CN111121537A - Sounding rocket system - Google Patents
Sounding rocket system Download PDFInfo
- Publication number
- CN111121537A CN111121537A CN201911389823.7A CN201911389823A CN111121537A CN 111121537 A CN111121537 A CN 111121537A CN 201911389823 A CN201911389823 A CN 201911389823A CN 111121537 A CN111121537 A CN 111121537A
- Authority
- CN
- China
- Prior art keywords
- sounding rocket
- platform
- movable platform
- fixed
- sounding
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000429 assembly Methods 0.000 claims description 8
- 230000000712 assembly Effects 0.000 claims description 8
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 5
- 229910052804 chromium Inorganic materials 0.000 claims description 5
- 239000011651 chromium Substances 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract 1
- 238000003466 welding Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 5
- 235000015842 Hesperis Nutrition 0.000 description 4
- 235000012633 Iberis amara Nutrition 0.000 description 4
- 238000012360 testing method Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002860 competitive effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000007747 plating Methods 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses a sounding rocket system, which comprises a sounding rocket and a launching device, wherein the launching device is arranged on the sounding rocket; the transmitting device includes: the ball head pin assembly comprises a fixed platform, a movable platform positioned above the fixed platform and a ball head pin assembly supported between the fixed platform and the movable platform; the ball head pin assembly comprises a ball head which is clamped by the movable platform and is matched with the spherical surface of the movable platform, a pin shaft which is connected with the ball head and is movably connected with the fixed platform, and an adjusting threaded sleeve which is in threaded connection with the pin shaft and is used for driving the pin shaft to do lifting motion along the axial direction of the pin shaft so as to adjust the relative inclination angle between the movable platform and the fixed platform; the periphery wall circumference of sounding rocket tail section is equipped with a plurality of fin that can support in the activity platform, and the lower terminal surface of fin flushes with the lower bottom surface of sounding rocket tail end. The supporting leg type simple launching device is adopted, so that the launching requirement of the simple sounding rocket can be met; and simple and quick rocket launching tasks can be performed in a site with simple facilities, and the dependence of the sounding rocket on a special launching site is reduced.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a sounding rocket system.
Background
The sounding rocket is used for space environment detection and space scientific experiments in the near ground, the flying height is between a sounding balloon and a low-orbit artificial earth satellite, and the sounding rocket is a unique field detection tool for 50 km-300 km in the near ground space. Sounding rockets are typically uncontrolled. The launching modes of the sounding rocket can be generally divided into a guide rail type and a cannon type.
With the rapid development of commercial aerospace and the increase of scientific test sounding rocket launching tasks in recent years, various space cable control projects of China are developed in a competitive mode, all test bases originally used for rocket launching tasks are in a launching task saturation state, and corresponding test bases need to preferentially guarantee large rocket launching tasks of national models. For small-sized sounding rockets for commercial aerospace and scientific experiments, the launching task is uncertain, cost factors are also considered comprehensively, the existing rocket launching bases are often not used, the launching bases are uneconomical to build independently, a large amount of capital is required to be invested, launching sites and launching devices are required to be built in advance, and the launching devices are required to be built according to special technical requirements of the sounding rockets, so that the universality is poor.
Therefore, there is an urgent need for a sounding rocket system that can temporarily find a site that can be simply processed to perform a rocket launching task.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that launching of a sounding rocket in the prior art depends on a special launching site, thereby providing a sounding rocket system.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a sounding rocket system comprises a sounding rocket and a launching device for providing support for the sounding rocket; the transmitting device includes:
the fixed platform is fixedly connected with the foundation plate fixed on the ground;
the movable platform is positioned above the fixed platform and used for supporting an rocket body of the sounding rocket;
a height adjustment mechanism comprising at least three ball pin assemblies supported between the fixed platform and the movable platform; the ball pin assembly comprises a ball head clamped by the movable platform and matched with the spherical surface of the movable platform, a pin shaft connected to the ball head and movably connected with the fixed platform, and an adjusting threaded sleeve which is in threaded connection with the pin shaft and is used for driving the pin shaft to do lifting motion along the axial direction of the pin shaft so as to adjust the relative inclination angle between the movable platform and the fixed platform;
the outer circumferential wall of the tail section of the sounding rocket is circumferentially provided with a plurality of tail wings which can be supported on the movable platform, and the lower end surface of each tail wing and the lower bottom surface of the tail end of the sounding rocket are positioned on the same plane.
Furthermore, the bottom of the movable platform is connected with a ball head seat, the bottom end surface of the ball head seat is a concave spherical surface, and the ball head is buckled in a spherical space formed by the enclosing of the concave spherical surface.
Further, the bottom of the movable platform is fixedly connected with a fixed block, and a T-shaped clamping groove is formed in the fixed block; the ball cup includes:
the upper sliding block is in sliding fit with the fixed block and is provided with a T-shaped clamping head in buckling fit with the T-shaped clamping groove;
and the lower sliding block is fixedly connected to the upper sliding block, and the bottom end of the lower sliding block is provided with the concave spherical surface.
Further, a chromium coating is arranged on the concave spherical surface of the lower sliding block.
Furthermore, the fixed platform is provided with a mounting through hole, a pin shaft of the ball pin assembly penetrates through the mounting through hole, and the adjusting threaded sleeve comprises an upper threaded sleeve and a lower threaded sleeve which are in threaded connection with the pin shaft and are respectively positioned at two opposite ends of the fixed platform.
Furthermore, the outer walls of the upper threaded sleeve and the lower threaded sleeve are both connected with traction handles extending along the radial direction of the pin shaft.
Furthermore, a boss structure which is smaller than the diameter of the ball head is formed by cutting one end of the pin shaft connected with the ball head.
Furthermore, the upper threaded sleeve and the lower threaded sleeve are matched with the pin shaft through trapezoidal threads.
Furthermore, fixed platform supports through a plurality of landing legs of four corners position and fixes on the foundatin plate on ground, be equipped with in the middle of fixed platform's the below and fix the water conservancy diversion awl on the foundatin plate, the water conservancy diversion awl is fixed into "people" style of calligraphy structure by two sections domatic relative links up.
The technical scheme of the invention has the following advantages:
1. according to the sounding rocket system provided by the invention, before launching the sounding rocket, the rocket body of the sounding rocket is vertically hung on the movable platform of the launching device, the plurality of ball pin assemblies are movably connected with the fixed platform through pin shafts, and the ball heads are clamped by the movable platform and are in fit connection with the spherical surface of the movable platform; moreover, the launching device can perform simple and quick rocket launching tasks in a site with simple facilities, and reduces the dependence of the sounding rocket on a special launching site.
2. According to the sounding rocket system provided by the invention, the ball head seat and the ball head are connected in a spherical matching manner, the ball head seat can rotate freely relative to the ball head in the spherical space at the periphery of the ball head, when the height and the inclination angle of the movable platform are adjusted, the phenomena of mutual interference and shell clamping cannot occur in the height adjusting process of a plurality of pin shafts, and the adjustment flexibility is better.
3. According to the sounding rocket system provided by the invention, the fixed block on the movable platform is in sliding fit with the upper sliding block of the ball socket, and the T-shaped clamping groove has a limiting effect on the turning motion of the T-shaped clamping head, so that the lower sliding block connected with the upper sliding block is limited to rotate around the spherical surface of the ball head within a smaller space angle adjusting range, and on one hand, the stability of the movable platform and the sounding rocket after inclination adjustment can be improved, and further the success rate of launching the sounding rocket according to a preset inclination angle is improved; on the other hand, the phenomenon that the fixed platform and the ball pin component at the lower position are excessively worn and even damaged and collapsed due to the fact that the bearing pressure of the fixed platform and the ball pin component is excessively large due to the fact that the inclination angle of the movable platform is adjusted is avoided.
4. According to the sounding rocket system provided by the invention, the chromium coating is arranged on the concave spherical surface of the lower sliding block, so that the wear resistance of the lower sliding block can be improved, the wear phenomenon of the lower sliding block is reduced, the problem that the inclination angle adjustment deviation of the sounding rocket is increased due to the wear of the lower sliding block is further reduced, and the success rate of launching the sounding rocket for multiple times by the launching device according to the preset inclination angle is improved.
5. According to the sounding rocket system provided by the invention, the adjusting threaded sleeve adopts a mode that the upper threaded sleeve and the lower threaded sleeve are matched to adjust the height of the pin shaft, so that the stability in the adjusting process is higher.
6. According to the sounding rocket system provided by the invention, the traction handles are arranged on the upper screw sleeve and the lower screw sleeve, so that the inclination angle adjusting process is more labor-saving.
7. According to the sounding rocket system provided by the invention, the boss structure with the diameter smaller than that of the ball head is formed by cutting one end of the pin shaft, which is in contact with the ball head, and the accommodating space is formed between the side surface of the boss structure and the upper surface of the end part of the pin shaft body, so that when the ball head is jointed on the boss structure of the pin shaft through resistance welding, welding burrs are generated at the contact end of the ball head and the boss structure, and can be accommodated in the accommodating space, therefore, the welding burrs can be prevented from extending out of the conical surface of the pin shaft, and the operation of deburring the pin shaft is omitted.
8. The sounding rocket system provided by the invention has the advantages of difficult looseness, large self-locking property, high tooth root strength, high manufacturability and centering property due to the trapezoidal thread structure, and can improve the stability and accuracy of pin shaft height adjustment.
9. According to the sounding rocket system provided by the invention, the guide cone can guide the gas flow to the spaces on two sides of the fixed platform when the sounding rocket is started, so that the damage of the gas flow to the fixed platform is reduced.
10. The launching system of the sounding rocket, provided by the invention, can meet the launching requirements of a simple sounding rocket by adopting the launching device; moreover, simple and quick rocket launching tasks can be performed in a site with simple facilities, and the dependence of the sounding rocket on a special launching site is reduced; on the other hand, the lower end face of the peripheral tail wing of the tail section of the sounding rocket is flush with the lower bottom face of the tail end of the sounding rocket, so that the tail wing can play a role in improving flight stability, can play a role in auxiliary support before launching of the sounding rocket, and improves the stability of the mounting structure of the sounding rocket on the movable platform.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic structural view of a sounding rocket vertically placed on a launching device in an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a launching device after a sounding rocket adjusts the direction and the angle in the embodiment of the invention;
FIG. 3 is a schematic view showing the connection relationship between the fixed platform, the movable platform and the ball pin assembly in the launching device according to the embodiment of the invention;
fig. 4 is a schematic view of the mounting structure of the ball pin assembly in the embodiment of the present invention, a part of which has been cut away to show the mechanism of the ball pin assembly.
Description of reference numerals: 1. a fixed platform; 2. a foundation plate; 3. a movable platform; 4. sounding rockets; 41. a tail wing; 5. a ball pin assembly; 51. a ball head; 52. a pin shaft; 521. a boss structure; 53. an upper threaded sleeve; 54. a lower thread insert; 55. a traction handle; 6. a ball cup seat; 61. an upper slide block; 611. a T-shaped chuck; 62. a lower slide block; 621. a concave spherical surface; 7. a fixed block; 71. a T-shaped clamping groove; 8. and (4) a flow guide cone.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; 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 in specific cases to those skilled in the art.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
A sounding rocket system, as shown in fig. 1-4, includes a sounding rocket 4 and a launching device providing support for the sounding rocket 4. The launching device comprises a fixed platform 1, a movable platform 3 and a height adjusting mechanism supported between the fixed platform 1 and the movable platform 3. The peripheral wall of the tail section of the sounding rocket 4 is circumferentially provided with a plurality of empennages 41 which can be supported on the movable platform 3, and the lower end surfaces of the empennages 41 and the lower bottom surface of the tail end of the sounding rocket 4 are positioned on the same plane. The lower end face of the peripheral tail fin 41 at the tail section of the sounding rocket 4 is flush with the lower bottom face of the tail end of the sounding rocket 4, so that the tail fin 41 can play a role in improving flight stability, can play a role in auxiliary support before the sounding rocket 4 is launched, and improves the stability of the installation structure of the sounding rocket 4 on the movable platform 3.
Specifically, the fixed platform 1 is fixed above the foundation plate 2 through a plurality of support legs on the periphery, the foundation plate 2 is fixed on the ground, and the upper surface of the foundation plate is a flat horizontal plane; the movable platform 3 is positioned above the fixed platform 1 and used for supporting the sounding rocket 4 to provide support. The height adjustment mechanism includes at least three ball pin assemblies 5 supported between the fixed platform 1 and the movable platform 3. In this embodiment, the upper surfaces of the fixed platform 1 and the movable platform 3 are both square, and the ball pin assemblies 5 are four and are respectively supported at four corners of the movable platform 3. It should be understood herein that the shape of the upper surfaces of the fixed platform 1 and the movable platform 3 may also be a polygon with other shapes, the number of the ball pin assemblies 5 may also be 3, 5 or more, and a plurality of the ball pin assemblies 5 may be respectively arranged on a plurality of vertexes of a regular polygon, or may be arranged in an irregular manner.
Before launching the sounding rocket 4, the launching device vertically hoists the sounding rocket 4 on the movable platform 3, and the tail section of the sounding rocket 4 is fixedly connected on the movable platform 3 through a windproof bolt. Before launching, the windproof bolt is detached, and the flight trajectory and the landing point of the sounding rocket 4 can be adjusted by adjusting the inclination angle of the movable platform 3 relative to the fixed platform 1.
In this embodiment, the ball pin assembly 5 includes a ball 51 clamped by the movable platform 3 and engaged with the spherical surface of the movable platform 3, a pin 52 connected to the ball 51 and movably connected to the fixed platform 1, and an adjusting screw sleeve in threaded connection with the pin 52 and used for driving the pin 52 to move up and down along the axial direction thereof so as to adjust the relative inclination angle between the movable platform 3 and the fixed platform 1.
The plurality of ball pin assemblies 5 are movably connected with the fixed platform 1 through the pin shafts 52, the ball heads 51 are clamped by the movable platform 3 and are in fit connection with the spherical surface of the movable platform 3, the heights of the movable platform 3 relative to the fixed platform 1 can be respectively adjusted by adjusting the heights of the pin shafts 52, when the heights adjusted by the pin shafts 52 are inconsistent, the adjustment of the relative inclination angle between the movable platform 3 and the fixed platform 1 can be realized, the adjustment of the launching direction and the inclination angle of the sounding rocket 4 installed on the movable platform 3 can be further realized, and the launching requirements of the simple sounding rocket 4 can be met; moreover, the launching device can perform simple and quick rocket launching tasks in a site with simple facilities, and reduces the dependence of the sounding rocket 4 on a special launching site.
In this embodiment, the bottom of the movable platform 3 is connected to a ball seat 6, the bottom end surface of the ball seat 6 is a concave spherical surface 621, and the ball 51 is fastened in a spherical space defined by the concave spherical surface 621. The ball head seat 6 and the ball head 51 are connected in a spherical matching mode, the ball head seat 6 can rotate freely in the spherical space at the periphery of the ball head 51 relative to the ball head 51, when the height and the inclination angle of the movable platform 3 are adjusted, the phenomena of mutual interference and shell clamping cannot occur in the height adjusting process of the plurality of pin shafts 52, and the adjusting flexibility is better.
Specifically, the bottom of the movable platform 3 is fixedly connected with a fixing block 7, and the fixing block 7 is provided with a T-shaped clamping groove 71. The ball seat 6 comprises an upper slide block 61 and a lower slide block 62, the upper slide block 61 is in sliding fit with the fixed block 7 and is provided with a T-shaped chuck 611 in snap fit with the T-shaped clamping groove 71, the lower slide block 62 is fixedly connected below the upper slide block 61, and the concave spherical surface 621 is located at the bottom end of the lower slide block 62. The structure that the fixed block 7 on the movable platform 3 is in sliding fit with the upper slide block 61 of the ball socket 6, and the T-shaped clamping groove 71 limits the T-shaped clamping head 611 to perform steering motion, so that the lower slide block 62 connected with the upper slide block 61 is limited to rotate around the spherical surface of the ball head 51 within a smaller space angle adjustment range, and on one hand, the stability of the movable platform 3 and the sounding rocket 4 after inclination adjustment can be improved, and further the success rate of launching the sounding rocket 4 according to a preset inclination angle is improved; on the other hand, the phenomena that the fixed platform 1 and the ball pin assembly 5 at a low position are excessively worn and even damaged and collapsed due to the excessively large bearing pressure caused by the excessively large inclination angle adjustment of the movable platform 3 are avoided.
Further, a chromium plating layer is provided on the concave spherical surface 621 of the lower slider 62. The chromium coating can improve the wear resistance of the lower sliding block 62, reduce the wear phenomenon of the lower sliding block 62, and further reduce the problem that the inclination angle adjustment deviation of the sounding rocket 4 is increased due to the wear of the lower sliding block 62, so that the success rate of the launching device for launching the sounding rocket 4 for multiple times according to the preset inclination angle is improved.
In this embodiment, the fixing platform 1 is provided with a mounting through hole, the pin shaft 52 of the ball pin assembly 5 penetrates through the mounting through hole, the outer peripheral wall of the pin shaft 52 is provided with an external thread, and the adjusting screw sleeve comprises an upper screw sleeve 53 and a lower screw sleeve 54 which are in threaded connection with the external thread of the pin shaft 52 and are respectively located at two opposite ends of the fixing platform 1. The upper threaded sleeve 53 and the lower threaded sleeve 54 are matched to adjust the height of the pin shaft 52, so that the stability of the pin shaft 52 in the height adjusting process can be improved. The outer walls of the upper and lower threaded sleeves 53 and 54 are integrally formed with a pull handle 55 extending radially along the pin 52. The traction handle 55 can make the adjusting process of the launching direction and the inclination angle of the sounding rocket 4 more labor-saving.
Specifically, in order to improve the stability and accuracy of the height adjustment of the pin 52, trapezoidal thread matching structures which are not easy to loosen, have high self-locking performance, high root strength, manufacturability and centering performance are adopted between the upper threaded sleeve 53 and the lower threaded sleeve 54 and the pin 52
In the present embodiment, since the boss 521 having a diameter smaller than that of the ball 51 is formed by cutting the end of the pin 52 in contact with the ball 51, and a receiving space is formed between the side surface of the boss 521 and the upper surface of the end of the pin 52, when the ball 51 is joined to the boss 521 of the pin 52 by resistance welding, welding burrs are generated at the contact end of the ball 51 and the boss 521, and the welding burrs can be received in the receiving space, so that the welding burrs can be prevented from protruding from the tapered surface of the pin 52, and the operation of deburring the pin 52 can be omitted.
In this embodiment, fixed platform 1 sets up in foundatin plate 2 top through four landing leg aerial that the four corners was put, is equipped with the water conservancy diversion awl 8 of fixing on foundatin plate 2 in the middle of fixed platform 1's the below, and water conservancy diversion awl 8 is fixed into "people" style of calligraphy structure by two sections domatic relative links up. The setting of water conservancy diversion awl 8 under fixed platform 1 can lead the gas stream row when sounding rocket 4 starts to the space of fixed platform 1 both sides, reduces the damage of gas stream to fixed platform 1 and recoil gas stream to sounding rocket 4.
In summary, the sounding rocket system provided by the embodiment of the invention adopts the leg-type simple launching device, so that the launching requirements of the simple sounding rocket can be met; and simple and quick rocket launching tasks can be performed in a site with simple facilities, and the dependence of the sounding rocket on a special launching site is reduced.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.
Claims (9)
1. A sounding rocket system comprising a sounding rocket (4) and launch means providing support for said sounding rocket (4); characterized in that said transmitting means comprises:
the fixed platform (1) is fixedly connected with a foundation plate (2) fixed on the ground;
the movable platform (3) is positioned above the fixed platform (1) and is used for supporting an rocket body of the sounding rocket (4);
a height adjustment mechanism comprising at least three ball pin assemblies (5) supported between the fixed platform (1) and the movable platform (3); the ball pin assembly (5) comprises a ball head (51) which is clamped by the movable platform (3) and is matched with the spherical surface of the movable platform (3), a pin shaft (52) which is connected to the ball head (51) and is movably connected with the fixed platform (1), and an adjusting screw sleeve which is in threaded connection with the pin shaft (52) and is used for driving the pin shaft (52) to do lifting motion along the axial direction of the pin shaft so as to adjust the relative inclination angle between the movable platform (3) and the fixed platform (1);
the peripheral wall of the tail section of the sounding rocket (4) is circumferentially provided with a plurality of tail wings (41) which can be supported on the movable platform (3), and the lower end surface of each tail wing (41) and the lower bottom surface of the tail end of the sounding rocket (4) are in the same plane.
2. The sounding rocket system according to claim 1, wherein a ball socket (6) is connected to the bottom of the movable platform (3), the bottom end surface of the ball socket (6) is a concave spherical surface (621), and the ball head (51) is fastened in a spherical space enclosed by the concave spherical surface (621).
3. The sounding rocket system according to claim 2, wherein a fixed block (7) is fixedly connected to the bottom of the movable platform (3), and a T-shaped slot (71) is formed in the fixed block (7); the ball cup (6) comprises:
the upper sliding block (61) is in sliding fit with the fixed block (7) and is provided with a T-shaped clamping head (611) in snap fit with the T-shaped clamping groove (71);
and the lower sliding block (62) is fixedly connected to the upper sliding block (61) and the bottom end of the lower sliding block is provided with the concave spherical surface (621).
4. A sounding rocket system according to claim 3, characterized in that the concave spherical surface (621) of the lower slider (62) is provided with a chromium coating.
5. The sounding rocket system according to claim 1, wherein the fixed platform (1) is provided with a mounting through hole, a pin shaft (52) of the ball pin assembly (5) penetrates through the mounting through hole, and the adjusting screw sleeve comprises an upper screw sleeve (53) and a lower screw sleeve (54) which are in threaded connection with the pin shaft (52) and are respectively located at two opposite ends of the fixed platform (1).
6. A sounding rocket system according to claim 5, characterized in that the outer walls of said upper and lower threaded sleeves (53, 54) are each connected to a traction handle (55) extending radially along said pin (52).
7. The sounding rocket system according to claim 1, characterized in that the end of the pin (52) connected to the ball head (51) is machined to form a boss structure (521) with a diameter smaller than that of the ball head (51).
8. A sounding rocket system according to claim 5, characterized in that the upper and lower threaded sleeves (53, 54) are in trapezoidal thread fit with the pin (52).
9. The sounding rocket system according to claim 1, wherein the fixed platform (1) is supported and fixed on a foundation plate (2) on the ground through a plurality of support legs at four corners, a diversion cone (8) fixed on the foundation plate (2) is arranged in the middle of the lower portion of the fixed platform (1), and the diversion cone (8) is relatively connected and fixed by two slope surfaces to form a herringbone structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911389823.7A CN111121537A (en) | 2019-12-27 | 2019-12-27 | Sounding rocket system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911389823.7A CN111121537A (en) | 2019-12-27 | 2019-12-27 | Sounding rocket system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111121537A true CN111121537A (en) | 2020-05-08 |
Family
ID=70504641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911389823.7A Pending CN111121537A (en) | 2019-12-27 | 2019-12-27 | Sounding rocket system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111121537A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361879A (en) * | 2020-11-02 | 2021-02-12 | 中国运载火箭技术研究院 | Rocket launching supporting device |
| CN113218247A (en) * | 2021-05-27 | 2021-08-06 | 北京星途探索科技有限公司 | Simple launching platform capable of adjusting launching inclination angle |
| CN115127395A (en) * | 2022-06-23 | 2022-09-30 | 北京中科宇航技术有限公司 | Fine leveling supporting device for rocket launching erection support |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101055164A (en) * | 2000-12-09 | 2007-10-17 | 施仲伟 | Rocket propulsion enhancing design |
| KR20080002959U (en) * | 2007-01-26 | 2008-07-30 | 정일조 | A water-rocket launcher for study |
| US20100282150A1 (en) * | 2007-10-23 | 2010-11-11 | Onuk Ekber I N | Foldable ramp for missile launchers |
| CN104236389A (en) * | 2014-08-08 | 2014-12-24 | 西安航天化学动力厂 | Rain increasing and hail suppressing rocket launcher |
| CN104596363A (en) * | 2015-02-06 | 2015-05-06 | 南京理工大学 | Space docking error compensation mechanism of carrier rocket connector system |
| CN104634165A (en) * | 2015-03-11 | 2015-05-20 | 安徽大学 | Control system and control method for adjusting inclination of rocket launch platform |
| CN104724297A (en) * | 2015-03-02 | 2015-06-24 | 南通大学 | Anti-toppling system used during carrier rocket vertical descending recovery |
| CN106197146A (en) * | 2016-08-12 | 2016-12-07 | 清华大学 | A kind of rocket model and the adjustable rocket launch platform of attitude |
| CN211601730U (en) * | 2019-12-27 | 2020-09-29 | 北京星际荣耀空间科技有限公司 | Sounding rocket system |
-
2019
- 2019-12-27 CN CN201911389823.7A patent/CN111121537A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101055164A (en) * | 2000-12-09 | 2007-10-17 | 施仲伟 | Rocket propulsion enhancing design |
| KR20080002959U (en) * | 2007-01-26 | 2008-07-30 | 정일조 | A water-rocket launcher for study |
| US20100282150A1 (en) * | 2007-10-23 | 2010-11-11 | Onuk Ekber I N | Foldable ramp for missile launchers |
| CN104236389A (en) * | 2014-08-08 | 2014-12-24 | 西安航天化学动力厂 | Rain increasing and hail suppressing rocket launcher |
| CN104596363A (en) * | 2015-02-06 | 2015-05-06 | 南京理工大学 | Space docking error compensation mechanism of carrier rocket connector system |
| CN104724297A (en) * | 2015-03-02 | 2015-06-24 | 南通大学 | Anti-toppling system used during carrier rocket vertical descending recovery |
| CN104634165A (en) * | 2015-03-11 | 2015-05-20 | 安徽大学 | Control system and control method for adjusting inclination of rocket launch platform |
| CN106197146A (en) * | 2016-08-12 | 2016-12-07 | 清华大学 | A kind of rocket model and the adjustable rocket launch platform of attitude |
| CN211601730U (en) * | 2019-12-27 | 2020-09-29 | 北京星际荣耀空间科技有限公司 | Sounding rocket system |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112361879A (en) * | 2020-11-02 | 2021-02-12 | 中国运载火箭技术研究院 | Rocket launching supporting device |
| CN113218247A (en) * | 2021-05-27 | 2021-08-06 | 北京星途探索科技有限公司 | Simple launching platform capable of adjusting launching inclination angle |
| CN115127395A (en) * | 2022-06-23 | 2022-09-30 | 北京中科宇航技术有限公司 | Fine leveling supporting device for rocket launching erection support |
| CN115127395B (en) * | 2022-06-23 | 2024-02-27 | 北京中科宇航技术有限公司 | Fine leveling supporting device for rocket launching erection support |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111121537A (en) | Sounding rocket system | |
| US11524797B2 (en) | Aircraft-retrieval system | |
| EP2441955B1 (en) | Tower Connector | |
| CN110104197B (en) | Small rocket launching pad | |
| US7344108B2 (en) | Landing assist apparatus interface bulkhead and method of installation | |
| US9278739B2 (en) | Modular foil | |
| CN108216487B (en) | Process method for installing rudder trunk in staged stage | |
| CN111673152B (en) | Manufacturing method of cabin body suitable for lunar exploration orbital vehicle | |
| CN211601730U (en) | Sounding rocket system | |
| CN109591958B (en) | Method for accurately positioning track of ship tail shaft entering trolley | |
| US7114924B2 (en) | Blade pin alignment and positioning system for installation of helicopter rotor blades | |
| CN106314820B (en) | Bolt type anti-escape process connector and application method thereof | |
| CN104176269B (en) | A kind of rotor system anchor fitting improving depopulated helicopter engines ground experiment safety | |
| CN105089851B (en) | Repeatable dismounting thrust chamber and this chamber thrust are to the control method of accuracy of measurement | |
| CN205472204U (en) | Supplementary operating system of built -in guide rail | |
| US20050279885A1 (en) | Landing assist apparatus with releasable slip ring | |
| CN109398597B (en) | Goat's horn gyro wheel positioner | |
| CN105775113A (en) | Rotary-wing aircraft capable of realizing vector control | |
| US7198226B2 (en) | Landing assist apparatus retention strap spool | |
| US20050269449A1 (en) | Landing assist probe mounting system | |
| CN219257743U (en) | Unmanned aerial vehicle quick detach foot rest | |
| CN218662346U (en) | Aircraft with a flight control device | |
| CN216952317U (en) | Support adjusting device | |
| US7114681B2 (en) | Landing assist apparatus with offset landing probe | |
| CN218296896U (en) | A remove structure and launch platform for carrier rocket supporting disk |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Applicant after: Beijing Star glory Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. Applicant before: Beijing Star glory Technology Co.,Ltd. |