CN108915898A - A kind of rocket engine reducing fuel consumption - Google Patents
A kind of rocket engine reducing fuel consumption Download PDFInfo
- Publication number
- CN108915898A CN108915898A CN201810756608.5A CN201810756608A CN108915898A CN 108915898 A CN108915898 A CN 108915898A CN 201810756608 A CN201810756608 A CN 201810756608A CN 108915898 A CN108915898 A CN 108915898A
- Authority
- CN
- China
- Prior art keywords
- slide plate
- shell
- fuel consumption
- fixedly connected
- inner cavity
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of rocket engines for reducing fuel consumption, including shell, the side of the shell is communicated with communicating pipe, and one end that communicating pipe is located at hull outside is communicated with heat dissipation tank, slide plate is fixedly connected between the top and bottom of the heat dissipation box cavity, and the back side of slide plate is fixedly connected with motor by connecting plate, the output shaft of the motor runs through slide plate and extends to the surface of slide plate, and one end that motor output shaft extends to sled surface is fixedly connected with disk, and the present invention relates to technical field of engines.The rocket engine of the reduction fuel consumption, it can reduce the loss of fuel, have the function of heat dissipation, rocket engine is avoided to damage because of overheat, transfer efficiency is high, incendiary agent and oxidant mixing are abundant, high combustion efficiency, easy to use, effect is good, fuel consumption is small, hot driving amount is small, reduces fuel cost, avoids energy waste and pollution environment.
Description
Technical field
The present invention relates to technical field of engines, specially a kind of rocket engine for reducing fuel consumption.
Background technique
Rocket engine carries propellant by aircraft, does not utilize the jet engine of outside air, can be dense big
Space-Work other than gas-bearing formation, the energy are converted into the kinetic energy of working medium in rocket engine, form high-speed jet discharge and generate and push away
Power, rocket engine are exactly to utilize impulse principle, included propellant, the jet engine for not depending on outside air, rocket motor
Machine is one kind of jet engine, and the reactant in propellant tank or delivery vehicle is become high-speed jet, due to newton
Three laws of motion and generate thrust, rocket engine can be used for spacecraft propulsion, it can also be used to guided missile etc. endoatmosphere fly,
Most of rocket engine is all internal combustion engine, also there is the engine of non-burning form, and existing rocket engine is difficult to decrease combustion
The loss of material.
Traditional rocket engine is very simple mechanism mostly, it is difficult to the loss for reducing fuel, the function without heat dissipation
Can, rocket engine is easy to damage because of overheat, and transfer efficiency is low, and incendiary agent and oxidant mixing are not enough, and burns
Low efficiency is not convenient to use, and effect is not good enough, and fuel consumption is big, hot driving amount is big, is increased fuel cost, is be easy to cause energy
Source waste and pollution environment.
Summary of the invention
In view of the deficiencies of the prior art, the present invention provides a kind of rocket engine for reducing fuel consumption, fire is solved
Arrow engine is difficult to decrease the loss of fuel, the function without heat dissipation and be easy to cause energy waste and pollute asking for environment
Topic.
In order to achieve the above object, the present invention is achieved by the following technical programs：A kind of rocket reducing fuel consumption
Engine, including shell, the side of the shell is communicated with communicating pipe, and the one end for being located at hull outside communicating pipe is communicated with
Heat dissipation tank is fixedly connected with slide plate between the top and bottom of the heat dissipation box cavity, and the back side of slide plate passes through connecting plate
It is fixedly connected with motor, the output shaft of the motor runs through slide plate and extends to the surface of slide plate, and motor output shaft extends
It is fixedly connected with disk to one end of sled surface, the surface of the disk is fixedly connected with fixed block, the side of the slide plate
The sliding block for being matched therewith and using is slidably connected, and the surface of sliding block is fixedly connected with link block, the surface of the slide plate
And the side for being located at disk is connected with motion bar, and offers in the middle part of motion bar surface and be used in combination with fixed block
First sliding groove, the side on the motion bar surface offers the second sliding slot being used in combination with link block, the sliding block
Side is fixedly connected with rotary electric machine by connecting plate, and the output shaft of rotary electric machine is fixedly connected with radiator shutter.
Preferably, controller is provided at the top of the housing cavity, combuster is arranged in the bottom of the housing cavity,
Jet pipe is provided on the bocca of combustion chamber
Preferably, the inner cavity of the shell and be located at the bottom of controller and be provided with incendiary agent tank, the inner cavity of the shell and
The bottom of incendiary agent tank is provided with oxidant tank.
Preferably, the side of the housing cavity and the bottom of oxidant tank are provided with incendiary agent conveying pump group assembly,
The other side of the housing cavity and the bottom of oxidant tank are provided with oxidant conveying pump group assembly.
Preferably, the outlet of the incendiary agent tank has incendiary agent conveyance conduit, the outlet of the oxidant tank
It is communicated with oxidant conveyance conduit.
Preferably, the incendiary agent conveyance conduit sequentially passes through incendiary agent conveying pump group assembly and combustion chamber and extends to combustion
The inner cavity of room is burnt, the oxidant conveyance conduit sequentially passes through oxidant conveying pump group assembly and combustion chamber and extends to combustion chamber
Inner cavity.
Beneficial effect
The present invention provides a kind of rocket engines for reducing fuel consumption.Has following beneficial effect：
（1）, the reduction fuel consumption rocket engine, the cunning for being matched therewith and using is slidably connected by the side of slide plate
Block, and the surface of sliding block is fixedly connected with link block, the surface of the slide plate and side for being located at disk is connected with motion bar,
And the first sliding groove being used in combination with fixed block is offered in the middle part of motion bar surface, the side on motion bar surface offers
The side of the second sliding slot being used in combination with link block, sliding block is fixedly connected with rotary electric machine by connecting plate, and rotates
The output shaft of motor is fixedly connected with radiator shutter, can reduce the loss of fuel, has the function of heat dissipation, avoids rocket motor
Machine is damaged because of overheat, and transfer efficiency is high, and sufficiently, high combustion efficiency is easy to use, effect for incendiary agent and oxidant mixing
It is good.
（2）, the reduction fuel consumption rocket engine, have incendiary agent delivery pipe by the outlet of incendiary agent tank
Road, the outlet of oxidant tank have oxidant conveyance conduit, and incendiary agent conveyance conduit sequentially passes through incendiary agent conveying pump group
Assembly and combustion chamber and the inner cavity for extending to combustion chamber, oxidant conveyance conduit sequentially pass through oxidant conveying pump group assembly and combustion
It burns room and extends to the inner cavity of combustion chamber, fuel consumption is small, hot driving amount is small, reduces fuel cost, avoids energy waste
With pollution environment.
Detailed description of the invention
Fig. 1 is schematic structural view of the invention；
Fig. 2 is the cross-sectional view of heat-dissipation box structure of the present invention；
Fig. 3 is the side view of motor of the present invention and skateboard.
In figure：1 support plate, 2 transformers, 3 heat dissipation tanks, 4 slide plates, 5 motors, 6 disks, 7 fixed blocks, 8 sliding blocks, 9 link blocks,
10 motion bars, 11 first sliding grooves, 12 second sliding slots, 13 rotary electric machines, 14 radiator shutters, 15 controllers, 16 combustion chambers, 17 sprays
Pipe, 18 incendiary agent tanks, 19 oxidant tanks, 20 incendiary agents conveying pump group assembly, 21 oxidants conveying pump group assembly, 22 burnings
Agent conveyance conduit, 23 oxidant conveyance conduits.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Fig. 1-3 is please referred to, the present invention provides a kind of technical solution：A kind of rocket engine reducing fuel consumption, including
Shell 1, the side of shell 1 is communicated with communicating pipe 2, and one end that communicating pipe 2 is located at outside shell 1 is communicated with heat dissipation tank 3, dissipates
Slide plate 4 is fixedly connected between the top and bottom of 3 inner cavity of hot tank, and the back side of slide plate 4 is fixedly connected with by connecting plate
The output shaft of motor 5, motor 5 runs through slide plate 4 and extends to the surface of slide plate 4, and 5 output shaft of motor extends to 4 table of slide plate
The one end in face is fixedly connected with disk 6, and the surface of disk 6 is fixedly connected with fixed block 7, the side of slide plate 4 slidably connect with
Its sliding block 8 being used in combination, and the surface of sliding block 8 is fixedly connected with link block 9, the surface of slide plate 4 and is located at disk 6
Side is connected with motion bar 10, and offers first be used in combination with fixed block 7 in the middle part of 10 surface of motion bar
Sliding slot 11, the side on 10 surface of motion bar offer the second sliding slot 12 being used in combination with link block 9, and the side of sliding block 8 is logical
It crosses connecting plate and is fixedly connected with rotary electric machine 13, and the output shaft of rotary electric machine 13 is fixedly connected with radiator shutter 14, has
The function of heat dissipation, avoids rocket engine from damaging because of overheat, and transfer efficiency is high, and incendiary agent and oxidant mixing are abundant,
High combustion efficiency, easy to use, effect is good, and controller 15, the bottom setting of 1 inner cavity of shell are provided at the top of 1 inner cavity of shell
Combuster 16, is provided with jet pipe 17 on the bocca of combustion chamber 16, the inner cavity of the shell 1 and bottom for being located at controller 15 is arranged
There is an incendiary agent tank 18, the inner cavity of shell 1 and the bottom for being located at incendiary agent tank 18 are provided with oxidant tank 19, in shell 1
The side of chamber and the bottom of oxidant tank 19 are provided with incendiary agent conveying pump group assembly 20, the other side of 1 inner cavity of shell and oxygen
The bottom of agent tank 19 is provided with oxidant conveying pump group assembly 21, and the outlet of incendiary agent tank 18 has incendiary agent conveying
Pipeline 22, the outlet of oxidant tank 19 have oxidant conveyance conduit 23, and incendiary agent conveyance conduit 22 sequentially passes through burning
Agent conveys pump group assembly 20 and combustion chamber 16 and the inner cavity for extending to combustion chamber 16, oxidant conveyance conduit 23 sequentially pass through oxidation
Agent conveys pump group assembly 20 and combustion chamber 16 and the inner cavity for extending to combustion chamber 16, and fuel consumption is small, hot driving amount is small, reduces
Fuel cost avoids energy waste and pollution environment.
When work, after generating a large amount of heat when rocket engine work, user can open according to the actual situation
Dynamic motor 5 and rotary electric machine 13, motor 5 will drive the rotation of 4 surface disc 6 of slide plate after starting, and then disk 6 has driven its table
The rotation of face fixed block 7, fixed block 7 can drive the movement of motion bar 10, and then motion bar by first sliding groove 11 after rotating
The second sliding slot 12 on 10 surfaces side will drive the movement of link block 9 again, and then link block 9 has driven sliding block 8 the one of slide plate 4
Side moves up and down, and then has driven the up and down motion of rotary electric machine 13 at the top of connecting plate, after rotary electric machine 13 starts, turns
Dynamic motor 13 will drive the rotation of radiator shutter 14, and then radiator shutter 14 can move up and down to the connection of 3 side of heat dissipation tank
Combustion chamber 16 is radiated, and rocket engine is avoided to damage because of overheat, to reduce the loss of fuel.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (6)
1. a kind of rocket engine for reducing fuel consumption, including shell（1）, it is characterised in that：The shell（1）Side connect
It is connected with communicating pipe（2）, and communicating pipe（2）Positioned at shell（1）External one end is communicated with heat dissipation tank（3）, the heat dissipation tank（3）
Slide plate is fixedly connected between the top and bottom of inner cavity（4）, and slide plate（4）The back side electricity is fixedly connected with by connecting plate
Machine（5）, the motor（5）Output shaft run through slide plate（4）And extend to slide plate（4）Surface, and motor（5）Output shaft prolongs
Extend to slide plate（4）The one end on surface is fixedly connected with disk（6）, the disk（6）Surface be fixedly connected with fixed block（7）,
The slide plate（4）Side slidably connect the sliding block for being matched therewith and using（8）, and sliding block（8）Surface be fixedly connected
There is link block（9）, the slide plate（4）Surface and be located at disk（6）Side be connected with motion bar（10）, and activity
Bar（10）It is offered in the middle part of surface and fixed block（7）The first sliding groove being used in combination（11）, the motion bar（10）Surface
Side offer and link block（9）The second sliding slot being used in combination（12）, the sliding block（8）Side it is solid by connecting plate
Surely it is connected with rotary electric machine（13）, and rotary electric machine（13）Output shaft be fixedly connected with radiator shutter（14）.
2. a kind of rocket engine for reducing fuel consumption according to claim 1, it is characterised in that：The shell（1）
Controller is provided at the top of inner cavity（15）, the shell（1）Combuster is arranged in the bottom of inner cavity（16）, combustion chamber（16）'s
Jet pipe is provided on bocca（17）.
3. a kind of rocket engine for reducing fuel consumption according to claim 2, it is characterised in that：The shell（1）
Inner cavity and be located at controller（15）Bottom be provided with incendiary agent tank（18）, the shell（1）Inner cavity and be located at burning
Agent tank（18）Bottom be provided with oxidant tank（19）.
4. a kind of rocket engine for reducing fuel consumption according to claim 3, it is characterised in that：The shell（1）
The side of inner cavity and oxidant tank（19）Bottom be provided with incendiary agent conveying pump group assembly（20）, the shell（1）Inner cavity
The other side and oxidant tank（19）Bottom be provided with oxidant conveying pump group assembly（21）.
5. a kind of rocket engine for reducing fuel consumption according to claim 2, it is characterised in that：The incendiary agent storage
Case（18）Outlet have incendiary agent conveyance conduit（22）, the oxidant tank（19）Outlet have oxidant conveying
Pipeline（23）.
6. a kind of rocket engine for reducing fuel consumption according to claim 5, it is characterised in that：The incendiary agent is defeated
Send pipeline（22）Sequentially pass through incendiary agent conveying pump group assembly（20）The combustion chamber and（16）And extend to combustion chamber（16）Inner cavity,
The oxidant conveyance conduit（23）Sequentially pass through oxidant conveying pump group assembly（20）The combustion chamber and（16）And extend to burning
Room（16）Inner cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810756608.5A CN108915898A (en) | 2018-07-11 | 2018-07-11 | A kind of rocket engine reducing fuel consumption |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810756608.5A CN108915898A (en) | 2018-07-11 | 2018-07-11 | A kind of rocket engine reducing fuel consumption |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108915898A true CN108915898A (en) | 2018-11-30 |
Family
ID=64412568
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810756608.5A Pending CN108915898A (en) | 2018-07-11 | 2018-07-11 | A kind of rocket engine reducing fuel consumption |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108915898A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175041A (en) * | 2010-12-23 | 2011-09-07 | 中国航天科技集团公司第六研究院第十一研究所 | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter |
| CN103629013A (en) * | 2013-11-27 | 2014-03-12 | 中国科学院力学研究所 | Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
-
2018
- 2018-07-11 CN CN201810756608.5A patent/CN108915898A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102175041A (en) * | 2010-12-23 | 2011-09-07 | 中国航天科技集团公司第六研究院第十一研究所 | Dividing wall type regenerative cooling air oxygen alcohol torch type igniter |
| CN103629013A (en) * | 2013-11-27 | 2014-03-12 | 中国科学院力学研究所 | Subsonic velocity combustion ramjet combustion chamber and regenerative cooling method thereof |
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN106640424A (en) * | 2016-10-26 | 2017-05-10 | 湖北航天技术研究院总体设计所 | Combustion chamber of liquid rocket engine |
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181130 |
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| WD01 | Invention patent application deemed withdrawn after publication |