CN114771397B - Supporting device for large rocket transportation and use method thereof - Google Patents
Supporting device for large rocket transportation and use method thereof Download PDFInfo
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- CN114771397B CN114771397B CN202210404290.0A CN202210404290A CN114771397B CN 114771397 B CN114771397 B CN 114771397B CN 202210404290 A CN202210404290 A CN 202210404290A CN 114771397 B CN114771397 B CN 114771397B
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- 238000000034 method Methods 0.000 title claims abstract description 14
- 238000006073 displacement reaction Methods 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 4
- 230000005540 biological transmission 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
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 210000005069 ears Anatomy 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P7/00—Securing or covering of load on vehicles
- B60P7/06—Securing of load
- B60P7/135—Securing or supporting by load bracing means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P7/00—Securing or covering of load on vehicles
- B60P7/06—Securing of load
- B60P7/16—Protecting against shocks
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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
- F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
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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
- F41F3/052—Means for securing the rocket in the launching apparatus
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention relates to the rocket field, in particular to a supporting device for transporting a large rocket and a use method thereof, comprising a rocket body and a erection unit, wherein the erection unit comprises a frame, an erection part for clamping the rocket body and a plurality of floating brackets which are arranged on the frame in a floating manner, the vertical part is arranged on the frame, the lower end of the floating bracket is fixedly arranged on the frame, and the upper end of the floating bracket can prop against the side wall surface of the rocket body. The floating bracket is arranged on the frame in a floating manner, when the vehicle drives the frame to undulate, the floating bracket can maintain the original supporting height, the rocket body is supported, the undulation displacement height of the rocket body in the vertical direction is reduced, meanwhile, the vibration force of the vehicle body and the frame can be counteracted, the rocket body and the frame are prevented from being in hard contact, and the collision probability of the rocket body can be effectively reduced.
Description
Technical Field
The invention relates to the technical field of rockets, in particular to a supporting device for large rocket transportation and a using method thereof.
Background
When the large rocket launcher is used for transporting the rocket, the rocket is stably fixed on the vertical boom through limit structures such as anchor ears, brackets and the like; during transportation, the whole rocket is in a horizontal installation state, and when the launching vehicle runs on a road surface with poor road conditions, the rocket and the launching vehicle shake synchronously under the fixation of the limiting structure and the vertical arm.
In the shaking process, the rocket body and the vertical arm possibly jolt along with the vehicle body, the vertical arm possibly rotates around the hinged position of the rocket body and the vertical arm, the end, away from the vertical arm, hinged with the vehicle body can be fluctuated up and down, further the end part of the vertical arm is in hard contact with the vehicle body, the end part of the rocket body is in hard contact with the limiting structure on the vertical arm, the hard contact part of the vertical arm and the end part of the rocket body is easy to collide, the damage to the outer wall of the vertical arm or the end part of the rocket body is easy to cause, the subsequent vertical lifting of the rocket body is influenced, and the quality of the rocket body is also easy to influence.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a supporting device for transporting a large rocket and a using method thereof, which are used for solving the problems that when a bumpy road condition is met in the transportation process, a rocket body is easy to be in hard contact with a frame or a limiting structure, and then the rocket body is bumped.
In order to achieve the above object, the basic scheme of the present invention is as follows: the utility model provides a strutting arrangement of large-scale rocket transportation, includes and erects the unit, erects the unit and includes the frame, erects the portion and a plurality of floating bracket that float and set up on the frame to rocket body centre gripping, erects the portion and installs on the frame, and floating bracket's lower extreme fixed mounting is on the frame, and floating bracket's upper end can offset with rocket body's lateral wall face.
The technical principle of the invention is as follows: when the rocket body is mounted on the supporting device, the rocket body is clamped and mounted on the erecting part, and meanwhile, when the rocket body is not erected, the rocket body is propped against a floating bracket on the frame.
When the vehicle moves to transport the rocket body, the rocket body can be limited and supported by the floating bracket and the erection part, so that the rocket body can be stably installed; when meeting the road conditions of jolting, because the floating bracket floats and sets up on the frame, when the vehicle drives the frame and rolls up and down in the twinkling of an eye, the floating bracket can keep original supporting height, supports the rocket body, reduces the fluctuation displacement height of the vertical direction of rocket body, can offset the vibration power of automobile body and frame simultaneously, avoids rocket body and frame to take place hard contact, can effectively reduce the probability that the rocket body took place to collide with, guarantees that the quality of rocket body is good.
Further, the floating bracket comprises a mounting seat, a bracket, an elastic supporting frame and a plurality of springs arranged between the bracket and the supporting frame, the bracket is fixedly arranged on the mounting seat, the axis of the springs can be collinear with the radius of the cross section of the rocket body, the upper ends of the springs are fixedly connected with the lower side of the supporting frame, and the lower ends of the springs are fixedly connected with the upper side of the bracket; the longitudinal section outline of the support frame is arc-shaped and is attached to the rocket body, and the two ends of the support frame, which are at the highest horizontal position of the longitudinal section outline, are propped against the upper side of the bracket.
Through the arrangement, the mounting seat and the bracket can provide stable supporting force for the two ends of the support frame with the highest horizontal position, so that the support frame can stably support the surface of the attached rocket body; meanwhile, when the floating bracket is used for floating and supporting the rocket body, the support frame is attached to the rocket body, the springs absorb vibration force transmitted to the mounting seat and the bracket by the frame, and further the upper ends of the springs can drive the support frame and the rocket body to float, so that the rocket body is prevented from being in hard contact with the frame to cause damage, and the springs can enable the absorption of elastic force to be more stable; meanwhile, the elastic support frame can also generate corresponding deformation under the action of vibration force and then follow up, so that the vibration force can be further absorbed, the purpose of stably wrapping the side wall of the rocket body can be achieved, and the rocket body can be kept stable in transportation.
Further, the spring is a hydro-pneumatic spring, and the hydro-pneumatic spring is located in the center of the support frame.
Through above-mentioned setting, the hydro-pneumatic spring can effectively alleviate and attenuate the vibration of frame department transmission, can let support frame and rocket body more stable.
Further, a support pad is covered on one side of the support frame away from the bracket.
Through above-mentioned setting, when the rocket body is installed on the floating bracket, the lateral wall of rocket body contacts with the back-up pad, and the back-up pad drives support frame and rocket body laminating better, and when jolting takes place, the back-up pad can protect the lateral wall of rocket body, also can avoid rocket body and support frame to take place to collide with.
Further, the rocket body comprises a first clamp capable of clamping the rocket body, the first clamp is fixedly arranged on the frame, and the circle center of the longitudinal section outline of the first clamp and the circle center of the longitudinal section outline of the support frame are positioned on the same horizontal line.
Through the arrangement, the first clamp can further fix the rocket body, and when jolting occurs, the rocket body can be stably attached to the floating bracket, and the end part of the rocket body is attached to the support frame more tightly; simultaneously under the spacing of first clamp, the rocket body and first clamp will play to erect the arm spacing between rocket body and frame, avoid play to erect the arm and take place to rotate around the articulated department with the frame, and then reduce and play to erect the arm and take place the possibility of hard contact with the frame, elastic support frame can carry out auxiliary stay for the unsteady of rocket body tip this moment.
Further, a spring seat is fixedly arranged on the lower surface of the supporting frame and fixedly connected with the upper end of the hydro-pneumatic spring.
Through above-mentioned setting, the spring holder can let the installation of hydro-pneumatic spring more stable, also can the elasticity transmission direction of hydro-pneumatic spring more stable and even.
Further, the erection part comprises an erection frame, an erection arm, an erection cylinder for pushing the erection frame to rotate by 0-90 degrees, a launching platform fixedly connected with the end part of the rocket body, a fixing bracket and a second clamp, one end of the erection frame is hinged with one end of the frame, the launching platform is fixedly arranged at one end, close to the frame, of the erection frame, and the plane where the launching platform is located is perpendicular to the plane where the erection frame is located; the vertical lifting arm is fixedly arranged on the side edge of the vertical lifting frame, one end of the vertical lifting oil cylinder is in sliding connection with the vertical lifting arm and hinged with the vertical lifting arm, and the other end of the vertical lifting oil cylinder is hinged with the frame; the fixed bracket and the second clamp are fixedly arranged on the erection frame, and the circle centers of the longitudinal section outlines of the fixed bracket and the second clamp can be positioned on the same horizontal line with the circle center of the longitudinal section outline of the support frame.
When the rocket body is erected, the first clamp is opened, the second clamp is closed, the rocket body is clamped by the second clamp, the erection cylinder is extended, thrust acts on the erection arm, so that the erection arm drives the erection frame, the launching pad, the fixing bracket and the second clamp to synchronously rotate around the hinge joint with the frame, and when the axis of the rocket body is vertical to the horizontal plane, the extension of the erection cylinder is stopped, so that the rocket body can be erected; the rocket body is convenient and quick to erect.
Further, the device also comprises a negative pressure machine fixedly arranged on the frame, a negative pressure cavity is arranged in the supporting frame, the negative pressure machine is communicated with the negative pressure cavity, and a plurality of negative pressure holes communicated with the negative pressure cavity are arranged on the supporting pad.
Through the arrangement, negative pressure at the negative pressure hole acts on the outer wall of the rocket body, so that the rocket body can be stably attached to the supporting pad, and the supporting frame, the supporting pad and the rocket body can more conveniently float under the support of the hydro-pneumatic spring.
The invention also provides a use method of the large rocket transporting and supporting device, which comprises the following steps:
Step 1: before the rocket body is transported, the erection cylinder is in a contracted state, the included angle between the plane where the erection frame is positioned and the horizontal plane is 0.5-1 degrees, the first clamp on the frame is opened, the second clamp on the erection frame is opened, the end part of the rocket body is fixed with the launching pad, the middle part of the rocket body is propped against the first clamp, the floating bracket, the fixed bracket and the second clamp, and the preinstallation of the rocket body is completed;
Step 2: when the rocket body is transported, the first clamp clamps the rocket body, the second clamp keeps an open state, and the rocket body is attached to the supporting pad; when the vehicle frame jolts along with the vehicle, the supporting pad drives the supporting frame to be attached to the rocket body, the hydro-pneumatic spring supports the supporting frame, the supporting pad and the rocket body, and the hydro-pneumatic spring absorbs vibration force transmitted to the mounting seat and the bracket by the vehicle frame;
Step 3: after the rocket body is transported to a launching place, opening a first clamp, closing a second clamp, and clamping the rocket body by the second clamp; the vertical lifting oil cylinder stretches, thrust acts on the vertical lifting arm, the vertical lifting arm drives the vertical lifting frame, the launching pad, the fixing bracket and the second clamp to synchronously rotate around the hinge joint with the frame, and when the axis of the rocket body is vertical to the horizontal plane, the stretching of the vertical lifting oil cylinder is stopped, so that the vertical lifting of the rocket body is completed.
The technical effect of this scheme: in the step 1, the center of the longitudinal section of the floating bracket, the first clamp, the second clamp, the fixed bracket and the right floating bracket are all positioned between the same horizontal planes, so that after the rocket body is preinstalled, the middle part of the rocket body is propped against the first clamp, the floating bracket, the fixed bracket and the second clamp, the rocket body can be stably supported, and the preinstallation, positioning and installation of the rocket body are simple; in the step 2, when the vehicle jolts in a road section, the hydro-pneumatic spring absorbs vibration force transmitted to the mounting seat and the bracket by the vehicle frame, and the hydro-pneumatic spring drives the support frame, the support pad and the rocket body to float, so that the rocket body is prevented from being in hard contact with the vehicle frame to cause damage; in step 3, through the cooperation of erection hydro-cylinder and erection arm, can control to erect the frame and drive the rocket body and erect, simultaneously, fixed bracket and second clamp can carry out spacing and support to the rocket body steadily for the rocket body can erect steadily.
In step 2, the negative pressure machine is started, negative pressure generated by the negative pressure machine is transmitted to the negative pressure hole through the negative pressure cavity, and the negative pressure at the single negative pressure hole reaches 100-175pa.
Through the arrangement, the negative pressure intensity of the negative pressure hole can be controlled more accurately, the side face of the rocket body can be adsorbed conveniently, and the rocket body can be limited conveniently.
Drawings
Fig. 1 is a schematic diagram of a structure of a supporting device for transporting a large rocket in a front view direction in embodiment 1 of the present invention.
Fig. 2 is an enlarged view of the floating bracket of fig. 1.
Fig. 3 is a cross-sectional view at A-A in fig. 2.
Fig. 4 is a longitudinal cross-sectional view of a floating bracket in a support device for large rocket ship according to embodiment 2 of the present invention.
In the above figures: frame 10, first clamp 101, erection frame 201, erection arm 202, erection cylinder 203, sleeve 213, launching pad 204, fixing bracket 205, second clamp 206, mount 30, bracket 301, support frame 302, spring seat 303, hydro-pneumatic spring 304, support pad 305, negative pressure machine 401, negative pressure cavity 402, negative pressure hole 403, rocket body 50.
Detailed Description
The technical scheme of the invention is further described below with reference to the accompanying drawings and examples.
Example 1
The embodiment of the invention basically discloses a supporting device for transporting a large rocket and a using method thereof, as shown in fig. 1, fig. 2 and fig. 3, comprising an erection unit, the erecting unit comprises a frame 10, an erecting part for clamping the rocket body 50, two floating brackets which are arranged on the frame 10 in a floating manner, and a first clamp 101 which can clamp the rocket body 50, wherein the frame 10 is horizontally arranged, the first clamp 101 is welded on the frame 10, and a cushion layer is glued on the inner wall of the first clamp; as shown in fig. 1, the erection part comprises an erection frame 201, an erection arm 202, an erection cylinder 203 for pushing the erection frame 201 to rotate by 0-90 degrees, a launching pad 204 welded with the end part of the rocket body 50, a fixing bracket 205 and a second clamp 206, wherein the right end of the erection frame 201 is hinged with the right end of the frame 10 through a rotating shaft, the launching pad 204 is welded on the right end of the erection frame 201, and the plane where the launching pad 204 is positioned is vertical to the plane where the erection frame 201 is positioned; the vertical lifting arm 202 is welded on the front side of the vertical lifting frame 201, the upper end of the vertical lifting oil cylinder 203 is in sliding connection with the vertical lifting arm 202 through a sleeve 213, the upper end of the vertical lifting oil cylinder 203 is hinged with the side surface of the sleeve 213, and the lower end of the vertical lifting oil cylinder 203 is hinged with the middle part of the frame 10; the fixing bracket 205 and the second clamp 206 are vertically welded to the upper surface of the erection frame 201, and the second clamp 206 is located at the left side of the fixing bracket 205.
As shown in fig. 3, the floating bracket comprises a mounting seat 30, a bracket 301, an elastic supporting frame 302, a spring seat 303 and a plurality of hydro-pneumatic springs 304 arranged between the bracket 301 and the supporting frame 302, wherein the bracket 301 is welded on the mounting seat 30, the mounting seat 30 is welded on the frame 10, the hydro-pneumatic springs 304 are one in number, the hydro-pneumatic springs 304 are vertically arranged, the axis of the hydro-pneumatic springs 304 can be collinear with the radius of the cross section of the rocket body 50, the spring seat 303 is welded at the center of the lower surface of the supporting frame 302, the spring seat 303 is welded with the upper end of the hydro-pneumatic springs 304, and the lower end of the hydro-pneumatic springs 304 is welded with the upper side of the bracket 301; meanwhile, the longitudinal section profile of the supporting frame 302 is in an arc shape which is attached to the rocket body 50, two ends of the highest horizontal position of the longitudinal section profile of the supporting frame 302 are propped against the upper side of the bracket 301, the circle center of the longitudinal section profile of the first clamp 101 and the circle center of the longitudinal section profile of the supporting frame 302 are positioned on the same horizontal line, the first clamp 101 is positioned on the left side of the vertical frame 201, the first clamp 101, the second clamp 206 and the fixing bracket 205 are positioned between two floating bracket seats, and meanwhile, the circle centers of the longitudinal section profiles of the fixing bracket 205 and the second clamp 206 can be positioned on the same horizontal line with the circle center of the longitudinal section profile of the supporting frame 302.
Further, as shown in fig. 3, a support pad 305 is adhered to the upper side of the support frame 302, and the support pad 305 is made of rubber.
The application method of the large rocket transporting and supporting device comprises the following steps:
step 1: before the rocket body 50 is transported, the lifting cylinder 203 is in a contracted state, the included angle between the plane where the lifting frame 201 is positioned and the horizontal plane is 0.5-1 degrees, the first clamp jaws 101 on the frame 10 are all opened, the second clamp jaws 206 on the lifting frame 201 are all opened, the end part of the rocket body 50 sequentially passes through the left floating bracket, the first clamp jaws 101, the second clamp jaws 206, the fixing bracket 205 and the right floating bracket and then contacts with the launching platform 204, and the launching platform 204 fixes the right end part of the rocket body 50 to finish the pre-installation of the rocket body 50; since the circle centers of the vertical section outlines of the fixed bracket 205 and the second clamp 206 can be positioned on the same horizontal line with the circle center of the vertical section outline of the support frame 302, the circle centers of the vertical section of the left floating bracket, the first clamp 101, the second clamp 206, the fixed bracket 205 and the right floating bracket are all positioned between the same horizontal line, after the rocket body 50 is pre-installed, the middle part of the rocket body 50 is propped against the first clamp 101, the floating bracket, the fixed bracket 205 and the second clamp 206, and the rocket body 50 can be stably supported;
Step 2: when the rocket body 50 is transported, the first clamp 101 clamps the rocket body 50, and the cushion layer contacts with the outer wall of the rocket body 50, so that the end part of the rocket body 50 is tightly attached to the supporting pad 305; meanwhile, under the limit of the first clamp 101, the rocket body 50 and the first clamp 101 limit the vertical boom 202 between the rocket body 50 and the frame 101, so that the vertical boom 202 is prevented from rotating around the hinge joint with the frame 101, and the possibility of hard contact between the vertical boom 202 and the frame 101 is further reduced; at this time, the second clamp 206 is kept in an open state, and the rocket body 50 is attached to the support pad 305; when the vehicle frame 10 jolts along with the vehicle, the support cushion 305 drives the support frame 302 to be attached to the rocket body 50, and the support cushion 305 made of rubber can be stably attached to the rocket body 50 and can protect the side wall of the rocket body 50; meanwhile, the hydro-pneumatic spring 304 supports the support frame 302, the support pad 305 and the rocket body 50, the hydro-pneumatic spring 304 absorbs vibration force transmitted to the mounting seat 30 and the bracket 301 by the frame 10, and the hydro-pneumatic spring 304 drives the support frame 302, the support pad 305 and the rocket body 50 to float, so that damage caused by hard contact between the rocket body 50 and the frame 10 is avoided;
Step 3: after the rocket body 50 is transported to the launching place, the first clamp 101 is opened, the second clamp 206 is closed, and the second clamp 206 clamps the rocket body 50; the erection cylinder 203 stretches, a pushing force acts on the erection arm 202, the sleeve 213 slides along the outer wall of the erection arm 202, the upper end of the erection cylinder 203 is hinged with the sleeve 213, and then the erection cylinder 203 can synchronously deflect, so that the erection arm 202 drives the erection frame 201, the launching pad 204, the fixing bracket 205 and the second clamp 206 to synchronously rotate around the hinged position with the frame 10, and when the axis of the rocket body 50 is vertical to the horizontal plane, the stretching of the erection cylinder 203 is stopped, and the erection of the rocket body 50 can be completed; in this process, the fixing bracket 205 and the second clamp 206 can stably limit and support the rocket body 50, so that the rocket body 50 can stably stand.
Example 2
The difference between the embodiment 2 and the embodiment 1 is basically as shown in fig. 4, and the vacuum pump 401 welded on the frame 10 is further included, a vacuum cavity 402 is disposed in the support frame 302, the vacuum pump 401 is communicated with the vacuum cavity 402, and a plurality of vacuum holes 403 are disposed on the support pad 305 and are communicated with the vacuum cavity 402.
When the rocket body 50 is transported in the step 2, the negative pressure machine 401 is in an open state, negative pressure generated by the negative pressure machine 401 is transmitted to the negative pressure hole 403 through the negative pressure cavity 402, the negative pressure at the single negative pressure hole 403 reaches 120-150pa, and the negative pressure at the negative pressure hole 403 acts on the outer wall of the rocket body 50, so that the rocket body 50 can be stably attached to the supporting pad 305, and the supporting frame 302, the supporting pad 305 and the rocket body 50 are more convenient to float under the support of the hydro-pneumatic spring 304.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (3)
1. The application method of the large rocket transporting and supporting device is characterized by comprising the following steps of:
Preparing a supporting device for transporting a large rocket, comprising a erection unit, wherein the erection unit comprises a frame, an erection part for clamping a rocket body and a plurality of floating brackets which are arranged on the frame in a floating manner, the erection part is arranged on the frame, the lower end of each floating bracket is fixedly arranged on the frame, and the upper end of each floating bracket can be propped against the side wall surface of the rocket body; the floating bracket comprises a mounting seat, a bracket, an elastic supporting frame and a plurality of springs arranged between the bracket and the supporting frame, the bracket is fixedly arranged on the mounting seat, the axis of the springs can be collinear with the radius of the cross section of the rocket body, the upper ends of the springs are fixedly connected with the lower side of the supporting frame, and the lower ends of the springs are fixedly connected with the upper side of the bracket; the longitudinal section outline of the support frame is arc-shaped and is attached to the rocket body, and the two ends of the support frame with the highest horizontal position of the longitudinal section outline are propped against the upper side of the bracket; the vertical lifting part comprises a vertical lifting frame, a vertical lifting arm, a vertical lifting oil cylinder for pushing the vertical lifting frame to rotate by 0-90 degrees, a launching pad welded with the end part of the rocket body, a fixed bracket and a second clamp, wherein the right end of the vertical lifting frame is hinged with the right end of the frame through a rotating shaft, the launching pad is welded on the right end of the vertical lifting frame, and the plane where the launching pad is located is perpendicular to the plane where the vertical lifting frame is located; the upper end of the erection cylinder is hinged with the side surface of the sleeve, and the lower end of the erection cylinder is hinged with the middle part of the frame; the fixed bracket and the second clamp are vertically welded on the upper surface of the erection frame, and the second clamp is positioned on the left side of the fixed bracket; the circle centers of the fixing bracket and the second clamp longitudinal section outline can be positioned on the same horizontal line with the circle center of the support frame longitudinal section outline;
one side of the support frame far away from the bracket is covered with a support pad;
The negative pressure machine is welded on the frame, a negative pressure cavity is arranged in the support frame, the negative pressure machine is communicated with the negative pressure cavity, and a plurality of negative pressure holes communicated with the negative pressure cavity are formed in the support pad;
The spring is a hydro-pneumatic spring, and the hydro-pneumatic spring is positioned at the center of the support frame;
The first clamp is fixedly arranged on the frame, and the circle center of the longitudinal section outline of the first clamp and the circle center of the longitudinal section outline of the support frame are positioned on the same horizontal line;
Step 1: before the rocket body is transported, the lifting oil cylinder is in a contracted state, the included angle between the plane where the lifting frame is positioned and the horizontal plane is 0.5-1 degrees, the first clamp on the frame is opened, the second clamp on the lifting frame is opened, and the end part of the rocket body sequentially passes through the left floating bracket, the first clamp, the second clamp, the fixing bracket and the right floating bracket and then contacts with the launching platform, and the launching platform fixes the right end of the rocket body to finish the preinstallation of the rocket body;
Step 2: when the rocket body is transported, the first clamp clamps the rocket body, and the cushion layer is contacted with the outer wall of the rocket body, so that the end part of the rocket body is tightly attached to the supporting pad; simultaneously, under the limit of the first clamp, the rocket body and the first clamp limit the vertical arm between the rocket body and the frame, so that the vertical arm is prevented from rotating around the hinge joint with the frame, and the possibility of hard contact between the vertical arm and the frame is further reduced; at the moment, the second clamp keeps an open state, and the rocket body (50) is attached to the supporting pad; when the vehicle frame jolts along with the vehicle, the supporting pad drives the supporting frame to be attached to the rocket body, and the supporting pad made of rubber can be stably attached to the rocket body and can protect the side wall of the rocket body; meanwhile, the hydro-pneumatic spring supports the support frame, the support pad and the rocket body, the hydro-pneumatic spring absorbs vibration force transmitted to the mounting seat and the bracket by the frame, and the hydro-pneumatic spring drives the support frame, the support pad and the rocket body to float;
Step 3: after the rocket body is transported to a launching place, opening a first clamp, closing a second clamp, and clamping the rocket body by the second clamp; the vertical lifting oil cylinder stretches, thrust acts on the vertical lifting arm, the sleeve slides along the outer wall of the vertical lifting arm, the upper end of the vertical lifting oil cylinder is hinged with the sleeve, and then the vertical lifting oil cylinder can synchronously deflect, so that the vertical lifting arm drives the vertical lifting frame, the launching pad, the fixing bracket and the second clamp to synchronously rotate around the hinged position with the frame, and when the axis of the rocket body is vertical to the horizontal plane, the stretching of the vertical lifting oil cylinder is stopped, so that the vertical lifting of the rocket body can be completed.
2. The method of claim 1, wherein a spring seat is fixedly mounted on the lower surface of the support frame and fixedly connected to the upper end of the hydro-pneumatic spring.
3. A method of using a large rocket transporting support according to claim 2 wherein in step 2, the negative pressure machine is turned on and negative pressure is transferred to the negative pressure hole through the negative pressure chamber, and the negative pressure in the single negative pressure hole reaches 100-175pa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210404290.0A CN114771397B (en) | 2022-04-18 | 2022-04-18 | Supporting device for large rocket transportation and use method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210404290.0A CN114771397B (en) | 2022-04-18 | 2022-04-18 | Supporting device for large rocket transportation and use method thereof |
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| Publication Number | Publication Date |
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| CN114771397A CN114771397A (en) | 2022-07-22 |
| CN114771397B true CN114771397B (en) | 2024-09-06 |
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| CN202210404290.0A Active CN114771397B (en) | 2022-04-18 | 2022-04-18 | Supporting device for large rocket transportation and use method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117549020B (en) * | 2023-04-11 | 2024-04-19 | 北京星河动力装备科技有限公司 | Assembly tool and assembly method of rocket rail attitude control power system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN210952524U (en) * | 2019-02-28 | 2020-07-07 | 北京零壹空间科技集团有限公司 | Movable rocket launching cradle and rocket launching vehicle |
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| CN111256534B (en) * | 2020-03-05 | 2022-02-01 | 北京中科宇航技术有限公司 | Rocket transport device and launching device |
| CN212555990U (en) * | 2020-07-16 | 2021-02-19 | 秦皇岛优益创联特种车辆制造有限公司 | Rocket mobile launching vehicle |
| CN113959259A (en) * | 2021-10-29 | 2022-01-21 | 重庆零壹空间科技集团有限公司 | Launch vehicle with locking mechanism and auxiliary erecting device |
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| CN210952524U (en) * | 2019-02-28 | 2020-07-07 | 北京零壹空间科技集团有限公司 | Movable rocket launching cradle and rocket launching vehicle |
| 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 |
| CN212737902U (en) * | 2020-07-17 | 2021-03-19 | 安徽华路畅安建材有限公司 | Prefabricated well of concrete is with conveyer |
| CN113043935A (en) * | 2021-03-18 | 2021-06-29 | 星河动力(北京)空间科技有限公司 | Launch preparation device for carrier rocket, launch preparation method for carrier rocket, and launch system |
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