CN110186326A - A kind of recyclable emission system and method - Google Patents
A kind of recyclable emission system and method Download PDFInfo
- Publication number
- CN110186326A CN110186326A CN201910477423.5A CN201910477423A CN110186326A CN 110186326 A CN110186326 A CN 110186326A CN 201910477423 A CN201910477423 A CN 201910477423A CN 110186326 A CN110186326 A CN 110186326A
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- Prior art keywords
- recyclable
- propeller
- magnetic
- aircraft
- aircraft body
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/06—Rocket or torpedo launchers for rockets from aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of recyclable emission system and methods, the system includes aircraft body and ground propulsion system, the aircraft body includes the final-stage rocket and recyclable propeller for loading payload, is equipped with punching engine on the recyclable propeller；The ground propulsion system includes magnetcisuspension suspension propeller, magnetic-levitation, power supply system and linear motor；The aircraft body is connected with magnetcisuspension suspension propeller but can be separated by control.The present invention provides aircraft initial velocity using magnetic levitation technology as ground propulsion system, reduces aircraft itself fuel and carries, greatly reduction launch cost.Further power is provided for aircraft body using punching engine, does not need self-contained oxidant, aircraft is lighter, and fuel economy is more preferable.Further, after recyclable propeller carries punching engine disengagement, it can be drop to ground reuse, further decrease launch cost.
Description
Technical field
The present invention relates to aerospace fields, are especially loaded with the recyclable emission system and method for punching engine.
Background technique
Rocket is by rocket engine, and the various spacecrafts that people are made push space to, these spacecrafts include man-made land
Ball satellite, manned spaceship, spaceport or interplanetary probe etc., rocket is generally 2-4 grades, due to technical restriction etc.,
Launch cost is high, hinders the development of space science and technology.
The main reason for launch cost is high is: the self-contained a large amount of fuel of rocket and oxidant, and the ratio of oxidant
It is generally higher than 1.4 again, the mass mixing ratio of oxygen combustion is also both greater than 1.4, could obtain optimum specific impulse to promote the speed of rocket, cause
Keep rocket weight and volume all very big, therefore, launch cost is extremely high；Another reason further includes that propellers at different levels can not recycle
It uses, further improves launch cost.In the prior art, have by arresting gear offer block pulling force based on, solve
The recycling problem (CN109099765A) of rocket cannot be from root although the recycling of propeller can be solved the problems, such as to a certain degree
Launch cost is solved the problems, such as in sheet.Therefore, how to develop the reusable carrier rocket of low cost is always space industry
Technical problem urgently to be resolved.
Ramjet be it is a kind of enter engine using windstream after, so that air is improved a kind of air of static pressure
Jet engine.Punching engine does not have compressor, so also known as without the air breathing jet engine of compressor, oxidant is logical
It crosses air intake duct sucking to obtain, does not need self-contained oxidant.Punching engine structure is simple, light-weight, and thrust ratio is big, cost
It is low.Due to it have the characteristics that it is this excellent --- thrust is big, light-weight, is very suitable for high speed flight at high altitude.At present
Maximum speed be about 4 times of velocities of sound (being equivalent to 4400 kilometers/hour), highly up to 30 kilometers or more.Its shortcomings that be using
It is unable to self start, other engines must be used as boost motor, flown under conditions of flight Mach number is greater than 1.5, and only
Row device could effectively work after reaching certain flying speed.Also just because of this disadvantage punching engine is not answered
For emission system.
Summary of the invention
In order to solve the deficiencies in the prior art, the object of the present invention is to provide a kind of recyclable hairs for reducing launch cost
System and method is penetrated, magnetic is creatively floated actuation techniques in conjunction with punching engine to replace or reduce tradition one by the present invention
The fuel of the carrying of grade rocket, so that aircraft carries the fuel and oxidant fewer than traditional technology and reduces the hair of launch cost
System and method are penetrated, further, the present invention also provides the emission system i.e. methods that one kind can drop to ground reuse.
In order to achieve the above-mentioned object of the invention, the present invention provides a kind of recyclable emission system for being loaded with punching engine,
Including aircraft body and ground propulsion system, the aircraft body includes loading the final-stage rocket of payload and can returning
Propeller is received, punching engine is installed on the recyclable propeller；The ground propulsion system include magnetcisuspension suspension propeller,
Magnetic-levitation, power supply system and linear motor；The aircraft body is connected with magnetcisuspension suspension propeller but can be controlled
Separation, the linear motor provide power by the electric energy that consumption power supply system provides for the emission system, and the ground pushes away
It is used to reaching aircraft speed into the flying speed for starting the punching engine into system.
Preferably, the aircraft body further includes booster-missile combination, final-stage rocket, the second level fire of the load payload
Arrow and recyclable propeller are sequentially connected composition aircraft body.
Preferably, the magnetic-levitation is at least formed from horizontal component and to vertical sloping portion.
Preferably, the magnetic-levitation can also be U-shaped, that is, includes acclive downing track, horizontal segment and have slope
The uplink path of degree forms.
Preferably, the magnetcisuspension suspension propeller is equipped with linear motor rotor, and the magnetcisuspension suspension propeller is equipped with straight line
Electric mover is equipped with linear motor stator electric on the magnetic-levitation.
Preferably, the magnetcisuspension suspension propeller includes the floating driving front support of magnetic and the floating driving rear support of magnetic.
Preferably, ground propulsion system further includes vacuum pipe sleeve, for the magnetcisuspension suspension propeller to be placed on wherein.
Preferably, itself has been installed on the recyclable propeller flows backwards plate and landing buffer device, it is low for working as speed
After the flying speed of the punching engine, punching engine is closed, starts the auxiliary power unit, is landed in specified rail
Road.
The present invention also provides a kind of recyclable launching techniques, include the following steps:
S1: it is placed on the magnetic-levitation of linear motor in the magnetcisuspension suspension propeller carrying aircraft body, described in starting
Magnetic suspension propulsion system；
S2: the linear motor drives the magnetcisuspension suspension propeller carrying aircraft to accelerate to flying for starting punching engine work
Scanning frequency degree, the punching engine are ignited, and continue to accelerate；
S3: the aircraft body is separated with magnetic-levitation；The aircraft body reaches specified altitude assignment.
Preferably, further include following steps:
The recyclable propeller is separated with aircraft body, is adjusted course by itself flowing backwards plate, is reduced height and speed, when
After speed is lower than the flying speed of the punching engine, closes punching engine, start the auxiliary power unit, landing in
Track designation.
The invention has the following beneficial effects:
Using magnetic levitation technology as ground propulsion system, aircraft initial velocity is provided, aircraft itself fuel is reduced and carries, pole
It is big to reduce launch cost.Further power is provided for aircraft body using punching engine, does not need self-contained oxidant,
Aircraft is lighter, and fuel economy is more preferable.Further, after recyclable propeller carries punching engine disengagement, can land
It is reused to ground, further decreases launch cost.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is front view (the magnetic suspension rail of the recyclable emission system for being loaded with punching engine of the embodiment of the present invention one
Part is only presented in road)；
Fig. 2 is the left view of the recyclable emission system for being loaded with punching engine of the embodiment of the present invention one；
Fig. 3 is the transmitting schematic diagram of the recyclable emission system for being loaded with punching engine of the embodiment of the present invention one；
Fig. 4 is the seperated schematic diagram of the recyclable emission system for being loaded with punching engine of the embodiment of the present invention one；
Fig. 5 is the recycling status diagram of the recyclable emission system for being loaded with punching engine of the embodiment of the present invention one.
Drawing reference numeral explanation:
1 grade of propeller, 5- magnetic can be recycled in the load grade of 1- three-stage rocket in figure, 2- booster-missile combination, 3- punching engine, 4-
Floating driving rear support, the floating driving front support of 6- magnetic, 7- magnetic-levitation, 8- auxiliary power unit.
The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.
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 embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is to be appreciated that if relating to directionality instruction (such as up, down, left, right, before and after ...) in the embodiment of the present invention,
Then directionality instruction be only used for explain under a certain particular pose (as shown in the picture) between each component relative positional relationship,
Motion conditions etc., if the particular pose changes, directionality instruction is also correspondingly changed correspondingly.
In addition, being somebody's turn to do " first ", " second " etc. if relating to the description of " first ", " second " etc. in the embodiment of the present invention
Description be used for description purposes only, be not understood to indicate or imply its relative importance or implicitly indicate indicated skill
The quantity of art feature." first " is defined as a result, the feature of " second " can explicitly or implicitly include at least one spy
Sign.It in addition, the technical solution between each embodiment can be combined with each other, but must be with those of ordinary skill in the art's energy
It is enough realize based on, will be understood that the knot of this technical solution when conflicting or cannot achieve when occurs in the combination of technical solution
Conjunction is not present, also not the present invention claims protection scope within.
Embodiment one:
This recyclable emission system aircraft body and ground launch propulsion system composition.The load grade 1 of three-stage rocket, two
Grade rocket 2 and recyclable 1 grade of propeller 4 are sequentially connected composition aircraft body, also install on recyclable 1 grade of propeller 3
Punching engine 3.It should be noted that the embodiment of the present invention is only used as example to three-stage rocket, be also possible to except rocket it
Outer emission system, also refers not only to three-level, can be level-one, is also possible to two-stage or more.
Ground propulsion system includes magnetcisuspension suspension propeller, magnetic-levitation 7, power supply system and linear motor.In this implementation
Magnetcisuspension suspension propeller includes the floating driving rear support 5 of magnetic and the floating driving front support 6 of magnetic in example, is also possible to single-point support or more than two
Point support.The aircraft body is placed on magnetic-levitation 7 by front support 6 and rear end support 5, the aircraft master
Body and the magnetcisuspension suspension propeller can controlled switch-off, linear motor, the linear motor are installed on the magnetcisuspension suspension propeller
Power is provided by the electric energy that consumption power supply system provides for the emission system.
The magnetic-levitation 7 is formed from horizontal component and to vertical sloping portion.Transmitting is initial, and aircraft body is put
It sets to (Fig. 1) on the horizontal segment of magnetic-levitation 7, linear motor stator electric is installed on the magnetic-levitation.
When work, linear motor driving magnetcisuspension suspension propeller carrying aircraft body constantly accelerates, and track is erected by horizontal direction
Straight inclination, when speed reaches 3 operating rate of punching engine, about 1~1.5Ma puts burning ramjet 3, continues to accelerate, together
When magnetcisuspension suspension propeller and aircraft body disconnect (Fig. 3).
Aircraft body continues after reaching disengaging height under the propulsion of punching engine 3, and 1 grade of propeller 4 can be recycled and carry
Punching engine 3 is detached from from aircraft body, and aircraft body remainder is transported load-carrying 1 using included rocket engine
To outer space track designation (Fig. 4).
Recyclable 1 grade of propeller 4 carries punching engine 3 and adjusts course by itself flowing backwards plate, constantly reduce height with
Speed closes punching engine 3 when speed is lower than 3 operating condition of punching engine, starts auxiliary power unit 8, and land
To designated airport runway (Fig. 5).
It include acclive downing track, horizontal segment and acclive uplink path when the magnetic-levitation is U-shaped
Composition, brake force of the aircraft body in addition to that can obtain linear motor driving, will also obtain the driving of One Earth One Family weight component
Power, the two superposition, further speeds up to aircraft body.When reaching horizontal segment, aircraft body reaches maximum speed, punching press
Engine ignition.When reaching acclive uplink path, magnetcisuspension suspension propeller is separated with aircraft body, aircraft body bullet
It is shot out, magnetcisuspension suspension propeller, which slows down, to be returned.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all at this
Under the inventive concept of invention, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/use indirectly
It is included in other related technical areas in scope of patent protection of the invention.
Claims (10)
1. a kind of recyclable emission system, which is characterized in that including aircraft body and ground propulsion system, the aircraft
Main body includes the final-stage rocket and recyclable propeller for loading payload, is equipped with punching press on the recyclable propeller and starts
Machine；The ground propulsion system includes magnetcisuspension suspension propeller, magnetic-levitation, power supply system and linear motor；The aircraft
Main body is connected with magnetcisuspension suspension propeller, can be separated by control.
2. recyclable emission system as described in claim 1, which is characterized in that the aircraft body further includes second level fire
Arrow, final-stage rocket, booster-missile combination and the recyclable propeller of the load payload are sequentially connected composition aircraft body.
3. recyclable emission system as described in claim 1, which is characterized in that the magnetic-levitation is at least by horizontal component
It is formed with to vertical sloping portion.
4. recyclable emission system as claimed in claim 3, which is characterized in that the magnetic-levitation can also be U-shaped, i.e.,
Comprising acclive downing track, horizontal segment and acclive uplink path composition.
5. recyclable emission system as described in claim 1, which is characterized in that the magnetcisuspension suspension propeller is equipped with straight-line electric
Machine rotor, the magnetcisuspension suspension propeller are equipped with linear motor rotor, are equipped with linear motor stator electric on the magnetic-levitation.
6. recyclable emission system as described in claim 1, which is characterized in that the magnetcisuspension suspension propeller includes the floating driving of magnetic
Front support and the floating driving rear support of magnetic.
7. recyclable emission system as described in claim 1, which is characterized in that ground propulsion system further includes vacuum pipe sleeve.
8. recyclable emission system as described in claim 1, which is characterized in that installed itself on the recyclable propeller
Flow backwards plate and landing buffer device.
9. any recyclable launching technique as described in claim 1 to 8, which comprises the steps of:
S1: it is placed on the magnetic-levitation of linear motor in the magnetcisuspension suspension propeller carrying aircraft body, described in starting
Magnetic suspension propulsion system；
S2: the linear motor drives the magnetcisuspension suspension propeller carrying aircraft to accelerate to flying for starting punching engine work
Scanning frequency degree, the punching engine are ignited；
S3: the aircraft body is separated with magnetic-levitation；The aircraft body reaches specified altitude assignment.
10. the launching technique that can be recycled as claimed in claim 9, which is characterized in that further include following steps:
The recyclable propeller is separated with aircraft body, is adjusted course by itself flowing backwards plate, is reduced height and speed, when
After speed is lower than the flying speed of the punching engine, closes punching engine, start the auxiliary power unit, landing in
Track designation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910477423.5A CN110186326A (en) | 2019-06-03 | 2019-06-03 | A kind of recyclable emission system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910477423.5A CN110186326A (en) | 2019-06-03 | 2019-06-03 | A kind of recyclable emission system and method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110186326A true CN110186326A (en) | 2019-08-30 |
Family
ID=67719970
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910477423.5A Pending CN110186326A (en) | 2019-06-03 | 2019-06-03 | A kind of recyclable emission system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110186326A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114963867A (en) * | 2022-06-16 | 2022-08-30 | 陕西空天动力研究院有限公司 | Vacuum high-speed launching system of combined power rocket and launching and recovering method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1337912A (en) * | 1998-12-31 | 2002-02-27 | 太空通道有限公司 | Payload carry and Launch system |
| CN1405527A (en) * | 2001-08-14 | 2003-03-26 | 王雪松 | Jet propelling aircraft |
| CN103025611A (en) * | 2010-06-14 | 2013-04-03 | 阿斯特里厄姆公司 | Simplified reusable module for launcher |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN108423196A (en) * | 2018-04-08 | 2018-08-21 | 中国人民解放军战略支援部队航天工程大学 | The two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft |
-
2019
- 2019-06-03 CN CN201910477423.5A patent/CN110186326A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1337912A (en) * | 1998-12-31 | 2002-02-27 | 太空通道有限公司 | Payload carry and Launch system |
| CN1405527A (en) * | 2001-08-14 | 2003-03-26 | 王雪松 | Jet propelling aircraft |
| CN103025611A (en) * | 2010-06-14 | 2013-04-03 | 阿斯特里厄姆公司 | Simplified reusable module for launcher |
| CN106871723A (en) * | 2017-02-07 | 2017-06-20 | 国网技术学院 | Rise pocket emission system and its launch assist method |
| CN108423196A (en) * | 2018-04-08 | 2018-08-21 | 中国人民解放军战略支援部队航天工程大学 | The two-stage that the first order can be reused is entered the orbit the method for entering the orbit of spacecraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114963867A (en) * | 2022-06-16 | 2022-08-30 | 陕西空天动力研究院有限公司 | Vacuum high-speed launching system of combined power rocket and launching and recovering method thereof |
| CN114963867B (en) * | 2022-06-16 | 2023-12-29 | 陕西空天动力研究院有限公司 | Vacuum high-speed emission system of combined power rocket and emission and recovery method thereof |
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Application publication date: 20190830 |