CN114754625B - Rocket erection device and rocket erection method - Google Patents
Rocket erection device and rocket erection method Download PDFInfo
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- CN114754625B CN114754625B CN202210318532.4A CN202210318532A CN114754625B CN 114754625 B CN114754625 B CN 114754625B CN 202210318532 A CN202210318532 A CN 202210318532A CN 114754625 B CN114754625 B CN 114754625B
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- loading
- erection
- rocket
- platform
- frame
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/052—Means for securing the rocket in the launching apparatus
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Conveying And Assembling Of Building Elements In Situ (AREA)
Abstract
The application discloses a rocket erection device and a rocket erection method, which belong to the field of rocket launching, and comprise a loading device, a hydraulic erection device and a launching pad; the loading device comprises a loading disc and a loading frame for loading rockets; the hydraulic erection mechanism comprises an erection platform and an erection cylinder with an arc-shaped piston rod; the loading frame is configured to be in a loading state that the loading frame is fixedly connected with the loading disc or an erecting state that the loading frame is fixedly connected with the erecting platform; the hydraulic erection mechanism is configured to erect a rocket loaded on a loading frame onto the launch pad. The application can reduce the time for transporting the rocket to the launching area, reduce the launching interval of a plurality of rockets and improve the launching efficiency.
Description
Technical Field
The application relates to the field of rocket launching, in particular to a rocket erection device and a rocket erection method.
Background
The conventional solid quick response rocket often takes a large structure as a carrier, and is erected in a land-based launching field, so that the erection efficiency is low, long-distance rocket transportation is required after one rocket is launched, the launching interval of a plurality of rockets is long, and the requirement of quick response in a special period cannot be met.
In view of the foregoing, it is necessary to provide a new solution to the above-mentioned problems.
Disclosure of Invention
In order to solve the technical problems, the application provides a rocket erection device which can realize quick erection of a rocket and improve rocket erection efficiency.
A rocket erection device comprises a loading device, a hydraulic erection device and a launching pad; the launching platform is provided with a diversion slot hole for diversion of rocket tail flame; the loading device comprises a loading disc and a loading frame for loading rockets; the loading disc is rotatably arranged relative to the launching platform; the number of the loading frames is not less than two; the hydraulic erection mechanism comprises an erection platform and an erection oil cylinder; the erection cylinder comprises an arc-shaped piston rod and a cylinder body for loading the piston rod; the erection platform is fixedly arranged at the end part of the piston rod; the loading frame is configured to be in a loading state or an erecting state, in the loading state, the loading frame is fixedly connected with the loading disc, and in the erecting state, the loading frame is fixedly connected with the erecting platform; the hydraulic erection mechanism is configured to erect a rocket loaded on the loading frame onto the launch pad.
Preferably, the loading frame comprises a frame body and not less than 2 clamping mechanisms; the clamping mechanism is arranged along the length direction of the frame body.
Preferably, the clamping mechanism is in sliding connection with the frame body; and a spacing adjusting oil cylinder is arranged between the adjacent clamping mechanisms.
Preferably, the loading device further comprises a connecting pin shaft for detachably and fixedly connecting the loading frame and the loading disc; the connecting pin shaft is spliced with the loading frame and the loading disc.
Preferably, the device further comprises an annular fluted disc for driving the loading disc to rotate; the fluted disc is fixedly connected with the loading disc.
Preferably, the loading frame further comprises a connecting device for detachably and fixedly connecting the lifting platform and the loading frame; the connecting device comprises a connecting rod, a limiting plate and a fixed end head; the limiting plate and the fixed end are fixedly connected with the connecting rod; the connecting rod penetrates through the erection platform, and the fixed end is arranged on one side, adjacent to the loading frame, of the erection platform; the limiting plate is arranged on the other side of the erection platform; the connecting rod is in sliding connection with the erection platform in the axial direction of the connecting rod; the connecting rod is rotatably connected with the erection platform in the radial direction.
Preferably, the connecting device further comprises a telescopic cylinder for pushing the connecting rod to move along the axial direction thereof.
Preferably, the connecting device further comprises a rotating motor for driving the connecting rod to rotate in a radial direction thereof.
Preferably, the arc angle of the piston rod is not less than 90 degrees.
According to another aspect of the present application, there is also disclosed a rocket erection method, for erection by a rocket erection device, comprising:
loading the rocket on a loading frame;
the loading frame is fixed on the loading disc through a connecting pin shaft, so that the loading frame is in a loading state;
rotating the loading disc to a stand-by vertical position, and removing the connecting pin shaft to enable the loading frame to be separated from the loading state;
the erection platform is fixedly connected with the loading frame through the connecting device, so that the loading frame is in an erection state;
the hydraulic oil is utilized to push the piston rod to do arc motion, and the rocket loaded on the loading frame is driven to be erected on the launching pad.
Compared with the prior art, the application has at least the following beneficial effects:
1. according to the application, the loading device is utilized to store a plurality of rockets, so that the time for transporting the rockets to a launching area is reduced, the launching interval of the plurality of rockets is reduced, and the launching efficiency is improved.
2. The hydraulic erection device can realize direct erection of the rocket, and has good erection effect and high erection efficiency.
Drawings
Some specific embodiments of the application will be described in detail hereinafter by way of example and not by way of limitation with reference to the accompanying drawings. The same reference numbers will be used throughout the drawings to refer to the same or like parts or portions. It will be appreciated by those skilled in the art that the drawings are not necessarily drawn to scale. Attached with
In the figure:
FIG. 1 is a schematic view of the overall cross-sectional structure of a rocket erection device according to the present application;
FIG. 2 is a schematic view of the loading device of the present application;
FIG. 3 is a schematic view of the structure of the loading frame of the present application;
FIG. 4 is an enlarged view of a portion of the position A of FIG. 3;
FIG. 5 is a view showing the connection of the fixed head to the carriage;
FIG. 6 is a view showing the erection state of a rocket erection device according to the present application.
Wherein the above figures include the following reference numerals:
1. the loading disc, 2, the loading frame, 3, the connecting pin shaft, 4, the launching platform, 5, the diversion slotted hole, 6, the supporting seat, 7, the fluted disc, 8, the gear, 9, the fixing seat, 10, the piston rod, 11, the cylinder body, 12, the piston cavity, 13, the erection platform, 14, the connecting device, 15 and the rocket;
21. the device comprises a frame body, 22, a fixing pin hole, 23, a clamping mechanism, 24, a slideway, 25, a position adjusting oil cylinder, 26, a spacing adjusting oil cylinder, 27 and a fixing groove;
141. the rotary motor, 142, the motor cabinet, 143, the connecting rod, 144, the limiting plate, 145, the telescopic cylinder, 146 and the fixed end.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be clearly and completely described below with reference to specific embodiments of the present application and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in fig. 1, a rocket erection device comprises a loading device, a hydraulic erection device and a launching pad 4. The loading device comprises a loading tray 1 and a loading rack 2. The loading tray 1 is detachably mounted on the loading frame 2. The launching platform 4 is provided with a diversion slot 5 for diversion of rocket tail flame. The hydraulic erection mechanism is fixed on the fixed seat 9 and comprises an erection platform 13 and an erection cylinder. The erection cylinder comprises a cylinder body 11 and an arc-shaped piston rod 10. The cylinder 11 is internally provided with a piston cavity 12 with an arc-shaped space, the arc-shaped piston rod 10 is loaded in the piston cavity 12, and can slide along the piston cavity 12 under the pressure of hydraulic oil after the hydraulic oil is pumped into the hydraulic pump, so that the end part of the piston rod 10 can move in an arc-shaped path. The erection platform 13 is fixedly arranged at the end part of the piston rod 10.
The loading frame 2 is configured to be in a loading state or an erecting state, and in the loading state, the loading frame 2 and the loading disc 1 are detachably and fixedly connected through the connecting pin shaft 3; in the erect state, the loading frame 2 and the erect platform 13 are detachably and fixedly connected through the connecting device 14. The hydraulic erection mechanism is configured to erect the rocket loaded on the carriage 2 onto the launch pad 4. The arc angle of the piston rod 10 is not smaller than 90 degrees, so that the erection platform 13 has enough movement path to ensure the realization of erection.
The bottom of the loading tray 1 is provided with a support seat 6 arranged in a ring shape. The loading plate 1 is slidably or rollably connected to the support base 6 via bearings so that it can rotate about its center of motion. The annular fluted disc 7 is fixedly arranged at the bottom of the loading disc 1 and is used for driving the loading disc 1 to rotate. The center of the toothed disc 7 coincides with the center of rotation of the loading disc 1. The gear 8 is meshed with the fluted disc 7 and is connected with an external motor, and can drive the loading disc 1 to rotate, so that the loading disc 1 can be arranged in a rotating way relative to the launching platform 4.
As shown in fig. 2, the loading device is a disk-like structure including a loading disk 1 and a loading frame 2 for loading a rocket. The connecting pin shaft 2 penetrates through the loading frame 2 and is fixedly connected with the loading disc 1 in an inserting mode, so that the loading frame 2 is detachably and fixedly connected with the loading disc 1 through the connecting pin shaft 3, and the loading disc 1 can synchronously rotate along with the loading disc 1 when in a loading state. After the connecting pin shaft 2 is pulled out, the loading frame 2 can be separated from the loading disc 1, and necessary conditions are provided for the rocket to erect.
Preferably, the loading frame 2 is a plurality of pieces with no less than two pieces, and more loading frames 2 can load more rockets within the loading range of the loading tray 1, so that the time consumed for transporting the rockets from the manufacturing site to the launching site can be reduced.
As shown in fig. 3 and referring to fig. 2, the loading frame 2 includes a frame body 21 and a clamping mechanism 23. The clamping mechanism 23 is not less than 2 pieces and is arranged along the length direction of the frame body 21 for fixing the rocket. The upper end face of the frame body 21 is provided with a slide 24, and the clamping mechanism 23 is clamped with the slide 24 and is in sliding connection with the frame body 21 through the slide 24. A spacing adjustment oil cylinder 26 is arranged between the adjacent clamping mechanisms 23, two ends of the spacing adjustment oil cylinder 26 are respectively fixedly connected with different clamping mechanisms 23, and the spacing adjustment of the adjacent clamping mechanisms 23 is realized through the expansion and the contraction of the spacing adjustment oil cylinder. After the distance between the adjacent clamping mechanisms 23 is adjusted, the loading frame 2 can clamp and fix rockets of different models, and the universality of the rockets is improved. The cylinder body of the position adjusting oil cylinder 25 is fixedly connected with the frame body 21, and the end part of a piston rod of the position adjusting oil cylinder is fixedly connected with the clamping mechanism 23 arranged at the end part of the frame body 21, so that the clamping mechanism 23 can adjust the position, the loading frame 2 can stand the rocket on the launching table 4 after the loading frame 2 is erected, and the loading frame 2 can load rockets of different types. The fixing groove 27 penetrates through the width direction of the frame body 21, so that the connecting pin shaft 3 can penetrate through the frame body 21, and the loading frame 2 and the loading disc 1 are fixed.
As shown in fig. 4, the connection device 14 includes a rotary motor 141, a motor housing 142, a connection rod 143, a limiting plate 144, a telescopic cylinder 145, and a fixed end 146. The rotary motor 141 is fixed to a motor base 142, and the motor base 142 is connected to the erection platform 13 through a telescopic cylinder 145. The fixed end 146 is fixedly connected with the end part of the connecting rod 143, and the other end of the connecting rod 143 is fixedly connected with the rotating motor 141. The connecting rod 143 penetrates the erection platform 13, the fixed end 146 is arranged on one side of the erection platform 13 adjacent to the loading frame 2, and the limiting plate 14 is arranged on the other side of the erection platform 13. The connecting rod 143 can be slidingly connected in its axial direction to the erection platform 13 and in its radial direction to the erection platform 13. The loading frame 2 is provided with the fixed slot 27, under the telescopic action of the telescopic cylinder 145, the fixed end 146 can extend into the fixed slot 27, under the rotating action of the rotating motor 141, the rotating angle of the fixed end 146 is clamped in the fixed slot 27, and meanwhile, under the limiting action of the limiting plate 144, the loading frame 2 is fixedly connected with the erection platform 13 through the connecting rod 143.
As a preferred embodiment of the present application, as shown in fig. 5, the fixing groove 2 is a pie-shaped cavity, the fixing end 146 is in a cube structure, and a connecting hole corresponding to the fixing end 146 is formed at the adjacent part of the loading frame 2 and the erection platform 1, so that the fixing end 146 can conveniently extend into the fixing groove 27.
The components of the rocket erection device are closely connected to form a complete whole, so that the rocket erection efficiency can be improved, the components cannot be independently split, and the superposition of similar functional independent components cannot solve the corresponding technical problems created by the application.
As shown in fig. 6, a rocket erecting method, which uses a rocket erecting device to erect, comprises the following steps:
s1, loading a rocket 15 on a loading frame 2;
s2, fixing the loading frame 2 on the loading disc 1 through a connecting pin shaft 3, so that the loading frame 2 is in a loading state;
s3, rotating the loading disc 1 to a standing position, and removing the connecting pin shaft 3 to enable the loading frame 2 to be separated from a loading state;
s4, fixedly connecting the erection platform 13 with the loading frame 2 through a connecting device 14 to enable the loading frame 2 to be in an erection state;
s5, pushing the piston rod 10 to do arc motion by utilizing hydraulic oil, and driving the rocket 15 loaded on the loading frame 2 to be erected on the launching platform 4.
Spatially relative terms, such as "above," "upper" and "upper surface," "above" and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above" may include both orientations of "above" and "below. The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the application described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (7)
1. The rocket erection device is characterized by comprising a loading device, a hydraulic erection device and a launching pad; the launching platform is provided with a diversion slot hole for diversion of rocket tail flame; the loading device comprises a loading disc and a loading frame for loading rockets; the loading disc is rotatably arranged relative to the launching platform; the number of the loading frames is not less than two; the hydraulic erection device comprises an erection platform and an erection oil cylinder; the erection cylinder comprises an arc-shaped piston rod and a cylinder body for loading the piston rod; the erection platform is fixedly arranged at the end part of the piston rod; the loading frame is configured to be in a loading state or an erecting state, in the loading state, the loading frame is fixedly connected with the loading disc, and in the erecting state, the loading frame is fixedly connected with the erecting platform; the hydraulic erection device is configured to erect the rocket loaded on the loading frame onto the launching platform;
the device also comprises a connecting pin shaft used for detachably and fixedly connecting the loading frame and the loading disc and a connecting device used for detachably and fixedly connecting the erection platform and the loading frame; the connecting pin shaft is spliced with the loading frame and the loading disc; the connecting device comprises a connecting rod, a limiting plate and a fixed end head;
the limiting plate and the fixed end are fixedly connected with the connecting rod; the connecting rod penetrates through the erection platform, the fixed end is arranged on one side, adjacent to the loading frame, of the erection platform, and the limiting plate is arranged on the other side of the erection platform; the connecting rod is in sliding connection with the erection platform in the axial direction of the connecting rod; the connecting rod is rotationally connected with the erection platform in the radial direction;
the arc angle of the piston rod is not smaller than 90 degrees.
2. A rocket apparatus as recited in claim 1, wherein said carriage comprises a frame body and no less than 2 gripping mechanisms; the clamping mechanism is arranged along the length direction of the frame body.
3. A rocket apparatus as recited in claim 2, wherein said gripping mechanism is slidably coupled to said frame; and a spacing adjusting oil cylinder is arranged between the adjacent clamping mechanisms.
4. A rocket apparatus as recited in claim 1, further comprising an annular toothed disc for driving said loading plate in rotation; the fluted disc is fixedly connected with the loading disc.
5. A rocket apparatus as recited in claim 1, wherein said connecting device further comprises a telescoping cylinder for pushing said connecting rod in axial movement thereof.
6. A rocket apparatus as recited in claim 1, wherein said connecting device further comprises a rotary motor for driving said connecting rod to rotate radially thereof.
7. A rocket erection method, characterized in that the rocket erection is performed by using a rocket erection device according to any one of claims 1 to 6, comprising:
loading the rocket on a loading frame;
the loading frame is fixed on the loading disc through a connecting pin shaft, so that the loading frame is in a loading state;
rotating the loading disc to a stand-by vertical position, and removing the connecting pin shaft to enable the loading frame to be separated from the loading state;
the erection platform is fixedly connected with the loading frame through the connecting device, so that the loading frame is in an erection state;
the hydraulic oil is utilized to push the piston rod to do arc motion, and the rocket loaded on the loading frame is driven to be erected on the launching pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210318532.4A CN114754625B (en) | 2022-03-29 | 2022-03-29 | Rocket erection device and rocket erection method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210318532.4A CN114754625B (en) | 2022-03-29 | 2022-03-29 | Rocket erection device and rocket erection method |
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| CN114754625A CN114754625A (en) | 2022-07-15 |
| CN114754625B true CN114754625B (en) | 2023-09-29 |
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| CN202210318532.4A Active CN114754625B (en) | 2022-03-29 | 2022-03-29 | Rocket erection device and rocket erection method |
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Families Citing this family (1)
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| CN115200407B (en) * | 2022-08-01 | 2023-08-18 | 东方空间技术(山东)有限公司 | Offshore suspension type rocket launching platform, rocket launching device and launching method |
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