CN107972892A - One kind volume inhales boosting carrier rocket - Google Patents
One kind volume inhales boosting carrier rocket Download PDFInfo
- Publication number
- CN107972892A CN107972892A CN201810015512.3A CN201810015512A CN107972892A CN 107972892 A CN107972892 A CN 107972892A CN 201810015512 A CN201810015512 A CN 201810015512A CN 107972892 A CN107972892 A CN 107972892A
- Authority
- CN
- China
- Prior art keywords
- rocket
- volume
- suction tube
- boosting
- inhales
- 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.)
- Pending
Links
- 238000002485 combustion reaction Methods 0.000 claims description 13
- 239000007921 spray Substances 0.000 claims description 8
- 239000002671 adjuvant Substances 0.000 claims description 6
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 239000001301 oxygen Substances 0.000 claims description 5
- 229910052760 oxygen Inorganic materials 0.000 claims description 5
- 230000001141 propulsive effect Effects 0.000 abstract description 5
- 239000007789 gas Substances 0.000 description 4
- 238000005096 rolling process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Classifications
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Engines (AREA)
Abstract
Rolled up the invention discloses one kind and inhale boosting carrier rocket, it includes rocket and the multistage assist device coupled with rocket, it is characterised in that outside the first-stage boost device of rocket, equipped with the volume suction tube for being used to occur Involving velocity being coupled.Compared with the prior art have the advantages that lower：First, utilize existing law of physics, there is provided a kind of improved new rocket propulsion mode；Second, the flying speed and propulsive efficiency of rocket can be significantly increased；Third, it is simple in structure, it is of low cost.
Description
Technical field：
The present invention relates to a kind of carrier rocket, particularly a kind of multistage boosting carrier rocket.
Background technology：
At present, carrier rocket, particularly powerful multistage boosting carrier rocket, in the mode of boosting, especially first
In terms of level rocket assist, existing physics principle is not made full use of also and reaches optimal propulsive efficiency.
One kind is provided and is based on existing physics principle it is an object of the invention to overcome the above-mentioned deficiency of prior art,
It has breakthrough on propulsion mode, and the volume that can reach optimal propulsive efficiency inhales boosting carrier rocket.
The content of the invention：
The object of the present invention is achieved like this, its technical solution is：One kind volume inhale boosting carrier rocket, it include rocket and with
The multistage assist device of rocket connection, it is characterised in that outside the first-stage boost device of rocket, be used for equipped with what is be coupled
The volume suction tube of Involving velocity occurs.This volume inhales boosting carrier rocket, in the starting stage taken off, due to the air of terrestrial space
Density is big, by the Involving velocity of the volume suction tube, just can obtain the flight of the thrust and higher than existing booster rocket bigger
Speed.Principle is as follows：
Rocket is the example using recoil, according to the principle of recoil, if system is made of two parts, and is interacted
Preceding aggregated momentum is zero, according to the law of conservation of momentum, is then had：m+(M-m)=0, M are rocket rocket body quality, and m is rocket spray
Go out the quality of gas,It is the speed that rocket sprays gas,It is the speed of rocket flight.By m+(M-m)=0, conversion
It can obtain.The formula shows：To improve the flying speed of rocket, must just improve rocket combustion gas ejection
Speed, the quality m of increase rocket ejection gas, reduces the quality (M-m) of rocket in itself.
, will be as long as Involving velocity will occur for the jet engine ignition operation of rocket according to Entraining Effect principle
Air is sucked in from the head volume of volume suction tube, and the speed of engine jet is bigger, and it is more to roll up the air sucked in.When rolling up
When suction acts on, due to adding the air quality rolled up and sucked in, spray gas gross mass and be just changed into（m+）, originally
Speed formula：Just it is changed into：.In practical applications, although volume suction tube tail wind
The speed of injectionIt has been reduced that, still（m+）Product can be more than original m, so, with regard to rocket can be improved
Flying speed.So as to improve the propulsive efficiency of rocket, therefore realize above-mentioned purpose.
In a preferred embodiment, the present invention is in the volume suction tube, except original rocket combustion flame sprays
Outside device, the spray combustion device using oxygen as the fuel of combustion adjuvant is additionally provided with, the bunkering which uses exists
In rocket rocket body, sprayed and burnt by nozzle preferably after gasification process, promote high-temperature fuel gas to accelerate from volume suction tube afterbody spray
Go out.In this way, after rocket motor ignition work, rolling up the oxygen in the air sucked in can use as combustion adjuvant, so that
Make spray combustion device described in the volume suction tube and Qi Nei, and constitute a kind of new jet engine.
The favorable factor that this volume inhales boosting carrier rocket is as follows：First, roll up the quality of suckRocket can be sprayed
Gaseous mass（m+) substantial increase；Second, the oxygen rolled up in suck can be used as combustion adjuvant, so that just can be appropriate
The quality that rocket carries combustion adjuvant is reduced, reaches the purpose for mitigating rocket sole mass M, especially on rocket takeoff phase, ground
Nearby the big combustion-supporting effect of atmospheric density is good in face；3rd, rolling up the air sucked in can in volume suction tube vigorous combustion with the fuel sprayed
To maintain even to improve the jet velocity of original rocket,（m+）Product will be far longer than original m.Institute
With this volume inhales booster rocket, is used as the first order of rocket, in the takeoff phase of rocket highly advantageous value.
Compared with the prior art the present invention has the advantages that lower：First, utilize existing law of physics, there is provided Yi Zhonggai
Into new rocket propulsion mode；Second, the flying speed and propulsive efficiency of rocket can be significantly increased；Third, structure is simple
It is single, it is of low cost.
Brief description of the drawings：
The present invention will pass through attached drawing below（Embodiment）Give and be described in detail：
Fig. 1, the structure diagram for the present invention；
Fig. 2, the cut-away diagram for being Fig. 1.
Embodiment：
With reference to Fig. 1, only for citing, a kind of specific embodiment of the present invention is given.As can be seen that this volume inhales boosting fortune
Rocket is carried, it includes rocket 1 and the assist device 2 coupled with rocket 1, it is characterised in that outside the assist device 2 of rocket, is equipped with
What is be coupled is used to occur the volume suction tube 3 of Involving velocity.
With reference to Fig. 2, only for citing, a kind of specific knot that fuel injection device is equipped with volume suction tube of the present invention is given
Structure.As can be seen that this volume inhales boosting carrier rocket, in volume suction tube 3, in addition to original combustion flame injection apparatus 4, also set
There is the fuel injection device 5 using oxygen as combustion adjuvant, so as to form a kind of new rocket jet engine.
In conclusion the present invention gives detailed description by specific embodiment, but much less conceive certainly in the present invention
On the basis of, according to knowledge known to a person of ordinary skill in the art, to the concrete structure shape of the volume suction tube, material and with
The connecting mode of assist device and position, specific parameter can be provided on the basis of experiment and makes appropriate change, and institute
There are these changes to should not exceed its scope of the claims.
Claims (2)
1. one kind volume inhales boosting carrier rocket, it includes rocket and the multistage assist device coupled with rocket, it is characterised in that
Outside the first-stage boost device of rocket, equipped with the volume suction tube for being used to occur Involving velocity being coupled.
2. volume according to claim 1 inhales boosting carrier rocket, it is characterised in that in the volume suction tube, except original
Outside rocket combustion flame injection apparatus, the spray combustion device using oxygen as the fuel of combustion adjuvant is additionally provided with.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810015512.3A CN107972892A (en) | 2018-01-08 | 2018-01-08 | One kind volume inhales boosting carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810015512.3A CN107972892A (en) | 2018-01-08 | 2018-01-08 | One kind volume inhales boosting carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107972892A true CN107972892A (en) | 2018-05-01 |
Family
ID=62005995
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810015512.3A Pending CN107972892A (en) | 2018-01-08 | 2018-01-08 | One kind volume inhales boosting carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107972892A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0849999A (en) * | 1994-05-17 | 1996-02-20 | Rockwell Internatl Corp | Missile by air suction type propulsion assistance |
| RU2150598C1 (en) * | 1999-06-09 | 2000-06-10 | Орловский государственный технический университет | Ramjet launch vehicle |
| JP2005233068A (en) * | 2004-02-19 | 2005-09-02 | Japan Aerospace Exploration Agency | Pulse detonation engine |
| CN102192045A (en) * | 2010-03-05 | 2011-09-21 | 余志刚 | Stamping type rotor fan engine |
| CN202023655U (en) * | 2011-03-03 | 2011-11-02 | 西北工业大学 | Pulse detonation engine with ejector |
| CN204041270U (en) * | 2014-07-30 | 2014-12-24 | 清华大学 | Combined cycle engine |
| CN104727978A (en) * | 2015-01-06 | 2015-06-24 | 杜善骥 | Working method of superimposed ram rocket |
-
2018
- 2018-01-08 CN CN201810015512.3A patent/CN107972892A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0849999A (en) * | 1994-05-17 | 1996-02-20 | Rockwell Internatl Corp | Missile by air suction type propulsion assistance |
| RU2150598C1 (en) * | 1999-06-09 | 2000-06-10 | Орловский государственный технический университет | Ramjet launch vehicle |
| JP2005233068A (en) * | 2004-02-19 | 2005-09-02 | Japan Aerospace Exploration Agency | Pulse detonation engine |
| CN102192045A (en) * | 2010-03-05 | 2011-09-21 | 余志刚 | Stamping type rotor fan engine |
| CN202023655U (en) * | 2011-03-03 | 2011-11-02 | 西北工业大学 | Pulse detonation engine with ejector |
| CN204041270U (en) * | 2014-07-30 | 2014-12-24 | 清华大学 | Combined cycle engine |
| CN104727978A (en) * | 2015-01-06 | 2015-06-24 | 杜善骥 | Working method of superimposed ram rocket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20180501 |