Spacecraft ejection launching system

Abstract

The invention relates to the field of aerospace, and particularly discloses a spacecraft ejection launching system. By arranging the launching track, the three sealing valves, the vacuum pump, the ultra-fast sealing valve and the catapult vehicle, an operator can place a rocket on the catapult vehicle, the catapult vehicle transports the rocket into the double-sealing door section, the vacuum pump is operated to enable the interior of the double-sealing door section to be vacuum, and the second sealing valve is opened; the driving module drives the catapult vehicle and the rocket to accelerate in the linear acceleration track section, the launching angle is adjusted through the turning track section, then the catapult vehicle and the rocket are separated in the separation track section, the rocket enters the free flight track section to do free flight motion due to inertia, and the ultra-fast sealing valve is controlled to be fast opened and closed. The high vacuum degree in the launching track is maintained, it is guaranteed that the rocket can conduct vacuum flight in the launching track, the rocket has the flight speed large enough, the rocket launching quality is reduced, and meanwhile the carrying capacity of the rocket is improved.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to spacecraft catapult launch systems. Background Technology

[0002] Traditional spacecraft launches mostly use rockets. The payload typically accounts for 1% to 4% of the total launch mass, with the first stage making up 70% to 80% of the total mass. The primary function of the first stage is to increase the rocket's initial velocity to Mach 6-8, helping it escape Earth's gravity. This means that most of the rocket's space is occupied by fuel. To improve space utilization, the amount of fuel carried can be reduced. Using electromagnetic catapults on the ground to accelerate the rocket to Mach 6-10 not only ensures sufficient initial velocity for escape but also effectively reduces the launch mass, saving launch costs. Furthermore, existing rocket technology allows for large payload launches, increasing launch efficiency by 10% to 20%. This is of great significance to human space exploration. Summary of the Invention

[0003] The purpose of this invention is to provide a spacecraft ejection system to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution:

[0005] Spacecraft ejection launch system, including:

[0006] The launch track consists of a linear acceleration track section, a turning track section, a rocket car brake separation track section, a free flight track section, an exit track section, and a braking track section. The turning track section is connected to the rocket car brake separation track section at its tail end. The rocket car brake separation track section is bifurcated at its tail end. One end of the rocket car brake separation track section is connected to the free flight track section, and the other end of the rocket car brake separation track section is connected to the braking track section. The exit track section is located on the free flight track section.

[0007] A double-sealed gate section is provided at the inlet of the linear acceleration track section, and a first sealing valve and a second sealing valve are respectively fixedly installed on the linear acceleration track section at both ends of the double-sealed gate section.

[0008] A vacuum pump, wherein multiple vacuum pumps are provided, and the multiple vacuum pumps are fixedly installed on the launch rail and communicate with the interior of the launch rail;

[0009] An ultra-fast sealing valve is installed at the end of the outlet track section;

[0010] The catapult is slidably mounted inside the launch track to carry spacecraft.

[0011] Preferably, the linear acceleration track segment is 55km long, the turning track segment has a turning radius of 85km and a length of 26.7km, the separation track segment is 500m long, and the free flight track segment is 3.2km long.

[0012] Preferably, the length of the double-sealed door section is greater than the length of the spacecraft, that is, the distance between the first sealing valve and the second sealing valve is greater than the length of the spacecraft.

[0013] Preferably, the ultra-fast sealing valve includes an electromagnetic catapult fixedly installed at the end of the exit track section, a collision block slidably connected to the electromagnetic catapult, a damping brake fixedly connected to the other side of the ultra-fast sealing valve, a valve core slidably connected in the middle of the ultra-fast sealing valve to block the exit of the free flight track section, and a third sealing valve fixedly connected to the exit track section.

[0014] Preferably, the catapult is arranged in a 120° arc plate shape, and the upper surface of the catapult is fixedly connected to two ends of a retaining ring. The corner of the upper surface of the retaining ring is provided with a 45° chamfer, and the side wall of the retaining ring at the rear end of the catapult is convex upward.

[0015] Preferably, an electromagnet is fixedly connected inside the retaining ring, the catapult vehicle attracts the rocket through the electromagnet, and the catapult vehicle and the rocket are separated from the electromagnetic attraction at the rocket vehicle braking separation track section, and a drive module is fixedly connected to the bottom of each end of the catapult vehicle.

[0016] Preferably, the vacuum level of the launch environment inside the launch track is less than 2000 Pa.

[0017] Compared with the prior art, the beneficial effects of the present invention are:

[0018] This invention, through the setup of a launch track, three sealing valves, a vacuum pump, an ultra-fast sealing valve, and an ejection vehicle, allows operators to place the rocket on the ejection vehicle. Electromagnets inside the ejection vehicle's retaining ring securely hold the rocket to the vehicle, with the rocket's tail end engaging a protrusion on the retaining ring. The ejection vehicle transports the rocket to the double-sealed section. The vacuum pump operates to create a vacuum within the double-sealed section and opens the second sealing valve. A drive module propels the ejection vehicle and rocket to accelerate within the linear acceleration track section. The launch angle is adjusted via a turning track section, after which the ejection vehicle and rocket separate on the separation track section. The ejection vehicle then enters the braking track section to a stop, while the rocket, due to inertia, enters the free-flight track section for free-flight motion. The ultra-fast sealing valve is controlled to rapidly open and close, maintaining a high vacuum within the launch track. This ensures the rocket can fly in a vacuum within the launch track, allowing it to achieve a sufficiently high flight speed upon launch. This effectively avoids carrying large amounts of fuel, reducing the rocket's launch mass while increasing its payload capacity. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the launch track structure of the present invention. Figure 1 ;

[0020] Figure 2 This is a schematic diagram of the enlarged launch track structure of the present invention. Figure 2 ;

[0021] Figure 3 For the present invention Figure 2 Enlarged view of part A in the middle;

[0022] Figure 4 This is a schematic diagram of the enlarged launch track structure of the present invention. Figure 4 ;

[0023] Figure 5 For the present invention Figure 4 Enlarged view of part B in the middle;

[0024] Figure 6 This is a schematic diagram of the closure of the ultra-fast sealing valve of the present invention;

[0025] Figure 7 This is a schematic diagram illustrating the opening of the ultra-fast sealing valve of the present invention;

[0026] Figure 8 This is a schematic diagram of the exit track section structure of the present invention;

[0027] Figure 9 This is a schematic diagram of the catapult vehicle structure of the present invention;

[0028] Figure 10 This is a schematic diagram of the overall structure of the launch track of the present invention;

[0029] In the diagram: 1. Linear acceleration track section; 2. Turning track section; 3. Arrow car brake separation track section; 4. Free flight track section; 41. Exit track section; 5. Braking track section; 6. First sealing valve; 7. Second sealing valve; 8. Vacuum pump; 9. Ultra-fast sealing valve; 91. Electromagnetic catapult; 92. Collision block; 93. Damping brake; 94. Valve core; 10. Catapult car; 11. Snap ring; 12. Drive module; 13. Third sealing valve. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] Example:

[0032] Please see Figure 1 - Figure 10 As shown, the spacecraft catapult launch system includes:

[0033] The launch track consists of a linear acceleration track section 1, a turning track section 2, a rocket car brake separation track section 3, a free flight track section 4, an exit track section 41, and a braking track section 5. The tail end of the turning track section 2 is connected to the rocket car brake separation track section 3. The tail end of the rocket car brake separation track section 3 is forked. One end of the rocket car brake separation track section 3 is connected to the free flight track section 4, and the other end of the rocket car brake separation track section 3 is connected to the braking track section 5. The exit track section 41 is located on the free flight track section 4.

[0034] A double-sealed gate section is provided at the inlet of the linear acceleration track section 1, and a first sealing valve 6 and a second sealing valve 7 are respectively fixedly installed on the linear acceleration track section 1 at both ends of the double-sealed gate section.

[0035] Vacuum pump 8, wherein multiple vacuum pumps 8 are provided, and multiple vacuum pumps 7 are fixedly installed on the launch rail and communicate with the interior of the launch rail;

[0036] Ultra-fast sealing valve 9, wherein the ultra-fast sealing valve 9 is disposed at the end of the outlet track section 41;

[0037] The catapult 10 is slidably disposed inside the launch track for carrying spacecraft.

[0038] The rocket carrying the spacecraft is placed on the surface of the catapult 10. The first sealing valve 6 is opened, and the catapult 10 and the rocket are moved between the first sealing valve 6 and the second sealing valve 7. The vacuum pump 8 is activated to evacuate the launch track, and the second sealing valve 7 is opened. The catapult 10 propels the rocket inside the launch track. Due to the vacuum inside the launch track, the catapult 10 and the rocket accelerate inside the linear acceleration section 1, with an acceleration of 5.2-6 times the gravitational acceleration, loading the velocity to 2380 m / s² within 46 seconds, thus increasing the rocket's initial velocity. Afterwards, the catapult 10 and the rocket enter the turning track section 2, and the rocket's launch angle is adjusted. The rocket is controlled to make uniform circular motion at a speed of 2380m / s inside the turning track. At this time, the rocket's gravitational acceleration is 6.8G, and the time is 11.2s. At this time, the rocket's launch angle adjustment is completed, and the launch angle is 18°. Then, the catapult 10 and the rocket enter the rocket-cart braking separation track. Within a range of 500m, the catapult 10 begins to brake and enters the braking track, while the rocket will separate from the catapult 10 due to inertia and then make free fall parabolic motion.

[0039] The linear acceleration track section 1 is 55 km long, the turning track section 2 has a turning radius of 85 km and a length of 26.7 km, the rocket chariot braking and separation track section 3 is 500 m long, and the free flight track section 4 is 3.2 km long.

[0040] The length of the double-sealed valve section is greater than the length of the spacecraft, that is, the distance between the first sealing valve 6 and the second sealing valve 7 is greater than the length of the spacecraft.

[0041] An electromagnetic catapult 91 is fixedly connected to one side of the ultra-fast sealing valve 9, and a collision block 92 is slidably connected to the electromagnetic catapult 91. A damping brake 93 is fixedly connected to the other side of the ultra-fast sealing valve 9. A valve core 94 that blocks the exit of the free flight track section 4 is slidably connected to the middle of the ultra-fast sealing valve 9. A third sealing valve 13 is fixedly connected to the exit track section 41. There is a rocket flight distance between the third sealing valve 13 and the ultra-fast sealing valve 9. The third sealing valve 13 is in the open state. After passing through this valve, the rocket enters the space between the third sealing valve 13 and the ultra-fast sealing valve 9. After passing through the third sealing valve 13, it is quickly closed to maintain the vacuum inside the flight track.

[0042] Since the air diffusion speed is 340m / s, in order to ensure that the vacuum state inside the orbital system is not disrupted after the rocket flies out, the third sealing valve 13 is set at a distance of more than 400m from the exit and the closing speed must be less than 1 second; an electromagnetic catapult 91 is used to open the ultra-fast sealing valve 9, and the opening time of the ultra-fast sealing valve 9 is controlled within 30ms. This ensures that the ultra-fast sealing valve 9 opens when the rocket is 72-112m away from the exit, ensuring that the rocket flies in a vacuum within the system throughout the entire process.

[0043] When the ultra-fast sealing valve 9 needs to be opened, the electromagnetic catapult 91 activates the acceleration collision block 92, accelerating the collision block 92 to 200-300 m / s at the end of the track. After the collision block 92 separates from the electromagnetic catapult 91, it collides completely with the valve core 94. The collision block 92 stops or moves back slightly. After receiving the momentum of the collision block 92, the valve core 94 opens the valve at a speed of 200-300 m / s. After the valve core 94 moves, it is connected to the damping brake 93 and begins to decelerate.

[0044] In unmanned launch: At launch, the acceleration is 11.2 times the gravitational acceleration. Within 31 seconds, the launch vehicle 10 accelerates to 3400 m / s. The launch vehicle 10 enters the turning track section 2. At this time, the launch vehicle 10 is controlled to make uniform circular motion at a speed of 3400 m / s within the turning track section 2. At this time, the rocket is subjected to a gravitational acceleration of 14G for 7.84 seconds. The rocket angle adjustment is completed at this time, and the launch angle is 18°. Then it enters the rocket vehicle braking separation track 3. Within a range of 500m, the launch vehicle 10 begins to brake. The launch vehicle 10 enters the braking track section 5. Due to inertia, the rocket will separate from the launch vehicle 10 and then undergo free fall parabolic motion.

[0045] The catapult 10 is designed in the shape of a 120° arc plate to ensure unobstructed separation of the rocket. Each end of the upper surface of the catapult 10 is fixedly connected to a retaining ring 11. The side wall of the retaining ring 11 at the tail end of the catapult 10 protrudes upwards to hold the tail end of the rocket, facilitating the catapult 10's propulsion of the rocket. An electromagnet is fixedly connected inside the retaining ring 11, which securely attaches the rocket to the catapult 10. Drive modules 12 are fixedly connected to the bottom of each end of the catapult 10. The use of two drive modules 12 with slight floating properties ensures more balanced force distribution within the turning track section 2. To reduce the stress caused by electromagnetic constraint on the lifting part of the catapult vehicle 10, when the rocket, which is arranged in three stages, is placed on the catapult vehicle 10, the front retaining ring 11 of the catapult vehicle 10 contacts the large cylinder of the rocket, the middle part is suspended in the air, and the rear small arc contacts the tail retaining ring 11 of the catapult vehicle 10. In order to facilitate the stable placement of the rocket on the catapult vehicle 10, a 45° chamfer is provided at the corner of the upper surface of the retaining ring 11, which fits tightly with the corresponding chamfer of the rocket.

[0046] The vacuum level inside the launch track is less than 2000 Pa.

[0047] All standard parts used in this invention can be purchased commercially, and irregularly shaped parts can be customized according to the description and drawings. The specific connection methods for each part all employ conventional methods such as bolts, rivets, and welding, which are mature technologies in the prior art. The machinery, parts, and equipment all use conventional models in the prior art, and the circuit connections also use conventional connection methods in the prior art, which will not be detailed here. Any content not described in detail in this specification belongs to the prior art known to those skilled in the art.

[0048] In the description of this invention, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. "A plurality of" means two or more, unless otherwise explicitly specified.

[0049] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0050] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0051] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0052] The accompanying drawings of the embodiments disclosed in this invention only involve structures relevant to the embodiments disclosed in this invention. Other structures can be referred to with common designs. Unless otherwise specified, the same embodiment and different embodiments of this invention can be combined with each other.

Claims

1. A spacecraft ejection launch system, characterized in that, include: The launch track consists of a linear acceleration track section (1), a turning track section (2), a rocket car brake separation track section (3), a free flight track section (4), an exit track section (41), and a braking track section (5). The tail end of the turning track section (2) is connected to the rocket car brake separation track section (3). The tail end of the rocket car brake separation track section (3) is bifurcated. One end of the rocket car brake separation track section (3) is connected to the free flight track section (4), and the other end of the rocket car brake separation track section (3) is connected to the braking track section (5). The exit track section (41) is located on the free flight track section (4). A double-sealed gate section is provided at the inlet of the linear acceleration track section (1). The two ends of the double-sealed gate section are respectively provided with a first sealing valve (6) and a second sealing valve (7) fixedly installed on the linear acceleration track section (1). Vacuum pump (8), multiple vacuum pumps (8) are provided, and multiple vacuum pumps (8) are fixedly installed on the launch rail and communicate with the inside of the launch rail; Ultra-fast sealing valve (9) and third sealing valve (13) are provided at the outlet end of the outlet track section (41); The catapult (10) is slidably positioned inside the launch track to carry the spacecraft.

2. The spacecraft ejection launch system according to claim 1, characterized in that: The linear acceleration track section (1) is 55km long, the turning track section (2) has a turning radius of 85km and a length of 26.7km, the rocket brake separation track section (3) is 500m long, and the free flight track section (4) is 3.2km long.

3. The spacecraft ejection launch system according to claim 2, characterized in that: The length of the double-sealed valve section is greater than the length of the spacecraft, that is, the distance between the first sealing valve (6) and the second sealing valve (7) is greater than the length of the spacecraft.

4. The spacecraft ejection launch system according to claim 3, characterized in that: The ultra-fast sealing valve (9) includes an electromagnetic catapult (91) fixedly installed at the end of the exit track section (41), a collision block (92) slidably connected to the electromagnetic catapult (91), a damping brake (93) fixedly connected to the other side of the ultra-fast sealing valve (9), a valve core (94) slidably connected to the middle of the ultra-fast sealing valve (9) to block the exit of the free flight track section (4), and a third sealing valve (13) fixedly connected to the exit track section (41).

5. The spacecraft ejection launch system according to claim 1, characterized in that: The catapult vehicle (10) is arranged in a 120° arc plate shape, and the two ends of the upper surface of the catapult vehicle (10) are respectively fixedly connected with retaining rings (11). The corner of the upper surface of the retaining ring (11) is provided with a 45° chamfer, and the side wall of the retaining ring (11) at the rear end of the catapult vehicle (10) is convex upward.

6. The spacecraft ejection launch system according to claim 5, characterized in that: An electromagnet is fixedly connected inside the retaining ring (11). The catapult (10) attracts the rocket through the electromagnet, and the catapult (10) and the rocket are separated from the electromagnetic attraction at the rocket car brake separation track section (3). A drive module (12) is fixedly connected to the bottom of both ends of the catapult (10).

7. The spacecraft ejection launch system according to claim 1, characterized in that: The vacuum level inside the launch track is less than 2000 Pa.

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