CN218296899U - Middle-sized liquid carrier rocket perpendicularity adjusting device - Google Patents
Middle-sized liquid carrier rocket perpendicularity adjusting device Download PDFInfo
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- CN218296899U CN218296899U CN202221730143.4U CN202221730143U CN218296899U CN 218296899 U CN218296899 U CN 218296899U CN 202221730143 U CN202221730143 U CN 202221730143U CN 218296899 U CN218296899 U CN 218296899U
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Abstract
The utility model discloses a verticality adjusting device for a medium-sized liquid carrier rocket, which comprises a launching platform and an adjusting mechanism, wherein the adjusting mechanism is used for adjusting the verticality of the rocket in cooperation with rocket feet, is positioned on the launching platform, the lower end of the adjusting mechanism is connected with the upper surface of the launching platform, and the upper end of the adjusting mechanism is connected with the lower end of the rocket feet and is used for supporting the rocket feet; the pressure measuring device is positioned at one end of the supporting disc main body, which is far away from the launching platform, and is used for measuring the pressure between the supporting disc main body and the rocket foot; the regulator is positioned in the support disc main body and used for regulating the distance between the support disc main body and the rocket foot so that the rocket perpendicularity meets the preset requirement. Compared with the prior art, the device has the advantages of convenience in operation and cost saving, and can improve the adjusting precision of the rocket perpendicularity and the rocket carrying capacity.
Description
Technical Field
The utility model relates to a rocket launch field, in particular to middle-sized liquid carrier rocket straightness adjusting device that hangs down.
Background
The perpendicularity adjustment of the liquid rocket is an important measure for adjusting the initial posture of the rocket and ensuring the takeoff safety and the flight precision of the rocket. The shell of the liquid carrier rocket is very thin and cannot be vertically launched after being filled in a horizontal state, so the verticality adjustment is performed after the rocket is vertically erected to a launching platform. For example, the adjustment of the verticality can be divided into two types, namely verticality adjustment in a no-load state before filling and verticality adjustment in a loaded state after filling.
In the leveling work flow of the existing carrier rocket launching device in China, a mode that one set of horizontal measuring instrument is arranged on the ground is generally adopted, and the tail end of the rocket and the instrument cabin are respectively provided with one set of horizontal measuring instrument. The mode can reliably meet the requirement of leveling the transmitting device and can basically meet the requirement of high precision of perpendicularity. There are three problems, however: firstly, the number of arrow/missile ground devices is large, and the implementation and operation processes are complex; secondly, equipment on the rocket is added, so that the carrying capacity of the rocket is reduced; thirdly, the cost of the rocket is greatly increased, and the market competitiveness is reduced. With the development of civil aerospace technology, the market puts new requirements on the simplification of the rocket launching process and the low-cost, maintenance-free and quick response of the launching of a single rocket.
Therefore, it is highly desirable to provide a perpendicularity adjusting device for a liquid rocket, which has the advantages of convenient operation and cost saving, and can improve the adjusting precision and the rocket carrying capacity.
Disclosure of Invention
The invention aims to provide a verticality adjusting device for a medium-sized liquid carrier rocket, which has the advantages of convenience in operation and cost saving and can improve the adjusting precision and the carrying capacity of the rocket.
In order to achieve the purpose, the invention provides the following technical scheme: a verticality adjusting device for a medium-sized liquid carrier rocket comprises a launching platform and an adjusting mechanism, wherein the adjusting mechanism is used for adjusting the verticality of the rocket in a matching manner with rocket feet, is positioned on the launching platform, is connected with the upper surface of the launching platform at the lower end and is connected with the lower ends of the rocket feet at the upper end and is used for supporting the rocket feet;
the pressure measuring device is positioned at one end of the supporting disc main body, which is far away from the launching platform, and is used for measuring the pressure between the supporting disc main body and the rocket foot; the regulator is positioned in the support disc main body and used for regulating the distance between the support disc main body and the rocket foot so that the rocket perpendicularity meets the preset requirement.
Furthermore, the supporting disk main body comprises a shell and a head flange, the two ends of the shell are communicated, a space is arranged inside the shell, the lower end of the shell is welded and fixed with the upper surface of the launching platform, and the head flange can move up and down relative to the shell.
Further, along the axial direction of the supporting disc main body, the head flange sequentially comprises a first cylinder and a second cylinder which are different in diameter, the diameter of the first cylinder is larger than that of the second cylinder, so that a limiting table is formed at the transition position of the first cylinder to the second cylinder, the first cylinder is located on one side close to the rocket foot, and the second cylinder is located on one side close to the shell.
Furthermore, the first cylinder is located the outside of casing, the second cylinder is located the inside of casing and can follow the shells inner wall removes, the lower terminal surface of spacing platform with the upper end terminal surface of casing is hugged closely.
Further, the first cylinder and the second cylinder are designed in an integrated forming mode.
Furthermore, one end, far away from the second column body, of the first column body is provided with a groove for fixing the pressure measuring device, and the pressure measuring device is a pressure sensor.
Further, the regulator comprises a lead screw structure and a driving device; the output end of the driving device is connected with the input end of the lead screw structure, the output end of the lead screw structure is abutted to the head flange, and the lead screw structure is used for driving the head flange to move up and down under the driving of the driving device.
Further, the driving device is a hydraulic motor, and the hydraulic motor is controlled by a programmable controller.
Furthermore, the adjusting mechanisms are evenly distributed along the circumferential direction of the upper surface of the launching platform.
Furthermore, the number of the adjusting mechanisms is A, wherein A is more than or equal to 4.
Compared with the prior art, the invention has the beneficial effects that: according to the rocket perpendicularity adjusting process, the pressure between the supporting disc main body and the rocket foot is measured through the pressure measuring device, and the distance between the supporting disc main body and the rocket foot is adjusted through the adjuster according to the numerical value of the pressure so that the pressure between the supporting disc main body and the rocket foot is equal.
In addition, the adjusting device of the application can be used for adjusting the supporting disc main body for multiple times, so that the base plane of the rocket engine frame is parallel to the initial plane of the supporting disc main body (the plane formed by the plurality of supporting disc main bodies far away from the launching platform). In addition, on the basis that a rocket measuring device is not added, the supporting disk main body can be adjusted for multiple times, the base plane of the rocket engine frame is parallel to the initial plane of the supporting disk main body, so that the accurate adjustment of the perpendicularity of the rocket is quickly realized, and a foundation is laid for subsequent adjustment. The device has the advantages of convenient operation and cost saving, and can improve the adjusting precision of the rocket perpendicularity and the rocket carrying capacity.
Drawings
FIG. 1 is a schematic structural diagram of a perpendicularity adjusting device of a liquid rocket according to the present invention;
fig. 2 is a schematic structural view of a support plate body and an adjuster according to the present invention.
Description of reference numerals:
1 emission platform 2 support disc main body
3 pressure measuring device 4 regulator
5 casing 6 head flange
7 rocket foot of rocket
Detailed Description
To further clarify the objects, technical solutions and advantages of the embodiments of the present invention, the spirit of the present disclosure will be clearly described in the following drawings and detailed description, and any person skilled in the art who knows the embodiments of the present disclosure can make changes and modifications to the technology taught by the present disclosure without departing from the spirit and scope of the present disclosure.
The exemplary embodiments of the present invention and the description thereof are provided to explain the present invention and not to limit the present invention. Additionally, the same or similar numbered elements/components used in the drawings and the embodiments are used to represent the same or similar parts.
As used herein, "first," "second," …, etc., are not specifically referred to in an orderly or sequential sense, nor are they intended to be limiting of the invention, but merely to distinguish between elements or operations described in the same technical language.
With respect to directional terminology used herein, for example: up, down, left, right, front or rear, etc., are directions with reference to the drawings only. Accordingly, the directional terminology used is intended to be illustrative and is not intended to be limiting of the present teachings.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the described items.
As used herein, the terms "substantially", "about" and the like are used to modify any slight variation in quantity or error that does not alter the nature of the variation. Generally, the range of slight variations or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments, or other values. It should be understood by those skilled in the art that the aforementioned values can be adjusted according to actual requirements, and are not limited thereto.
Certain words used to describe the present application are discussed below or elsewhere in this specification to provide additional guidance to those skilled in the art in describing the present application.
The embodiment of the invention provides a verticality adjusting device for a medium-sized liquid carrier rocket. As shown in fig. 1 and 2, the device comprises a launching platform 1 and an adjusting mechanism for adjusting the perpendicularity of the rocket in cooperation with a rocket foot 7 of the rocket. The adjusting mechanism is located on the launching platform 1, the lower end of the adjusting mechanism is connected with the upper surface of the launching platform 1, and the upper end of the adjusting mechanism is connected with the lower end of the rocket foot 7 and used for supporting the rocket foot 7. The adjusting mechanism comprises a supporting disc main body 2, a pressure measuring device 3 and an adjuster 4. The pressure measuring device 3 is located at one end of the support disc main body 2 far away from the launching platform 1 and is used for measuring the pressure between the support disc main body 2 and the rocket foot 7. The adjuster 4 is positioned inside the supporting disc main body 2 and used for adjusting the distance between the supporting disc main body 2 and the rocket foot 7 so as to enable the rocket perpendicularity to meet preset requirements.
The utility model provides a middle-sized liquid carrier rocket straightness adjusting device that hangs down measures the pressure between supporting disk main part 2 and the rocket arrow foot 7 through the pressure measurement device, according to the numerical value of pressure through the distance between regulator 4 regulation supporting disk main part 2 and the rocket arrow foot 7 so that the pressure between supporting disk main part 2 and the rocket arrow foot 7 equals, and through adjusting supporting disk main part 2 many times, can make rocket engine frame reference surface parallel with supporting disk main part 2 initial face (the plane that the launching platform end was formed is kept away from to a plurality of supporting disk main parts). This application can be on the basis that does not increase measuring device on the rocket, through adjusting supporting disk main part 2 many times to realize the accurate adjustment to the rocket straightness that hangs down fast, lay the basis for follow-up regulation. The device has the advantages of convenient operation and cost saving, and can improve the adjustment precision and the rocket carrying capacity.
It should be noted that, for the convenience of adjusting the support plate main body 2, for example, the support plate main body 2 includes a housing 5 and a head flange 6, wherein the housing 5 is a structure with two ends communicating with each other and an inner space is provided. In order to fix the housing 5 firmly, for example, the lower end of the housing 5 is welded and fixed to the upper surface of the launching platform 1. In addition, in order to facilitate the head flange 6 to move along the inner wall of the housing 5, for example, the upper end of the housing 5 is used to cooperate with one end of the head flange 6 to limit the downward movement of the head flange 6, and the other end of the head flange 6 can move up and down along the inner wall of the housing 5.
It is worth mentioning that, in order to facilitate fixing of the head flange 6, for example, in the axial direction of the support disc body 2, the head flange 6 comprises in sequence a first cylinder and a second cylinder of different diameters. Wherein the diameter of first cylinder is greater than the second cylinder to first cylinder forms spacing platform to the transition position of second cylinder. The first cylinder is located near one side of the rocket foot 7 and used for being abutted against the rocket foot, and the second cylinder is located near the inner side of the shell 5 and used for moving along the inner side of the shell. Specifically, the first cylinder is located the outside of casing 5, and the second cylinder is located the inside of casing 5 and can move along the casing 5 inner wall, and the lower terminal surface of spacing platform is used for with the upper end terminal surface butt of casing 5 to the downward motion limit position of restriction head flange 6.
In addition, in order to make the first cylinder and the second cylinder tightly connected and firmly fixed, for example, the first cylinder and the second cylinder are designed to be integrally formed.
It should be noted that, in order to fix the pressure measuring device 3 conveniently, the pressure measuring device 3 is prevented from moving on the surface of the first column body, and a groove (the groove is matched with the pressure measuring device) for fixing the pressure measuring device is formed in one end, away from the second column body, of the first column body. In order to facilitate the pressure measurement device 3 to measure the pressure, the pressure measurement device 3 is, for example, a pressure sensor.
It is particularly noted that in order to facilitate the adjustment (up-down movement) of the adjuster, the adjuster 4 comprises a lead screw structure and a drive means, for example. Wherein, drive arrangement's output and the input connection of lead screw structure, it is concrete, when drive arrangement drove lead screw structure and removes for lead screw structure's output and head flange 6 (the terminal surface of first cylinder one end is kept away from to the second cylinder) contact, and then drive head flange 6 and reciprocate.
In the present embodiment, in order to ensure sufficient power, the driving device is, for example, a hydraulic motor. To facilitate control of the output of the hydraulic motor, the hydraulic motor is controlled by a programmable controller, for example.
In addition, in order to facilitate the support of the rocket feet 7 by the adjusting mechanisms, for example, the adjusting mechanisms are uniformly arranged along the circumferential direction of the upper surface of the launching platform. Through a large amount of experimental simulation, when the number of the adjusting mechanisms is A and A is more than or equal to 4, the adjusting mechanisms can support rocket feet 7 of the rocket more firmly, so that the rocket can be better prevented from inclining, and the accurate adjustment of the perpendicularity of the rocket is facilitated.
The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.
Claims (10)
1. The device for adjusting the verticality of the medium-sized liquid carrier rocket is characterized by comprising a launching platform and an adjusting mechanism for adjusting the verticality of the rocket in a manner of being matched with rocket feet, wherein the adjusting mechanism is positioned on the launching platform, the lower end of the adjusting mechanism is connected with the upper surface of the launching platform, and the upper end of the adjusting mechanism is connected with the lower ends of the rocket feet and is used for supporting the rocket feet;
the pressure measuring device is positioned at one end of the supporting disc main body, which is far away from the launching platform, and is used for measuring the pressure between the supporting disc main body and the rocket foot; the regulator is positioned in the support disc main body and used for regulating the distance between the support disc main body and the rocket foot so that the rocket perpendicularity meets the preset requirement.
2. The perpendicularity adjusting device of the medium-sized liquid carrier rocket according to claim 1, wherein the supporting plate main body comprises a housing and a head flange, and the housing is a structure with two communicated ends and a space inside; the lower end of the shell is fixedly welded with the upper surface of the launching platform, and the head flange can move up and down relative to the shell.
3. The apparatus for adjusting the verticality of a medium-sized liquid carrier rocket according to claim 2, wherein the head flange comprises a first column and a second column with different diameters in sequence along the axial direction of the support disc main body; the diameter of the first cylinder is larger than that of the second cylinder, so that a limiting table is formed at the transition part of the first cylinder to the second cylinder, the first cylinder is positioned at one side close to the rocket foot, and the second cylinder is positioned at one side close to the shell.
4. The mid-sized liquid carrier rocket perpendicularity adjusting apparatus according to claim 3, wherein the first column is located outside the housing in the axial direction, and the second column is located inside the housing and is movable up and down along the inner wall of the housing.
5. The apparatus of claim 3, wherein the first and second cylinders are integrally formed.
6. The device for adjusting the verticality of a medium-sized liquid carrier rocket according to claim 3, wherein the end of the first column body, which is far away from the second column body, is provided with a groove for fixing the pressure measuring device, and the pressure measuring device is a pressure sensor.
7. The mid-sized liquid carrier rocket perpendicularity adjusting apparatus according to claim 2, wherein the adjuster includes a lead screw structure and a driving device; the output end of the driving device is connected with the input end of the lead screw structure, the output end of the lead screw structure is abutted to the head flange, and the lead screw structure is used for driving the head flange to move up and down under the driving of the driving device.
8. The apparatus of claim 7, wherein the driving device is a hydraulic motor, and the hydraulic motor is controlled by a programmable controller.
9. The apparatus of claim 1, wherein the adjusting mechanisms are arranged uniformly along the circumference of the upper surface of the launching platform.
10. The verticality adjusting device for the medium-sized liquid carrier rocket according to claim 9, wherein the number of the adjusting mechanisms is A, and A is greater than or equal to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221730143.4U CN218296899U (en) | 2022-07-05 | 2022-07-05 | Middle-sized liquid carrier rocket perpendicularity adjusting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221730143.4U CN218296899U (en) | 2022-07-05 | 2022-07-05 | Middle-sized liquid carrier rocket perpendicularity adjusting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218296899U true CN218296899U (en) | 2023-01-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221730143.4U Active CN218296899U (en) | 2022-07-05 | 2022-07-05 | Middle-sized liquid carrier rocket perpendicularity adjusting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218296899U (en) |
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2022
- 2022-07-05 CN CN202221730143.4U patent/CN218296899U/en active Active
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