CN218296899U - Middle-sized liquid carrier rocket perpendicularity adjusting device - Google Patents

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

A verticality adjustment device for a medium-sized liquid launch vehicle

technical field

The utility model relates to the rocket launch field, in particular to a verticality adjustment device for a medium-sized liquid carrier rocket.

Background technique

The vertical adjustment of liquid rocket is an important measure to adjust the initial attitude of the rocket and ensure the safety of rocket take-off and flight accuracy. The shell of the liquid launch vehicle is very thin, and it cannot be launched vertically after filling in a horizontal state, so its verticality adjustment is performed after the rocket is erected on the launch platform. For example, the verticality adjustment can be divided into verticality adjustment in the no-load state before filling and verticality adjustment in the loaded state after filling.

In the current leveling workflow of launch vehicle launchers in our country, a set of leveling instruments on the ground, a set of leveling instruments on the tail end of the arrow and a set of leveling instruments in the instrument cabin are generally used. This method can reliably meet the leveling requirements of the launching device, and can basically meet the high-precision requirements of verticality. However, there are three problems: one is that the number of arrows/ground launch equipment is large, and the implementation and operation process is complicated; the second is that the increase of arrow equipment reduces the rocket’s carrying capacity; the third is that the cost of the rocket has increased significantly and the market competitiveness has declined. With the development of private aerospace technology, the market has put forward new requirements for the simplification of the rocket launch process and the low cost, maintenance-free, and rapid response of a single rocket launch.

Therefore, there is an urgent need to provide a liquid rocket verticality adjustment device, which has the advantages of easy operation and cost saving, and can improve adjustment accuracy and rocket carrying capacity.

Contents of the invention

The object of the present invention is to provide a verticality adjustment device for a medium-sized liquid carrier rocket, which has the advantages of easy operation and cost saving, and can improve the adjustment accuracy and rocket carrying capacity.

In order to achieve the above object, the present invention provides the following technical solutions: a verticality adjustment device for a medium-sized liquid carrier rocket, comprising a launch platform and an adjustment mechanism for adjusting the verticality of the rocket in cooperation with the arrow legs of the rocket, the adjustment mechanism is located at the launch platform, and the lower end of the adjustment mechanism is connected to the upper surface of the launch platform, and the upper end is connected to the lower end of the rocket foot and used to support the rocket foot;

Wherein, the adjustment mechanism includes a main body of the support plate, a pressure measuring device and a regulator. The pressure measuring device is located at the end of the main body of the support plate away from the launch platform and is used to measure the distance between the main body of the support plate and the rocket. The pressure between the feet; the regulator is located inside the main body of the support plate, and is used to adjust the distance between the main body of the support plate and the arrow foot of the rocket so that the verticality of the rocket meets the preset requirements.

Further, the main body of the support plate includes a shell and a head flange. The shell is a structure with two ends connected to each other and a space is provided inside. The lower end of the shell is welded and fixed to the upper surface of the launching platform. The head flange can move up and down relative to the housing.

Further, along the axial direction of the main body of the support disc, the head flange successively includes a first cylinder and a second cylinder with different diameters, the diameter of the first cylinder is larger than that of the second cylinder diameter, so that the transition from the first cylinder to the second cylinder forms a limit platform, and the first cylinder is located on the side close to the arrow foot of the rocket, and the second cylinder is located on the side close to the arrow foot of the rocket. side of the housing.

Further, the first cylinder is located outside the housing, the second cylinder is located inside the housing and can move along the inner wall of the housing, and the lower end surface of the limiting platform is in contact with the housing. The upper end face of the housing is in close contact.

Further, the first column and the second column are integrally formed.

Further, the end of the first cylinder away from the second cylinder is provided with a groove for fixing the pressure measuring device, and the pressure measuring device is a pressure sensor.

Further, the regulator includes a screw structure and a driving device; the output end of the driving device is connected to the input of the screw structure, and the output end of the screw structure abuts against the head flange, The lead screw structure is used to drive 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.

Further, the adjustment mechanisms are uniformly arranged circumferentially along the upper surface of the launching platform.

Further, the number of the adjustment mechanism is A, wherein, A≥4.

Compared with the prior art, the beneficial effect of the present invention is: the rocket verticality adjustment process of the present application measures the pressure between the main body of the support plate and the arrow foot of the rocket through the pressure measuring device, and adjusts the support plate through the regulator according to the value of the pressure The distance between the main body and the rocket foot to equalize the pressure between the support plate body and the rocket foot.

In addition, the adjustment device of the present application can adjust the main body of the support plate multiple times so that the base plane of the rocket engine frame is parallel to the initial surface of the main body of the support plate (the plane formed by the ends of the support plate bodies away from the launch platform). In addition, on the basis of not increasing the measurement device on the arrow, the application can adjust the main body of the support plate multiple times, and make the reference plane of the rocket engine frame parallel to the initial surface of the main body of the support plate, so as to quickly realize the accurate verticality of the rocket. Adjustment lays the foundation for subsequent adjustments. The device has the advantages of convenient operation and cost saving, and can improve the adjustment accuracy of the verticality of the rocket and the carrying capacity of the rocket.

Description of drawings

Fig. 1 is the structural representation of liquid rocket verticality adjusting device of the present invention;

Fig. 2 is a structural schematic diagram of the main body of the support plate and the adjuster of the present invention.

Explanation of reference signs:

1 launch platform 2 support plate main body

3 Pressure measuring device 4 Regulator

5 shell 6 head flange

7 Rocket Knuckles

detailed description

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the spirit of the disclosure of the present invention will be clearly described below with the accompanying drawings and detailed descriptions. Any person skilled in the art will understand the embodiments of the present invention. , when it can be changed and modified by the technology taught in the content of the present invention, it does not depart from the spirit and scope of the content of the present invention.

The exemplary embodiments and descriptions of the present invention are used to explain the present invention, but not to limit the present invention. In addition, elements/members with the same or similar numbers used in the drawings and embodiments are used to represent the same or similar parts.

As used herein, "first", "second", ... etc. do not refer to a particular sequence or order, nor are they used to limit the present invention, but are only used to distinguish elements or operations described with the same technical terms .

Regarding the directional terms used herein, such as: up, down, left, right, front or rear, etc., only refer to the directions of the drawings. Accordingly, the directional terms used are for illustration and not for limitation of the present invention.

As used herein, "comprising", "comprising", "having", "comprising" and so on are all open terms, meaning including but not limited to.

As used herein, "and/or" includes any or all combinations of the stated things.

The terms "approximately" and "about" used herein are used to modify any quantity or error that may vary slightly, but these slight changes or errors will not change its essence. Generally speaking, the range of slight changes or errors modified by such terms may be 20% in some embodiments, 10% in some embodiments, 5% in some embodiments or other numerical values. Those skilled in the art should understand that the aforementioned values can be adjusted according to actual needs, and are not limited thereto.

Certain terms used to describe the present application are discussed below or elsewhere in this specification to provide those skilled in the art with additional guidance in describing the present application.

An embodiment of the invention provides a verticality adjustment device for a medium-sized liquid launch vehicle. As shown in Figures 1 and 2, the device includes a launch platform 1 and an adjustment mechanism for adjusting the verticality of the rocket in cooperation with the arrow foot 7 of the rocket. The adjustment mechanism is located on the launch platform 1 , and the lower end of the adjustment mechanism is connected to the upper surface of the launch platform 1 , and the upper end is connected to the lower end of the arrow foot 7 of the rocket and is used to support the arrow foot 7 of the rocket. The adjustment mechanism includes a main body 2 of the support disc, a pressure measuring device 3 and a regulator 4 . The pressure measuring device 3 is located at the end of the support plate main body 2 away from the launch platform 1 and is used to measure the pressure between the support plate main body 2 and the arrow foot 7 of the rocket. The adjuster 4 is located inside the main body 2 of the support plate, and is used for adjusting the distance between the main body 2 of the support plate and the arrow foot 7 of the rocket so that the verticality of the rocket meets the preset requirements.

The verticality adjustment device of the medium-sized liquid carrier rocket of the present application measures the pressure between the main body 2 of the support plate and the arrow foot 7 of the rocket through the pressure measuring device, and adjusts the distance between the main body 2 of the support plate and the arrow foot 7 of the rocket through the regulator 4 according to the value of the pressure. The distance between so that the pressure between the support plate main body 2 and the arrow foot 7 of the rocket is equal, and by repeatedly adjusting the support plate main body 2, the rocket engine frame reference plane and the support plate main body 2 initial surfaces (multiple The main body of the support plate is parallel to the plane formed by the end of the launching platform). In this application, on the basis of not increasing the measurement device on the arrow, the main body 2 of the support plate can be adjusted multiple times to quickly realize the precise adjustment of the verticality of the rocket and lay the foundation for subsequent adjustments. The device has the advantages of convenient operation and cost saving, and can improve adjustment accuracy and rocket carrying capacity.

It should be noted that, for the convenience of adjusting the main body 2 of the support plate, for example, the main body 2 of the support plate includes a shell 5 and a head flange 6 , wherein the shell 5 is a structure in which both ends communicate with each other and a space is provided inside. In order to make the casing 5 be fixed firmly, for example, the lower end of the casing 5 is welded and fixed to the upper surface of the launching platform 1 . In addition, in order to facilitate the movement of the head flange 6 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. The other end of the flange 6 can move up and down along the inner wall of the housing 5 .

It is worth mentioning that, in order to fix the head flange 6 conveniently, for example, along the axial direction of the main body 2 of the support plate, the head flange 6 sequentially includes a first cylinder and a second cylinder with different diameters. Wherein the diameter of the first cylinder is larger than that of the second cylinder, so that the transition from the first cylinder to the second cylinder forms a limiting platform. The first cylinder is located on the side close to the arrow foot 7 of the rocket, and is used to abut the arrow foot of the rocket, and the second cylinder is located on the inner side close to the shell 5, and is used to move along the inner side of the shell. Specifically, the first cylinder is located outside the housing 5, the second cylinder is located inside the housing 5 and can move along the inner wall of the housing 5, and the lower end surface of the limiting platform is used to abut against the upper end surface of the housing 5 , to limit the limit position of the downward movement of the head flange 6 .

In addition, in order to make the first cylinder and the second cylinder tightly connected and fixed firmly, for example, the first cylinder and the second cylinder adopt an integral molding design.

It should be pointed out that, in order to facilitate the fixing of the pressure measuring device 3 and avoid the displacement of the pressure measuring device 3 on the surface of the first cylinder, the end of the first cylinder away from the second cylinder is provided with a groove for fixing the pressure measuring device ( The groove is set to match the pressure measuring device). For the convenience of the pressure measuring device 3 to measure pressure, for example, the pressure measuring device 3 is a pressure sensor.

It should be particularly noted that, in order to facilitate the adjustment (up and down movement) of the regulator, for example, the regulator 4 includes a lead screw structure and a driving device. Wherein, the output end of the driving device is connected with the input of the lead screw structure. Specifically, when the driving device drives the lead screw structure to move, the output end of the lead screw structure is connected to the head flange 6 (the second cylinder is far away from the first cylinder) One end face) contact, and then drive the head flange 6 to move up and down.

In this embodiment, in order to ensure sufficient power, for example, the driving device is a hydraulic motor. In order to control the output of the hydraulic motor, for example, the hydraulic motor is controlled by a programmable controller.

In addition, in order to facilitate the adjustment mechanism to support the arrow foot 7 of the rocket, for example, the adjustment mechanisms are evenly arranged circumferentially along the upper surface of the launch platform. After a large number of experimental simulations, when the number of adjustment mechanisms is A and satisfies A≥4, the support of the adjustment mechanism to the arrow foot 7 of the rocket will be more firm, which can better prevent the rocket from tilting, and is conducive to improving the verticality of the rocket. Fine adjustment.

The above are only illustrative specific implementations of the present invention. Under the premise of not departing from the concept and principle of the present invention, any equivalent changes and modifications made by those skilled in the art shall 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.

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