CN117146103A - Rocket air conditioner pipeline system - Google Patents
Rocket air conditioner pipeline system Download PDFInfo
- Publication number
- CN117146103A CN117146103A CN202311416845.4A CN202311416845A CN117146103A CN 117146103 A CN117146103 A CN 117146103A CN 202311416845 A CN202311416845 A CN 202311416845A CN 117146103 A CN117146103 A CN 117146103A
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- Prior art keywords
- pipe
- telescopic
- fixed
- sleeve
- fixedly connected
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- 238000004378 air conditioning Methods 0.000 claims abstract description 32
- 238000004321 preservation Methods 0.000 claims abstract description 30
- 238000009423 ventilation Methods 0.000 claims abstract description 17
- 229910052751 metal Inorganic materials 0.000 claims abstract description 7
- 239000002184 metal Substances 0.000 claims abstract description 7
- 239000012774 insulation material Substances 0.000 claims abstract description 3
- 238000009413 insulation Methods 0.000 claims description 14
- 230000009471 action Effects 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 3
- 230000003044 adaptive effect Effects 0.000 claims description 2
- 230000008602 contraction Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 abstract 1
- 239000011810 insulating material Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000004804 winding Methods 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 229920000742 Cotton Polymers 0.000 description 1
- 229910001182 Mo alloy Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- MGRWKWACZDFZJT-UHFFFAOYSA-N molybdenum tungsten Chemical compound [Mo].[W] MGRWKWACZDFZJT-UHFFFAOYSA-N 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L57/00—Protection of pipes or objects of similar shape against external or internal damage or wear
- F16L57/04—Protection of pipes or objects of similar shape against external or internal damage or wear against fire or other external sources of extreme heat
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L23/00—Flanged joints
- F16L23/02—Flanged joints the flanges being connected by members tensioned axially
- F16L23/032—Flanged joints the flanges being connected by members tensioned axially characterised by the shape or composition of the flanges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L27/00—Adjustable joints, Joints allowing movement
- F16L27/12—Adjustable joints, Joints allowing movement allowing substantial longitudinal adjustment or movement
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
- F16L3/02—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets partly surrounding the pipes, cables or protective tubing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L59/00—Thermal insulation in general
- F16L59/02—Shape or form of insulating materials, with or without coverings integral with the insulating materials
- F16L59/028—Composition or method of fixing a thermally insulating material
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
The application discloses a rocket air-conditioning pipeline system, which belongs to rocket launching equipment technology and comprises a telescopic bracket, a ventilation pipe and a heat-insulating sleeve; the telescopic bracket comprises a fixed bracket and a movable bracket; the movable frame is configured to be telescopic along the length direction of the fixed frame; the ventilation pipe comprises a telescopic pipe and a fixed pipe; the fixed pipe is fixedly connected with the movable frame; the fixed pipe is a hard metal pipe with a heat insulation material sleeved inside; one end of the telescopic pipe is fixedly connected with the fixed pipe, and the other end of the telescopic pipe is fixedly connected with the fixed frame; the heat preservation sleeve is configured to be sleeved outside the telescopic pipe or the fixed pipe; when the heat preservation sleeve is sleeved outside the telescopic pipe, the heat preservation sleeve is used for heat preservation of the telescopic pipe. The application can realize the expansion and contraction of the air-conditioning pipeline, effectively avoid the problem of burning the pipeline during the rocket launching, realize the reusability of the air-conditioning pipeline and ensure the safety of the rocket launching.
Description
Technical Field
The application relates to the technical field of rocket launching equipment, in particular to a rocket air-conditioning pipeline system.
Background
Ventilation is continuously carried out on the rectification cover before the rocket is launched, so that the temperature and humidity requirements are met. The air conditioning pipeline is communicated with the air inlet of the fairing after being discharged from the air conditioner in the transmitting platform, and the air conditioning pipeline is disconnected with the fairing before transmitting. At present, air conditioning pipelines of rockets of various types are coiled or embedded on a telescopic or backward device, and the integral front shooting follow-up device is separated from the rockets so as to realize pipeline ventilation and disconnection.
In daily practice, the inventor finds that the prior technical scheme has the following problems:
when the rocket is launched, the pipeline is not reusable and has low universality because the flexible pipeline has poor temperature resistance and the pipeline is easy to burn through wholly or locally by rocket tail flame. Meanwhile, the air conditioning unit system is easy to damage due to pipeline combustion, and potential safety hazards exist in open flame.
In view of the foregoing, it is necessary to provide a new solution to the above-mentioned problems.
Disclosure of Invention
In order to solve the technical problems, the application provides the rocket air-conditioning pipeline system, which can effectively avoid the problem of burning out the pipeline during rocket launching while realizing the expansion and contraction of the air-conditioning pipeline, realizes the reusability of the air-conditioning pipeline and ensures the safety of rocket launching.
A rocket air conditioning piping system comprising:
a telescopic bracket; the telescopic bracket comprises a fixed bracket and a movable bracket; the movable frame is configured to be telescopic along the length direction of the fixed frame;
a ventilation pipe; the ventilating pipe comprises a telescopic pipe and a fixed pipe; the fixed pipe is fixedly connected with the movable frame; the fixed pipe is a hard metal pipe with a heat insulation material sleeved inside; one end of the telescopic pipe is fixedly connected with the fixed pipe; the other end of the telescopic tube is fixedly connected with the fixing frame;
a heat-insulating sleeve; the heat preservation sleeve is configured to be sleeved outside the telescopic pipe or the fixed pipe; when the heat preservation sleeve is sleeved outside the telescopic pipe, the heat preservation sleeve is used for preserving heat of the telescopic pipe.
Preferably, the fixing frame is internally provided with an installation cavity which is arranged along the length direction and penetrates through the fixing frame; the movable frame is movably arranged in the mounting cavity and can extend out of the mounting cavity under the action of external force.
Preferably, the fixing frame is a truss structure with an installation cavity inside; the fixed frame is sleeved outside the movable frame.
Preferably, the movable frame is internally provided with a loading cavity arranged along the length direction; the fixed pipe is fixedly arranged in the loading cavity.
Preferably, the movable frame is detachably and fixedly provided with a connecting seat; the fixed pipe is fixedly connected with the movable frame through the connecting seat.
Preferably, the device further comprises a lifting device for adjusting the position of the heat-insulating sleeve; the lifting device comprises a lifter and a cable; the lifter is fixedly connected with the movable frame; the upper end of the mooring rope is fixed with the lifter, and the length of the mooring rope can be controlled by means of the hoisting action of the lifter; the lower end of the mooring rope is fixedly connected with the heat insulation sleeve.
Preferably, the device further comprises a positioning plate fixedly connected with the fixing frame; the telescopic pipe is fixedly connected with the positioning plate; a positioning piece is fixedly arranged at the lower end of the heat-insulating sleeve; the locating plate is provided with a limiting hole; the limiting hole is arranged below the moving path of the positioning piece; the shape of the limiting hole is adapted to the positioning piece.
Preferably, the heat insulation sleeve further comprises a support sleeve for supporting the heat insulation sleeve; the support sleeve is fixedly arranged on the upper surface of the positioning plate; the upper end part of the support sleeve is fixedly provided with a support flange.
Preferably, the support flange is arranged below the moving path of the heat insulation sleeve; the support flange comprises a flange body and a limiting convex ring fixedly arranged on the upper surface of the flange body; the lower end of the heat preservation sleeve is provided with a support disc; and a limiting groove which is adaptive to the limiting convex ring is formed in the lower surface of the supporting disc.
Preferably, the heat insulation sleeve further comprises a radial limiting piece for radially limiting the heat insulation sleeve; the radial limiting piece is fixedly connected with the movable frame.
Compared with the prior art, the application has at least the following beneficial effects:
1. the fixing pipe is a hard metal pipe, has a thermal protection effect, effectively avoids the problem that a pipeline is burnt out during rocket launching, realizes the reusability of the air-conditioning pipeline, and ensures the rocket launching safety.
2. The telescopic pipe is connected with the fixed pipe, and can realize the telescopic function of the pipeline.
3. The application is provided with the heat preservation sleeve which can be sleeved outside the telescopic pipe and is used for realizing heat preservation of the position of the telescopic pipe.
4. The application has the casing cavity and the support flange, can position and support the heat-insulating casing, and stabilizes the pipeline.
Drawings
Some specific embodiments of the application 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 will be used throughout the drawings to refer to the same or like parts or portions. It will be appreciated by those skilled in the art that the drawings are not necessarily drawn to scale. In the accompanying drawings:
FIG. 1 is a schematic view of the whole structure in a contracted state according to an embodiment of the present application;
FIG. 2 is a schematic view of the whole structure of the present application in an extended state;
FIG. 3 is a schematic view of a part of the position of the lifting device according to the present application;
FIG. 4 is a schematic view of a partial structure of the positioning plate according to the present application;
FIG. 5 is a schematic view of the connection position of the locating plate and the supporting sleeve according to the present application.
Wherein the above figures include the following reference numerals:
11. the movable frame, 12, the fixed frame, 13, the connecting seat, 21, the first connecting flange, 22, the fixed pipe, 23, the heat insulation sleeve, 24, the second connecting flange, 25, the telescopic pipe, 31, the lifter, 32, the cable, 33, the lifting disc, 34, the fixed rope ring, 41, the locating plate, 42, the supporting sleeve, 43, the limiting hole, 44, the locating piece, 45, the sleeve cavity, 46, the supporting flange, 461, the flange body, 462 and the limiting convex ring.
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 clearly and completely described below with reference to specific embodiments of the present application and corresponding drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
As shown in fig. 1 and 2, a rocket air conditioning pipeline system includes: a telescopic bracket, a ventilation pipe and a heat preservation sleeve 23.
The telescopic bracket comprises a fixed bracket 12 and a movable bracket 11, and the movable bracket 11 is configured to be telescopic along the length direction of the fixed bracket 12.
The ventilating pipe comprises a telescopic pipe 25 and a fixed pipe 22, and the fixed pipe 22 is fixedly connected with the movable frame 11. The fixed pipe 22 is a hard metal pipe with a heat insulating material sleeved inside. One end of the telescopic tube 25 is fixedly connected with the fixed tube 22, and the other end is fixedly connected with the fixed frame 12. The telescopic tube 25 can realize synchronous expansion and contraction along with the relative movement between the movable frame 11 and the fixed frame 12.
The heat-insulating sleeve 23 is configured to be able to be sleeved outside the telescopic tube 25 or the fixed tube 22, and is used for heat insulation of the telescopic tube 25 when the heat-insulating sleeve 23 is sleeved outside the telescopic tube 25.
The fixing frame 12 is internally provided with a mounting cavity (not shown in the figure) which is arranged along the length direction and penetrates through the fixing frame, and the movable frame 11 is movably arranged in the mounting cavity and can move in the mounting cavity under the action of external force so as to extend out of or retract into the mounting cavity.
The movable frame 11 has a loading chamber (not shown) provided along the length direction thereof, and the fixed tube 22 is fixedly provided in the loading chamber so that the fixed tube 22 can move synchronously with the movable frame 11. Meanwhile, the fixed pipe 22 is fixedly arranged in the loading cavity, so that the movable frame 11 can be used as an external protection structure of the fixed pipe 22, and damage to the fixed pipe due to external collision is avoided. In addition, the structure can effectively save space and reduce the whole volume of the rocket air-conditioning pipeline system.
The mount 12 is preferably a truss structure. The fixed frame 12 is sleeved outside the movable frame 11.
As a preferred embodiment of the present application, the fixing tube 22 may be a 3-layered tube structure including an inner tube, an outer tube, and a heat insulating layer disposed between the inner tube and the outer tube. Wherein, the outer tube is made of hard metal tube, the heat-insulating layer is made of nonflammable heat-insulating material, and the material can be foaming heat-insulating material or heat-insulating cotton meeting corresponding fire-proof grade. Because the outer tube adopts a hard metal tube, the outer tube has higher melting point and better heat dissipation property when the rocket is launched, the burning-through of rocket tail flame can be effectively avoided, and the reutilization of an air-conditioning pipeline is realized. In addition, in order to further improve the temperature resistance of the air conditioner pipeline, the outer pipe can be made of metal materials with good temperature resistance, such as titanium alloy, tungsten-molybdenum alloy, nickel-based alloy and the like. The inner tube can be selected from a corresponding hard tube or flexible tube according to ventilation requirements on the premise of meeting tightness and ventilation requirements.
As a preferred embodiment of the application, the bellows 25 is preferably a three-proof flexible vent. On the premise of meeting the ventilation requirement and the expansion requirement, the expansion pipe 25 can be of other pipe structures with expansion functions. In addition, the telescopic length of the device is correspondingly designed according to the height of the rocket and the height of the umbilical tower. Taking a certain rocket as an example, the telescopic height is required to be about 9m, and the telescopic ratio is set to be 1:10 according to environmental requirements such as air temperature conditions, pressure intensity and the like and the requirement of redundant design. Also, the ventilation diameter of the ventilation pipe is phi 300 according to the functional requirements of the rocket type. Furthermore, the ventilation diameter of the ventilation pipe can be designed to be of other dimensions according to corresponding requirements according to different rocket models and fairing dimensions.
As a preferred embodiment of the application, the fixing tube 22 is fixedly provided with a first connecting flange 21 and the bottom of the telescopic tube 25 is fixedly provided with a second connecting flange 24 for the connection of the ventilating tube to the outside. The telescopic tube 25 and the fixed tube 22 may be connected by a flange.
As another embodiment of the present application, the telescopic bracket further includes a driving structure for driving the relative movement between the fixed frame 12 and the movable frame 11. For example, the drive mechanism may employ a gear train.
When the driving structure adopts a gear transmission mechanism, the driving structure comprises a gear and a rack which are respectively fixed on the fixed frame 12 and the movable frame 11, the gear is connected with a motor in a transmission way, the motor is used for providing rotation power, and the relative movement between the fixed frame 12 and the movable frame 11 is realized by the meshing of the gear and the rack.
In addition, external hoisting equipment such as travelling crane, crane and the like can be used for hoisting the movable frame 11 so as to realize the relative movement between the movable frame and the fixed frame 12.
Preferably, a slideway is further arranged between the fixed frame 12 and the movable frame 11 to ensure that the fixed frame 12 and the movable frame move according to a preset track in a relative movement state.
As another embodiment of the present application, the holder 12 may alternatively have other structures with supporting capability and having a mounting cavity therein, such as a tubular structure or a box structure.
As another embodiment of the present application, the movable frame 11 is detachably fixed with the connection base 13. The fixed tube 22 can be fixedly connected with the movable frame 11 through the connection base 13. The connection base 13 can be detachably connected with the movable frame 11 by means of a bolt connection. Through changing the connecting seat 13 of different sizes and types, can realize the change of the fixed pipe 22 of different specifications, types, and then adapt to the fixed pipe 22 of different specifications, types, improve the adaptability that reduces rocket air conditioner pipe system. Meanwhile, the position of the fixed pipe 22 can be adjusted by replacing the connecting seats 13 with different sizes and types, and the fixed pipe is suitable for supplementing rocket fairings with different types and sizes.
As another embodiment of the present application, as shown in fig. 3, the rocket air conditioning piping system further includes a lifting device for adjusting the position of the insulating sleeve 23. The lifting device comprises a lift 31 and a cable 32. The lifter 31 is preferably a hoist and is fixedly connected to the moving frame 11. The lifter 31 is fixedly arranged at the upper end part or the upper part of the side surface of the movable frame 11 and is arranged above the heat insulation sleeve 23. The upper end of the cable 32 is fixed to the lifter 31, and the length thereof can be controlled by the winding action of the lifter 31. The upper end of the heat preservation sleeve 23 is provided with a lifting disk 33 fixedly connected with the main body part of the heat preservation sleeve. The lifting disk 33 is provided with the same number of fixed rope loops 34 as the ropes 32. The lower end of the cable 32 is fixedly connected with the heat insulation sleeve 23 through a fixed rope ring 34. The elevator 31 controls the length of the cable 32 by the winding action, and can control the height of the heat insulation sleeve 23, thereby realizing the adjustment of the relative position between the heat insulation sleeve 23 and the telescopic pipe 25. Meanwhile, by means of the start and stop of the lifter 31, the movement and stop of the insulating sleeve 23 can be realized to ensure that the insulating sleeve 23 stays in place.
As another embodiment of the present application, as shown in fig. 4 and 5, the rocket air conditioning pipeline system further includes a positioning plate 41 fixedly connected to the fixing frame 12. The telescopic tube 25 is fixedly connected with the positioning plate 41, so that the telescopic tube 25 can realize synchronous telescopic along with the relative movement between the movable frame 11 and the fixed frame 12. A positioning piece 44 is fixed at the lower end of the heat preservation sleeve 23. The positioning members 44 are preferably tapered positioning columns, which are arranged on a circle centered on the center of the insulating sleeve 23. The positioning plate 41 is provided with a limiting hole 43. The limiting holes 43 are arranged below the moving path of the positioning piece 44, and the shape and the number of the limiting holes are matched with those of the positioning piece 44, so that the positioning piece 44 is inserted into the limiting holes 43 in the downward moving process of the heat preservation sleeve 23, and the limit of the heat preservation sleeve 23 is realized.
As another embodiment of the present application, the rocket air conditioning piping system further includes a support sleeve 42 for supporting the insulating sleeve 23. The support sleeve 42 is fixedly arranged on the upper surface of the positioning plate 41, and the upper end part of the support sleeve 42 is fixedly provided with a support flange 46. The support sleeve 42 comprises a sleeve cavity 45, the sleeve cavity 45 penetrating the support flange 46, so that the body of the telescopic tube 25 can pass through the support sleeve 42. The support sleeve 42 can support the insulation sleeve 23, thereby reducing the stress of the lifter 31 and the cable 32 and prolonging the service life thereof. The support flange 46 is arranged below the moving path of the heat preservation sleeve 23, and can limit the heat preservation sleeve 23, so that the heat preservation sleeve 23 can be stopped at a proper position, the extension pipe 25 is ensured to be surrounded, and the heat preservation effect is improved.
As another embodiment of the present application, the support flange 46 includes a flange body 461 and a limiting collar 462 fixedly provided on an upper surface of the flange body 461. Correspondingly, the lower end of the heat preservation sleeve 23 is provided with a supporting disc (not shown in the figure), and the lower surface of the supporting disc is provided with a limiting groove which is matched with the limiting convex ring 462, so that when the heat preservation sleeve 23 is contacted with the supporting flange 46, the limiting convex ring 462 can be inserted into the limiting groove, the limit of the supporting flange 46 to the heat preservation sleeve 23 is further realized, and the heat preservation sleeve 23 can be ensured to be in a preset position in the horizontal direction.
As another embodiment of the present application, the rocket air conditioning piping system further includes a radial limiter (not shown) for radially limiting the insulating sleeve 23. The radial limiting piece is fixedly connected with the movable frame 11 and is arranged on the outer circumference of the heat preservation sleeve 23. The radial limiting part comprises a support frame and a wheel body arranged at the end part of the support frame, one side of the support frame is fixedly connected with the fixing frame 12, and the wheel body is rotatably arranged for the other time.
As a modification of the present application, a moving rack is disposed parallel to a fixed rack, and the moving rack is slidably disposed on a side surface of the fixed rack. The two rely on the spout structure to realize spacing non-moving direction's spacing, for example, adopt dovetail and dovetail slider structure, or T type groove and T type slider structure, realize the connection of movable rack and mount. Likewise, the movable frame and the fixed frame are driven by means of the existing driving structure, so that the movable frame can move along the length direction of the fixed frame, and the telescopic function of the telescopic bracket is achieved. The use of the driving structure to drive the two sliding structures to move belongs to the prior art, and will not be described in detail here.
In operation, as shown in fig. 1 and 2, when the cowling is supplied in real time, the movable frame 11 moves relative to the fixed frame 12, and the telescopic frame is extended. At this time, the telescopic tube 25 is stretched by the movement of the moving frame 11, ensuring that the ventilating tube has a sufficient stretching length. Thereafter, the lifter 31 works to elongate the cable 32 under the winding action thereof, and the heat-insulating sleeve 23 moves downward gradually and is completely sleeved outside the telescopic tube 25 to insulate the telescopic tube 25. Meanwhile, one end of the ventilation pipe is communicated with the inside of the fairing, and the other end of the ventilation pipe is communicated with the air conditioning system, so that the air conditioning system supplies air into the fairing in real time.
Before the rocket is launched, the ventilation pipe is separated from the communication position of the fairing, the heat preservation sleeve 23 is lifted to the initial position, the movable frame 11 moves relative to the fixed frame 12, the telescopic frame is shortened, and finally the initial state is restored.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (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 also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated 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 the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the application described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A rocket air conditioning piping system, comprising:
a telescopic bracket; the telescopic bracket comprises a fixed bracket and a movable bracket; the movable frame is configured to be telescopic along the length direction of the fixed frame;
a ventilation pipe; the ventilating pipe comprises a telescopic pipe and a fixed pipe; the fixed pipe is fixedly connected with the movable frame; the fixed pipe is a hard metal pipe with a heat insulation material sleeved inside; one end of the telescopic pipe is fixedly connected with the fixed pipe; the other end of the telescopic tube is fixedly connected with the fixing frame;
a heat-insulating sleeve; the heat preservation sleeve is configured to be sleeved outside the telescopic pipe or the fixed pipe; when the heat preservation sleeve is sleeved outside the telescopic pipe, the heat preservation sleeve is used for preserving heat of the telescopic pipe.
2. A rocket air-conditioning duct system as recited in claim 1 wherein said mount has a mounting cavity therein along a length thereof and disposed therethrough; the movable frame is movably arranged in the mounting cavity and can extend out of the mounting cavity under the action of external force.
3. A rocket air-conditioning piping system according to claim 2, wherein said mount is a truss structure having an installation cavity therein; the fixed frame is sleeved outside the movable frame.
4. A rocket air-conditioning duct system according to any one of claims 1-3 wherein said mobile carriage has a loading chamber disposed along a length thereof; the fixed pipe is fixedly arranged in the loading cavity.
5. A rocket air-conditioning pipeline system according to claim 4 wherein said mobile frame is detachably secured with a connecting seat; the fixed pipe is fixedly connected with the movable frame through the connecting seat.
6. A rocket air-conditioning piping system according to claim 1, further comprising lifting means for adjusting the position of said insulating sleeve; the lifting device comprises a lifter and a cable; the lifter is fixedly connected with the movable frame; the upper end of the mooring rope is fixed with the lifter, and the length of the mooring rope can be controlled by means of the hoisting action of the lifter; the lower end of the mooring rope is fixedly connected with the heat insulation sleeve.
7. A rocket air-conditioning duct system as recited in claim 6, further comprising a locating plate fixedly connected to said mount; the telescopic pipe is fixedly connected with the positioning plate; a positioning piece is fixedly arranged at the lower end of the heat-insulating sleeve; the locating plate is provided with a limiting hole; the limiting hole is arranged below the moving path of the positioning piece; the shape of the limiting hole is adapted to the positioning piece.
8. A rocket air-conditioning piping system according to claim 7, further comprising a support sleeve for supporting said insulating sleeve; the support sleeve is fixedly arranged on the upper surface of the positioning plate; the upper end part of the support sleeve is fixedly provided with a support flange.
9. A rocket air conditioning piping system according to claim 8, wherein said support flange is disposed below said insulating sleeve travel path; the support flange comprises a flange body and a limiting convex ring fixedly arranged on the upper surface of the flange body; the lower end of the heat preservation sleeve is provided with a support disc; and a limiting groove which is adaptive to the limiting convex ring is formed in the lower surface of the supporting disc.
10. A rocket air-conditioning piping system according to claim 9, further comprising a radial stop for radially stopping said insulating sleeve; the radial limiting piece is fixedly connected with the movable frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311416845.4A CN117146103B (en) | 2023-10-30 | 2023-10-30 | Rocket air conditioner pipeline system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
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| CN117146103B (en) | 2024-01-30 |
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