CN117589009A - Rocket secondary capable of releasing satellite and working method - Google Patents

Abstract

The application discloses a rocket secondary stage of a releasable satellite and a working method, wherein the rocket secondary stage of the releasable satellite comprises the following steps: rocket secondary with payload cabin in the middle; wherein the payload bay comprises at least: the load cabin comprises a load cabin body provided with a cabin door, a left cabin door, a right cabin door, a cabin door driving system, a left front radiation plate, a right front radiation plate, an electromechanical actuating system, a left rear radiation plate, a right rear radiation plate, a remote control mechanical arm and an automatic locking mechanism. According to the method, the two split cabin door structures are adopted on the payload cabin, so that the load bearing capacity of the rocket secondary is improved.

Description

Rocket secondary capable of releasing satellite and working method

Technical Field

The application relates to the technical field of aerospace, in particular to a rocket secondary stage capable of releasing satellites and a working method.

Background

With the rapid development of aerospace technology, the desire of human beings to expand civilization to outer space is gradually enhanced, and the reusable rocket technology is also more mature. The full rocket is divided into two stages, and the two-stage full recovery recoverable rocket technology has also been provided with a complete scheme, wherein one sub-stage of the rocket is used for improving the height and speed of the rocket, and the two sub-stages of the rocket are used for completing the tasks of orbit entering, satellite separation, reentry recovery and the like.

In the payload launching task of satellites and the like, the safe separation of the satellites and the rockets is a key step of accurately entering a preset orbit, and therefore, higher requirements are also put on the separation reliability of the satellites. In the current scheme, a rocket secondary adopts a single flip type cabin door structure, when a satellite is to be deployed, the cabin door is opened, a payload adapter and a payload are separated by tilting at a certain angle, and the problems of limited large-scale load in and out and the like exist, so that a new satellite separation mode is necessary to be studied.

In the current scheme, a flip type cabin door structure is adopted for a load cabin door of a rocket secondary stage, and the rocket secondary stage and the load cabin are integrally designed and cannot be separated. The arrow body structure and the load cabin can be recycled as a whole, so that the recycling efficiency is improved, the inside of the load cabin is not required to be subjected to complex external atmospheric environment tests in the flying process, an external large shell is not required, and the assembly is simpler. However, since the rocket body itself has a cylindrical structure, when payload separation is performed in satellites and the like, the flip-type structure can limit load access, especially, large-sized loads such as space station cabins with irregular shapes, so that payload can not be reliably separated, and the carrying capacity of the payload is also disadvantageous in competition with heavy rockets.

Disclosure of Invention

The purpose of the application is to provide a rocket secondary stage capable of releasing satellites and a working method, wherein a two-leaf split cabin door structure is adopted on a payload cabin, so that the load bearing capacity of the rocket secondary stage is improved.

To achieve the above object, the present application provides a rocket secondary for a releasable satellite, comprising: rocket secondary with payload cabin in the middle; wherein the payload bay comprises at least: the load cabin comprises a load cabin body provided with a cabin door, a left cabin door, a right cabin door, a cabin door driving system, a left front radiation plate, a right front radiation plate, an electromechanical actuating system, a left rear radiation plate, a right rear radiation plate, a remote control mechanical arm and an automatic locking mechanism; one end of the left cabin door is rotationally connected with the left side of the cabin door, one end of the right cabin door is rotationally connected with the right side of the cabin door, and when the cabin door is closed, the other end of the left cabin door is tightly contacted with the other end of the right cabin door; the left cabin door and the right cabin door are connected with a cabin door driving system, and the opening and closing of the left cabin door and/or the right cabin door are controlled by the cabin door driving system; the left front radiation plate is rotationally connected with the inner side of the left cabin door and is positioned at the front end of the left cabin door; the right front radiation plate is rotationally connected with the inner side of the right cabin door and is positioned at the front end of the right cabin door; the left front radiation plate and the right front radiation plate are connected with an electromechanical actuating system, and the extension and retraction of the left front radiation plate and/or the right front radiation plate are controlled by the electromechanical actuating system; the left rear radiation plate is fixedly connected with the inner side of the left cabin door and is positioned at the rear end of the left cabin door; the right rear radiation plate is fixedly connected with the inner side of the right cabin door and is positioned at the rear end of the right cabin door; the remote control mechanical arm is arranged in the load cabin main body, and is used for grabbing and moving the effective load; the automatic locking mechanism is arranged on the load cabin body, and locks or unlocks the left cabin door and the right cabin door through the automatic locking mechanism before the left cabin door and the right cabin door are opened.

As above, wherein the payload bay further comprises: a load hatch left longitudinal beam and a load hatch right longitudinal beam; the load cabin door left longitudinal beam is arranged at the left side of the cabin door, and one end of the left cabin door is rotationally connected with the load cabin door left longitudinal beam; the right longitudinal beam of the load cabin door is arranged on the right side of the cabin door, and one end of the right cabin door is rotationally connected with the right longitudinal beam of the load cabin door.

As above, the left longitudinal beam of the load cabin door is provided with a left cabin door hinge, and one end of the left cabin door is hinged with the left longitudinal beam of the load cabin door through the left cabin door hinge; the right longitudinal beam of the load cabin door is provided with a right cabin door hinge, and one end of the right cabin door is hinged with the right longitudinal beam of the load cabin door through the right cabin door hinge.

As above, wherein the left side front radiating plate is hinged with the inner side of the left side cabin door and the right side front radiating plate is hinged with the inner side of the right side cabin door.

As above, the remote control mechanical arm at least includes: a robotic arm and a load actuation system; the mechanical arm is connected with a load actuating system, and the load actuating system is communicated with a ground control center; the load actuating system receives and executes a load actuating instruction sent by the ground control center or executes a load actuating instruction preset by the load actuating system, and the mechanical arm is controlled to grasp and move the effective load, so that the effective load is reliably separated from the rocket body of the rocket secondary stage and enters space.

As above, the payload cabin is provided with a plate-type longitudinal beam for supporting and storing the remote control mechanical arm, and the remote control mechanical arm is arranged on the plate-type longitudinal beam.

As described above, when the rocket is closed, the other end of the left cabin door is in close contact with the other end of the right cabin door, and the close contact position is located at the symmetrical line position above the rocket body of the rocket secondary.

The application also provides a working method which is applied to the rocket secondary stage of the releasable satellite and comprises the following steps: s1: before the rocket is launched in the second sub-stage, after loading of the payload is completed, the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; after closing, the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door; s2: after the rocket is in orbit in the second sub-stage, the automatic locking mechanism receives and executes an unlocking instruction to unlock the left cabin door and the right cabin door; after unlocking is completed, the cabin door driving system receives and executes an opening instruction to drive the left cabin door and the right cabin door to be opened; after the opening is finished, the electromechanical actuating system receives and executes an extension instruction, and the action adjustment is carried out on the left front radiating plate and the right front radiating plate; s3: the remote control mechanical arm receives and executes a load actuating instruction to grab and move the effective load, so that the effective load is reliably separated from the rocket body of the rocket secondary stage and enters into space; s4: when the rocket is returned to the second-level, the remote control mechanical arm is contracted into the effective load cabin; the electromechanical actuating system receives and executes a retraction instruction, and retracts the left front radiation plate and the right front radiation plate to the inner sides of the left cabin door and the right cabin door; the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door.

As above, the automatic locking mechanism receives and executes an unlocking instruction or a locking instruction sent by the ground control center.

As above, the automatic locking mechanism executes an unlocking instruction or a locking instruction preset by itself.

The beneficial effects realized by the application are as follows:

(1) According to the rocket secondary stage capable of releasing the satellite and the working method, the rocket body and the load cabin are integrally designed, and the reusability and the recovery efficiency are improved.

(2) Aiming at the defects of the existing payload separation modes such as a rocket secondary satellite, the rocket secondary of the releasable satellite is designed into a two-wing split type cabin door structure, the two-wing split type cabin door structure can work independently and can work in a coordinated manner, and the reliability of satellite separation and the carrying capacity of the load can be improved on the premise of ensuring that an rocket body and the payload cabin can be recovered integrally.

(3) The automatic locking mechanism has the advantages that the independent driving system is arranged, the automatic locking mechanism can work independently, the cabin door can be locked and kept at any position, and the reliability of the separation system is improved.

(4) The payload cabin of the rocket secondary adopts the two split cabin door structures to replace the existing single flip cabin door structure, so that the influence of the shapes on the payload in and out is small, and the load bearing capacity and the separation reliability of the rocket are improved to a certain extent.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following description will briefly introduce the drawings that are required to be used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may also be obtained according to these drawings for a person having ordinary skill in the art.

FIG. 1 is a schematic view of an embodiment of a rocket secondary stage of a releasable satellite in a closed position;

FIG. 2 is a schematic view of an embodiment of a rocket secondary stage of a releasable satellite in an open condition;

FIG. 3 is a flow chart of one embodiment of a method of operation.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

As shown in fig. 1-2, the present application provides a rocket secondary for a releasable satellite, comprising: the rocket secondary 1 with payload bay 11 is arranged in the middle. Wherein the payload bay 11 comprises at least: a load compartment body 112 with a compartment door 111, a left compartment door 113, a right compartment door 114, a compartment door drive system, a left front radiant panel 115, a right front radiant panel 116, an electromechanical actuation system, a left rear radiant panel 117, a right rear radiant panel 118, a remote robot 119, and an automatic locking mechanism 120. One end of the left cabin door 113 is rotatably connected with the left side of the cabin door opening 111, one end of the right cabin door 114 is rotatably connected with the right side of the cabin door opening 111, and when the cabin door is closed, the other end of the left cabin door 113 is closely contacted with the other end of the right cabin door 114; the left door 113 and the right door 114 are each connected to a door drive system by which the opening and closing of the left door 113 and/or the right door 114 is controlled. The left front radiation plate 115 is rotatably connected to the inner side of the left door 113 and is positioned at the front end of the left door 113; the right front radiation plate 116 is rotatably connected to the inner side of the right cabin door 114 and is located at the front end of the right cabin door 114; the left and right front radiating plates 115, 116 are each connected to an electro-mechanical actuation system by which extension and retraction of the left and/or right front radiating plates 115, 116 is manipulated. The left rear radiation plate 117 is fixedly connected with the inner side of the left cabin door 113 and is positioned at the rear end of the left cabin door 113; the right rear radiating plate 118 is fixedly coupled to the inside of the right door 114 and is located at the rear end of the right door 114. The teleoperated robot 119 is provided in the load cell main body 112, and the teleoperated robot 119 grips and moves the payload 2. The automatic locking mechanism 120 is provided on the load compartment body 112, and locks or unlocks the left and right doors 113 and 114 by the automatic locking mechanism 120 before the left and right doors 113 and 114 are opened.

Specifically, the split door structure formed by the left door 113 and the right door 114 can improve the load carrying capacity of the rocket secondary.

The cabin door driving system is a driving system specially used for controlling the opening and closing of the left cabin door 113 and the right cabin door 114, and can open and close the left cabin door 113 and/or the right cabin door 114 at any time according to the requirement. The specific type of hatch drive system is not limited in this application, namely: the door driving system may be used to provide a function of opening and closing the left door 113 and/or the right door 114 as required, for example: a rotating motor, a telescopic cylinder, a gear rotating mechanism and the like.

Further, the left door 113 and/or the right door 114 are opened and closed in an independent operation manner or a coordinated operation manner. The independent working mode is to open or close any door of the left cabin door 113 and the right cabin door 114 according to actual requirements. The coordination working mode is to open or close two doors of the left cabin door 113 and the right cabin door 114 simultaneously according to actual requirements.

Further, the specific setting position of the automatic locking mechanism 120 and the number of setting automatic locking mechanisms 120 are not limited in this application.

As an example, an automatic locking mechanism 120 is provided, and the automatic locking mechanism 120 is provided at the rear side of the door opening 111, and the left door 113 and the right door 114 are locked or unlocked by the automatic locking mechanism 120 before the left door 113 and the right door 114 are opened.

As another embodiment, two automatic locking mechanisms 120 are provided, wherein one automatic locking mechanism 120 is provided at the rear side of the door opening 111, the other automatic locking mechanism 120 is provided at the front side of the door opening 111, and the left door 113 and the right door 114 are locked or unlocked by the two automatic locking mechanisms 120.

Further, as an embodiment, the plurality of automatic locking mechanisms 120 share a locking driving system, and the automatic locking mechanism 120 is driven by the locking driving system to open and close the left door 113 and/or the right door 114

Further, as another embodiment, each of the automatic locking mechanisms 120 has a locking driving system by which the automatic locking mechanism 120 connected to itself is driven to open and close the left door 113 and/or the right door 114.

Specifically, the automatic locking mechanism 120 has an independent driving system, can work independently of each other, and can lock and hold the door (the left door 113 and/or the right door 114) at any position, thereby enabling the separation system to have high reliability. The type of automatic locking mechanism 120 is not specifically limited in this application, namely: the automatic locking mechanism 120 may be used to automatically open and close the left door 113 and/or the right door 114.

The type of electromechanical actuation system is not particularly limited in this application, namely: the electromechanical actuation system used may be one that is capable of automatically manipulating the extension and retraction of the left and/or right front radiating panels.

Further, the payload bay further comprises: a load hatch left longitudinal beam and a load hatch right longitudinal beam; the load cabin door left longitudinal beam is arranged at the left side of the cabin door 111, and one end of the left cabin door 113 is rotationally connected with the load cabin door left longitudinal beam; the load port right stringer is disposed on the right side of the door opening 111, and one end of the right port 114 is rotatably connected to the load port right stringer.

Further, the load cabin door left longitudinal beam is provided with a left cabin door hinge, but not limited to the left cabin door hinge, and can be a connecting piece capable of realizing rotary connection such as a rotary bearing, the connecting piece is preferably a left cabin door hinge, and one end of the left cabin door 113 is hinged with the load cabin door left longitudinal beam through the left cabin door hinge. The right longitudinal beam of the load cabin door is provided with a right cabin door hinge, but the load cabin door is not limited to the right cabin door hinge, and can also be a connecting piece such as a rotating bearing which can realize rotating connection, and the right cabin door hinge is preferred in the application; one end of the right door 114 is hinged to the load door right stringer by a right door hinge.

Further, the left door hinge is located outside the left side of the payload bay 11, and the right door hinge is located outside the right side of the payload bay 11, i.e.: the left door hinge and the right door hinge are both external hinges, but are not limited to external hinges, and the application is preferably an external hinge, which does not affect the internal equipment of the payload bay 11 when opened.

Further, the left front radiating plate 115 is hinged with the inner side of the left door 113, but is not limited to the hinge, and is preferably hinged in this application. The right front radiant panel 116 is hinged to the inside of the right door 114, but is not limited to being hinged, and is preferably hinged in this application.

Further, as an embodiment, the remote control robot 119 includes at least: a robotic arm and a load actuation system; the mechanical arm is connected with a load actuating system, and the load actuating system is communicated with a ground control center; the load actuating system receives and executes a load actuating instruction sent by the ground control center or executes a load actuating instruction preset by the load actuating system, and the mechanical arm is controlled to grasp and move the effective load 2, so that the effective load 2 is reliably separated from an rocket body of the rocket secondary stage 1 and enters space.

Specifically, the type of the remote control robot 119 is not specifically limited in this application, namely: the remote control mechanical arm 119 can automatically grasp and move the payload 2, so that the payload 2 and the rocket body of the rocket secondary stage can be reliably separated and enter space. The load actuation command preset by itself is a command preset according to the automatic operation and the preset operation time of the remote control arm 119.

Further, a plate-type stringer for supporting and storing a remote control arm is provided in the payload bay 112, and a remote control arm 119 is provided on the plate-type stringer.

Further, when the rocket is closed, the other end of the left side cabin door 113 is in close contact with the other end of the right side cabin door 114, and the close contact position is located at the symmetry line position above the rocket body of the rocket secondary stage 1, but not limited to the symmetry line position above the rocket body of the rocket secondary stage 1, the symmetry line position above the rocket body of the rocket secondary stage 1 is preferred.

Further, a joint 21 is provided on the payload 2, and the joint 21 is connected to the robot arm of the remote robot 119.

As shown in fig. 3, the present application further provides a working method applied to the rocket secondary stage of the releasable satellite, where the working method includes the following steps:

s1: before the rocket is launched in the second sub-stage, after loading of the payload is completed, the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; after closing, the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door.

S2: after the rocket is in orbit in the second sub-stage, the automatic locking mechanism receives and executes an unlocking instruction to unlock the left cabin door and the right cabin door; after unlocking is completed, the cabin door driving system receives and executes an opening instruction to drive the left cabin door and the right cabin door to be opened; after the opening is completed, the electromechanical actuating system receives and executes the stretching instruction, and the action adjustment is carried out on the left front radiating plate and the right front radiating plate.

S3: the remote control mechanical arm receives and executes the load actuating instruction to grab and move the effective load, so that the effective load is reliably separated from the rocket body of the rocket secondary stage and enters into space.

S4: when the rocket is returned to the second-level, the remote control mechanical arm is contracted into the effective load cabin; the electromechanical actuating system receives and executes a retraction instruction, and retracts the left front radiation plate and the right front radiation plate to the inner sides of the left cabin door and the right cabin door; the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door.

Further, as an embodiment, the automatic locking mechanism receives and executes an unlocking instruction or a locking instruction sent by the ground control center.

Specifically, the automatic locking mechanism is communicated with the ground control center, and receives and executes an unlocking instruction or a locking instruction sent by the ground control center.

Further, as another embodiment, the automatic locking mechanism executes an unlocking instruction or a locking instruction preset by itself.

Specifically, the preset unlocking instruction or locking instruction is preset according to the automatic operation flow and the preset operation time of the automatic locking mechanism.

The beneficial effects realized by the application are as follows:

(1) According to the rocket secondary stage capable of releasing the satellite and the working method, the rocket body and the load cabin are integrally designed, and the reusability and the recovery efficiency are improved.

(2) Aiming at the defects of the existing payload separation modes such as a rocket secondary satellite, the rocket secondary of the releasable satellite is designed into a two-wing split type cabin door structure, the two-wing split type cabin door structure can work independently and can work in a coordinated manner, and the reliability of satellite separation and the carrying capacity of the load can be improved on the premise of ensuring that an rocket body and the payload cabin can be recovered integrally.

(3) The automatic locking mechanism has the advantages that the independent driving system is arranged, the automatic locking mechanism can work independently, the cabin door can be locked and kept at any position, and the reliability of the separation system is improved.

(4) The payload cabin of the rocket secondary adopts the two split cabin door structures to replace the existing single flip cabin door structure, so that the influence of the shapes on the payload in and out is small, and the load bearing capacity and the separation reliability of the rocket are improved to a certain extent.

While preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the scope of the present application be interpreted as including the preferred embodiments and all alterations and modifications that fall within the scope of the present application. It will be apparent to those skilled in the art that various modifications and variations can be made in the present application without departing from the spirit or scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the protection of the present application and the equivalents thereof, the present application is intended to cover such modifications and variations.

Claims (10)

1. A rocket secondary for a releasable satellite, comprising: rocket secondary with payload cabin in the middle;

wherein the payload bay comprises at least: the load cabin comprises a load cabin body provided with a cabin door, a left cabin door, a right cabin door, a cabin door driving system, a left front radiation plate, a right front radiation plate, an electromechanical actuating system, a left rear radiation plate, a right rear radiation plate, a remote control mechanical arm and an automatic locking mechanism;

one end of the left cabin door is rotationally connected with the left side of the cabin door, one end of the right cabin door is rotationally connected with the right side of the cabin door, and when the cabin door is closed, the other end of the left cabin door is tightly contacted with the other end of the right cabin door; the left cabin door and the right cabin door are connected with a cabin door driving system, and the opening and closing of the left cabin door and/or the right cabin door are controlled by the cabin door driving system;

the left front radiation plate is rotationally connected with the inner side of the left cabin door and is positioned at the front end of the left cabin door; the right front radiation plate is rotationally connected with the inner side of the right cabin door and is positioned at the front end of the right cabin door; the left front radiation plate and the right front radiation plate are connected with an electromechanical actuating system, and the extension and retraction of the left front radiation plate and/or the right front radiation plate are controlled by the electromechanical actuating system;

the left rear radiation plate is fixedly connected with the inner side of the left cabin door and is positioned at the rear end of the left cabin door; the right rear radiation plate is fixedly connected with the inner side of the right cabin door and is positioned at the rear end of the right cabin door;

the remote control mechanical arm is arranged in the load cabin main body, and is used for grabbing and moving the effective load;

the automatic locking mechanism is arranged on the load cabin body, and locks or unlocks the left cabin door and the right cabin door through the automatic locking mechanism before the left cabin door and the right cabin door are opened.

2. A rocket secondary for a releasable satellite according to claim 1, wherein the payload bay further comprises: a load hatch left longitudinal beam and a load hatch right longitudinal beam;

the load cabin door left longitudinal beam is arranged at the left side of the cabin door, and one end of the left cabin door is rotationally connected with the load cabin door left longitudinal beam;

the right longitudinal beam of the load cabin door is arranged on the right side of the cabin door, and one end of the right cabin door is rotationally connected with the right longitudinal beam of the load cabin door.

3. The rocket secondary of releasable satellites according to claim 2 wherein a left door hinge is provided on the left side rail of the load door, one end of the left side door being hinged to the left side rail of the load door by the left door hinge;

the right longitudinal beam of the load cabin door is provided with a right cabin door hinge, and one end of the right cabin door is hinged with the right longitudinal beam of the load cabin door through the right cabin door hinge.

4. A rocket secondary for a releasable satellite according to claim 3, wherein the left front radiating plate is hinged to the inside of the left door and the right front radiating plate is hinged to the inside of the right door.

5. A rocket secondary for a releasable satellite according to claim 4, wherein the telerobotic arm comprises at least: a robotic arm and a load actuation system;

the mechanical arm is connected with a load actuating system, and the load actuating system is communicated with a ground control center;

the load actuating system receives and executes a load actuating instruction sent by the ground control center or executes a load actuating instruction preset by the load actuating system, and the mechanical arm is controlled to grasp and move the effective load, so that the effective load is reliably separated from the rocket body of the rocket secondary stage and enters space.

6. A rocket secondary for a releasable satellite according to claim 5, wherein a plate-type stringer for supporting and storing a remote-controlled robot is provided in the payload bay, the remote-controlled robot being provided on the plate-type stringer.

7. A rocket secondary for a releasable satellite according to claim 6, wherein the other end of the left side door is in close contact with the other end of the right side door when closed, and the position of the close contact is located at a symmetry line position above the rocket body of the rocket secondary.

8. A method of operation for a rocket secondary for a releasable satellite according to any one of claims 1-7, the method comprising the steps of:

s1: before the rocket is launched in the second sub-stage, after loading of the payload is completed, the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; after closing, the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door;

s2: after the rocket is in orbit in the second sub-stage, the automatic locking mechanism receives and executes an unlocking instruction to unlock the left cabin door and the right cabin door; after unlocking is completed, the cabin door driving system receives and executes an opening instruction to drive the left cabin door and the right cabin door to be opened; after the opening is finished, the electromechanical actuating system receives and executes an extension instruction, and the action adjustment is carried out on the left front radiating plate and the right front radiating plate;

s3: the remote control mechanical arm receives and executes a load actuating instruction to grab and move the effective load, so that the effective load is reliably separated from the rocket body of the rocket secondary stage and enters into space;

s4: when the rocket is returned to the second-level, the remote control mechanical arm is contracted into the effective load cabin; the electromechanical actuating system receives and executes a retraction instruction, and retracts the left front radiation plate and the right front radiation plate to the inner sides of the left cabin door and the right cabin door; the cabin door driving system receives and executes a closing instruction to drive the left cabin door and the right cabin door to be closed; the automatic locking mechanism receives and executes a locking instruction to lock the left cabin door and the right cabin door.

9. The method of claim 8, wherein the automatic locking mechanism receives and executes an unlock command or a lock command sent by the ground control center.

10. The working method according to claim 8, wherein the automatic locking mechanism executes an unlocking instruction or a locking instruction preset by itself.