CN217761153U

CN217761153U - Heavy solid rocket engine uniform loading bracket

Info

Publication number: CN217761153U
Application number: CN202221685725.5U
Authority: CN
Inventors: 王亚男; 布向伟; 王永刚; 黄亚军; 刘睿哲; 郝丁
Original assignee: Dongfang Space Technology Shandong Co Ltd; Orienspace Technology Beijing Co Ltd; Orienspace Xian Aerospace Technology Co Ltd
Current assignee: Dongfang Space Jiangsu Aerospace Power Co ltd; Dongfang Space Technology Shandong Co Ltd; Orienspace Hainan Technology Co Ltd; Orienspace Technology Beijing Co Ltd
Priority date: 2022-07-01
Filing date: 2022-07-01
Publication date: 2022-11-08
Anticipated expiration: 2032-07-01

Abstract

The utility model discloses a load balancing bracket of a heavy solid rocket engine, belonging to the technical field of rocket carrying, comprising a base, a swing arm and a bracket; the swing arm is hinged with the base; the swing arm and the base form a lever mechanism by taking a hinge point as a fulcrum; the bracket upper part comprises a supporting groove for supporting the heavy solid rocket engine; the bracket is fixedly connected with the swing arm and comprises a first support seat body and a second support seat body; the first bracket body and the second bracket body are respectively arranged at two sides of the fulcrum of the lever mechanism. The utility model discloses it is accurate controllable to possess the fulcrum load to easy and simple to handle, nimble, do through adjusting the bracket position, satisfy the inconsistent condition of each fulcrum load, solved heavy solid rocket engine and supported the overrun problem of load, improved assembly efficiency.

Description

Heavy solid rocket engine uniform loading bracket

Technical Field

The utility model relates to a rocket ship technical field, in particular to heavy solid rocket engine all carries bracket.

Background

The shapes and structures of modern rockets, missiles, airplanes and other aircrafts are more and more complex, and the solid rocket engine tends to be larger. At present, solid rocket engines are mostly supported by two points, and the weight of the heavy solid rocket engine is greatly increased compared with that of a conventional rocket engine, so that the existing scheme is difficult to meet the requirements of supporting load and surface pressure. In order to solve the problem that the prior art is difficult to meet the requirements of supporting load and surface pressure, the supporting mode is realized through a plurality of single points.

In daily practice, the inventors found that the prior art solutions have the following problems:

the existing mode of adopting a plurality of independent single points of pure mechanical structures to support can bear the weight of the heavy solid rocket engine, but because the supporting force of each supporting point is not balanced, the heavy solid rocket engine is easily damaged in the process of final assembly and transportation. In addition, the existing multi-point supporting electronic sensing system is used for carrying out balance control on the load, but the equipment is complex, the cost is greatly increased, the operation of the load adjusting process is complex, the efficiency is low, and the failure rate is high.

In view of the above, it is necessary to provide a new technical solution to solve the above problems.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, the application provides a heavy solid rocket engine all carries bracket, possesses accurate controllable fulcrum load to easy and simple to handle, nimble, do and satisfy the inconsistent condition of each fulcrum load through adjusting the bracket position, solved heavy solid rocket engine support load overrun problem, improved assembly efficiency.

A heavy solid rocket engine averaging bracket, comprising:

a base;

swinging arms; the swing arm is hinged with the base; the swing arm and the base form a lever mechanism by taking a hinge point as a fulcrum;

a bracket; the bracket upper part comprises a supporting groove for supporting the heavy solid rocket engine; the bracket is fixedly connected with the swing arm and comprises a first support seat body and a second support seat body; the first bracket body and the second bracket body are respectively arranged at two sides of the fulcrum of the lever mechanism.

Preferably, the swing arm mechanism further comprises a pin shaft which is arranged on the fulcrum of the lever mechanism and is connected with the base and the swing arm; the pin shaft penetrates through the base and the swing arm.

Preferably, the pin shaft is of an integral structure or a split structure.

Preferably, the base comprises a base body and a mounting groove arranged on the base body; the swing arm set up in the mounting groove.

Preferably, the bracket and the swing arm are detachably and fixedly connected.

Preferably, the swing arm is provided with an adjusting device for adjusting the position of the bracket.

Preferably, the supporting bracket is of an arc-shaped structure; the size of the bearing groove is the same as the outer diameter of the heavy solid rocket engine.

Compared with the prior art, the application has at least the following beneficial effects:

the utility model discloses utilize pure mechanical structure, adopt two strong points to be a set of form that forms lever mechanism, realize all carrying the self-balancing of bracket to heavy solid rocket engine, reduced the multiple spot and supported debugging and measure and control process, simple structure, it is stable all to carry the effect.

Drawings

Some specific embodiments of the invention will be described in detail hereinafter by way of example and not by way of limitation with reference to the accompanying drawings. The same reference numbers in the drawings identify the same or similar elements or components. Those skilled in the art will appreciate that the drawings are not necessarily to scale. In the drawings:

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic structural view of the base of the present invention;

fig. 3 is a usage state diagram of the present invention.

Wherein the figures include the following reference numerals:

1. the bracket 2, the swing arm 3, the pin shaft 4 and the base; 5. heavy duty solid rocket engines;

11. a first pedestal body 12 and a second pedestal body;

101. a support body 102 and a support groove;

21. a swing arm body 22 and a connecting hole groove;

41. base body, 42, mounting groove.

Detailed Description

In order to make the objects, technical solutions and advantages of the present application more apparent, the technical solutions of the present application will be described in detail and completely with reference to the following specific embodiments of the present application and the accompanying drawings. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. 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 application.

As shown in fig. 1 and 2, a heavy-duty solid rocket engine load balancing bracket includes: bracket 1, swing arm 2, round pin axle 3 and base 4, swing arm 2 and base 4 are articulated, and swing arm 2 and base 4 use the pin joint to constitute lever mechanism as the fulcrum.

The bracket 1 comprises a bracket body 101 and an arc-shaped supporting groove 102 adapted to the outer diameter of the heavy solid rocket engine 5, wherein the supporting groove 102 is arranged on the upper part of the bracket body 101, and the size of the supporting groove 102 is the same as the outer diameter of the heavy solid rocket engine 5 and is used for supporting the heavy solid rocket engine 5. The bracket 1 includes a first supporting base 11 and a second supporting base 12, and the first supporting base 11 and the second supporting base 12 are respectively disposed at two ends of the upper portion of the swing arm 2, i.e. respectively located at two sides of the fulcrum of the lever mechanism.

The base 4 includes a base body 41 and a mounting groove 42 provided on the base body 41. The size of the mounting groove 42 is adapted to the size of the swing arm 2 so that the swing arm 2 can be placed in the mounting groove 42.

The pin shaft 3 is of a split structure and is divided into two mutually independent parts, and the two parts are arranged on the fulcrum of the lever mechanism and can be used for penetrating and connecting the joint of the connecting base 4 and the swing arm 2, so that the swing arm 2 is hinged to the connecting base 4. In other embodiments of the present invention, the pin 3 may also be an integral rod-like structure, and simultaneously penetrates through the base 4 and the swing arm 2.

Swing arm 2 includes swing arm body 21 and sets up in a plurality of groups of connecting hole grooves 22 that its upper surface set up along length direction, and bracket 1 passes through connecting bolt and connecting

hole groove

22 and 2 detachably fixed connection of swing arm for when carrying out the bearing to the rocket engine of different models, can carry out the change of not unidimensional bracket 1 according to the model and the size of rocket engine, improve the adaptability that heavy solid rocket engine all carried the bracket. In addition, the connecting hole slot 22 can also be used as an adjusting device, so that the first pedestal body 11 and/or the second pedestal body 12 can be adjusted in position along the length direction of the swing arm body 21 according to the difference of the bearing position and the bearing capacity of the rocket engine, thereby realizing more balanced stress or adapting to rocket engines with different lengths.

In other embodiments of the present invention, the upper surface of the swing arm body 21 may also be provided with an adjusting sliding groove for adjusting the position of the bracket 1, and the adjusting sliding groove may be a dovetail groove structure.

As shown in fig. 3 and referring to fig. 1, when in use, according to the model or size of the heavy solid rocket engine 5, the two heavy solid rocket engine load balancing brackets are arranged at the preset positions at two sides of the gravity center of the heavy solid rocket engine 5 and fixed on a moving vehicle or transportation equipment, the heavy solid rocket engine 5 is placed in the supporting groove 102 of the bracket 1, and the load balancing and supporting are realized by the self-balancing capability of the heavy solid rocket engine load balancing brackets.

The working principle is as follows: in order to simplify the equipment complexity of heavy solid rocket engine supporting equipment in the horizontal parking and horizontal transportation process, the heavy solid rocket engine load balancing bracket adopts a pure mechanical structure, the load balancing is realized by utilizing the lever principle, the structure is simple and reliable, the multi-point supporting debugging and measuring process is reduced, the load is accurately controlled through mechanical mass distribution, the operation efficiency is improved, and the vertical assembly period is greatly reduced.

For ease of description, spatially relative terms, such as "over", "above", "on", "upper surface", "over", and the like, may be used herein to describe one element or feature's spatial relationship to another element or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above" may encompass both an orientation of "above" and "below. The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly dictates otherwise, and it should be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of features, steps, operations, devices, components, and/or combinations thereof.

It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in other sequences than those illustrated or described herein.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A heavy solid rocket engine load balancing bracket, comprising:

a base;

2. The heavy solid rocket engine load leveling bracket of claim 1 further comprising a pin disposed on said leverage pivot connecting said base to said swing arm; the pin shaft penetrates through the base and the swing arm.

3. The heavy solid rocket engine load sharing bracket of claim 2 wherein said pin is of a one-piece or split construction.

4. The heavy solid rocket engine load leveling bracket of claim 1 wherein said base comprises a base body and a mounting slot disposed on said base body; the swing arm set up in the mounting groove.

5. The heavy solid rocket engine load-sharing bracket of claim 1 wherein said bracket is detachably fixedly attached to said swing arm.

6. The heavy solid rocket engine averaging bracket of claim 1 wherein said swing arm is provided with adjustment means for adjusting the position of said bracket.

7. The heavy solid rocket engine load-sharing bracket of claim 1 wherein said bracket is of arcuate configuration; the size of the bearing groove is the same as the outer diameter of the heavy solid rocket engine.