direction, and each fairing plate is connected with at least one reinforcing rib plate through a first connecting and unlocking mechanism to realize connection and separation of the fairing plate and the reinforcing rib plate.
2. A fairing and rocket adapter integrated structure as recited in claim 1, wherein said adapter body further comprises a reinforcing ring, said reinforcing ring being disposed at one end of said adapter frame, said reinforcing ring being connected to said plurality of reinforcing ribs.
3. A fairing and rocket adapter integral structure as recited in claim 1, wherein said adapter frame is provided at one end with a second connection release mechanism and is connected to and disconnected from a nose cone structure of a rocket through said second connection release mechanism, and said adapter frame is provided at another end with a third connection release mechanism and is connected to and disconnected from a final structure of a rocket through said third connection release mechanism.
4. A fairing and rocket adapter integral structure as recited in claim 1, wherein said fairing comprises an arc-shaped plate, and said plurality of circumferentially sequentially spliced fairing plates enclose said fairing body having a cylindrical structure.
5. A fairing and rocket adapter one piece structure as recited in claim 4, wherein a central axis of said fairing body is coincident with a central axis of said adapter body.
6. A fairing and rocket adapter integrated structure as recited in claim 1, wherein said adapter frame comprises a hollow interior force bearing cylinder.
7. A launch vehicle comprising a fairing and rocket adapter integrated structure as recited in any one of claims 1-6, and further comprising a nose cone segment structure and a final stage structure disposed at opposite ends of said integrated structure, respectively.
8. A launch vehicle according to claim 1, wherein said plurality of reinforcing ribs of said unified structure are uniformly spaced along a circumferential direction of said adapter frame, and one of said fairings is disposed between every two circumferentially adjacent reinforcing ribs, and forms an enveloping space with said adapter frame between said two reinforcing ribs.
9. A launch vehicle according to claim 8, wherein a fourth coupling and unlocking mechanism and a payload are provided in each of said envelope spaces, said payload being coupled to and decoupled from said adapter body by said fourth coupling and unlocking mechanism.
10. A launch vehicle according to claim 9, wherein a plurality of said payloads are disposed within each of said envelope spaces at intervals along the length of said adapter body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574959.0A CN114812290A (en) | 2022-05-24 | 2022-05-24 | Integrated structure of fairing and rocket adapter and carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574959.0A CN114812290A (en) | 2022-05-24 | 2022-05-24 | Integrated structure of fairing and rocket adapter and carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114812290A true CN114812290A (en) | 2022-07-29 |
Family
ID=82516701
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210574959.0A Pending CN114812290A (en) | 2022-05-24 | 2022-05-24 | Integrated structure of fairing and rocket adapter and carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114812290A (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3544022A (en) * | 1967-08-08 | 1970-12-01 | Imp Metal Ind Kynoch Ltd | Structures |
| US3814350A (en) * | 1973-03-21 | 1974-06-04 | Nasa | Thrust-isolating mounting |
| US4374577A (en) * | 1976-01-14 | 1983-02-22 | The United States Of America As Represented By The Secretary Of The Navy | Adapter assembly for flat trajectory flight |
| JPH08164899A (en) * | 1994-12-13 | 1996-06-25 | Mitsubishi Heavy Ind Ltd | Plural artificial satellite mounting mechanism |
| WO2000009396A2 (en) * | 1998-08-10 | 2000-02-24 | The Boeing Company | Multiple spacecraft carrier on launcher |
| EP1104743A2 (en) * | 1999-12-01 | 2001-06-06 | The Boeing Company | Cantilever, bi-level platform satellite dispenser |
| US20110114793A1 (en) * | 2009-11-18 | 2011-05-19 | Ruag Schweiz Ag | Zero-shock separation system |
| CN106864773A (en) * | 2017-03-31 | 2017-06-20 | 陕西蓝箭航天技术有限公司 | A kind of instrument cabin structure of vehicle |
| US20210031952A1 (en) * | 2018-01-22 | 2021-02-04 | Ruag Schweiz Ag | Payload carrier assembly |
| CN212667707U (en) * | 2019-12-30 | 2021-03-09 | 茅台学院 | Novel single-layer detachable multi-load satellite-rocket adapter |
| CN215495687U (en) * | 2021-09-15 | 2022-01-11 | 西南石油大学 | Novel recoverable two-stage model solid rocket |
| CN114044174A (en) * | 2021-12-20 | 2022-02-15 | 北京微分航宇科技有限公司 | Multi-star distributor of beam-slab combined structure |
-
2022
- 2022-05-24 CN CN202210574959.0A patent/CN114812290A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3544022A (en) * | 1967-08-08 | 1970-12-01 | Imp Metal Ind Kynoch Ltd | Structures |
| US3814350A (en) * | 1973-03-21 | 1974-06-04 | Nasa | Thrust-isolating mounting |
| US4374577A (en) * | 1976-01-14 | 1983-02-22 | The United States Of America As Represented By The Secretary Of The Navy | Adapter assembly for flat trajectory flight |
| JPH08164899A (en) * | 1994-12-13 | 1996-06-25 | Mitsubishi Heavy Ind Ltd | Plural artificial satellite mounting mechanism |
| WO2000009396A2 (en) * | 1998-08-10 | 2000-02-24 | The Boeing Company | Multiple spacecraft carrier on launcher |
| EP1104743A2 (en) * | 1999-12-01 | 2001-06-06 | The Boeing Company | Cantilever, bi-level platform satellite dispenser |
| US20110114793A1 (en) * | 2009-11-18 | 2011-05-19 | Ruag Schweiz Ag | Zero-shock separation system |
| CN106864773A (en) * | 2017-03-31 | 2017-06-20 | 陕西蓝箭航天技术有限公司 | A kind of instrument cabin structure of vehicle |
| US20210031952A1 (en) * | 2018-01-22 | 2021-02-04 | Ruag Schweiz Ag | Payload carrier assembly |
| CN212667707U (en) * | 2019-12-30 | 2021-03-09 | 茅台学院 | Novel single-layer detachable multi-load satellite-rocket adapter |
| CN215495687U (en) * | 2021-09-15 | 2022-01-11 | 西南石油大学 | Novel recoverable two-stage model solid rocket |
| CN114044174A (en) * | 2021-12-20 | 2022-02-15 | 北京微分航宇科技有限公司 | Multi-star distributor of beam-slab combined structure |
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