CN205559074U - Dedicated spacecraft of aerospace burning circulating device - Google Patents
Dedicated spacecraft of aerospace burning circulating device Download PDFInfo
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- CN205559074U CN205559074U CN201620266404.XU CN201620266404U CN205559074U CN 205559074 U CN205559074 U CN 205559074U CN 201620266404 U CN201620266404 U CN 201620266404U CN 205559074 U CN205559074 U CN 205559074U
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- heat exchanger
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Abstract
The utility model discloses a dedicated spacecraft of aerospace burning circulating device, including fuel cell, hot airflow outlet and heat exchanger, heat exchanger installs the both sides in the combustion chamber, heat exchanger's right side is provided with the gear motor, the right side of fuel pump is provided with the turbopump, the right side of turbopump is provided with the control valve, fuel pump, gear motor, heat exchanger, turbopump and oxygen pump all with external control panel electric connection. Compared with the prior art, the beneficial effects of the utility model are that: the utility model relates to a dedicated spacecraft of aerospace burning circulating device structure scientific and reasonable, the operation is convenient safely, is provided with heat exchanger in the both sides of combustion chamber, can be the cold air with the empty gas shift of the heat that combustion chamber internal combustion produced, then convey through conveying pipe and locate cyclic utilization to the turbopump, has not only reduced to the heat of propagating in the air, has practiced thrift the resource moreover, and the environmental protection is practical.
Description
Technical field
This utility model relates to field of aerospace technology, the spacecraft burn cycle device that a kind of Aero-Space are special.
Background technology
The appearance of spacecraft makes the range of activity of the mankind expand unmeasured vastness cosmic space to from earth atmosphere, causes the natural leap with nature remodeling ability of human knowledge, social economy and social life are created significant impact.
Spacecraft runs beyond earth atmosphere, has broken away from atmosphere obstruction, can receive the whole electromagnetic radiation informations from universe celestial body, open all band astronomical observation；Spacecraft from terrestrial space fly interplanetary space flight, it is achieved that to the direct detection of spatial environments and the moon and solar system major planet are approached observation and direct sample observation；The spacecraft orbited round the earth observes the earth from hundreds of km to the distance of tens thousand of kms, collect rapidly and in large quantities the various electromagnetic radiation informations about earth atmosphere, ocean and land, directly serve in the aspects such as meteorological observation, military surveillance and resource survey；Artificial earth satellite is as space radio relay station, it is achieved that global satellite communication and broadcast, and as space reference point, can carry out global navigation satellite and geodesic survey；Utilize the special environments such as space fine vacuum, intense radiation and weightlessness, various important scientific experiments research can be carried out on spacecraft.
The burner of existing spacecraft also exists some drawbacks during using, such as, spacecraft needs the thermal current produced by fuel combustion to increase power during lift-off, but the spacecraft of existing solid fuel does not has special heat abstractor, mainly blow over by air and take away heat, the heat produced adds the temperature in air, so it is proposed that the special spacecraft burn cycle device of the recycled Aero-Space of a kind of heat.
Utility model content
The purpose of this utility model is the spacecraft burn cycle device providing a kind of Aero-Space special, the problem too much increasing air temperature with the heat solving to propose in above-mentioned background technology.
nullFor achieving the above object，This utility model following technical scheme of offer: the spacecraft burn cycle device that a kind of Aero-Space are special，Including fuel tank、Thermal current outlet and heat exchanger，The outlet of described thermal current is arranged on the lower section of shell body，And thermal current outlet be provided above combuster，Described heat exchanger is arranged on the both sides of combustor，And the protected shell of surface configuration of heat exchanger，The right side of described heat exchanger is provided with gear motor，And the right side of heat exchanger is provided with dispatch tube，The left side of described combustor is provided with fuel access tube，Described fuel access tube be provided above petrolift，Described fuel tank is arranged on the top of petrolift，The lower section of described fuel tank is provided with fuel inlet，The right side of described petrolift is provided with turbine pump，The right side of described turbine pump is provided with control valve，Described combustor be provided above oxygen dispatch tube，The right side of described oxygen dispatch tube is provided with oxygen pump，Described petrolift、Gear motor、Heat exchanger、Turbine pump and oxygen pump are all electrically connected with external control panel.
Preferably, described heat exchanger is provided with two altogether, and two heat exchangers are separately mounted to the both sides of combustor.
Preferably, described gear motor is provided with two altogether, and two gear motors are separately mounted to the both sides of heat exchanger.
Preferably, described turbine pump is provided with two altogether, and two turbine pumps are separately mounted to the both sides of dispatch tube.
Preferably, described dispatch tube is provided with two altogether, and two dispatch tubes are separately mounted to the both sides of heat exchanger.
Compared with prior art, the beneficial effects of the utility model are: the special spacecraft burn cycle apparatus structure of a kind of Aero-Space of this utility model is scientific and reasonable, easy-to-operate, the both sides of combustor are provided with heat exchanger, the hot-air that combustion chamber burning produces can be converted to cold air, then be sent at turbine pump recycle by dispatch tube, not only reduce the heat propagated in air, and saved resource, environmental protection is practical.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model；
In figure: the outlet of 1-fuel tank, 2-fuel inlet, 3-petrolift, 4-fuel access tube, 5-containment vessel, 6-thermal current, 7-combustor, 8-gear motor, 9-heat exchanger, 10-oxygen dispatch tube, 11-oxygen pump, 12-dispatch tube, 13-shell body, 14-turbine pump, 15-control valve.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is clearly and completely described, it is clear that described embodiment is only a part of embodiment of this utility model rather than whole embodiments.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art are obtained under not making creative work premise, broadly fall into the scope of this utility model protection.
nullRefer to Fig. 1，The spacecraft burn cycle device technique scheme that a kind of Aero-Space of this utility model offer are special: the spacecraft burn cycle device that a kind of Aero-Space are special，Including fuel tank 1、Thermal current outlet 6 and heat exchanger 9，Thermal current outlet 6 is arranged on the lower section of shell body 13，And thermal current outlet 6 be provided above combuster 7，Heat exchanger 9 is arranged on the both sides of combustor 7，And the protected shell of surface configuration 5 of heat exchanger 9，The right side of heat exchanger 9 is provided with gear motor 8，And the right side of heat exchanger 9 is provided with dispatch tube 12，The left side of combustor 7 is provided with fuel access tube 4，Fuel access tube 4 be provided above petrolift 3，Fuel tank 1 is arranged on the top of petrolift 3，The lower section of fuel tank 1 is provided with fuel inlet 2，The right side of petrolift 3 is provided with turbine pump 14，The right side of turbine pump 14 is provided with control valve 15，Combustor 7 be provided above oxygen dispatch tube 10，The right side of oxygen dispatch tube 10 is provided with oxygen pump 11，Petrolift 3、Gear motor 8、Heat exchanger 9、Turbine pump 14 and oxygen pump 11 are all electrically connected with external control panel.
Heat exchanger 9 is provided with two altogether, and two heat exchangers 9 are separately mounted to the both sides of combustor 7.Gear motor 8 is provided with two altogether, and two gear motors 8 are separately mounted to the both sides of heat exchanger 9.Turbine pump 14 is provided with two altogether, and two turbine pumps 14 are separately mounted to the both sides of dispatch tube 12.Dispatch tube 12 is provided with two altogether, and two dispatch tubes 12 are separately mounted to the both sides of heat exchanger 9.
Operation principle: after this utility model installs, connect external power source, at fuel inlet 2, the fuel within fuel tank 1 is put into the inside of petrolift 3, then by turbine pump 14 supercharging, the fuel within petrolift 3 is sent to by fuel access tube 4 inside of combustor 7, oxygen within oxygen pump 11 is then passed through oxygen dispatch tube 10 by turbine pump 14 supercharging simultaneously and is sent to the inside of combustor 7, the thermal current that combustor 7 burning produces exports from thermal current and discharges at 6, hot blast is converted to cold wind by heat exchanger 9 by the residue steam in combustor 7, it is then passed through dispatch tube 12 to be sent at turbine pump 14 again recycle.
Embodiment the most of the present utility model, for the ordinary skill in the art, being appreciated that in the case of without departing from principle of the present utility model and spirit and these embodiments can carry out multiple change, revise, replace and modification, scope of the present utility model is defined by the appended claims and the equivalents thereof.
Claims (5)
- null1. the spacecraft burn cycle device that Aero-Space are special，Including fuel tank (1)、Thermal current outlet (6) and heat exchanger (9)，It is characterized in that: described thermal current outlet (6) is arranged on the lower section of shell body (13)，And thermal current outlet (6) be provided above combuster (7)，Described heat exchanger (9) is arranged on the both sides of combustor (7)，And the protected shell of the surface configuration (5) of heat exchanger (9)，The right side of described heat exchanger (9) is provided with gear motor (8)，And the right side of heat exchanger (9) is provided with dispatch tube (12)，The left side of described combustor (7) is provided with fuel access tube (4)，Described fuel access tube (4) be provided above petrolift (3)，Described fuel tank (1) is arranged on the top of petrolift (3)，The lower section of described fuel tank (1) is provided with fuel inlet (2)，The right side of described petrolift (3) is provided with turbine pump (14)，The right side of described turbine pump (14) is provided with control valve (15)，Described combustor (7) be provided above oxygen dispatch tube (10)，The right side of described oxygen dispatch tube (10) is provided with oxygen pump (11)，Described petrolift (3)、Gear motor (8)、Heat exchanger (9)、Turbine pump (14) and oxygen pump (11) are all electrically connected with external control panel.
- The spacecraft burn cycle device that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described heat exchanger (9) is provided with two altogether, and two heat exchangers (9) are separately mounted to the both sides of combustor (7).
- The spacecraft burn cycle device that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described gear motor (8) is provided with two altogether, and two gear motors (8) are separately mounted to the both sides of heat exchanger (9).
- The spacecraft burn cycle device that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described turbine pump (14) is provided with two altogether, and two turbine pumps (14) are separately mounted to the both sides of dispatch tube (12).
- The spacecraft burn cycle device that a kind of Aero-Space the most according to claim 1 are special, it is characterised in that: described dispatch tube (12) is provided with two altogether, and two dispatch tubes (12) are separately mounted to the both sides of heat exchanger (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620266404.XU CN205559074U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft of aerospace burning circulating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620266404.XU CN205559074U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft of aerospace burning circulating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205559074U true CN205559074U (en) | 2016-09-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620266404.XU Expired - Fee Related CN205559074U (en) | 2016-04-04 | 2016-04-04 | Dedicated spacecraft of aerospace burning circulating device |
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| Country | Link |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107989698A (en) * | 2017-11-30 | 2018-05-04 | 中山市小榄企业服务有限公司 | A kind of dedicated spacecraft burn cycle device of aerospace |
-
2016
- 2016-04-04 CN CN201620266404.XU patent/CN205559074U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107989698A (en) * | 2017-11-30 | 2018-05-04 | 中山市小榄企业服务有限公司 | A kind of dedicated spacecraft burn cycle device of aerospace |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160907 Termination date: 20170404 |
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| CF01 | Termination of patent right due to non-payment of annual fee |