CN106828985B - A kind of carburretion heat absorption carrier rocket cooling system - Google Patents
A kind of carburretion heat absorption carrier rocket cooling system Download PDFInfo
- Publication number
- CN106828985B CN106828985B CN201611243478.2A CN201611243478A CN106828985B CN 106828985 B CN106828985 B CN 106828985B CN 201611243478 A CN201611243478 A CN 201611243478A CN 106828985 B CN106828985 B CN 106828985B
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- CN
- China
- Prior art keywords
- heat exchanger
- rocket
- carrier
- delivery pipe
- outlet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
Abstract
The invention discloses a kind of carburretion heat absorption carrier rocket cooling systems, it is intended to solve rocket launching generating process end carrier cooling system investment greatly, the big deficiency of occupied space.The invention includes carrier, several grades of rocket bodies, separable plate heat exchanger is mounted between adjacent two rockets body and between rocket body and carrier, fuel reservoir is mounted in rocket body, evaporating heat exchanger, escape pipe is connected on fuel reservoir, evaporating heat exchanger and fuel reservoir, it is all connected with generating tube between escape pipe and forms circulation path, connection refrigerant delivery pipe forms circulation path between plate heat exchanger and its lower intracorporal evaporating heat exchanger of rocket, it delivers intracorporal plate heat exchanger and blower is connected by heat exchanger tube, the intracorporal plate heat exchanger of rocket is connected in parallel in the intracorporal refrigerant delivery pipe of this grade of rocket by pipeline；Booster pump is installed on the generating tube between evaporating heat exchanger and fuel reservoir, refrigerant circulation pump is installed in refrigerant delivery pipe.
Description
Technical field
The present invention relates to a kind of rocket cooling system, the carrier rocket more specifically, it relates to which a kind of carburretion absorbs heat
Cooling system.
Background technique
Rocket launching is in the process and windage, a large amount of heat of generation are intracorporal in the delivery of rocket end in order to make to be arranged
Equipment generally requires to cool down to the rocket end intracorporal space of delivery from the invasion of high temperature.Common method is in fire
Installation refrigeration equipment cools down in the carrier of arrow end, and this not only adds equipment investments, and occupied space is big.
Summary of the invention
The present invention overcomes rocket launching generating process end carrier cooling system investments greatly, and occupied space is big not
Foot provides a kind of carburretion heat absorption carrier rocket cooling system, the principle of heat is absorbed by carburretion process, is used
Evaporating heat exchanger, plate heat exchanger level-one grade carry out heat exchange, to cooling down in the carrier of rocket end, improve and transport to rocket
The cooling effect of carrier inside is conducive to the reliability service of equipment, reduces the investment of cooling system, reduces occupied space.
In order to solve the above-mentioned technical problem, the carrier rocket the invention adopts the following technical scheme: a kind of carburretion absorbs heat
Cooling system, including carrier, several grades of rocket bodies are respectively mounted between adjacent two rockets body and between rocket body and carrier
There is separable plate heat exchanger, fuel reservoir, evaporating heat exchanger are mounted in rocket body, connects outlet on fuel reservoir
Pipe, escape pipe lower end connect thrust chamber, and generating tube is all connected between evaporating heat exchanger and fuel reservoir, escape pipe and is formed to recycle and is led to
Road, connection refrigerant delivery pipe forms circulation path, carrier between plate heat exchanger and its lower intracorporal evaporating heat exchanger of rocket
Interior plate heat exchanger connects blower by heat exchanger tube, and the intracorporal plate heat exchanger of rocket is connected in parallel on this grade of rocket body by pipeline
In interior refrigerant delivery pipe；Booster pump is installed, in refrigerant delivery pipe on the generating tube between evaporating heat exchanger and fuel reservoir
Refrigerant circulation pump is installed, is respectively arranged with refrigerant in refrigerant delivery pipe.
When rocket is run, liquid fuel is sent out after escape pipe from fuel reservoir in thrust Indoor Combustion, to push away
Get angry flight, and a part of fuel is transported to evaporating heat exchanger by generating tube, to refrigerant delivery pipe in evaporating heat exchanger
Interior refrigerant carries out heat exchange, and the refrigerant circulation after refrigeration is transported to the intracorporal plate heat exchanger of upper level rocket to this grade of rocket
Refrigerant in body refrigerant delivery pipe carries out heat exchange, and circulation conveying is to again upper one after the coolant refrigeration in upper level refrigerant delivery pipe
The intracorporal plate heat exchanger of rocket of grade carries out heat exchange to the refrigerant in this grade of rocket body refrigerant delivery pipe；Such level-one level-one
Heat exchange is up carried out, to intracorporal plate heat exchanger is delivered cold wind is discharged after blower exhausting is cooled, to fortune in heat exchange always
Cool down in carrier.Refrigerant circulation pump drives refrigerant continuous circulation conveying in refrigerant delivery pipe to carry out heat exchange, booster pump
Be conducive to the conveying of generating tube fuel, fuel temperature after evaporating heat exchanger carries out heat exchange increases, the increasing of booster pump at this time
Pressure effect is conducive to improve the pressure in fuel reservoir, it is ensured that the jet power that fuel is exported to escape pipe.When most junior's rocket body
It is interior run out of gas after, this grade of rocket body is separated with rocket main body, the plate heat exchanger point of refrigerant delivery pipe and higher level's rocket body
From separation rocket body drives refrigerant delivery pipe to fall off downwardly together.This carburretion heat absorption carrier rocket cooling system, passes through
Carburretion process absorbs the principle of heat, heat exchange is carried out using evaporating heat exchanger, plate heat exchanger level-one grade, to rocket end
Cool down in portion's carrier, improves to the cooling effect inside rocket carrier, be conducive to the reliability service of equipment, reduce
The investment of cooling system, reduces occupied space.
Preferably, being equipped with mounting head with refrigerant delivery pipe position on plate heat exchanger, refrigerant conveying tube end is connected with
Separating joint, mounting head outer wall are equipped with a circle limiting slot, are socketed with sliding sleeve on separating joint outer wall, sliding sleeve and separating joint it
Between return spring is installed, the mounting hole of several perforations is laid on separating joint, positive stop bead, limit are installed in mounting hole
Pearl is stuck between limiting slot and mounting hole, and sliding sleeve inner wall is equipped with throw-out collar, and sliding sleeve outer wall, which is equipped with, pushes set, sets on separating joint
There is abutment ring, return spring is mounted between abutment ring and throw-out collar, and the card for limiting throw-out collar is socketed on separating joint outer wall
Circle, positive stop bead are arranged between abutment ring and throw-out collar, and promotion, which is put on, is hinged with push rod, the vertically arranged cunning of push rod slidable connection
Rail, sliding rail are connected in rocket body or carrier, are hinged with connecting rod on push rod with sliding rail link position, and connecting rod is connected to junior's fire
On rocket body.
When rocket body falls off, connecting rod is pulled downward on rocket body, to drive push rod to push out sliding sleeve, since refrigerant is defeated
It send pipe that there is certain flexibility, can be bent, refrigerant delivery pipe will not be pulled downward on mounting head connecting pin by rocket body at this time,
After the throw-out collar on sliding sleeve slips over positive stop bead, positive stop bead can be displaced outwardly, and continuing to press on sliding sleeve can be by separating joint from installation
It is pushed on head, connecting rod slips away sliding rail, so that refrigerant delivery pipe, push rod, connecting rod and rocket body be made to fall off downwardly together.It is this
Plate heat exchanger is completely disengaged with refrigerant delivery pipe when structure setting enables junior's rocket body to fall off, it is ensured that the safety of rocket can
By operation.
Preferably, mounting hole structure in a circular table shape, mounting hole inside bore is less than positive stop bead diameter, mounting hole lateral port
Diameter is greater than positive stop bead diameter, and positive stop bead diameter is greater than the distance between two open end of mounting hole.Positive stop bead can be displaced outwardly de-
Be pierced by mounting hole without moving inward from mounting hole, it is convenient that positive stop bead and limiting slot are sticked into and be detached from, be convenient for separating joint from
It is disassembled in mounting head.
Preferably, being equipped with sealing ring with mounting head link position on separating joint inner wall.Sealing ring improves separation
The sealing performance that connector is connect with mounting head.
Preferably, being hinged with slide post on push rod with sliding rail link position, sliding rail is equipped with vertically arranged sliding slot, sliding
Dynamic column is adapted to sliding slot to be slidably connected, and small end is equipped with and helps pull a cart, and helps pull a cart and is actively socketed on slide post.Connecting rod passes through slide post
It slides on the slide rail, sliding process is steadily reliable, and connecting rod is actively socketed on slide post by helping pull a cart, and avoids connecting rod drawing process
In there is stuck phenomenon.
Preferably, evaporating heat exchanger is equipped with fuel inlet, fuel outlet, heat exchange import, heat exchange outlet, plate-type heat-exchange
Device is equipped with junior's import, junior outlet, higher level's import, higher level outlet, and fuel inlet is connected to escape pipe, fuel outlet and increasing
Press pump connection, heat exchange import and junior's outlet, heat exchange outlet and junior's inlet communication, higher level's import, higher level export difference
It is communicated in the refrigerant delivery pipe between heat exchange import and junior outlet by heat exchanger tube, with higher level's import, higher level's outlet
Heat exchanger tube on be mounted on normally open solenoid valve, normally closed solenoid valve is installed in the refrigerant delivery pipe between two normally open solenoid valves.When
When next stage rocket body is not fallen off, normally closed solenoid valve closure, two normally open solenoid valves are opened, the intracorporal refrigerant delivery pipe of this grade of rocket
It is connected to heat exchanger tube.Instantly after one-stage rocket body falls off, normally closed solenoid valve is opened, and two normally open solenoid valves are closed, this grade of rocket body
Interior refrigerant delivery pipe and heat exchanger tube disconnects.
Compared with prior art, the carrier rocket cooling system the beneficial effects of the present invention are: carburretion absorbs heat, passes through combustion
Expect that vaporescence absorbs the principle of heat, heat exchange is carried out using evaporating heat exchanger, plate heat exchanger level-one grade, to rocket end
Cool down in carrier, improves to the cooling effect inside rocket carrier, be conducive to the reliability service of equipment, reduce drop
The investment of warm equipment, reduces occupied space.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of the invention；
Fig. 2 is partial schematic diagram of the invention；
Fig. 3 is the attachment structure schematic diagram of mounting head and separating joint of the invention；
In figure: 1, carrier, 2, rocket body, 3, plate heat exchanger, 4, fuel reservoir, 5, evaporating heat exchanger, 6, escape pipe,
7, thrust chamber, 8, generating tube, 9, refrigerant delivery pipe, 10, blower, 11, booster pump, 12, refrigerant circulation pump, 13, mounting head, 14,
Separating joint, 15, limiting slot, 16, sliding sleeve, 17, return spring, 18, mounting hole, 19, positive stop bead, 20, throw-out collar, 21, promotion set,
22, abutment ring, 23, retainer ring, 24, push rod, 25, sliding rail, 26, connecting rod, 27, sealing ring, 28, slide post, 29, sliding slot, 30, drawing
Set, 31, fuel inlet, 32, fuel outlet, 33, heat exchange import, 34, heat exchange outlet, 35, junior's import, 36, junior outlet,
37, higher level's import, 38, higher level outlet, 39, normally open solenoid valve, 40, normally closed solenoid valve.
Specific embodiment
Below by specific embodiment, and in conjunction with attached drawing, technical scheme of the present invention is further described:
Embodiment: a kind of carburretion absorbs heat carrier rocket cooling system (referring to attached drawing 1 to 3), if including carrier 1,
Dry grade rocket body 2, the present embodiment are arranged three-stage rocket body, pacify between adjacent two rockets body and between rocket body and carrier
Equipped with separable plate heat exchanger 3, booster-missile combination body, three-stage rocket body, carrier lower end are mounted on plate heat exchanger.Fire
It is mounted on fuel reservoir 4, evaporating heat exchanger 5 in rocket body, escape pipe 6 is connected on fuel reservoir, escape pipe lower end connects thrust
Room 7, be all connected between evaporating heat exchanger and fuel reservoir, escape pipe generating tube 8 formed circulation path, plate heat exchanger and its under
Refrigerant delivery pipe 9 is connected between the intracorporal evaporating heat exchanger of rocket and forms circulation path, is delivered intracorporal plate heat exchanger and is passed through
Heat exchanger tube connects blower 10, and the intracorporal plate heat exchanger of rocket is connected in parallel on the intracorporal refrigerant delivery pipe of this grade of rocket by pipeline
On；Booster pump 11 is installed on the generating tube between evaporating heat exchanger and fuel reservoir, refrigerant is installed in refrigerant delivery pipe and is followed
Ring pumps 12, is respectively arranged with refrigerant in refrigerant delivery pipe.It is equipped with mounting head 13 with refrigerant delivery pipe position on plate heat exchanger, refrigerant is defeated
Tube end is sent to be connected with separating joint 14, mounting head outer wall is equipped with a circle limiting slot 15, is socketed with cunning on separating joint outer wall
Set 16, is equipped with return spring 17 between sliding sleeve and separating joint, the mounting hole of several perforations is laid on separating joint
18, mounting hole is interior to install positive stop bead 19, and positive stop bead is stuck between limiting slot and mounting hole, and sliding sleeve inner wall is equipped with throw-out collar 20, sliding
It covering outer wall and is equipped with to push and cover 21, separating joint is equipped with abutment ring 22, and return spring is mounted between abutment ring and throw-out collar, point
From the retainer ring 23 being socketed on connector outer wall for limiting throw-out collar, positive stop bead is arranged between abutment ring and throw-out collar, and promotion is put on
It is hinged with push rod 24, the vertically arranged sliding rail 25 of push rod slidable connection, sliding rail is connected in rocket body or carrier, on push rod
It is hinged with connecting rod 26 with sliding rail link position, connecting rod is connected on junior's rocket body.Mounting hole structure in a circular table shape, in mounting hole
Side port diameter is less than positive stop bead diameter, and bore is greater than positive stop bead diameter on the outside of mounting hole, and positive stop bead diameter is open greater than mounting hole two
The distance between end.On separating joint inner wall and mounting head link position is equipped with sealing ring 27.On push rod with sliding rail connection position
It sets and is hinged with slide post 28, sliding rail is equipped with vertically arranged sliding slot 29, and slide post is adapted to sliding slot and is slidably connected, small end
Equipped with helping pull a cart 30, helps pull a cart and be actively socketed on slide post.Evaporating heat exchanger is equipped with fuel inlet 31, fuel outlet 32, heat exchange
Import 33, heat exchange outlet 34, plate heat exchanger are equipped with junior's import 35, junior outlet 36, higher level's import 37, higher level outlet
38, fuel inlet is connected to escape pipe, and fuel outlet is connected to booster pump, heat exchange import and junior's outlet, heat exchange outlet
With junior's inlet communication, higher level's import, higher level outlet are communicated between heat exchange import and junior outlet by heat exchanger tube respectively
In refrigerant delivery pipe, with higher level's import, higher level's outlet heat exchanger tube on be mounted on normally open solenoid valve 39, two normally opened electromagnetism
Normally closed solenoid valve 40 is installed in the refrigerant delivery pipe between valve.
When rocket is run, liquid fuel is sent out after escape pipe from fuel reservoir in thrust Indoor Combustion, to push away
Get angry flight, and a part of fuel is transported to evaporating heat exchanger by generating tube, to refrigerant delivery pipe in evaporating heat exchanger
Interior refrigerant carries out heat exchange, and the refrigerant circulation after refrigeration is transported to the intracorporal plate heat exchanger of upper level rocket to this grade of rocket
Refrigerant in body refrigerant delivery pipe carries out heat exchange, and circulation conveying is to again upper one after the coolant refrigeration in upper level refrigerant delivery pipe
The intracorporal plate heat exchanger of rocket of grade carries out heat exchange to the refrigerant in this grade of rocket body refrigerant delivery pipe；Such level-one level-one
Heat exchange is up carried out, to intracorporal plate heat exchanger is delivered cold wind is discharged after blower exhausting is cooled, to fortune in heat exchange always
Cool down in carrier.Refrigerant circulation pump drives refrigerant continuous circulation conveying in refrigerant delivery pipe to carry out heat exchange, booster pump
Be conducive to the conveying of generating tube fuel, fuel temperature after evaporating heat exchanger carries out heat exchange increases, the increasing of booster pump at this time
Pressure effect is conducive to improve the pressure in fuel reservoir, it is ensured that the jet power that fuel is exported to escape pipe.When most junior's rocket body
It is interior run out of gas after, this grade of rocket body is separated with rocket main body, the plate heat exchanger point of refrigerant delivery pipe and higher level's rocket body
From separation rocket body drives refrigerant delivery pipe to fall off downwardly together.This carburretion heat absorption carrier rocket cooling system, passes through
Carburretion process absorbs the principle of heat, heat exchange is carried out using evaporating heat exchanger, plate heat exchanger level-one grade, to rocket end
Cool down in portion's carrier, improves to the cooling effect inside rocket carrier, be conducive to the reliability service of equipment, reduce
The investment of cooling system, reduces occupied space.
Above-mentioned embodiment is only a preferred solution of the present invention, not the present invention is made in any form
Limitation, there are also other variations and modifications on the premise of not exceeding the technical scheme recorded in the claims.
Claims (6)
- The carrier rocket cooling system 1. a kind of carburretion absorbs heat, characterized in that adjacent including carrier, several grades of rocket bodies It is mounted on separable plate heat exchanger between two rocket bodies and between rocket body and carrier, is mounted in rocket body Fuel reservoir, evaporating heat exchanger, escape pipe is connected on fuel reservoir, and escape pipe lower end connects thrust chamber, evaporating heat exchanger and combustion It is all connected with generating tube between material storage tank, escape pipe and forms circulation path, plate heat exchanger and its lower intracorporal evaporation and heat-exchange of rocket Refrigerant delivery pipe is connected between device and forms circulation path, is delivered intracorporal plate heat exchanger by heat exchanger tube and is connected blower, rocket Intracorporal plate heat exchanger is connected in parallel in the intracorporal refrigerant delivery pipe of this grade of rocket by pipeline；Evaporating heat exchanger and fuel reservoir Between generating tube on booster pump is installed, refrigerant circulation pump is installed in refrigerant delivery pipe, is respectively arranged in refrigerant delivery pipe cold Matchmaker.
- The carrier rocket cooling system 2. a kind of carburretion according to claim 1 absorbs heat, characterized in that plate heat exchanger Upper and refrigerant delivery pipe position is equipped with mounting head, and refrigerant conveying tube end is connected with separating joint, and mounting head outer wall is equipped with one Limiting slot is enclosed, is socketed with sliding sleeve on separating joint outer wall, return spring is installed between sliding sleeve and separating joint, on separating joint It is laid with the mounting hole of several perforations, positive stop bead is installed in mounting hole, positive stop bead is stuck between limiting slot and mounting hole, sliding It covers inner wall and is equipped with throw-out collar, sliding sleeve outer wall, which is equipped with, pushes set, and separating joint is equipped with abutment ring, and return spring is mounted on abutting Between ring and throw-out collar, the retainer ring for limiting throw-out collar is socketed on separating joint outer wall, positive stop bead is arranged in abutment ring and throw-out collar Between, promotion, which is put on, is hinged with push rod, and the vertically arranged sliding rail of push rod slidable connection, sliding rail is connected to rocket body or carrier It is interior, connecting rod is hinged on push rod with sliding rail link position, connecting rod is connected on junior's rocket body.
- The carrier rocket cooling system 3. a kind of carburretion according to claim 2 absorbs heat, characterized in that mounting hole is in circle Mesa-shaped structure, mounting hole inside bore are less than positive stop bead diameter, and bore is greater than positive stop bead diameter, positive stop bead diameter on the outside of mounting hole Greater than the distance between two open end of mounting hole.
- The carrier rocket cooling system 4. a kind of carburretion according to claim 2 absorbs heat, characterized in that in separating joint On wall and mounting head link position is equipped with sealing ring.
- 5. a kind of carburretion heat absorption carrier rocket cooling system according to Claims 2 or 3 or 4, characterized in that push rod Upper and sliding rail link position is hinged with slide post, and sliding rail is equipped with vertically arranged sliding slot, and slide post is adapted to sliding with sliding slot and connects It connects, small end is equipped with and helps pull a cart, and helps pull a cart and is actively socketed on slide post.
- The carrier rocket cooling system 6. a kind of carburretion according to claim 1 or 2 or 3 or 4 absorbs heat, characterized in that Evaporating heat exchanger be equipped with fuel inlet, fuel outlet, heat exchange import, heat exchange outlet, plate heat exchanger be equipped with junior's import, Junior outlet, higher level's import, higher level outlet, fuel inlet are connected to escape pipe, and fuel outlet is connected to booster pump, and exchange heat import With junior's outlet, heat exchange outlet and junior's inlet communication, higher level's import, higher level outlet are communicated to by heat exchanger tube change respectively Hot import and junior outlet between refrigerant delivery pipe on, with higher level's import, higher level's outlet heat exchanger tube on be mounted on Normally open solenoid valve installs normally closed solenoid valve in the refrigerant delivery pipe between two normally open solenoid valves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611243478.2A CN106828985B (en) | 2016-12-29 | 2016-12-29 | A kind of carburretion heat absorption carrier rocket cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611243478.2A CN106828985B (en) | 2016-12-29 | 2016-12-29 | A kind of carburretion heat absorption carrier rocket cooling system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106828985A CN106828985A (en) | 2017-06-13 |
| CN106828985B true CN106828985B (en) | 2019-01-15 |
Family
ID=59113886
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611243478.2A Expired - Fee Related CN106828985B (en) | 2016-12-29 | 2016-12-29 | A kind of carburretion heat absorption carrier rocket cooling system |
Country Status (1)
| Country | Link |
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| CN (1) | CN106828985B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5103897A (en) * | 1991-06-05 | 1992-04-14 | Martin Marietta Corporation | Flowrate controller for hybrid capillary/mechanical two-phase thermal loops |
| US5954298A (en) * | 1997-04-28 | 1999-09-21 | Motorola, Inc. | Active spacecraft thermal control system and method |
| FR2829746B1 (en) * | 2001-09-18 | 2003-12-19 | Cit Alcatel | HEAT TRANSFER DEVICE |
| FR2912995B1 (en) * | 2007-02-26 | 2009-05-22 | Alcatel Lucent Sas | THERMAL CONTROL DEVICE ON BOARD A SPACE ENGINE |
| CN101580134A (en) * | 2009-06-19 | 2009-11-18 | 哈尔滨工业大学 | Cooling system of hypersonic aircraft based on Stirling cycle |
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2016
- 2016-12-29 CN CN201611243478.2A patent/CN106828985B/en not_active Expired - Fee Related
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| Publication number | Publication date |
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| CN106828985A (en) | 2017-06-13 |
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Granted publication date: 20190115 Termination date: 20191229 |