Rotating launch device and method capable of continuously launching satellites

Abstract

The present application relates to a rotary launch device and method capable of continuously launching satellites. The device comprises a base mechanism, a launch cabin, a rotary support mechanism, a plurality of release mechanisms, a loading mechanism and an accelerator. The base mechanism comprises a base and a connecting shaft. The launch cabin comprises a launch cabin and a launch tube connected to the launch cabin, and the launch cabin is rotatably connected to the connecting shaft. The rotary support mechanism comprises a plurality of support arms arranged radially in a uniform array along a circumference with a rotation point as the center. A plurality of release devices are respectively arranged at the tail end of a support arm, and are used to lock / unlock the corresponding carrier at the tail end of the support arm. The loading device is located in the launch cabin and is used to load the carriers to the tail ends of the plurality of support arms. The accelerator is fixed on the connecting shaft and is used to drive the rotary support mechanism to rotate. The embodiment of the present application provides a rotary launch device capable of continuously launching satellites. The carrier carrying the satellite is launched to a predetermined orbit by using centrifugal force. The device is reusable and has low launch cost.

Description

Technical Field

[0001] The present application relates to the field of ground satellite launch technology, and in particular to a rotating launch device and method capable of continuously launching satellites. Background Art

[0002] Traditional launch methods for carriers are mainly divided into cold launch and hot launch. Hot launch refers to the launch method in which the carrier relies on the thrust generated by its own engine to fly away from the launch device, which is easy to cause ablation and contamination to the launch platform; the traditional cold launch method mainly uses auxiliary power to eject the missile from the launch tube, and then ignites the engine when the missile reaches a certain height.

[0003] Both traditional hot launch and cold launch require high-thrust engines and large amounts of fuel, resulting in large size and mass of traditional satellite launch vehicles. The combustion of large amounts of fuel and the separation of multi-stage engines cause serious environmental pollution. Traditional launch vehicles have large energy losses, are difficult to reuse, and have high launch costs.

[0004] Low-cost, fast-response satellite launch technology has always been the goal pursued by commercial aerospace. In particular, low-orbit small satellites and micro-nano satellites have significant characteristics such as low cost, short development cycle, and rapid technological updates. They are of high value in various civil fields and military applications. Summary of the invention

[0005] The embodiments of the present application provide a rotating launch device and method that can continuously launch satellites, so as to solve the technical problems in the related technology that both traditional satellite hot launch and cold launch require large thrust engines and a large amount of fuel, resulting in large size and mass of traditional satellite launch vehicles, large combustion of large amounts of fuel and separation of multi-stage engines, high environmental pollution, large energy loss, high difficulty in reusing the vehicle, and high cost of launching the vehicle.

[0006] In a first aspect, the present application provides a rotating launch device capable of continuously launching satellites, comprising:

[0007] A base mechanism, comprising a base and a connecting shaft fixed to the base, wherein the connection between the base and the connecting shaft is a rotation point;

[0008] A launching cabin, comprising a rotating cabin and a launching tube connected to the rotating cabin, wherein the rotating cabin is rotatably connected to the connecting shaft;

[0009] The rotating support mechanism comprises a plurality of support arms which are arranged radially in a uniform array along the circumference with the rotating point as the center;

[0010] A plurality of release devices, each correspondingly disposed at the tail end of a support arm, for locking / unlocking the carrier at the corresponding tail end of the support arm;

[0011] A loading device, located in the launch cabin, for loading the tail ends of the plurality of support arms with carriers;

[0012] An accelerator is fixed on the connecting shaft and is used to drive the rotating support mechanism to rotate.

[0013] In some embodiments, an environmental control device is also included, and the environmental control device is used to adjust the temperature, pressure and humidity in the launch cabin.

[0014] In some embodiments, the environmental control equipment includes an air conditioning system, an air compression system, and an environmental monitoring system.

[0015] In some embodiments, the environmental monitoring system includes a temperature and humidity sensor and a pressure sensor.

[0016] In some embodiments, the loading device includes a transmission chain, a carrier storage location and a chain power system, the transmission chain is equipped with a plurality of carrier storage locations, the transmission chain is transmission-connected to the chain power system, and the chain power system is disposed at the bottom of the launch cabin.

[0017] In some embodiments, the accelerator includes an electric drive system and a speed controller, the rotation support mechanism is transmission-connected to the electric drive system, and the speed controller is used to control the rotation speed of the rotation support mechanism.

[0018] In some embodiments, the accelerator includes a diesel generator and an energy storage system, and the electric drive system is driven by the diesel generator and the energy storage system.

[0019] In some embodiments, the carrier includes a protective shell and an engine and a satellite disposed therein, wherein the satellite is transmission-connected to the engine.

[0020] In a second aspect, the present application provides a rotational launch method capable of continuously launching satellites, comprising the following steps:

[0021] The loading device at the bottom of the launch cabin is used to automatically load the carriers at the tail ends of multiple support arms;

[0022] Control the vacuum degree in the launch cabin to meet the preset vacuum degree standard;

[0023] The electric drive system of the accelerator is controlled to start, driving the rotating support mechanism and the carrier to rotate;

[0024] Control the carriers at the tail ends of multiple support arms to launch in sequence.

[0025] In some embodiments, the step of controlling the carriers at the tail ends of the multiple support arms to be launched sequentially specifically comprises the following steps:

[0026] The carriers at the tail ends of the multiple support arms are controlled to launch in sequence according to a diagonal launch strategy according to the distribution rule of the multiple carriers.

[0027] The beneficial effects of the technical solution provided by this application include:

[0028] An embodiment of the present application provides a rotating launch device that can continuously launch satellites. The carrier is loaded on the tail end of a plurality of support arms that are evenly spaced radially. The acceleration drives the rotating support mechanism to rotate, and the centrifugal force is used to launch the carrier carrying the satellite into a predetermined orbit. The device is reusable and has a low launch cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0030] Figure 1 A schematic diagram of the structure of a rotating launch device capable of continuously launching satellites provided by an embodiment of the present invention;

[0031] Figure 2 A schematic diagram of the structure of a loading device for a rotary launching device provided by an embodiment of the present invention;

[0032] Figure 3 A functional module block diagram of an integrated control system for a rotating launch device provided by an embodiment of the present invention;

[0033] Figure 4 A schematic structural diagram of a carrier of a rotary launch device provided in an embodiment of the present invention.

[0034] In the figure: 1. base; 2. launch cabin; 3. rotating support mechanism; 4. loading device; 5. accelerator; 6. release device; 7. environmental control equipment; 8. carrier; 9. transmission chain; 10. carrier storage position; 11. carrier loading position; 12. chain power system; 13. integrated controller; 14. speed controller; 15. brake controller; 16. electric drive system; 17. brake system; 18. diesel generator; 19. energy storage system; 20. speed monitoring system; 21. protective shell; 22. engine; 23. satellite; 24. air conditioning system; 25. air compression system; 26. environmental monitoring system; 27. release system controller. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0036] The embodiment of the present application provides a rotating launch device that can continuously launch satellites 23, which can solve the technical problems of large launch energy loss of traditional carriers 8, high difficulty in reusing carriers 8, high launch costs, and serious environmental pollution.

[0037] First, please refer to Figure 1 The present application provides a rotary launch device capable of continuously launching satellites 23, comprising a base mechanism, a launch cabin 2, a rotary support mechanism 3, a plurality of release devices 6, a loading device 4 and an accelerator 5. The base mechanism comprises a base 1 and a connecting shaft fixed to the base 1. The base 1 is used to support the entire rotary launch device capable of continuously launching satellites 23, and is an installation platform for the rotary launch device. The exit direction of the carrier 8 can be adjusted by rotating and pitching the base 1. The connection between the base 1 and the connecting shaft is a rotation point. The launch cabin 2 comprises a rotating cabin and a launching tube connected with the rotating cabin, wherein the rotating cabin is rotatably connected to the connecting shaft; a rotating support mechanism 3 comprises a plurality of supporting arms which are arranged radially in a uniform array along a circumference with a rotating point as the center; a plurality of releasing devices 6 are respectively arranged at the tail end of a supporting arm, and are used to lock / unlock the carrier 8 at the tail end of the corresponding supporting arm; a loading device 4 is located in the launching cabin 2, and is used to load the carrier 8 into the tail ends of the plurality of supporting arms; an accelerator 5 is fixed on the connecting shaft, and is used to drive the rotating support mechanism 3 to rotate.

[0038] The rotary launch device provided in the present application can continuously launch satellites 23. The rotary support mechanism 3 is driven to rotate by acceleration. The carriers 8 at the tail ends of multiple support arms are released in sequence by the release device 6. The carriers 8 carrying the satellites 23 are launched into a predetermined orbit under the action of centrifugal force. The launch device is reusable and has a low launch cost.

[0039] In one embodiment, the plurality of support arms are radially distributed around the rotation center.

[0040] In one embodiment, the plurality of support arms are radially arranged around the rotation center and are evenly arranged along the circumference, that is, the angles between two adjacent support arms are the same.

[0041] In one embodiment, a plurality of support arms intersect and converge into a connection disk, and the accelerator 5 is fixed on the connection disk, and drives the connection disk to rotate, thereby driving the plurality of support arms to rotate.

[0042] In one embodiment, the launch cabin 2 is a circular cabin, and the launch tube is located in the tangential direction of the circular cabin, so that the carrier 8 located at the tail end of multiple support arms is launched along the tangential direction under the action of centrifugal force and smoothly enters the predetermined orbit.

[0043] In one embodiment, the rotating cabin is a circular cabin, and the launching tube is located in the vertical tangent direction of the circular cabin, so that the carrier 8 located at the tail end of multiple support arms is launched along the vertical tangent direction under the action of centrifugal force and smoothly enters the predetermined orbit.

[0044] In one embodiment, a launch tube top cover is provided at the muzzle of the launch tube, and the launch tube top cover is broken by the carrier 8 during launching, and the top cover can be quickly and automatically replaced after completing a round of launching.

[0045] In one embodiment, the launch cabin 2 is a circular cabin, the launch tube is located in the vertical tangent direction of the circular cabin, the carrier 8 is firmly and reliably locked to the tail end of the corresponding support arm through the release device 6, and the accelerator 5 drives the rotating support mechanism 3 to rotate. When the carrier 8 moves to a direction consistent with the launch tube under the rotation of its support arm, the release device 6 unlocks the carrier 8 on the corresponding support arm to achieve rapid separation and release of the carrier 8 with high precision at the millisecond level, so that the carrier 8 is launched along the vertical tangent direction under the action of centrifugal force and smoothly enters the predetermined orbit.

[0046] In one embodiment, when the carrier 8 is locked to the corresponding tail end of the support arm by the release device 6, the length extension direction of the carrier 8 is perpendicular to the length extension direction of the support arm.

[0047] In one embodiment, when the carrier 8 is locked to the corresponding tail end of the support arm by the release device 6, the length extension direction of the carrier 8 is perpendicular to the length extension direction of the support arm and the bottom surface is flush with the tail end of the support arm.

[0048] In one embodiment, the rotating launch device capable of continuously launching satellites 23 provided in the present application also includes an environmental control device 7, which is used to regulate the temperature, pressure and humidity in the launch cabin 2 to provide a suitable storage environment for the carrier 8.

[0049] In one embodiment, the environmental control equipment 7 includes an air conditioning system 24, an air compression system 25 and an environmental monitoring system 26. The environmental monitoring system 26 includes a temperature and humidity sensor and a pressure sensor, which is used to monitor the environmental status in the launch cabin 2. The information obtained by the temperature and humidity sensor is collected, calculated and processed in real time, and the temperature and humidity values ​​in the launch cabin 2 are obtained to determine whether to start or stop the air conditioning in the launch cabin 2 to achieve heating, cooling or dehumidification control in the launch cabin 2. The temperature and humidity in the launch cabin 2 cannot be ultimately controlled within a specified range. In order to reduce the energy loss of the rotating support mechanism 3 and multiple carriers 8 during the rotation process, the launch cabin 2 needs to be continuously evacuated before the launch of the carrier 8, during the rotation acceleration process, and after the launch is completed, and the atmospheric pressure in the launch cabin 2 is monitored by a pressure sensor to evaluate the vacuum degree in the launch cabin 2, effectively reducing the launch cost and energy loss of the carrier 8.

[0050] In one embodiment, there are multiple environmental control devices 7 fixed on the inner wall of the rotating cabin so as not to interfere with the rotational movement of the support arm and the carrier 8 .

[0051] In one embodiment, please refer to Figure 2 The loading device 4 includes a transmission chain 9, a carrier storage part 10 and a chain power system 12. The transmission chain 9 is equipped with a plurality of carrier storage parts 10. The transmission chain 9 is in transmission connection with the chain power system 12. The chain power system 12 is arranged at the bottom of the launch cabin 2. The chain power system 12 can be realized as a drive motor. The loading device 4 is placed at the bottom of the launch cabin 2. The main body of the loading device 4 is an automatic loading structure of a chain. Through rotation, the chain carries a plurality of carriers 8. When loading to the arm of the rotating support mechanism 3, automatic continuous loading can be realized. At the same time, the loading device 4 has an entrance for externally filling ammunition. After completing a round of firing, the chain carrier 8 can continue to be replenished.

[0052] In one embodiment, when the carrier storage part 10 rotates to the top, it becomes the carrier loading part 11. When loading the carrier 8, the support arm of the rotating support mechanism 3 rotates to the carrier loading part 11, and the release device 6 at the tail of the support arm grabs and locks the carrier 8 to complete the loading of one support arm. The chain power system 12 works synchronously with the accelerator 5, and the transmission chain 9 and the rotating support mechanism 3 rotate at the same time to complete the alignment of the next support arm with the loading position, and load the second carrier 8. By rotating, 6 carriers 8 can be automatically and quickly loaded. At the same time, the loading device 4 has an external ammunition filling entrance, and the carrier 8 can be replenished after completing a round of firing.

[0053] In one embodiment, the rotating support mechanism 3 has six support arms arranged evenly around a circumference, and each support arm can carry one carrier 8 at a time.

[0054] In one embodiment, the release device 6 is placed at the rear of the support arm. During the loading process of the carrier 8, the electric actuator on the release device 6 can be reliably connected and locked with the carrier 8, and the loading device 4 is unlocked at the same time, and the loading of the carrier 8 is completed. During the acceleration process, the release device 6 firmly and reliably fixes the carrier 8. After the acceleration is completed, the electric actuator is quickly unlocked, and the carrier 8 is quickly released with high precision at the millisecond level.

[0055] In one embodiment, the accelerator 5 includes an electric drive system, which drives the rotating support mechanism 3 to rotate to provide rotational acceleration for the carrier 8, thereby achieving the exit speed of the carrier 8 from the launch tube.

[0056] In one embodiment, the accelerator 5 includes an electric drive system and a speed controller 14, and the speed controller 14 is communicatively connected to the electric drive system. The speed controller 14 is used to adjust the speed at which the electric drive system drives the rotating support mechanism 3 to rotate, thereby adjusting the ejection speed of the carrier 8, that is, the launching speed.

[0057] In one embodiment, the accelerator 5 includes an electric drive system, a speed controller 14, and a braking and energy recovery system. The speed controller 14 and the braking and energy recovery system are electrically connected to the electric drive system. The braking and energy recovery system is used to quickly brake the rotating support mechanism 3 and recover energy after the carrier 8 is launched.

[0058] In one embodiment, the accelerator 5 includes an electric drive system, a speed controller 14, a braking and energy recovery system and an energy storage system 19. The braking and energy recovery system is electrically connected to the energy storage system 19. The energy storage system 19 is used to store energy recovered by the braking and energy recovery system. The energy storage system 19 is connected to the electric drive system, and the electric drive system is driven by the energy storage system 19 to fully utilize the recycled energy.

[0059] In one embodiment, the accelerator 5 includes an electric drive system, a speed controller 14 , a braking and energy recovery system, an energy storage system 19 and a diesel generator 18 , and the electric drive system is driven by the diesel generator 18 and the energy storage system 19 .

[0060] In one embodiment, please refer to Figure 3The accelerator 5 includes an integrated controller 13, a speed controller 14, a brake controller 15, an electric drive system 16, a brake system 17, a diesel generator 18, an energy storage system 19, and a speed monitoring system 20. The accelerator 5 uses the electric drive system 16 to drive the rotating support to provide rotational acceleration for the carrier 8, so as to provide a barrel discharge speed that meets the requirements. The electric drive system 16 is driven by the diesel generator 18 and the energy storage system 19. The accelerator 5 has a speed controller 14, which can adjust the loading speed and the rotational launch speed. The rotational speed of the support device is fed back through the speed monitoring system 20 to achieve precise closed-loop control of the speed. The accelerator 5 has a braking energy recovery system, which can quickly brake and recover energy after the launch is completed, and store the recovery capacity in the energy storage system 19 to improve energy utilization.

[0061] In one embodiment, please refer to Figure 4 The carrier 8 includes a protective shell 21 and an engine 22 and a satellite 23 arranged therein. The satellite 23 is connected to the engine 22 in a transmission manner. The protective shell 21 is used to prevent the engine 22 and the satellite 23 from being damaged by centrifugal force. After the carrier 8 leaves the tube at a certain height, the protective shell 21 separates automatically. The engine 22 is ignited in the active flight segment to push the satellite 23 to continue to rise and adjust the attitude of the satellite 23. After the satellite 23 is sent into a predetermined orbit, the engine 22 separates from the satellite 23.

[0062] The embodiment of the present invention provides a rotary launch device capable of continuously launching satellites 23. The rotary launch device can realize a tube exit speed of a carrier 8 carrying satellites 23 of not less than Mach 10, and use an environmental control system to provide a suitable rotary launch environment; use an accelerator 5 to accelerate the rotary support mechanism 3, and use a braking energy recovery system to improve energy utilization; use a bullet chain loading device 4 to quickly, automatically, and continuously complete the loading of the carrier 8; use a release device 6 to reliably fix the carrier 8 during rotation, and release it quickly and accurately during launch; use a carrier 8 protective shell 21 to protect the satellite 23, and use an engine 22 to send the satellite 23 to a predetermined orbit. The rotary launch device of the present invention can quickly launch multiple carriers 8, and the launch device is safe, reliable, reusable, has high energy utilization, and low launch cost.

[0063] In a second aspect, the present application provides a rotational launch method capable of continuously launching satellites 23, comprising the following steps:

[0064] The loading device 4 at the bottom of the launch cabin 2 is used to automatically load the carriers 8 at the tail ends of the multiple support arms;

[0065] Controlling the vacuum degree in the launch cabin 2 to meet the preset vacuum degree standard;

[0066] The electric drive system 16 controlling the accelerator 5 is turned on to drive the rotating support mechanism 3 and the carrier 8 to rotate;

[0067] The carriers 8 at the tail ends of the multiple support arms are controlled to be launched in sequence.

[0068] In one embodiment, the present application provides a rotational launch method capable of continuously launching satellites 23, comprising the following steps:

[0069] The first step is to load the carriers 8: the loading device 4 at the bottom of the launch cabin 2 is used to automatically load the six carriers 8;

[0070] In the second step, the environmental control device 7 starts to adjust the vacuum degree in the launch cabin 2 synchronously to provide a vacuum environment for rotation;

[0071] In the third step, the electric drive system 16 of the accelerator 5 is turned on to drive the rotating support mechanism 3 and the carrier 8 to rotate at high speed;

[0072] Step 4: When the rotation speed of the rotating support mechanism 3 reaches the required speed, the release device 6 releases the carrier 8 rapidly and continuously with high precision at the millisecond level;

[0073] Step 5: The carrier 8 breaks through the top cover of the launch cabin 2 and starts to fly at high speed. After reaching a predetermined height, the protective shell 21 separates itself.

[0074] In the sixth step, the engine 22 is ignited to provide boost, and at the same time the attitude of the carrier 8 is adjusted to send the satellite 23 to the predetermined orbit and then separate, thus completing a round of launch.

[0075] In one embodiment, the step of controlling the carriers 8 at the tail ends of the multiple support arms to be launched sequentially specifically comprises the following steps:

[0076] The carriers 8 at the tail ends of multiple support arms are controlled to execute a diagonal launch strategy and launch in sequence according to the distribution pattern of the multiple carriers 8. When releasing the carriers 8, a diagonal release scheme is adopted, and the release sequence is No. 1, No. 4, No. 2, No. 5, No. 3, and No. 6 (6 carriers 8 are arranged clockwise). This can improve the release stability of the launch system and the launch safety of the carriers 8. The release interval is 20 seconds, and one round of launch can be completed within two minutes.

[0077] The working principle of the rotating launch device capable of continuously launching satellites 23 is as follows:

[0078] The rotary launch device adopts the technical scheme of ground rotation acceleration, inertial penetration of the atmosphere, and orbit entry by a single-stage engine 22. In this rotary launch scheme, the carrier 8 no longer uses chemical propellants as fuel in the initial acceleration phase, but uses electric energy to drive the accelerator 5, using centrifugal force to accelerate the carrier 8, and the carrier 8 relies on the initial speed inertial flight to leave the atmosphere, and then the carrier 8, under the action of the engine 22, sends the satellite 23 into the predetermined orbit.

[0079] The orbital altitude of the low-orbit small satellite 23 is 120km~600km, the length of a single support arm of the rotating support mechanism 3 is 50m, the mass of the small satellite 23 is 40kg~300kg, the exit speed of the carrier 8 is greater than 10 Mach, the rotation speed of the rotating support mechanism 3 is greater than 650r / min, and when the carrier 8 inertially flies to more than 100km, the engine 2222 ignites for boost and enters the active flight phase.

[0080] The environmental control equipment 7 can evacuate the interior of the launch cabin 2 to a medium vacuum level within 1 hour. The loading device 4 can quickly complete the loading of 6 carriers 8, and the loading time is 1 minute. The accelerator 5 can accelerate the rotating support mechanism 3 to 650r / min within 90 minutes. In order to prevent the continuous launch of multiple carriers 8 from affecting each other, the launch interval must be more than 20 seconds. It takes 2 minutes to launch 6 carriers 8. The braking and deceleration of the rotating support mechanism 3 can be completed within 30 minutes, and it takes 3 hours to complete a round of launch. It is expected that 48 carriers 8 can be launched in one day.

[0081] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0082] It should be noted that, in the present application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "include one..." do not exclude the existence of other identical elements in the process, method, article or device including the elements. The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be obvious to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features applied herein.

Claims

1. A rotating launch device capable of continuously launching satellites, characterized in that: include: A base mechanism, comprising a base and a connecting shaft fixed to the base, wherein the connection between the base and the connecting shaft is a rotation point; A launching cabin, comprising a rotating cabin and a launching tube connected to the rotating cabin, wherein the rotating cabin is rotatably connected to the connecting shaft; The rotating support mechanism comprises a plurality of supporting arms arranged in a uniform array along a circumference with a rotating point as the center; A plurality of release devices, each correspondingly disposed at the tail end of a support arm, for locking / unlocking the carrier at the corresponding tail end of the support arm; A loading device, located in the launch cabin, for loading the tail ends of the plurality of support arms with carriers; An accelerator is fixed on the connecting shaft and is used to drive the rotating support mechanism to rotate.

2. The rotating launch device capable of continuously launching satellites as claimed in claim 1, characterized in that: It also includes environmental control equipment, which is used to adjust the temperature, pressure and humidity in the launch cabin.

3. The rotating launch device capable of continuously launching satellites as claimed in claim 2, characterized in that: The environmental control equipment includes an air conditioning system, an air compression system and an environmental monitoring system.

4. The rotary launch device capable of continuously launching satellites as claimed in claim 3, characterized in that: The environmental monitoring system includes a temperature and humidity sensor and a pressure sensor.

5. The rotary launch device capable of continuously launching satellites as claimed in claim 1, characterized in that: The loading device includes a transmission chain, a carrier storage part and a chain power system. The transmission chain is equipped with multiple carrier storage parts. The transmission chain is transmission-connected to the chain power system. The chain power system is arranged at the bottom of the launch cabin.

6. The rotary launch device capable of continuously launching satellites as claimed in claim 1, characterized in that: The accelerator comprises an electric drive system and a speed controller. The rotation support mechanism is transmission-connected to the electric drive system. The speed controller is used to control the rotation speed of the rotation support mechanism.

7. The rotary launch device capable of continuously launching satellites as claimed in claim 6, characterized in that: The accelerator comprises a diesel generator and an energy storage system, and the electric drive system is driven by the diesel generator and the energy storage system.

8. The rotary launch device capable of continuously launching satellites as claimed in claim 1, characterized in that: The carrier comprises a protective shell, an engine and a satellite arranged therein, and the satellite is transmission-connected with the engine.

9. A rotational launching method capable of continuously launching satellites, using the rotational launching device capable of continuously launching satellites as claimed in any one of claims 1 to 8, characterized in that: The following steps are involved: The loading device at the bottom of the launch cabin is used to automatically load the carriers at the tail ends of multiple support arms; Control the vacuum degree in the launch cabin to meet the preset vacuum degree standard; The electric drive system of the accelerator is controlled to start, driving the rotating support mechanism and the carrier to rotate; Control the carriers at the tail ends of multiple support arms to launch in sequence.

10. The rotational launching method capable of continuously launching satellites as claimed in claim 9, characterized in that: The step of controlling the carriers at the tail ends of the multiple support arms to be launched in sequence specifically comprises the following steps: The carriers at the tail ends of multiple support arms are controlled to execute a diagonal launch strategy to launch in sequence.

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