CN111547268A - Device and method for balancing air pressure at aerospace launching tail section of vacuum pipeline - Google Patents
Device and method for balancing air pressure at aerospace launching tail section of vacuum pipeline Download PDFInfo
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Abstract
A device and a method for balancing air pressure at the tail section of vacuum pipeline aerospace launching comprise a pipeline built according to a mountain body, wherein a vehicle is arranged in the pipeline, the vehicle is provided with a rocket, the outlet of the pipeline is positioned at the top of the mountain body, and a plurality of air vents are arranged on the pipeline close to the outlet; the pipeline consists of an originating section, an accelerating section and an emitting section, and the originating section, the accelerating section and the emitting section are respectively provided with a vacuum pump; a first air gate valve is arranged between the starting section and the accelerating section, a second air gate valve is arranged between the accelerating section and the launching section, the starting section is provided with an inlet door, the launching section is provided with an outlet door, the tail end of the launching section is provided with a plurality of air vents, and the air vents are controlled by automatic air valves to be communicated with the atmosphere or not; the invention eliminates huge airflow impact caused by pressure difference when the rocket rushes out of the vacuum pipeline with less vacuum environment loss cost, and improves the safety of the vacuum pipeline in space launching.
Description
Technical Field
The invention belongs to the technical field of vacuum pipeline traffic and aerospace engineering, and particularly relates to a device and a method for balancing air pressure at the aerospace launching tail section of a vacuum pipeline.
Background
The vacuum pipeline transportation is that an airtight pipeline is built on the ground or underground, a magnetic suspension track is laid in the pipeline, a certain vacuum is pumped, and a magnetic suspension vehicle runs in the pipeline; because the air resistance and the mechanical friction are eliminated at the same time, the speed of the vacuum pipeline magnetic levitation vehicle can reach supersonic speed, theoretically, the speed can be close to the first cosmic speed of 7.9km/s, and the space travel on the ground is realized.
While ground travel is faster and faster, human steps have taken steps into space. On the basis that the early-stage space exploration project is continuously successful, the space development and application steps are faster and faster. However, the current state of the art has not yet met the needs of human large-scale space development, with the biggest bottlenecks and constraints being: the launch efficiency of the launch vehicle is too low and the launch cost is too high. Moreover, these rockets are all disposable, and although reusable rockets have been developed, the situation that the specific gravity of fuel is too high during the takeoff of the rocket and the fuel consumption is high during the launching process cannot be changed.
If the high initial speed can be obtained when the space launching process leaves the ground, the weight of the first-stage rocket can be saved, the launching efficiency is improved, and the launching cost is reduced. One feasible method is to build a vacuum pipeline by depending on a high-altitude mountain on the ground, wherein an outlet is positioned at the top of the mountain and has a certain elevation angle with the horizontal plane; the vacuum pipeline is utilized to transport the vehicle chassis to carry the rocket and accelerate, when the vehicle chassis approaches the exit, the vehicle chassis is separated from the rocket, the rocket with higher initial speed rushes out of the pipeline and enters the sky, partial fuel and self weight of the first-stage rocket can be saved, the launching cost of the rocket and the spacecraft is reduced, and the launching efficiency is improved. The vacuum pipeline assisted accelerated aerospace launching has the specific technical problem that when a rocket with a high initial speed rushes out of a pipeline, the pipeline is vacuum, normal atmospheric pressure (although the atmospheric pressure is lower than rarefied air pressure at a low altitude) is outside the pipeline, and under the action of huge pressure difference, the rocket can be impacted by large instantaneous airflow, so that the operation stability and the self structure stability of the rocket are influenced, and safety risks are brought to launching work.
Disclosure of Invention
In order to overcome the technical problems in the prior art, the invention aims to provide a vacuum pipeline aerospace launching tail-section air pressure balancing device and method, which can eliminate huge airflow impact caused by pressure difference when a rocket rushes out of a vacuum pipeline at the cost of less vacuum environment loss and improve the aerospace launching safety of the vacuum pipeline.
In order to achieve the purpose, the invention adopts the technical scheme that:
a vacuum pipeline aerospace launching tail-section air pressure balancing device comprises a pipeline 1 built according to a mountain 3, a vehicle 2 is arranged in the pipeline 1, a rocket 4 is carried on the vehicle 2, an outlet of the pipeline 1 is located at the top of the mountain 3 and forms a certain elevation angle alpha with the horizontal plane, and a plurality of air release holes 8 are formed in the pipeline 1 close to the outlet;
the pipeline 1 consists of an initial section 11, an acceleration section 12 and an emission section 13, wherein the initial section 11, the acceleration section 12 and the emission section 13 are respectively provided with a vacuum pump 6; a first air lock door 51 is arranged between the starting section 11 and the accelerating section 12, a second air lock door 52 is arranged between the accelerating section 12 and the launching section 13, the starting section 11 is provided with an inlet door 111, the launching section 13 is provided with an outlet door 131, the tail end of the launching section 13 is provided with a plurality of air release holes 8, and the air release holes 8 are controlled to be communicated with the atmosphere through automatic air valves.
The vehicle 2 is a vacuum pipeline traffic vehicle, a carriage is removed, a chassis is reserved for transformation, and the vehicle 2 is a magnetic suspension vehicle.
The pipeline 1 is a vacuum pipeline.
The vehicle 2 and the rocket 4 are arranged in an automatic separation mode, after entering the launching section 13, the vehicle 2 decelerates, the rocket 4 is separated from the vehicle 2, and rushes out of the exit door 131 of the launching section 13 to enter the sky under the action of the continuity.
The rocket 4 is loaded with a cargo ship, and the vehicle 2 carrying the rocket 4 is accelerated by 10g (about 10 m/s)2) The speed of the rocket 4 when leaving the pipeline 1 is 1km/s, the acceleration time of the rocket 4 in the pipeline 1 is 100s, the total length of the pipeline is 50km, the elevation of the mountain body 3 is 8000m, the launching elevation α is reached, and tg α is 0.016.
The air pressure at the outlet of the pipeline 1 is about 35000 Pa.
The launching tail section air pressure balancing method of the vacuum pipeline spaceflight launching tail section air pressure balancing device comprises the following steps of:
setting the rocket length as a, the starting point O of the rocket 4 as the origin of coordinates, and the terminal coordinates of the pipeline as l; from a distance b from the emission opening E (outlet door 131), the pipe wall of the pipeline 1 is provided with air vents 8 at intervals of c, and the first air vent 8 is H1A marker having a coordinate of l on the x-axis-b；
T is t for the start of transmission0At the moment, the speed of the rocket 4 and the vehicle 2 is 0, and the internal air pressure of the pipeline 1 is p110Pa, the air pressure outside the outlet door 131 of the pipeline 1 is p0＝35000Pa，p0>>p1；
t＝t1When the rocket 4 and the vehicle 2 reach the H where the first vent hole 8 is located1At a velocity v1Opening all automatic air valves of the air release holes 8 and starting to release air into the pipeline 1; then from t1Starting from the moment, the air pressure in the pipeline 1 through which the rocket passes gradually rises; the size of the air vent 8 and the air venting speed are required to be achieved, when the rocket 4 reaches the outlet door 131, the air pressure in the pipeline 1 at the outlet is equal to the air pressure outside the pipeline 1, namely 35000 Pa;
with the increase of the speed of the vehicle 2 and rocket 4 in the duct 1, the driving force F applied to the vehicle 2 is kept constant in order to keep the acceleration constantqThe need for a corresponding continuous increase;
when t is<t1When F is presentq＝f(t,Fd) In which F isdAlso a function of time t, Fd＝g(t)；
When t is>t1When F is presentq＝f(t,Fd) In which F isd＝g(t，Fa)，FaAdditional aerodynamic resistance added to the bleed orifice 8 after admission, which is also a function of time t;
required driving force FqGreater than aerodynamic resistance FdTo ensure the acceleration required for the rocket 4;
the size of b is determined by optimization calculation or experimental analysis.
After the rocket 4 passes through the air vents 8, the air vents 8 behind the rocket 4 are closed in sequence immediately; after the rocket 4 rushes out of the outlet door 131 at the end of the pipeline 1, the last vent hole 8 is closed, and the outlet door 131 is closed at the same time.
The end of the acceleration section 12 and the launch section 13 are arranged in a vertical curvilinear line with a radius of curvature R to increase the launch elevation angle, which is up to 90 ° at maximum.
The invention has the beneficial effects that:
by arranging the vent holes 8, when the rocket 4 accelerated by the vehicle 2 approaches the outlet at the tail end of the pipeline 1, the air pressure in the pipeline 1 uniformly rises, and when the rocket reaches the outlet of the pipeline 1, the air pressure inside and outside the pipeline 1 at the outlet is completely balanced, so that the rocket 4 is prevented from being impacted by instantaneous airflow when rushing out of the pipeline 1; meanwhile, the air quantity flowing into the pipeline 1 can be ensured to be minimized, and the loss of the vacuum degree in the pipeline 1 is minimized.
Drawings
Fig. 1 is a schematic view of an air pressure balancing device at the tail section of a vacuum pipeline aerospace launching, wherein a pipeline 1 is in a linear shape, a rocket 4 is in a state to be launched, and a first air lock door 51 and a second air lock door 52 are opened.
FIG. 2 is a schematic view of the air pressure balancing device at the final stage of the aerospace launching of the vacuum pipe of the present invention, wherein the x coordinate axis is shown along the pipe 1, the length a of the rocket 4 and the initial vent hole 8 (H)1) Position coordinates l-b, and air vent 8 interval c.
FIG. 3 is t<t1At the moment, the air pressure in the pipeline 1 and the air pressure outside the outlet of the pipeline 1 are shown schematically, wherein the air pressure in the pipeline 1 is p1The external air pressure at the outlet of the pipeline 1 is p0。
FIG. 4 is t>t1The pressure change of the path of the time rocket is shown as H1The latter oblique straight line.
FIG. 5 is a graph of the aerodynamic drag experienced by rocket 4 during its travel in duct 1 (OGK)3) And an additional aerodynamic resistance curve (H) added by the deflation of the deflation orifice 81K1) Schematic representation.
Fig. 6 is a schematic view of an air pressure balancing device at the tail end of a vacuum tube aerospace launching according to the present invention, wherein the tail end (launching section 13) of a tube 1 is a curve with a radius R, and a launching elevation angle α' is larger than the launching elevation angle α in fig. 1 and 2.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
As shown in fig. 1, the vacuum pipeline aerospace launching tail-end air pressure balancing device comprises a pipeline 1 built according to a mountain 3, wherein a vehicle 2 is arranged in the pipeline 1, a rocket 4 is carried on the vehicle 2, an outlet of the pipeline 1 is positioned at the top of the mountain 3 and forms a certain elevation angle alpha with the horizontal plane, and a plurality of air vents 8 are formed in the pipeline 1 close to the outlet;
the pipeline 1 consists of an initial section 11, an acceleration section 12 and an emission section 13, wherein the initial section 11, the acceleration section 12 and the emission section 13 are respectively provided with a vacuum pump 6; a first air lock door 51 is arranged between the starting section 11 and the accelerating section 12, a second air lock door 52 is arranged between the accelerating section 12 and the launching section 13, the starting section 11 is provided with an entrance door 111 for air-tight isolation from the outside and for the vehicle 2 and the rocket 4 to enter, and the launching section 13 is provided with an exit door 131 for air-tight isolation from the outside and for the rocket 4 to launch; the end of the emission section 13 is provided with a plurality of air vents 8, and the air vents 8 are controlled by an automatic air valve to be communicated with the atmosphere.
The vehicle 2 is a vacuum pipeline transportation vehicle, a carriage is removed, a chassis is reserved and transformed, the vehicle 2 is a magnetic suspension vehicle and is used for carrying the rocket 4 and providing initial acceleration for the rocket 4, and the vehicle 2 carrying the rocket 4 can reach high supersonic speed of more than 2km/s due to elimination of air resistance and mechanical friction.
The pipeline 1 is a vacuum pipeline.
The vehicle 2 and the rocket 4 are arranged in an automatic separation mode, after entering the launching section 13, the vehicle 2 decelerates, the rocket 4 is separated from the vehicle 2, and rushes out of the exit door 131 of the launching section 13 to enter the sky under the action of the continuity.
The rocket 4 is loaded with a cargo ship, and the vehicle 2 carrying the rocket 4 is accelerated by 10g (about 10 m/s)2) The speed of the rocket 4 when leaving the pipeline 1 is 1km/s, the acceleration time of the rocket 4 in the pipeline 1 is 100s, the total length of the pipeline is 50km, the elevation of the mountain body 3 is 8000m, the launching elevation α is reached, and tg α is 0.016.
The air pressure at the outlet of the pipeline 1 is about 35000Pa, which is beneficial to reducing the aerodynamic resistance of the rocket 4.
The interior of the pipeline 1 is vacuum with the air pressure less than 10Pa, the exterior of the pipeline outlet is 35000Pa, and under the action of huge pressure difference, the rocket which has obtained very high initial speed can be impacted by very large instantaneous air flow when rushing out of the pipeline, so that the running stability and the self structure stability of the rocket are influenced, and safety risk is brought to space launching. In order to overcome the launching safety risk brought by the air flow impact, the following launching tail section air pressure balancing method is provided:
the launching tail section air pressure balancing method of the vacuum pipeline spaceflight launching tail section air pressure balancing device comprises the following steps of:
setting the rocket length as a, the starting point O of the rocket 4 as the origin of coordinates, and the terminal coordinates of the pipeline as l; from a distance b from the emission opening E (outlet door 131), the pipe wall of the pipeline 1 is provided with air vents 8 at intervals of c, and the first air vent 8 is H1A mark with coordinates l-b on the x-axis, as shown in fig. 2 and 3;
t is t for the start of transmission0At the moment, the speed of the rocket 4 and the vehicle 2 is 0, and the internal air pressure of the pipeline 1 is p110Pa, the air pressure outside the outlet door 131 of the pipeline 1 is p0＝35000Pa，p0>>p1As shown in fig. 3;
t＝t1when the rocket 4 and the vehicle 2 reach the H where the first vent hole 8 is located1At a velocity v1Opening all automatic air valves of the air release holes 8 and starting to release air into the pipeline 1; then from t1Starting from the moment, the air pressure in the pipeline 1 through which the rocket passes gradually rises; the size of the air vent 8 and the air release speed are required to be achieved, when the rocket 4 reaches the outlet, the air pressure in the pipeline 1 at the outlet is equal to the air pressure outside the pipeline 1, namely equal to 35000Pa, as shown in figure 4; thus, rocket 4 is at t1While advancing in the pipe 1 after the moment, encounters an additional resistance which increases uniformly, as indicated by the line segment H in figure 51K1As shown, when the rocket 4 finally rushes out of the outlet door 131 at the tail end of the pipeline 1, no pressure difference exists between the inside and the outside of the pipeline 1, so that the rocket 4 is prevented from being impacted by instantaneous airflow due to the pressure difference between the inside and the outside of the pipeline. The air release mode of the air release holes 8 is adopted, so that the additional resistance of the rocket 4 can be uniformly increased, the air quantity entering the pipeline 1 can be smaller, and the damage degree to the vacuum environment is minimum.
As the speed of the vehicle 2 and rocket 4 increases in the duct 1, the aerodynamic drag F encountered by the vehicle increasesdThe greater the aerodynamic drag FdProportional to the square of the velocity, e.g. curve OGK in fig. 52(ii) a To maintain constant acceleration, drive applied to the vehicleForce FqThe need for a corresponding continuous increase;
when t is<t1When F is presentq＝f(t,Fd) In which F isdAlso a function of time t, Fd＝g(t)；
When t is>t1When F is presentq＝f(t,Fd) In which F isd＝g(t，Fa)，FaAdditional aerodynamic resistance added to the bleed orifice 8 after admission, which is also a function of time t;
required driving force FqGreater than aerodynamic resistance FdTo ensure the required acceleration of the rocket 4. As shown in fig. 5, at time t>t1After that, i.e. rocket 4 passes through H1Then, the rocket 4 can be subjected to additional resistance after the air is discharged from the air discharge holes 8; additional drag force corresponding to different x-coordinates is given by Δ fiShowing that the total resistance after the superposition is shown as the curve GK in FIG. 53As shown.
The closer the first bleed hole 8 is located to the origin of the pipeline (point O), i.e. the larger b, the advantage is that the smaller the required bleed rate of each bleed hole, the smaller the required additional driving force; the disadvantages are that the more air flows into the pipeline 1 during the launching process, the greater the damage to the whole vacuum environment of the pipeline 1, the greater the cost of re-establishing the vacuum environment (vacuumizing), and the more fragile the overall structure of the pipeline 1.
The closer the first air vent 8 is arranged to the tail end (point E) of the pipeline, namely the smaller b is, the less air flows into the pipeline 1 in the launching process, the smaller the damage to the whole-section vacuum environment of the pipeline 1 is, and the lower the cost of establishing the vacuum environment (vacuumizing) is; the disadvantage is that the greater the required deflation rate of the deflation holes, the greater the additional driving force required.
Therefore, the size of b is determined by optimization calculation or experimental analysis.
In order to further reduce the loss of the vacuum degree in the pipeline 1, after the rocket 4 passes through the vent holes 8, the vent holes 8 behind the rocket 4 are sequentially and immediately closed; after the rocket 4 is flushed out of the end outlet of the pipeline 1, the last vent hole 8 (close to the outlet door 131) is closed, and the outlet door 131 is closed.
The end of the accelerating section 12 and the transmitting section 13 are arranged in a vertical curved line with a radius of curvature R to increase the transmitting elevation angle, as shown in fig. 6, where α '> α is shown, and the transmitting elevation angle α' can reach 90 ° at most.
Claims (9)
1. The utility model provides a vacuum tube space launch terminal segment atmospheric pressure balancing unit, includes pipeline 1 that builds according to massif (3), its characterized in that: a vehicle (2) is arranged in the pipeline (1), a rocket (4) is carried on the vehicle (2), the outlet of the pipeline (1) is positioned at the top of the mountain body (3) and forms a certain elevation angle alpha with the horizontal plane, and a plurality of air vents (8) are arranged on the pipeline (1) close to the outlet;
the pipeline (1) consists of an originating section (11), an accelerating section (12) and an emitting section (13), wherein the originating section (11), the accelerating section (12) and the emitting section (13) are respectively provided with a vacuum pump (6); a first air gate (51) is arranged between the starting section (11) and the accelerating section (12), a second air gate (52) is arranged between the accelerating section (12) and the launching section (13), the starting section (11) is provided with an inlet door (111), the launching section (13) is provided with an outlet door (131), the tail end of the launching section (13) is provided with a plurality of air vents (8), and the air vents (8) are controlled to be communicated with the atmosphere through automatic air valves.
2. The vacuum pipe aerospace launching terminal air pressure balancing device according to claim 1, wherein: the vehicle (2) is a vacuum pipeline traffic vehicle, a carriage is removed, a chassis is reserved for transformation, and the vehicle (2) is a magnetic suspension vehicle.
3. The vacuum pipe aerospace launching terminal air pressure balancing device according to claim 1, wherein: the pipeline (1) is a vacuum pipeline.
4. The vacuum pipe aerospace launching terminal air pressure balancing device according to claim 1, wherein: the vehicle (2) and the rocket (4) are arranged in an automatic separation mode, after entering the launching section (13), the vehicle (2) decelerates, the rocket (4) breaks away from the vehicle (2), and rushes out of an exit door (131) of the launching section (13) under the action of the coherence to enter the sky.
5. The vacuum pipe aerospace launching terminal air pressure balancing device according to claim 1, wherein: the rocket (4) is carried with a cargo ship, the acceleration of a vehicle (2) carrying the rocket (4) is 10g, and the speed of the rocket (4) when leaving the pipeline (1) is 1 km/s; the acceleration time of the rocket (4) in the pipeline (1) is 100s, the total length of the pipeline is 50km, the altitude of the mountain body (3) is 8000m, and the launching elevation angle alpha and tg alpha are 0.016.
6. The vacuum pipe aerospace launching terminal air pressure balancing device according to claim 1, wherein: the air pressure at the outlet of the pipeline (1) is about 35000 Pa.
7. The launching tail section air pressure balancing method of the vacuum pipeline aerospace launching tail section air pressure balancing device is used, and is characterized by comprising the following steps:
setting the rocket length as a, the starting point O of the rocket (4) as the origin of coordinates, and the terminal coordinate of the pipeline as l; from a distance b away from the outlet door (131), air vents (8) are arranged on the pipe wall of the pipeline (1) at intervals of c, and H is used for the first air vent (8)1A marker having coordinates l-b on the x-axis;
t is t for the start of transmission0At the moment, the speed of the rocket (4) and the vehicle (2) is 0, and the internal air pressure of the pipeline (1) is p1The external air pressure of an outlet door (131) of the pipeline (1) is p under the condition of 10Pa0＝35000Pa，p0>>p1；
t＝t1When the rocket (4) and the vehicle (2) reach the H where the first vent hole (8) is positioned1At a velocity v1Opening all automatic air valves of the air release holes (8) and beginning to release air into the pipeline (1); then from t1Starting from the moment, the air pressure in the pipeline (1) through which the rocket passes gradually rises; the size and the air release speed of the air release hole (8) are required to be achieved, when the rocket (4) reaches the outlet door (131), the air pressure in the pipeline (1) at the outlet is equal to the air pressure outside the pipeline (1), namely equal to 35000 Pa;
the driving force F applied to the vehicle (2) is kept constant in order to keep the acceleration along with the increase of the speed of the vehicle (2) and the rocket (4) in the pipeline (1)qNeed to make sure thatCorrespondingly, the increase continues;
when t is<t1When F is presentq＝f(t,Fd) In which F isdAlso a function of time t, Fd＝g(t)；
When t is>t1When F is presentq＝f(t,Fd) In which F isd＝g(t，Fa)，FaAn additional aerodynamic resistance added after the air bleed (8) has been bled, which is also a function of time t;
required driving force FqGreater than aerodynamic resistance FdTo ensure the acceleration required for the rocket (4);
the size of b is determined by optimization calculation or experimental analysis.
8. The method for balancing the air pressure at the final launching section of the vacuum pipe aerospace final launching section air pressure balancing device according to claim 7, wherein after the rocket (4) passes through the air vents (8), the air vents (8) behind the rocket (4) are closed immediately in sequence; after the rocket (4) rushes out of the outlet door (131) of the pipeline (1), the last vent hole (8) is closed, and meanwhile, the outlet door (131) is closed.
9. The method for balancing the gas pressure at the launching end of a vacuum tube aerospace launching end gas pressure balancing device according to claim 7, wherein the tip of the accelerating section (12) and the launching section (13) are arranged in a vertical curve with a radius of curvature R to increase the launching elevation angle, and the launching elevation angle α' is up to 90 °.
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| CN113844681A (en) * | 2021-09-01 | 2021-12-28 | 中国化学工程第三建设有限公司 | Magnetic suspension vacuum pipeline carrying system |
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| CN113844681A (en) * | 2021-09-01 | 2021-12-28 | 中国化学工程第三建设有限公司 | Magnetic suspension vacuum pipeline carrying system |
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Application publication date: 20200818 |