CN216382839U - Space pipeline fixing device for aircraft - Google Patents
Space pipeline fixing device for aircraft Download PDFInfo
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- CN216382839U CN216382839U CN202121968153.7U CN202121968153U CN216382839U CN 216382839 U CN216382839 U CN 216382839U CN 202121968153 U CN202121968153 U CN 202121968153U CN 216382839 U CN216382839 U CN 216382839U
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Abstract
The utility model relates to a space pipeline fixing device for an aircraft, which comprises a first base, a second base, a first clamp and a second clamp, wherein the first base is provided with a first hole; the first end of the first clamp is fixed to the first end of the second clamp and is connected to the first base; the second end of the first clamp is fixed to the second end of the second clamp and connected to the second base; the first clamp and the second clamp form a limiting ring which is sleeved on the pipeline to limit the pipeline; the first clamp and the second clamp are rotatable relative to the first base and the second base. The utility model changes the connection mode of the hoop and the base in the original scheme, so that the hoop can rotate around the connecting shaft of the base while clamping the pipeline, thereby adapting to the installation angle of the pipeline, rotating along with the pipeline when the pipeline deforms, providing certain deformation compensation for the pipeline, and playing a role in protecting the pipeline.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a spatial pipeline fixing device for an aircraft.
Background
The pipeline is an important component of a rocket pressurizing and conveying system, and the pipeline fixing device is an important auxiliary device of a pipeline system, particularly a pipeline with high temperature, high pressure, low temperature, toxicity, flammability and strong corrosiveness. The correct fixing device can meet the requirements of pipeline strength and rigidity, and can effectively reduce the additional load of the pipeline on the arrow body structure, prevent the pipeline from leakage, explosion and other accidents caused by vibration, displacement and other reasons, and effectively protect the pipeline and the arrow body structure.
Pipeline fixing devices can be divided into three major categories according to the role they play: a load-bearing support, a limiting support and a vibration-damping support. The bearing support can be divided into a sliding support, a rod type hanging bracket, a constant force support and a rolling support. The limiting bracket can be divided into a guide bracket, a limiting bracket and a fixed bracket. The primary stress problem is often considered by pipeline designers when initially piping, and the brackets mainly considered at this stage are sliding brackets, guide brackets and fixed brackets. The sliding support is a bracket below the supporting point, and has no resistance except for the axial supporting force vertical to the pipeline and the friction force parallel to the axis of the pipeline. The guide bracket is a bracket which enables the pipeline to move only along the axial direction and prevents the rotation caused by bending moment or torque. Often combined with the effect of limiting lateral linear displacement for structural reasons. The guide support is the direction constraint that has increased the pipeline on the basis of carriage, prevents the emergence of the condition such as pipeline lateral displacement. A fixed bracket is one that does not allow full linear and angular displacement of the support point in three axes.
The rocket cabin section is compact in structure and dense in equipment, so that the trend of a pipeline of the rocket pressurizing and conveying system is greatly limited, and most of the pipelines are bent at multiple positions in a short distance. The tail end of the pipeline is connected with a rocket storage tank, and the tank body can be deformed by filling low-temperature fuel or oxidant into the storage tank, so that the pipeline is deformed. During the flight, the pipeline bears the overload of several times of gravity, which requires that the spatial pipeline fixing device on the rocket has the compensation capacity of pipeline deformation and the capacity of sufficiently bearing the pipeline overload.
In the existing rocket pressurized conveying system, a pipeline fixing device mostly adopts a mode of combining a fixed support and a sliding support, the fixed support is basically in a mode that one end of the fixed support is connected with a flange of a pipeline, and the other end of the fixed support is fixed on a truss beam of a rocket body shell section partition frame, a box body or a rack so as to realize the functions of bearing and transmission. The specific structure differs depending on the installation site.
The sliding support has a complete structure and an incomplete structure, wherein the typical structure of the sliding support is shown in figure 1, the sliding support is provided with a complete component of the support, a pipeline is supported by the support and is mostly a stamping welding part, a base is installed according to specific requirements and is generally fixed on a bulkhead or a special support plate, and the support is generally used on the pipeline in a rocket shell section. The incomplete structure is also called a clamp structure and comprises a semicircular clamp and a support, the clamp and the support are combined into an integral support, a pipeline is erected on the support of a large section, and the typical structure is shown in figure 2. The sliding support structure should not interfere with movement of the pipeline due to temperature deformation, and the support should not deflect as the pipeline slides within the support.
Most of the existing pipeline sliding supports are welded on a support plate at the thickened area of the bottom of a box or a compartment partition frame before a rocket storage box or a compartment leaves a factory, when a rocket is assembled, matching deviation between a pipeline and the designed supports often occurs due to machining deviation, welding deformation and the like, and the adaptability to the condition that the pipeline and the rocket wall form a larger angle is poor; in addition, the rocket storage tank can be deformed after filling and pressurization, so that the influence on a pipeline connected with the rocket storage tank is deformed, when the pipeline is deformed, the clamp, the base and the pipeline of the sliding support are not in sufficient contact, the effective bearing and compensation effects on the space pipeline are difficult to play, the severe vibration of the pipeline in the flying process causes the stress concentration of the pipeline, the pipeline is damaged, and even the other structures of the rocket body are damaged. The existing sliding support structure needs to be additionally provided with a compensator structure on a pipeline facing the problems, on the premise of the same flow capacity, the appearance of the compensator is thicker than that of the pipeline, the connection between the compensator and the pipeline needs to consider the addition of a flange or a welding point, and if the flange is added, the sealing problem at the flange is also considered. The compensator structure increases the design and processing difficulty of the pipeline, the increase of the complexity of the pipeline further reduces the reliability of a pipeline system, and meanwhile, the production cost is increased.
SUMMERY OF THE UTILITY MODEL
Aiming at the problems in the prior art, the utility model provides a space pipeline fixing device for an aircraft, wherein two hoops can rotate around a connecting bolt with a base so as to adapt to the installation angle of a pipeline, and the hoops can rotate along with the connecting bolt when the pipeline deforms so as to provide certain deformation compensation for the pipeline, thereby playing a role in protecting the pipeline.
In order to achieve the purpose, the utility model provides a space pipeline fixing device for an aircraft, which comprises a first base, a second base, a first clamp and a second clamp;
the first end of the first clamp is fixed to the first end of the second clamp and is connected to the first base; the second end of the first clamp is fixed to the second end of the second clamp and connected to the second base;
the first clamp and the second clamp form a limiting ring which is sleeved on the pipeline to limit the pipeline;
the first clamp and the second clamp are rotatable relative to the first base and the second base.
Further, the first base and the second base respectively comprise a fixing part and a rotating shaft bolt; the fixing part is used for being fixed to a rocket wall or a rocket storage box body structure, and two ends of the rotating shaft bolt are fixed to the fixing part; the first connecting end of the first clamp is connected to the middle of the rotating shaft bolt of the first base and can rotate relative to the first base; the second link of first clamp is connected to the pivot bolt middle part of second base, and can rotate for the second base.
Furthermore, two sides of the first connecting end are respectively clamped and limited by sleeve cushion blocks sleeved on the first base rotating shaft bolt; and the two sides of the second connecting end are respectively clamped and limited by sleeve cushion blocks sleeved on the second base rotating shaft bolt.
Further, the second clamp is a semicircular ring in the middle, and the first end and the second end are turned outwards and extend along the diameter direction.
Furthermore, the middle part of the first clamp is a semicircular ring, the first end and the second end are turned outwards and extend along the diameter direction, the first end and the second end are respectively provided with a first connecting end and a second connecting end which extend outwards, and the extending directions of the first connecting end and the second connecting end are different from the extending directions of the first end and the second end.
Furthermore, the first connecting end and the second connecting end can be bent, and the extending direction can be adjusted.
Further, the first end of first clamp is through the first end of bolt fastening to the second clamp, the second end of first clamp is through the second end of bolt fastening to the second clamp
Further, the width of the first clamp is L1, the width of the second clamp is L2, and the width of the connecting end is (L1-L2).
Furthermore, elastic cushions are arranged between the first clamp and the pipeline, between the second clamp and the pipeline.
The technical scheme of the utility model has the following beneficial technical effects:
(1) the utility model changes the connection mode of the hoop and the base in the original scheme, so that the hoop can rotate around the connecting shaft of the base while clamping the pipeline, thereby adapting to the installation angle of the pipeline, rotating along with the pipeline when the pipeline deforms, providing certain deformation compensation for the pipeline, and playing a role in protecting the pipeline.
(2) The utility model can reduce the complexity of the pipeline and improve the reliability of the pipeline system by supporting and fixing the pipeline with large drift diameter and complex space of the rocket, and when the pipeline deforms, the clamping state of the hoop and the pipeline can be kept through the relative angle change of the hoop and the base, and simultaneously the stress generated by the deformation of the pipeline is released.
(3) The elastic cushion is arranged between the pipeline and the first clamp and between the pipeline and the second clamp during installation, so that the circumferential compensation capacity of the pipeline fixing device can be enhanced, the stress generated by pipeline deformation is released, and the pipeline is prevented from being damaged due to stress concentration.
Drawings
FIG. 1 is a schematic view of a prior art full-scale sliding support;
FIG. 2 is a schematic view of a prior art incomplete slide bracket;
fig. 3 is a schematic view of the fixing device.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The utility model provides a space pipeline fixing device for an aircraft, which is combined with a figure 3 and comprises a first base 1, a second base 2, a first clamp 3 and a second clamp 4.
The first end 3-2 of the first clip 3 is fixed to the first end 4-2 of the second clip 4 and is connected to the first base 1; the second end 3-3 of the first clip 3 is secured to the second end 4-3 of the second clip 4 and is attached to the second base 2.
The first clamp 3 and the second clamp 4 form a limiting ring, and the limiting ring is sleeved on the pipeline and limits the pipeline.
The first clamp 3 and the second clamp 4 are rotatable relative to the first base 1 and the second base 2.
The first base 1 comprises a fixing part 1-1 and a rotating shaft bolt 1-2. The fixing part 1-1 is of a support structure, the bottom of the fixing part is a flat plate, and two sides of the fixing part are vertical to the bottom and extend upwards to form side flanges. The fixing part 1-1 is fixed to the rocket wall or the rocket storage box body structure through a bolt 5, and a strong pipeline fixing support foundation is established. The spindle bolt 1-2 is fixed to the side flange. The first connecting end 3-4 of the first clamp 3 is connected to the middle of the spindle bolt 1-2 of the first base 1 and can rotate relative to the first base 1. The sleeve cushion blocks 1-3 on the rotating shaft bolts 1-2 are clamped and limited at two sides of the first connecting end 3-4.
The second chassis 2 has the same structure as the first chassis 1. The second base 2 comprises a fixed part 2-1 and a rotating shaft bolt 2-2 respectively; the second connection end 3-5 of the first yoke 3 is connected to the middle of the spindle bolt 2-2 of the second base 2 and can rotate relative to the second base 2. And the sleeve cushion blocks 2-3 on the rotating shaft bolts 2-2 are clamped and limited at two sides of the second connecting end 3-5.
The second clamp 4 is characterized in that the middle part 4-1 is a semicircular ring, and the first end 4-2 and the second end 4-3 are turned outwards and extend along the diameter direction.
The middle part of the first hoop 3 is a semicircular ring 3-1, the first end 3-2 and the second end 3-3 are folded outwards and extend along the diameter direction, the first end 3-2 and the second end 3-3 are provided with connecting ends 3-4 and 3-5 extending outwards, and the extending direction of the connecting ends 3-4 and 3-5 is different from the extending direction of the first end 3-2 and the second end 3-3. Further, the connecting ends 3-4 and 3-5 can be bent, and the extending direction can be adjusted to meet the requirements of different spatial positions. In the embodiment of fig. 3, the connection ends 3-4 and 3-5 are perpendicular to the first end 3-2 and the second end 3-3, respectively.
The first end 3-2 of the first clamp 3 is secured to the first end 4-2 of the second clamp 4 by bolts 6 and the second end 3-3 of the first clamp 3 is secured to the second end 4-3 of the second clamp 4 by bolts.
As shown in FIG. 3, the width of the first clip is L1, the width of the second clip is L2, the width of the first clip is greater than the width of the second clip, and the widened portion forms the connecting end. The width of the connecting ends 3-4 and 3-5 is (L1-L2).
Elastic cushions are arranged between the first clamp 3 and the second clamp 4 and the pipeline.
The space pipeline fixing device clamps the pipeline and limits the movement of the pipeline in the axial direction and the circumferential direction of the rocket. In addition, when the pipeline causes the angle change between the pipeline and the arrow wall due to the deformation of other structures, the first clamp 3 and the second clamp 4 rotate around the rotating shaft bolt along with the pipeline, and certain deformation compensation is provided for the pipeline. During installation, the elastic cushion is arranged between the pipeline and the first clamp 3 and the second clamp 4, the circumferential compensation capacity of the pipeline fixing device can be enhanced, the stress generated by pipeline deformation is released, and the pipeline is prevented from being damaged due to stress concentration.
In summary, the present invention relates to a spatial pipeline fixing device for an aircraft, which includes a first base, a second base, a first clamp, and a second clamp; the first end of the first clamp is fixed to the first end of the second clamp and is connected to the first base; the second end of the first clamp is fixed to the second end of the second clamp and connected to the second base; the first clamp and the second clamp form a limiting ring which is sleeved on the pipeline to limit the pipeline; the first clamp and the second clamp are rotatable relative to the first base and the second base. The utility model changes the connection mode of the hoop and the base in the original scheme, so that the hoop can rotate around the connecting shaft of the base while clamping the pipeline, thereby adapting to the installation angle of the pipeline, rotating along with the pipeline when the pipeline deforms, providing certain deformation compensation for the pipeline, and playing a role in protecting the pipeline.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the utility model and are not to be construed as limiting the utility model. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (9)
1. A space pipeline fixing device for an aircraft is characterized by comprising a first base, a second base, a first clamp and a second clamp;
the first end of the first clamp is fixed to the first end of the second clamp and is connected to the first base; the second end of the first clamp is fixed to the second end of the second clamp and connected to the second base;
the first clamp and the second clamp form a limiting ring which is sleeved on the pipeline to limit the pipeline;
the first clamp and the second clamp are rotatable relative to the first base and the second base.
2. The aircraft spatial pipeline securing device of claim 1, wherein the first and second mounts each comprise a securing portion and a spindle bolt; the fixing part is used for being fixed to a rocket wall or a rocket storage box body structure, and two ends of the rotating shaft bolt are fixed to the fixing part; the first connecting end of the first clamp is connected to the middle of the rotating shaft bolt of the first base and can rotate relative to the first base; the second link of first clamp is connected to the pivot bolt middle part of second base, and can rotate for the second base.
3. The aircraft space pipeline fixing device as claimed in claim 2, wherein two sides of the first connecting end are respectively clamped and limited by sleeve cushion blocks sleeved on the first base rotating shaft bolt; and the two sides of the second connecting end are respectively clamped and limited by sleeve cushion blocks sleeved on the second base rotating shaft bolt.
4. The aircraft spatial pipeline securing device of claim 2, wherein said second clip is a semi-circular ring having a central portion, and wherein said first and second ends are folded outwardly and extend diametrically.
5. The aircraft space tube fixing device of claim 4, wherein the first clamp middle portion is a semicircular ring, the first end and the second end are folded outwards and extend along a diameter direction, the first end and the second end are respectively provided with a first connecting end and a second connecting end which extend outwards, and the extending direction of the first connecting end and the extending direction of the second connecting end are different from the extending direction of the first end and the extending direction of the second end.
6. The aircraft spatial pipeline fixing device of claim 5, wherein the first connecting end and the second connecting end can be bent to adjust the extending direction.
7. The aircraft space tube attachment device of claim 6 wherein the first end of the first clamp is bolted to the first end of the second clamp and the second end of the first clamp is bolted to the second end of the second clamp.
8. The aircraft space tube attachment device of claim 7, wherein the first clip has a width of L1, the second clip has a width of L2, and the attachment end has a width of L1-L2.
9. A space tube attachment apparatus as claimed in claim 1 or claim 2, wherein resilient cushioning is provided between the first and second clips and the tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121968153.7U CN216382839U (en) | 2021-08-20 | 2021-08-20 | Space pipeline fixing device for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121968153.7U CN216382839U (en) | 2021-08-20 | 2021-08-20 | Space pipeline fixing device for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216382839U true CN216382839U (en) | 2022-04-26 |
Family
ID=81238857
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121968153.7U Active CN216382839U (en) | 2021-08-20 | 2021-08-20 | Space pipeline fixing device for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216382839U (en) |
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2021
- 2021-08-20 CN CN202121968153.7U patent/CN216382839U/en active Active
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