CN114216365A - Simple rocket erecting device - Google Patents
Simple rocket erecting device Download PDFInfo
- Publication number
- CN114216365A CN114216365A CN202111308110.0A CN202111308110A CN114216365A CN 114216365 A CN114216365 A CN 114216365A CN 202111308110 A CN202111308110 A CN 202111308110A CN 114216365 A CN114216365 A CN 114216365A
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- Prior art keywords
- rocket
- erecting
- base
- arm
- easel
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- 230000007246 mechanism Effects 0.000 claims abstract description 21
- 238000006243 chemical reaction Methods 0.000 claims abstract description 13
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 5
- 210000000080 chela (arthropods) Anatomy 0.000 abstract 3
- 239000000725 suspension Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Images
Classifications
-
- 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
Abstract
The utility model relates to a rocket simply erects device, including erecting the arm and erecting the base, it is located the side of rocket launching pad and arranges to erect the base, the one end of erecting the arm is articulated mutually with erecting the base, the side interval arrangement who erects the base has auxiliary support seat, rocket launching pad and auxiliary support seat are located the both sides of erecting the base respectively, it is provided with the supporting part to rise one side that the arm is close to the rocket body, the afterbody of rocket body is provided with conversion equipment, it still is provided with on the erecting arm and embraces pincers mechanism, it lies in between two supporting parts far away from erecting the base to embrace pincers mechanism, it is connected with the hoist cable of crane to embrace pincers mechanism or the supporting part far away from erecting the base, it is less than the height of rocket launching pad to rise the height of erecting the base. The application has the following expected technical effects: the rocket body is erected through the single crane, the required equipment investment is low, the structure is simple, the development period is short, the development cost is low, and the rocket body is convenient to operate and short in erection time.
Description
Technical Field
The application relates to the technical field of rockets, in particular to a simple rocket erecting device.
Background
After the rocket is horizontally transported to a launching field, the rocket needs to be converted into a vertical state from a horizontal state, and in the prior art, a launching vehicle is generally adopted for erecting the rocket, a winch is adopted for erecting the rocket, or a double-crane is adopted for overturning the rocket. Both a launching vehicle and a winch need to invest a large amount of capital, and the development cycle is long, so that the development requirement of the commercial space rocket is not met; although the double-crane is low in cost, the double-crane needs more equipment, is complex to operate, has long operation time and poor wind resistance, and thus needs to be improved.
Disclosure of Invention
In order to solve the problem that the rocket is inconvenient to erect or high in manufacturing cost after being transported to a launching field, the simple rocket erecting device is provided.
The application provides a simple rocket erecting device, which adopts the following technical scheme:
a simple rocket erecting device comprises erecting arms and erecting bases, wherein the erecting bases are arranged on the side edges of a rocket launching pad, one end of each erecting arm is hinged to the erecting bases, auxiliary supporting seats used for supporting the erecting arms are arranged on the side edges of the erecting bases at intervals, the rocket launching pad and the auxiliary supporting seats are respectively arranged on two sides of the erecting bases, one side, close to a rocket body, of each erecting arm is provided with a plurality of supporting parts arranged at intervals, the tail part of the rocket body is provided with a conversion device which can be connected with the erecting arms and can be connected with the rocket launching pad, each erecting arm is further provided with a holding clamp mechanism, the holding clamp mechanisms are arranged between two supporting parts which are farthest away from the erecting bases, and the holding clamp mechanisms or the supporting parts which are farthest away from the erecting bases are connected with slings of cranes, the height of the erecting base is lower than that of the rocket launching pad.
Furthermore, the vertical arm is a truss structure or a frame structure made of steel.
Furthermore, the height of the auxiliary supporting seat is consistent with that of the erecting base, and the rocket body is in a horizontal state before being hoisted.
Further, the distance D1 between the auxiliary support seat and the erecting base is greater than the distance D2 between the auxiliary support seat and the erecting arm away from the hinged end.
Furthermore, the holding clamp mechanism comprises two groups of holding clamp bases and arc-shaped clamping arms driven to rotate by cylinders or oil cylinders, one ends of the arc-shaped clamping arms are hinged to the holding clamp bases, the holding clamp bases are installed on the vertical arms, and the two groups of arc-shaped clamping arms are driven to mutually approach and rotate to clamp the rocket body.
Furthermore, the outer side surface of the holding clamp base is hinged with a movable connecting lug connected with a sling of a crane.
Furthermore, a connecting seat matched with the conversion device is arranged at the end part of the erecting arm close to the erecting base, and the connecting seat is just level with the upper end face of the rocket launching pad when the erecting arm is in a vertical state.
Furthermore, the surface that the supporting part is connected with the rocket body sets up to the concave arc face, just be provided with the elastic rubber board on the concave arc face, be provided with the non-slip texture on the elastic rubber board.
Furthermore, the top of the auxiliary supporting seat is provided with an elastic rubber block.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the rocket body can be erected through a single crane, the required equipment investment is low, the structure is simple, the development period is short, and the development cost is low;
2. the operation time for erecting the rocket body is short, and the rocket can adapt to the launching task of the commercial space rocket with non-operational requirements.
3. Belongs to a non-supported launch rocket and has wide range of application to the field level.
Drawings
Fig. 1 is a schematic structural view of a rocket simple-structure erecting device according to an embodiment of the present application before hoisting.
Fig. 2 is a schematic structural view of a rocket simple-construction lifting device in the embodiment of the present application.
Fig. 3 is a schematic structural diagram of the rocket simple-structure erecting device according to the embodiment of the present application after being lifted.
Fig. 4 is a schematic structural diagram of a support portion according to an embodiment of the present application.
Description of reference numerals:
101. a rocket launching pad; 102. a rocket body; 103. a conversion device; 104. a sling; 1. a vertical arm; 2. erecting a base; 3. an auxiliary support seat; 31. an elastic rubber block; 4. a support portion; 41. an elastic rubber plate; 5. a clamp holding mechanism; 51. a clasping clamp base; 52. an arc-shaped clamping arm; 53. the movable connecting lug; 6. a connecting seat.
Detailed Description
The present application is described in further detail below with reference to figures 1-4.
The embodiment of the application discloses a simple rocket erecting device. Referring to fig. 1-3, the rocket simple erecting device comprises an erecting arm 1 and an erecting base 2, the erecting base 2 is arranged at the side of a rocket launching platform 101, one end of the erecting arm 1 is hinged with the erecting base 2, auxiliary supporting seats 3 for supporting the erecting arm 1 are arranged at intervals at the side of the erecting base 2, the rocket launching platform 101 and the auxiliary supporting seats 3 are respectively arranged at two sides of the erecting base 2, one side of the erecting arm 1 close to a rocket body 102 is provided with a plurality of supporting parts 4 which are arranged at intervals, the tail part of the rocket body 102 is provided with a conversion device 103 which can be connected with the erecting arm 1 and can be connected with the rocket launching platform 101, the erecting arm 1 is also provided with a holding clamp mechanism 5, the holding clamp mechanism 5 is arranged between two supporting parts 4 which are farthest from the erecting base 2, a sling 104 of a crane of the holding clamp mechanism 5 is connected (in other embodiments, the sling 104 can also be connected with the supporting part 4 which is farthest from the erecting base 2), the height of the erecting bed 2 is lower than that of the rocket launching pad 101.
The operation process and the implementation principle of the simple rocket erecting device in the embodiment of the application are as follows:
before hoisting, the rocket body 102 is horizontally placed on the lifting arm 1 in a horizontal state, a plurality of groups of supporting parts 4 are used for supporting and stabilizing the rocket body 102, the holding clamp mechanism 5 is started simultaneously, the holding clamp mechanism 5 is used for clamping the rocket body 102, the conversion device 103 at the tail part of the rocket body 102 is fixed at the tail part of the lifting arm 1, then the sling 104 of a crane is connected with the holding clamp mechanism 5, the crane is slowly lifted, the rocket body 102 is ensured to be in a vertical state, the conversion device 103 is connected to the rocket launching platform 1018, then the holding clamp mechanism 5 is unlocked, and the connection between the conversion device 103 and the lifting arm 1 is unlocked. The crane then lowers the vertical arm 1 to the horizontal position, the front end of the vertical arm 1 is supported by the auxiliary support base 3, and the vertical operation of the rocket body 102 is finished.
The simple rocket erecting device with the structural design can erect the rocket body 102 through the single crane, the required equipment investment is less, the structure is simple, the development period is short, and the development cost is low; the operation time for erecting the rocket body 102 is short, and the rocket can adapt to the launching task of the commercial space rocket which is not required by combat; belongs to a non-supported launch rocket and has wide range of application to the field level.
In order to solve the problems that the common erecting arm 1 is unstable in structure, heavy in weight, difficult to hoist and the like, the erecting arm 1 is a truss structure or a frame structure made of steel, firstly the steel has better structural strength, the material is convenient to obtain, the manufactured erecting arm 1 is firm, secondly the weight of the truss structure or the frame structure is also small, and the single hoisting is convenient, the erecting arm 1 is hoisted fast and easily, and the rocket body 102 fixed on the erecting arm 1 is fixed.
Referring to fig. 1 and 3, in order to solve the problem that the rocket body 102 is easy to slide due to the fact that the vertical arm 1 is not horizontal in the process of installing the rocket body 102 on the vertical arm 1, the height of the auxiliary support base 3 is consistent with that of the vertical base 2, the rocket body 102 is in a horizontal state before being lifted, and the vertical arm 1 is supported by the auxiliary support base 3 and the vertical base 2 before being lifted, so that the vertical arm 1 can be kept in a relatively horizontal state, and the rocket body 102 is not easy to slide due to inclination in the process of installing the rocket body 102 later, and installation is more efficient.
In order to solve the fragile problem of rigid contact between the vertical arm 1 and the auxiliary support seat 3, the top of the auxiliary support seat 3 is provided with an elastic rubber block 31, and the elastic rubber block 31 has better impact force and shock absorption effects of alleviating, thereby realizing 'soft contact' between the vertical arm 1 and the auxiliary support seat 3 and prolonging the service life.
Referring to fig. 1 and 3, after the rocket body 102 is installed on the erecting arm 1, the pressure on the hinge point between the erecting arm 1 and the erecting base 2 is also large due to too large weight, and in order to solve the problem that the hinge point is easily damaged, the distance D1 between the auxiliary supporting seat 3 and the erecting base 2 is greater than the distance D2 between the auxiliary supporting seat 3 and the erecting arm 1 away from the hinge end, so that the weight of the head of the rocket body 102 can be pressed on the auxiliary supporting seat 3 as much as possible, the pressure on the hinge point between the erecting arm 1 and the erecting base 2 is reduced, and the rocket body has a good protection effect on the hinge point between the erecting arm 1 and the erecting base 2 and is not easily damaged.
Referring to fig. 1-3, in order to solve the problem that the holding-clamp mechanism 5 is inconvenient to install, the holding-clamp mechanism 5 includes two sets of holding-clamp bases 51 and arc-shaped clamping arms 52 driven to rotate by cylinders or oil cylinders, one ends of the arc-shaped clamping arms 52 are hinged to the holding-clamp bases 51, the holding-clamp bases 51 are installed on the vertical arm 1, the two sets of arc-shaped clamping arms 52 are driven to mutually approach and rotate to clamp the rocket body 102, and the holding-clamp bases 51 provide stable installation positions for the arc-shaped clamping arms 52 so that the arc-shaped clamping arms 52 can stably clamp the rocket body 102.
Referring to fig. 1 to 3, in order to solve the problem of difficult connection of the suspension cable 104, the outer side surface of the clasping clamp base 51 is hinged with a movable connecting lug 53 connected with the suspension cable 104 of the crane, the clasping clamp base 51 provides a stable mounting position for the movable connecting lug 53, and a firmer rotation connection relationship can be realized between the movable connecting lug 53 and the suspension cable 104, so that the suspension cable 104 can stably and efficiently drive the rocket body 102 to a vertical state.
Referring to fig. 1-3, in order to solve the problem of difficult connection between the vertical arm 1 and the conversion device 103 at the tail of the rocket body 102, the end of the vertical arm 1 close to the vertical base 2 is provided with a connecting seat 6 matched with the conversion device 103, when the vertical arm 1 is in a vertical state, the connecting seat 6 is just flush with the upper end face of the rocket launching pad 101, and the connecting seat 6 not only facilitates the connection of the conversion device 103 with the vertical arm 1, but also can further support and stabilize the rocket body 102 until the rocket body 102 is vertical.
Referring to fig. 1 and 4, in order to solve the problem of not laminating between the surface of supporting part 4 and rocket body 102, the surface that supporting part 4 is connected with rocket body 102 sets up to the concave arc face, and be provided with elastic rubber plate 41 on the concave arc face, be provided with anti-skidding line on the elastic rubber plate 41, concave arc face just can with the convex surface looks adaptation of rocket body 102, and elastic rubber plate 41 still has certain impact force and the shock attenuation effect of alleviating, have certain guard action to the surface of rocket body 102, simultaneously the protection line on the elastic rubber plate 41, also can effectively prevent rocket body 102 from sliding, make things convenient for rocket body 102 to install fixedly fast.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (9)
1. A simple rocket erecting device is characterized in that: the rocket launching device comprises a lifting vertical arm (1) and a lifting vertical base (2), wherein the lifting vertical base (2) is arranged on the side of a rocket launching pad (101), one end of the lifting vertical arm (1) is hinged to the lifting vertical base (2), auxiliary supporting seats (3) for supporting the lifting vertical arm (1) are arranged on the side of the lifting vertical base (2) at intervals, the rocket launching pad (101) and the auxiliary supporting seats (3) are respectively arranged on two sides of the lifting vertical base (2), one side, close to the rocket body (102), of the lifting vertical arm (1) is provided with a plurality of supporting parts (4) which are arranged at intervals, the tail part of the rocket body (102) is provided with a conversion device (103) which can be connected with the lifting vertical arm (1) and can be connected with the rocket launching pad (101), the lifting vertical arm (1) is further provided with a holding clamp mechanism (5), and the holding clamp mechanism (5) is located on the two supporting parts (4) farthest from the lifting vertical base (2) ) The holding clamp mechanism (5) or the support part (4) farthest away from the erecting base (2) is connected with a sling (104) of a crane, and the height of the erecting base (2) is lower than that of the rocket launching platform (101).
2. A rocket easel erection device according to claim 1 and wherein: the vertical arm (1) is a truss structure or a frame structure made of steel.
3. A rocket easel erection device according to claim 1 and wherein: the height of the auxiliary supporting seat (3) is consistent with that of the erecting base (2), and the rocket body (102) is in a horizontal state before hoisting.
4. A rocket easel erection device according to claim 3 and wherein: the distance D1 between the auxiliary supporting seat (3) and the erecting base (2) is greater than the distance D2 between the auxiliary supporting seat (3) and the erecting arm (1) far away from the hinged end.
5. A rocket easel erection device according to claim 1 and wherein: the holding clamp mechanism (5) comprises two sets of holding clamp bases (51) and arc-shaped clamping arms (52) driven to rotate by cylinders or oil cylinders, one ends of the arc-shaped clamping arms (52) are hinged to the holding clamp bases (51), the holding clamp bases (51) are installed on the vertical arm (1), and the two sets of arc-shaped clamping arms (52) are driven to mutually approach and rotate to clamp the rocket body (102).
6. A rocket easel erection device according to claim 5 and wherein: the outer side surface of the clamp base (51) is hinged with a movable connecting lug (53) connected with a sling (104) of a crane.
7. A rocket easel erection device according to claim 1 and wherein: the end part of the vertical arm (1) close to the vertical base (2) is provided with a connecting seat (6) matched with the conversion device (103), and when the vertical arm (1) is in a vertical state, the connecting seat (6) is just flush with the upper end face of the rocket launching pad (101).
8. A rocket easel erection device according to claim 1 and wherein: the surface of the supporting part (4) connected with the rocket body (102) is a concave arc surface, an elastic rubber plate (41) is arranged on the concave arc surface, and anti-skid grains are arranged on the elastic rubber plate (41).
9. A rocket easel erection device according to claim 1 and wherein: and an elastic rubber block (31) is arranged at the top of the auxiliary supporting seat (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111308110.0A CN114216365A (en) | 2021-11-05 | 2021-11-05 | Simple rocket erecting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111308110.0A CN114216365A (en) | 2021-11-05 | 2021-11-05 | Simple rocket erecting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114216365A true CN114216365A (en) | 2022-03-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111308110.0A Pending CN114216365A (en) | 2021-11-05 | 2021-11-05 | Simple rocket erecting device |
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| CN (1) | CN114216365A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000247300A (en) * | 1999-02-26 | 2000-09-12 | Ishikawajima Harima Heavy Ind Co Ltd | Rocket launcher and rocket launch complex equipment |
| JP2007045191A (en) * | 2005-08-05 | 2007-02-22 | Kawasaki Heavy Ind Ltd | Rocket raising assistance device in rocket maintenance system |
| RU2354593C1 (en) * | 2007-10-01 | 2009-05-10 | Сергей Евгеньевич Варламов | Installation to launch rockets from moon and method of preparing rocket for launching |
| CN203259340U (en) * | 2013-05-09 | 2013-10-30 | 重庆齿轮箱有限责任公司 | Variable pitch gear box overturn no-load test device |
| CN109764749A (en) * | 2018-12-07 | 2019-05-17 | 湖北航天飞行器研究所 | Rocket weapon or transmitter emission system and method |
| CN110274520A (en) * | 2019-06-13 | 2019-09-24 | 蓝箭航天空间科技股份有限公司 | Perpendicular device and rocket launching auxiliary system are played for rocket launching |
| CN111006546A (en) * | 2019-11-05 | 2020-04-14 | 蓝箭航天空间科技股份有限公司 | Rocket erecting arm |
| CN216482529U (en) * | 2021-11-05 | 2022-05-10 | 航天科工火箭技术有限公司 | Simple rocket erecting device |
-
2021
- 2021-11-05 CN CN202111308110.0A patent/CN114216365A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000247300A (en) * | 1999-02-26 | 2000-09-12 | Ishikawajima Harima Heavy Ind Co Ltd | Rocket launcher and rocket launch complex equipment |
| JP2007045191A (en) * | 2005-08-05 | 2007-02-22 | Kawasaki Heavy Ind Ltd | Rocket raising assistance device in rocket maintenance system |
| RU2354593C1 (en) * | 2007-10-01 | 2009-05-10 | Сергей Евгеньевич Варламов | Installation to launch rockets from moon and method of preparing rocket for launching |
| CN203259340U (en) * | 2013-05-09 | 2013-10-30 | 重庆齿轮箱有限责任公司 | Variable pitch gear box overturn no-load test device |
| CN109764749A (en) * | 2018-12-07 | 2019-05-17 | 湖北航天飞行器研究所 | Rocket weapon or transmitter emission system and method |
| CN110274520A (en) * | 2019-06-13 | 2019-09-24 | 蓝箭航天空间科技股份有限公司 | Perpendicular device and rocket launching auxiliary system are played for rocket launching |
| CN111006546A (en) * | 2019-11-05 | 2020-04-14 | 蓝箭航天空间科技股份有限公司 | Rocket erecting arm |
| CN216482529U (en) * | 2021-11-05 | 2022-05-10 | 航天科工火箭技术有限公司 | Simple rocket erecting device |
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