CN116697813A - Annular electromagnetic orbit rocket launching device and method - Google Patents

Abstract

The application provides a ring-shaped electromagnetic track rocket launching device and method, which belong to the technical field of rocket launch. The device includes a ring-shaped electromagnetic track, which is used to provide power; The electromagnetic track provides power to the electromagnetic catapult to accelerate the movement of the electromagnetic catapult in the circular electromagnetic track; the rocket bracket, one end of the rocket bracket is connected with the electromagnetic catapult, and the other end of the rocket bracket carries the unpowered rocket; the electromagnetic track launcher , the electromagnetic track launcher is connected with the exit of the circular electromagnetic track, and the electromagnetic track launcher is provided with an adjustable launch exit. Through the processing scheme of the present application, the structural weight is reduced, the system space and cost are saved, and the launch accuracy and efficiency are improved.

Description

An annular electromagnetic orbital rocket launching device and method

technical field

The present application relates to the technical field of rocket launch, in particular to a circular electromagnetic orbital rocket launch device and method.

Background technique

At present, my country's aerospace industry is developing rapidly, and the rocket design is developing towards the trend of high efficiency, economy and multi-purpose, and the launch of rockets is no longer limited to vertical launch. At present, the main launch methods are vertical launch, air launch by aircraft, etc. At the same time, the cost can be saved by recyclable methods. However, the above-mentioned methods are all limited by the design and manufacture of the engine, requiring advanced manufacturing technology and control level, and the pre-launch preparations are complicated, the cycle is long, and the efficiency is low; the input cost of the power system is high.

Contents of the invention

In view of this, the embodiments of the present application provide a circular electromagnetic orbital rocket launching device and method, which at least partially solve the problems of complex structure and low launching efficiency of the rocket launching device in the prior art.

In the first aspect, the embodiment of the present application provides a circular electromagnetic orbital rocket launcher, including:

An annular electromagnetic track, which is used to provide power;

An electromagnetic catapult, the electromagnetic catapult is arranged in the annular electromagnetic track, and the annular electromagnetic track provides power to the electromagnetic catapult to accelerate the movement of the electromagnetic catapult in the annular electromagnetic track;

A rocket bracket, one end of the rocket bracket is connected to the electromagnetic catapult, and the other end of the rocket bracket carries an unpowered rocket;

An electromagnetic track launcher, the electromagnetic track launcher is connected to the exit of the annular electromagnetic track, and the electromagnetic track launcher is provided with an adjustable-angle launch exit.

According to a specific implementation of the embodiment of the present application, the electromagnetic track launcher includes a plurality of connected track adjustment units, and each track adjustment unit includes an electromagnetic track module, an adjustment mechanism and a lifting platform, and the adjustment mechanism It is arranged on the upper side of the lifting platform, and the electromagnetic track module is arranged on the upper side of the adjustment mechanism, and the height and angle of the electromagnetic track module are adjusted through the adjustment mechanism, thereby adjusting the position of the electromagnetic track transmitter. Angle of the launch exit.

According to a specific implementation of the embodiment of the present application, the adjustment mechanism includes a plurality of adjustment rods, the top ends of the adjustment rods are connected to the electromagnetic track module, and the bottom ends of the adjustment rods are connected to the lifting platform. connection; the number of the adjustment rods is greater than or equal to two, two of the plurality of adjustment rods are respectively located at both ends of the electromagnetic track module along the track direction, and the height of each adjustment rod is independently controlled and adjusted, through Adjusting the height of each of the adjusting rods realizes the adjustment of the height and angle of the electromagnetic track module.

According to a specific implementation of the embodiment of the present application, the annular electromagnetic orbital rocket launching device further includes a locking mechanism, the locking mechanism is connected to the starting point of the annular electromagnetic orbit, and the locking mechanism is used for The electromagnetic catapult is fixed at the starting point of the circular electromagnetic track.

According to a specific implementation of the embodiment of the present application, an electromagnetic ejection system is provided inside the annular electromagnetic track, the electromagnetic ejection system provides power for the electromagnetic ejector, and the ejection load provided by the electromagnetic ejection system is at most 2000kN .

According to a specific implementation of the embodiment of the present application, the connection between the electromagnetic catapult and the annular electromagnetic track is in the form of magnetic levitation.

According to a specific implementation manner of the embodiment of the present application, the shape structure of the unpowered rocket is configured as a cone.

According to a specific implementation of the embodiment of the present application, the annular electromagnetic track is made of high-temperature alloy steel, and a cooling system is provided inside the annular electromagnetic track, and the cooling system makes the annular electromagnetic track The track is maintained at a working temperature below 800°C; the heat-resistant temperature of the high-temperature alloy steel is 1500°C, and the percentage decrease in mechanical properties of the high-temperature alloy steel is less than 50% at a temperature of 800°C.

In the second aspect, the embodiment of the present application also provides a method for launching a circular electromagnetic orbit rocket, using the annular electromagnetic orbit rocket launch device described in any embodiment of the first aspect, including:

Adjust the angle of the launch exit of the electromagnetic rail launcher according to the rocket launch requirements;

Fix the electromagnetic catapult and the rocket bracket at the starting point of the circular electromagnetic track;

The annular electromagnetic track provides power for the electromagnetic catapult, and releases the electromagnetic catapult when the power meets the demand;

According to the acceleration requirement, the circular electromagnetic track continues to provide power for the electromagnetic catapult to accelerate the movement of the electromagnetic catapult;

When the electromagnetic catapult reaches the launch speed, it changes orbit and enters the electromagnetic rail launcher;

When the electromagnetic catapult reaches the launch exit, the unpowered rocket is separated from the rocket bracket, and the unpowered rocket maintains the launch speed and launches into the sky.

According to a specific implementation manner of the embodiment of the present application, the method further includes:

After the unpowered rocket is separated from the rocket bracket, the electromagnetic catapult and the rocket bracket are decelerated and braked by the electromagnetic track launcher, and return to the starting point of the circular electromagnetic track when the speed is reduced to the return speed place.

Beneficial effect

The annular electromagnetic rail rocket launching device and method in the embodiment of the present application launch a non-powered rocket by setting an annular electromagnetic orbit with an adjustable launch exit angle, which is different from the research direction of the engine recovery technology. The engine is directly discarded in the rocket design. While saving R&D and manufacturing costs, the structural weight is significantly reduced. The circular electromagnetic track can adapt to the acceleration distance of various loads, and there is no need to design another track, which saves the space and cost of the system. The de-orbit speed and angle of the rocket can be adjusted, which can meet the mission requirements of various ranges and has high precision. The electromagnetic ejection has a fast response speed and a short preparation period, which can greatly shorten the interval between multiple rocket launches.

Description of drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the accompanying drawings that need to be used in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. Those of ordinary skill in the art can also obtain other drawings based on these drawings without any creative effort.

Fig. 1 is a structural diagram of a circular electromagnetic orbital rocket launcher according to an embodiment of the present invention;

Fig. 2 is a structural diagram of an electromagnetic track launcher according to an embodiment of the present invention.

In the figure: 1, electromagnetic track launcher; 1a, electromagnetic track module; 1b, adjustment mechanism; 1c, lifting platform; 2, circular electromagnetic track; 3, electromagnetic catapult; 4, rocket bracket; 5, unpowered rocket.

Detailed ways

Embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

Embodiments of the present application are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of this application, not all of them. The present application can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.

It is noted that the following describes various aspects of the embodiments that are within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is illustrative only. Based on the present application one skilled in the art should appreciate that an aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, any number of the aspects set forth herein can be used to implement an apparatus and/or practice a method. In addition, such an apparatus may be implemented and/or such a method practiced using other structure and/or functionality than one or more of the aspects set forth herein.

It should also be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic idea of the application, and only the components related to the application are shown in the drawings rather than the number, shape and number of components in actual implementation. Dimensional drawing, the type, quantity and proportion of each component can be changed arbitrarily during actual implementation, and the component layout type may also be more complicated.

Additionally, in the following description, specific details are provided to facilitate a thorough understanding of examples. However, it will be understood by those skilled in the art that the described aspects may be practiced without these specific details.

In a first aspect, an embodiment of the present application provides a circular electromagnetic orbital rocket launcher, which will be described in detail below with reference to FIG. 1 and FIG. 2 .

In one embodiment, the annular electromagnetic orbital rocket launcher includes the following structures:

Ring-shaped electromagnetic track 2, which is used to provide power;

Electromagnetic catapult 3, described electromagnetic catapult 3 is arranged in described annular electromagnetic track 2, and described annular electromagnetic track 2 provides power to described electromagnetic catapult 3 to make described electromagnetic catapult 3 in described annular electromagnetic track 2 internal acceleration movement;

A rocket bracket 4, one end of the rocket bracket 4 is connected to the electromagnetic catapult 3, and the other end of the rocket bracket 4 carries an unpowered rocket 5;

An electromagnetic track launcher 1, the electromagnetic track launcher 1 is connected to the exit of the annular electromagnetic track 2, and the electromagnetic track launcher 1 is provided with an adjustable launch outlet.

The ring-shaped electromagnetic rail rocket launching device in the above-mentioned embodiment is based on the electromagnetic ejection technology, and a ring-shaped electromagnetic rail 2 with an adjustable launching outlet angle is designed for launching the unpowered rocket 5, and the unpowered rocket 5 is installed on the rocket bracket 4 , and is integrally installed on the electromagnetic catapult 3 located in the annular electromagnetic track 2 . The ring-shaped electromagnetic track 2 provides a power source for the electromagnetic catapult 3, which can continuously accelerate the electromagnetic catapult 3, the rocket carriage 4, and the unpowered rocket 5 to the required launch speed, and the launch outlet of the adjustable electromagnetic track launcher 1 Adjust to the required launch inclination, when the electromagnetic catapult 3 reaches the launch speed and meets the launching conditions, carry the rocket bracket 4, the unpowered rocket 5 to change orbits and enter the adjustable electromagnetic orbit launcher 1, the unpowered rocket 5 and the rocket bracket 4. Separation at the launch exit to realize launch into space.

The requirements for the acceleration time and distance of the electromagnetic catapult 3 can be met by setting the circular electromagnetic track 2, and can adapt to the requirements of various launch tasks, without the need to design another track, which saves space and cost of the system.

By adopting electromagnetic ejection technology, electromagnetic ejection has the advantages of fast response speed, short preparation period, and can greatly shorten the interval between multiple rocket launches.

In one embodiment, the electromagnetic track launcher 1 includes a plurality of connected track adjustment units, each track adjustment unit includes an electromagnetic track module 1a, an adjustment mechanism 1b and a lifting platform 1c, and the adjustment mechanism 1b is set On the upper side of the lifting platform 1c, the electromagnetic track module 1a is arranged on the upper side of the adjustment mechanism 1b, and the height and angle of the electromagnetic track module 1a are adjusted through the adjustment mechanism 1b, and then the electromagnetic track module 1a is adjusted. The angle of the launch exit of Orbital Launcher 1.

In this embodiment, each track adjustment unit is independently controlled, and each adjacent electromagnetic track module 1a joins to form the track of the electromagnetic track launcher 1, and the height and height of each electromagnetic track module 1a are adjusted by the adjustment mechanism 1b. The angle is adjusted, and with the change of each electromagnetic track module 1a, the angle of the launch exit is finally adjusted to meet the launch requirements. By setting the rocket launching device whose off-orbit speed and angle can be adjusted, it can meet the mission requirements of various ranges and has high precision at the same time.

Further, the adjustment mechanism 1b includes a plurality of adjustment rods, the top ends of the adjustment rods are connected to the electromagnetic track module 1a, and the bottom ends of the adjustment rods are connected to the lifting platform 1c; the adjustment rods The number is greater than or equal to two, two of the plurality of adjustment rods are respectively located at both ends of the electromagnetic track module 1a along the track direction, and the height of each adjustment rod is individually controlled and adjusted, by adjusting each of the The height of the adjusting rod realizes the adjustment of the height and angle of the electromagnetic track module 1a.

By setting a plurality of adjustment rods under each electromagnetic track module 1a, the height and inclination angle of the electromagnetic track module 1a can be precisely controlled. The adjustment rod below the module 1a is stretched to different lengths, so that the electromagnetic track module 1a can be adjusted to a tilted state, thereby adjusting the launch angle of the track launch outlet.

In one embodiment, the rocket launching device of the circular electromagnetic track also includes a locking mechanism, the locking mechanism is connected with the starting point of the circular electromagnetic track 2, and the locking mechanism is used for The electromagnetic ejector 3 is fixed at the starting point. The electromagnetic catapult 3 is fixed with the rocket bracket 4, and the electromagnetic catapult 3 is fixed by the locking mechanism at the starting point of the annular electromagnetic track 2. The annular electromagnetic track 2 provides power to the electromagnetic catapult 3, and is released by the locking mechanism when the power meets the demand. Electromagnetic catapult 3 in the ring electromagnetic track 2.

In one embodiment, an electromagnetic ejection system is provided inside the annular electromagnetic track 2, and the electromagnetic ejection system provides power for the electromagnetic ejector 3, and the ejection load provided by the electromagnetic ejection system is a maximum of 2000 kN. In this embodiment, the unpowered rocket 5 can be launched. Unlike the research direction of the engine recovery technology, the engine is directly discarded in the rocket design, which saves R&D and manufacturing costs and significantly reduces the structural weight.

In one embodiment, the connection between the electromagnetic catapult 3 and the annular electromagnetic track 2 is in the form of magnetic levitation. By setting the magnetic levitation form, the frictional resistance can be effectively reduced.

In one embodiment, the external structure of the unpowered rocket 5 is configured as a cone. Since the rocket is an unpowered rocket 5, the shape is set as a slender cone, which can reduce air resistance as much as possible.

In one embodiment, the annular electromagnetic track 2 is made of high-temperature alloy steel, and a cooling system is arranged inside the annular electromagnetic track 2, and the cooling system maintains the annular electromagnetic track 2 at a temperature of Working temperature below 800°C; the heat-resistant temperature of the high-temperature alloy steel is 1500°C, and when the temperature is 800°C, the decrease percentage of the mechanical properties of the high-temperature alloy steel is less than 50%. High-temperature alloy steel materials have good mechanical properties and high-temperature resistance.

In the second aspect, the embodiment of the present application also provides a method for launching a circular electromagnetic orbital rocket, using the annular electromagnetic orbital rocket launcher described in any embodiment of the first aspect, the method comprising:

Step 1, adjust the angle of the launch outlet of the electromagnetic orbit launcher 1 according to the rocket launch requirement;

Step 2, fixing the electromagnetic catapult 3 and the rocket bracket 4 at the starting point of the annular electromagnetic track 2;

Step 3, the annular electromagnetic track 2 provides power for the electromagnetic catapult 3, and releases the electromagnetic catapult 3 when the power meets the demand;

Step 4. According to the acceleration requirement, the annular electromagnetic track 2 continues to provide power for the electromagnetic catapult 3 to accelerate the movement of the electromagnetic catapult 3;

Step 5, when the electromagnetic catapult 3 reaches the launch speed, change orbit and enter the electromagnetic rail launcher 1;

Step 6. When the electromagnetic catapult 3 reaches the launch exit, the unpowered rocket 5 is separated from the rocket bracket 4, and the unpowered rocket 5 is launched into the air while maintaining the launch speed.

Further, the method also includes:

After the unpowered rocket 5 is separated from the rocket bracket 4, the electromagnetic catapult 3 and the rocket bracket 4 are decelerated and braked by the electromagnetic rail launcher 1, and return to the At the starting point of the circular electromagnetic track 2.

Let's take the following as an example where the goal is to vertically launch a 1-ton unpowered rocket 5 at a speed of 10 times the speed of sound.

The ring-shaped electromagnetic track 2 is made of high-temperature alloy steel, which has good mechanical properties and high-temperature resistance. Inside the track is an electromagnetic ejection system, which provides power for the electromagnetic ejector 3. The ejection load can be adjusted in real time according to the acceleration requirement, and the maximum power can reach 2000kN.

The electromagnetic catapult 3 is powered by the circular electromagnetic track 2 to provide stable acceleration for the rocket carrier 4 and the unpowered rocket 5 . Affected by factors such as frictional resistance, aerodynamic resistance, and gravity, the maximum power required is 892kN, and the initial power is 588kN. The acceleration distance of circular electromagnetic track 2 needs to be 11km, and the exit angle is adjusted to be perpendicular to the ground. The electromagnetic catapult 3 is fixed with the rocket bracket 4, and the electromagnetic catapult 3 is fixed by the locking mechanism at the starting point. After the power is reached, the electromagnetic catapult 3 is released, and according to the acceleration requirement, the circular electromagnetic track 2 continues to provide power to the electromagnetic catapult 3 After reaching the launch speed, the orbit changes and enters the electromagnetic orbit launcher 1, then the unpowered rocket 5 is separated from the rocket bracket 4, and the rocket body maintains the launch speed and is launched into the sky. The electromagnetic catapult 3 and the rocket carriage 4 are decelerated and braked by the electromagnetic rail launcher 1 .

The circular electromagnetic track 2 can meet the requirements for the acceleration time and distance of the electromagnetic catapult 3, and can adapt to the requirements of various launch tasks. After the electromagnetic catapult 3 and the rocket bracket 4 carry the unpowered rocket 5 into the electromagnetic orbit launcher 1 whose exit angle has been adjusted in advance, the angle changes with the orbit. The unpowered rocket 5 is separated from the rocket bracket 4 when it arrives at the launch exit, and the rocket body still maintains the launch speed and angle. The electromagnetic catapult 3 and the rocket bracket 4 are decelerated and braked by the orbital launcher, and return to the starting point after the speed drops to 0.

In the embodiment provided by the present invention, the unpowered rocket is launched by setting a ring-shaped electromagnetic track with an adjustable launch exit angle, which is different from the research direction of the engine recovery technology. The engine is directly discarded in the rocket design, which saves R&D and manufacturing costs and significantly reduces structural weight. The circular electromagnetic track can adapt to the acceleration distance of various loads, and there is no need to design another track, which saves the space and cost of the system. The de-orbit speed and angle of the rocket can be adjusted, which can meet the mission requirements of various ranges and has high precision. The electromagnetic ejection has a fast response speed and a short preparation period, which can greatly shorten the interval between multiple rocket launches.

The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the application. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims (10)

1. A ring-shaped electromagnetic orbital rocket launching device is characterized in that, comprising: An annular electromagnetic track (2), which is used to provide power; Electromagnetic catapult (3), described electromagnetic catapult (3) is arranged in described circular electromagnetic track (2), and described circular electromagnetic track (2) provides power to described electromagnetic catapult (3) to make described electromagnetic The catapult (3) accelerates to move in the said annular electromagnetic track (2); A rocket bracket (4), one end of the rocket bracket (4) is connected to the electromagnetic catapult (3), and the other end of the rocket bracket (4) carries an unpowered rocket (5); An electromagnetic track launcher (1), the electromagnetic track launcher (1) is connected to the exit of the annular electromagnetic track (2), and the electromagnetic track launcher (1) is provided with an angle-adjustable launch exit. 2. ring-shaped electromagnetic rail rocket launcher according to claim 1, is characterized in that, described electromagnetic rail launcher (1) comprises a plurality of connected rail adjustment units, and each described rail adjustment unit comprises electromagnetic rail module (1a), an adjustment mechanism (1b) and a lifting platform (1c), the adjustment mechanism (1b) is arranged on the upper side of the lifting platform (1c), and the electromagnetic track module (1a) is arranged on the adjustment mechanism ( 1b) On the upper side, the height and angle of the electromagnetic track module (1a) are adjusted through the adjustment mechanism (1b), and then the angle of the launch outlet of the electromagnetic track launcher (1) is adjusted. 3. annular electromagnetic rail rocket launcher according to claim 2, is characterized in that, described regulating mechanism (1b) comprises a plurality of regulating rods, and the top of described regulating rod is connected with described electromagnetic rail module (1a) , the bottom end of the adjustment rod is connected to the lifting platform (1c); the number of the adjustment rods is greater than or equal to two, and two of the plurality of adjustment rods are respectively located in the electromagnetic track module (1a) At both ends along the track direction, the height of each of the adjusting rods is independently controlled and adjusted, and the height and angle of the electromagnetic track module (1a) can be adjusted by adjusting the height of each of the adjusting rods. 4. annular electromagnetic orbit rocket launcher according to claim 1, is characterized in that, described annular electromagnetic orbit rocket launcher also comprises locking mechanism, and described locking mechanism is in phase with the starting point of described annular electromagnetic orbit (2). connected, the locking mechanism is used to fix the electromagnetic ejector (3) at the starting point of the annular electromagnetic track (2). 5. the annular electromagnetic orbit rocket launcher according to claim 1, is characterized in that, described annular electromagnetic orbit (2) inside is provided with electromagnetic ejection system, and described electromagnetic ejection system provides for described electromagnetic ejector (3) Power, the maximum ejection load provided by the electromagnetic ejection system is 2000kN. 6. The annular electromagnetic rail rocket launcher according to any one of claims 1-5, characterized in that, the connection mode between the electromagnetic catapult (3) and the annular electromagnetic rail (2) is a magnetic levitation form . 7. According to any one of claims 1-5, the annular electromagnetic orbital rocket launcher is characterized in that, the external structure of the unpowered rocket (5) is set as a cone. 8. according to any one of claim 1-5 ring-shaped electromagnetic track rocket launcher, it is characterized in that, described ring-shaped electromagnetic track (2) adopts high-temperature alloy steel material, and described ring-shaped electromagnetic track (2) is provided with cooling system , the cooling system maintains the annular electromagnetic track (2) at a working temperature below 800°C through the heat exchange of the internal liquid medium; the heat-resistant temperature of the high-temperature alloy steel is 1500°C, and the temperature is 800°C The decrease percentage of the mechanical properties of the high-temperature alloy steel is less than 50%. 9. A method for launching a circular electromagnetic orbit rocket, adopting the annular electromagnetic orbit rocket launcher as claimed in any one of claims 1-8, wherein the method comprises: Adjust the angle of the launch outlet of the electromagnetic rail launcher (1) according to the rocket launch requirement; Fix the electromagnetic catapult (3) and the rocket bracket (4) at the starting point of the circular electromagnetic track (2); The annular electromagnetic track (2) provides power for the electromagnetic catapult (3), and releases the electromagnetic catapult (3) when the power meets the demand; According to the acceleration requirement, the annular electromagnetic track (2) continues to provide power for the electromagnetic catapult (3) to accelerate the movement of the electromagnetic catapult (3); When the electromagnetic catapult (3) reaches the launch speed, it changes orbit and enters the electromagnetic rail launcher (1); When the electromagnetic catapult (3) arrives at the launch exit, the unpowered rocket (5) is separated from the rocket bracket (4), and the unpowered rocket (5) is launched into the air maintaining the launch speed. 10. The ring-shaped electromagnetic orbital rocket launch method according to claim 9, wherein the method further comprises: After the unpowered rocket (5) is separated from the rocket bracket (4), the electromagnetic catapult (3) and the rocket bracket (4) are decelerated and braked by the electromagnetic rail launcher (1) , return to the starting point of the circular electromagnetic track (2) after the speed is reduced to the return speed.