阅读说明：本技术 一种基于真空管道加速的航天发射系统管道与发射方法 (Aerospace launching system pipeline based on vacuum pipeline acceleration and launching method ) 是由 张耀平 青山 赵勇 于 2020-05-25 设计创作，主要内容包括：一种基于真空管道加速的航天发射系统管道与发射方法,包括依山体而建的管道,管道出口位于山体顶部,管道内设置有车辆,车辆上装载有火箭/航天器；管道为真空管道,由始发段、加速段和发射段组成,始发段和加速段之间设有第一气闸门,加速段和发射段之间设有第二气闸门,始发段初始端头设置入口门,发射段结尾端头设置出口门,始发段、加速段和发射段均配有抽真空的真空泵；车辆为真空管道交通车辆,去掉车厢,保留底盘改造而成；车辆与火箭/航天器之间设置成可自动分离形式,进入发射段后,车辆减速,火箭/航天器脱离车辆,在贯性作用下冲出发射段的出口进入天空；本发明提高航天发射效率,降低航天发射成本。(A space launching system pipeline based on vacuum pipeline acceleration and a launching method thereof comprise a pipeline built according to a mountain, wherein a pipeline outlet is positioned at the top of the mountain, a vehicle is arranged in the pipeline, and a rocket/spacecraft is loaded on the vehicle; the pipeline is a vacuum pipeline and consists of an initial section, an acceleration section and a launching section, wherein a first air gate is arranged between the initial section and the acceleration section, a second air gate is arranged between the acceleration section and the launching section, an inlet door is arranged at the initial end of the initial section, an outlet door is arranged at the tail end of the launching section, and the initial section, the acceleration section and the launching section are all provided with vacuum pumps for vacuumizing; the vehicle is a vacuum pipeline transportation vehicle, a carriage is removed, and a chassis is reserved for transformation; the vehicle and the rocket/spacecraft are arranged in an automatic separation mode, after entering a launching section, the vehicle decelerates, the rocket/spacecraft is separated from the vehicle, and rushes out of an outlet of the launching section to enter the sky under the action of inertia; the invention improves the space launching efficiency and reduces the space launching cost.)

1. An aerospace launching system pipeline based on vacuum pipeline acceleration is characterized in that: comprises a pipeline (1) built according to a mountain body (3), wherein the outlet of the pipeline (1) is positioned at the top of the mountain body (3) and forms an elevation angle alpha with the horizontal plane; a vehicle (2) is arranged in the pipeline (1), a rocket/spacecraft (4) is loaded on the vehicle (2), and the pipeline (1) is provided with a vacuum pump (6) for vacuumizing.

2. A vacuum tube acceleration based space launch system tube according to claim 1, characterized in that: the pipeline (1) is a vacuum pipeline and consists of an initial starting section (11), an accelerating section (12) and a launching section (13), a first air gate (51) is arranged between the initial 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), an inlet door (111) is arranged at the initial end of the initial starting section (11), an outlet door (131) is arranged at the tail end of the launching section (13), and the initial starting section (11), the accelerating section (12) and the launching section (13) are all provided with a vacuum pump (6) for vacuumizing.

3. A vacuum tube acceleration based space launch system tube according to claim 1, characterized in that: the vehicle (2) is a vacuum pipeline traffic vehicle, a carriage is removed, and a chassis is reserved for transformation; the vehicle (2) is a magnetic levitation vehicle, and the vehicle (2) mounted with the rocket/spacecraft (4) can reach a high supersonic speed of more than 2 km/s.

4. A vacuum tube acceleration based space launch system tube according to claim 1, characterized in that: the vehicle (2) and the rocket/spacecraft (4) are arranged in an automatic separation mode, after entering the launching section (13), the vehicle (2) decelerates, and the rocket/spacecraft (4) breaks away from the vehicle (2) and rushes out of an outlet (131) of the launching section (13) to enter the sky under the action of the continuity.

5. A vacuum tube acceleration based space launch system tube according to claim 1, characterized in that: the altitude of the mountain body (3) is more than 7000m, so that the launched rocket/spacecraft (4) can directly enter the rarefied gas space less than 0.4 atm.

6. The launching method of the aerospace launching system pipeline based on vacuum pipeline acceleration, as claimed in claim 2, is characterized by comprising the following steps:

step 1: a first air lock door (51) between the starting section (11) and the accelerating section (12) is in a closed state, a second air lock door (52) between the accelerating section (12) and the launching section (13) is in a closed state, an outlet door (131) of the launching section (13) is in a closed state, a vacuum pump (6) is started, and the accelerating section (12) and the launching section (13) are vacuumized until the required vacuum degree is reached;

step 2: a vehicle (2) carrying a rocket/spacecraft (4) is sent into an initiating section (11), and an entrance door (111) is closed;

and step 3: vacuumizing the starting section (11) until reaching the required vacuum degree;

and 4, step 4: opening a first air lock (51) between the originating section (11) and the acceleration section (12), and opening a second air lock (52) between the acceleration section (12) and the launch section (13);

and 5: starting a vehicle (2) carrying a rocket/spacecraft (4), driving into an acceleration section (12) and continuously accelerating;

step 6: after the vehicle (2) carrying the rocket/spacecraft (4) passes through the second air gate (52), the vehicle (2) decelerates and brakes, and the rocket/spacecraft (4) departs from the vehicle (2) and rushes to the exit door (131);

and 7: when the rocket/spacecraft (4) approaches the exit door (131), the pneumatic stamping acting force of the rocket/spacecraft (4) rushes open the exit door (131), and the rocket/spacecraft (4) rushes out of the exit door (131) and enters the sky; meanwhile, the rocket/spacecraft (4) is ignited to start providing thrust for the rocket/spacecraft (4);

and 8: after the rocket/spacecraft (4) rushes out of the exit door (131), the exit door (131) is immediately closed, and the vehicle (2) retreats to the starting section (11);

and step 9: and (3) closing the first air lock door (51) and the second air lock door (52), starting the vacuum pump (6), and further vacuumizing the acceleration section (12) and the launching section (13) until the required vacuum degree is reached to prepare for the next launching task.

7. The transmission method according to claim 6, characterized in that: the end of the accelerating section (12) and the launching section (13) are arranged in a vertical curve with a curvature radius R so as to increase the launching elevation angle alpha ', alpha' of the accelerating section to 90 degrees at most.

Technical Field

The invention belongs to the technical field of vacuum pipeline traffic and aerospace engineering, and particularly relates to a pipeline and a launching method of an aerospace launching system based on vacuum pipeline acceleration.

Background

The vacuum pipeline transportation is to build an airtight pipeline 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: launch efficiency of the launch vehicles is too low, launch costs are too high, and these rockets are all disposable. Although reusable rockets have been developed, it is impossible to change the situation that the specific gravity of fuel is too high at the time of take-off of the rocket and the fuel consumption is large during the launching process.

The existing space launching is vertically launched from the ground, ignition is started from a static state, and the stage is also the stage with the largest fuel consumption rate of the space launching due to the largest total mass during take-off. For a three-stage rocket, when the speed is increased to 2km/s, the mission is generally completed when the fuel of the first-stage rocket is exhausted. While the mass of the first stage rocket usually accounts for about half of the total mass. 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.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention aims to provide a vacuum pipeline acceleration-based aerospace launching system pipeline and a launching method, so that the aerospace launching efficiency is improved, the aerospace launching cost is reduced, and conditions are created for large-scale space development.

In order to achieve the purpose, the invention adopts the technical scheme that:

a space launching system pipeline based on vacuum pipeline acceleration comprises a pipeline 1 built according to a mountain 3, wherein an outlet of the pipeline 1 is positioned at the top of the mountain 3, and an elevation angle alpha is formed between the outlet and the horizontal plane; a vehicle 2 is arranged in the pipeline 1, a rocket/spacecraft 4 is loaded on the vehicle 2, and the pipeline 1 is provided with a vacuum pump 6 for vacuumizing.

The pipeline 1 is a vacuum pipeline and comprises an initial section 11, an acceleration section 12 and a launching section 13, wherein a first air lock door 51 is arranged between the initial section 11 and the acceleration section 12, a second air lock door 52 is arranged between the acceleration section 12 and the launching section 13, an inlet door 111 is arranged at the initial end of the initial section 11, an outlet door 131 is arranged at the tail end of the launching section 13, and the initial section 11, the acceleration section 12 and the launching section 13 are all provided with a vacuum pump 6 for vacuumizing.

The vehicle 2 is a vacuum pipeline traffic vehicle, a carriage is removed, and a chassis is reserved for transformation; the vehicle 2 is a magnetic levitation vehicle, and the vehicle 2 mounted with the rocket/spacecraft 4 can reach a high supersonic speed of 2km/s or more.

The vehicle 2 and the rocket/spacecraft 4 are arranged in an automatic separation mode, after entering the launching section 13, the vehicle 2 decelerates, the rocket/spacecraft 4 is separated from the vehicle 2 and rushes out of an outlet 131 of the launching section 13 to enter the sky under the action of inertia.

The mountain 3 has an altitude of more than 7000m, so that the launched rocket/spacecraft 4 can directly enter a rarefied gas space of less than 0.4atm (about 40000 Pa).

The launching method of the aerospace launching system pipeline based on vacuum pipeline acceleration comprises the following steps:

step 1: the first air lock door 51 between the starting section 11 and the accelerating section 12 is in a closed state, the second air lock door 52 between the accelerating section 12 and the launching section 13 is in a closed state, the outlet door 131 of the launching section 13 is in a closed state, and the vacuum pump 6 is started to vacuumize the accelerating section 12 and the launching section 13 until the required vacuum degree is reached;

step 2: the vehicle 2 carrying the rocket/spacecraft 4 is sent to the initiation section 11, and the entrance door 111 is closed;

and step 3: vacuumizing the starting section 11 until reaching the required vacuum degree;

and 4, step 4: opening a first air lock door 51 between the originating section 11 and the acceleration section 12, and opening a second air lock door 52 between the acceleration section 12 and the launch section 13;

and 5: starting the vehicle 2 carrying the rocket/spacecraft 4, and driving into the acceleration section 12 to accelerate continuously;

step 6: after the vehicle 2 carrying the rocket/spacecraft 4 passes through the second air lock door 52, the vehicle 2 decelerates and brakes, and the rocket/spacecraft 4 departs from the vehicle 2 and rushes to the exit door 131;

and 7: when the rocket/spacecraft 4 approaches the exit door 131, the pneumatic stamping acting force of the rocket/spacecraft 4 rushes the exit door 131, and the rocket/spacecraft 4 rushes out of the exit door 131 and enters the sky; meanwhile, the rocket/spacecraft 4 is ignited to start providing thrust for the rocket/spacecraft 4;

and 8: after the rocket/spacecraft 4 rushes out of the exit door 131, the exit door 131 is immediately closed, and the vehicle 2 retreats to the starting section 11;

and step 9: the first air lock door 51 and the second air lock door 52 are closed, the vacuum pump 6 is started, and the acceleration section 12 and the launching section 13 are further vacuumized until the required vacuum degree is reached, and the next launching task is prepared.

The end of the acceleration section 12 and the emission section 13 are arranged in the shape of a vertical curve with a radius of curvature R, so as to increase the emission elevation angle α', which can be up to 90 ° at the maximum.

The invention has the beneficial effects that:

the mountain 3 with the ground more than 7000m is used as a support for building the pipeline 1, so that the engineering cost is saved; the air enters the air layer with rarer air at high altitude immediately, and has smaller aerodynamic resistance than the prior low altitude rocket launching site; the initial acceleration is provided for the rocket/spacecraft 4 through the pipeline 1 and the vehicle 2, so that the rocket/spacecraft 4 has higher initial speed when leaving the ground surface, and the fuel and the weight of the fuel of the first-stage rocket of the existing multi-stage rocket can be saved; the vehicle 2 for accelerating the rocket/spacecraft 4 is reusable. The invention can effectively reduce the space launching cost, accelerate the launching period and provide technical support for large-scale space development.

Drawings

Fig. 1 is a schematic view of the present invention, wherein the pipe 1 is in the form of a straight line, and the rocket/spacecraft 4 is in a state to be launched, and the first air lock door 51 and the second air lock door 52 are not yet opened.

Fig. 2 is a schematic view of the invention with the rocket/spacecraft 4 in the impending launch state with the first and second airlock doors 51, 52 already open.

Figure 3 is a schematic view of the invention in which the vehicle 2 is starting to brake and the rocket/spacecraft 4 has been detached from the vehicle 2.

Fig. 4 is a schematic view of the invention, where the vehicle 2 has been braked to a stop and the rocket/spacecraft 4 has been flushed out of the tube 1.

Fig. 5 is a schematic view of the present invention, in which the rocket/spacecraft 4 has been launched, the vehicle 2 has been retracted to the launch section 11, and the first air lock door 51 and the second air lock door 52 are about to close.

Fig. 6 is a schematic view of the present invention, wherein the end of the pipe 1 (the launch section 13) is a curve with a radius R, and the launch elevation angle α' is greater than the launch elevation angle α in fig. 1-5, wherein the rocket/spacecraft 4 is in a state to be launched, and the first air lock door 51 and the second air lock door 52 are not yet opened.

Detailed Description

The invention is described in detail below with reference to the figures and examples.

As shown in fig. 1, a vacuum tube acceleration-based aerospace launching system tube comprises a tube 1 built according to a mountain 3, wherein an outlet of the tube 1 is positioned at the top of the mountain 3 and forms an elevation angle alpha with a horizontal plane; a vehicle 2 is arranged in the pipeline 1, a rocket/spacecraft 4 (such as a satellite, a spacecraft, a space detector and the like) is loaded on the vehicle 2, and the pipeline 1 is provided with a vacuum pump 6 for vacuumizing.

The pipeline 1 is a vacuum pipeline and consists of an initial section 11, an acceleration section 12 and a launching section 13, wherein a first air gate 51 is arranged between the initial section 11 and the acceleration section 12, a second air gate 52 is arranged between the acceleration section 12 and the launching section 13, and an inlet door 111 is arranged at the initial end of the initial section 11 and is used for air-tight isolation from the outside and for vehicles 2 and rockets/spacecrafts 4 to enter; the end head of the tail end of the launching section 13 is provided with an outlet door 131 which is used for air-tight isolation with the outside and for the rocket/spacecraft 4 to launch; the starting section 11, the acceleration section 12 and the launch section 13 are each provided with a vacuum pump 6 for evacuation.

The vehicle 2 is a vacuum pipeline transportation vehicle, a carriage is removed, a chassis is reserved and is formed by transformation, and the vehicle is used for carrying the rocket/spacecraft 4 and providing initial acceleration for the rocket/spacecraft 4; the vehicle 2 is a magnetic levitation vehicle, and the vehicle 2 mounted with the rocket/spacecraft 4 can reach a high supersonic speed of 2km/s or more because of eliminating air resistance and mechanical friction.

The vehicle 2 and the rocket/spacecraft 4 are arranged in an automatic separation mode, after entering the launching section 13, the vehicle 2 decelerates, the rocket/spacecraft 4 is separated from the vehicle 2 and rushes out of an outlet 131 of the launching section 13 to enter the sky under the action of inertia; the altitude of the mountain 3 is more than 7000m, so that the pipeline 1 has enough acceleration length, and the launched rocket/spacecraft 4 can directly enter a rarefied gas space less than 0.4atm (about 40000Pa), thereby reducing the aerodynamic drag of the rocket/spacecraft 4 when flying in the atmosphere.

The launching method of the aerospace launching system pipeline based on vacuum pipeline acceleration comprises the following steps:

step 1: the first air lock door 51 between the starting section 11 and the accelerating section 12 is in a closed state, the second air lock door 52 between the accelerating section 12 and the launching section 13 is in a closed state, the outlet door 131 of the launching section 13 is in a closed state, and the vacuum pump 6 is started to vacuumize the accelerating section 12 and the launching section 13 until the required vacuum degree is reached;

step 2: the vehicle 2 carrying the rocket/spacecraft 4 is sent into the initiation section 11, and the entrance door 111 is closed, as shown in fig. 1;

and step 3: vacuumizing the starting section 11 until reaching the required vacuum degree;

and 4, step 4: opening a first air lock door 51 between the originating section 11 and the acceleration section 12 and opening a second air lock door 52 between the acceleration section 12 and the launch section 13, as shown in fig. 2;

and 5: starting the vehicle 2 carrying the rocket/spacecraft 4, and driving into the acceleration section 12 to accelerate continuously;

step 6: after the vehicle 2 carrying the rocket/spacecraft 4 passes through the second air lock door 52, the vehicle 2 decelerates and brakes, and the rocket/spacecraft 4 departs from the vehicle 2 and rushes to the exit door 131, as shown in fig. 3;

and 7: when the rocket/spacecraft 4 approaches the exit door 131, the pneumatic stamping acting force of the rocket/spacecraft 4 rushes the exit door 131, the rocket/spacecraft 4 rushes out of the exit door 131 and enters the sky, and the working principle of the exit door 131 is similar to a method for launching torpedoes and missiles from the water by a submarine launching tube; at the same time, the rocket/spacecraft 4 fires, starting to provide thrust to the rocket/spacecraft 4 itself, as shown in fig. 4;

and 8: after the rocket/spacecraft 4 rushes out of the exit door 131, the exit door 131 is immediately closed to prevent a large amount of air from entering the launching section 13, and the vehicle 2 retreats to the launching section 11, as shown in fig. 5;

and step 9: the first air lock door 51 and the second air lock door 52 are closed, the vacuum pump 6 is started, and the acceleration section 12 and the launching section 13 are further vacuumized until the required vacuum degree is reached, and the next launching task is prepared.

As shown in fig. 6, the end of the accelerating section 12 and the transmitting section 13 are arranged in a vertical curved line with a curvature radius R to increase the transmitting elevation angle α ', in the figure α ' > α, and α ' can reach 90 ° at most.