CN104527996B - Overall rail mounted cube star discharger - Google Patents

Abstract

The invention discloses an integral orbital cubesat launching device for carrying and launching single or multiple standard cubesats; the main components include a rectangular frame, an unlocking mechanism and a spring mechanism, etc., and the rectangular frame is mainly composed of a hatch, a baffle, Bottom plate, side plate, upper cover plate, rear cover plate, etc. are threadedly connected, and the upper, lower, left, and right four plates are symmetrically distributed with thin bosses along the long axis, and two of them form an integral track, which is used as a satellite slide rail; the suction cup electromagnet is used as an unlocking mechanism The spring mechanism includes a push plate and a compression spring; the present invention has strong versatility and low cost, can ensure the safe transportation and reliable launch of the satellite, can prevent the satellite from moving during the transportation process, and the hatch will not collide during the opening process Go to the running platform or reverse, and set the push plate anti-falling out measures, etc.

Description

Integral Orbiting CubeSat Launcher

technical field

The invention belongs to the technical field of standard cubesat carrying and launching, in particular to an integral orbit type cubesat launching device.

Background technique

With the development of microelectronics technology, new materials, new energy and other technologies, the application of microsatellites has developed rapidly. At present, they are mainly used for communication, remote sensing of the earth, interplanetary exploration, scientific research and technical experiments, etc., and also have military applications. Wide application prospects, so many countries have included it in the national research plan, as a commanding height of technology and economic development in the 21st century. my country Aerospace Dongfanghong Satellite Company, Shanghai Microsatellite Engineering Center of the Chinese Academy of Sciences, National University of Defense Technology, Tsinghua University, Harbin Institute of Technology, Zhejiang University, Nanjing University of Aeronautics and Astronautics and many other units have successively developed and launched small satellites. At present, the development of micro-satellites is in the ascendant in China.

It is generally believed that satellites with a mass of less than 1000kg are collectively referred to as microsatellites, and satellites with a mass of less than 1kg are called pico-satellites. In 1999, the satellite was defined as a CubeSat, and several CubeSats can form a nano-satellite (Nanosat). ). In recent years, these two kinds of satellites have developed rapidly and have been successfully applied in distributed space systems. The cube star refers to a picostar or nano star. Usually, the typical volume of a 1-unit cube star is 1dm3, and the typical mass is 1kg; the typical volume of a 2-unit cube star is 2dm3, and the typical mass is 2kg; the typical volume of a 3-unit cube star is The volume is 3dm3, and the typical mass is 3kg. Similarly, the development and research of cube stars is urgent. Internationally, CubeSats have standard shape, size, and weight requirements, which makes it possible to manufacture standard and unified CubeSat launchers.

At present, micro-satellite release devices developed abroad are in the experimental stage or finished products, such as P-POD in the United States, J-SSOD in Japan, X-POD in Canada, ISIPOD in Norway, etc., and are still actively being developed in China. The principle of the microsatellite release device is basically the same. Usually, the microsatellite is locked in the device, unlocked in the predetermined orbit, and uses the spring to push the small satellite out of the device and enters space. The separation is reliable and the cost is low, but still needs to be improved, mainly as follows What time is it:

(1) Cost problem: the structure is exquisite and complex, and the processing cost and processing accuracy are high;

(2) The problem of hatch rotation: when the unlocking device is unlocked, the hatch opens and may rotate excessively, colliding with the carrying platform, causing unnecessary damage;

(3) Anti-restoration of the cabin door: During the release process of the microsatellite, if the cabin door recovers during the rotation process, it will affect the release of the microsatellite, and may even cause damage to the microsatellite;

(4) The problem of push plate coming out: the push plate is between the compression spring and the micro-satellite, and the small satellite is pushed out of the release device by using the energy inside the compression spring. When the small satellite is completely released, the push plate may come out of the release device under the action of inertia;

(5) Applicability problem: the current satellite release device is not very versatile, and it is only suitable for small satellites that are square and without any additional devices.

(6) The problem of the degree of freedom of micro-satellites: During the launch process of the launch vehicle, the force environment is relatively complicated. If the micro-satellites have no freedom restriction measures, they will scurry around in the launch device, which may cause damage to the device and small satellites.

Contents of the invention

The object of the present invention is to provide a kind of integral orbit type CubeSat launching device that can keep transportation safe before launching, prevent the hatch door from colliding with the carrier platform, prevent the hatch door from reversing during the satellite release process, and has good versatility and low cost.

The technical solution that realizes the object of the present invention is:

An integral orbital cubesat launching device, including a main frame, a spring mechanism, and an unlocking mechanism; the main frame includes a hatch, a door baffle, a bottom plate, a side plate, an upper cover and a rear cover, and the side plates are symmetrically installed on both sides of the bottom plate , the upper cover plate is installed above the side plate, and the four plates are symmetrically distributed with thin bosses along the long axis, and the slide rails are formed in pairs. The front and rear of the frame are respectively fixed with a door baffle and a rear cover. A shaft seat is provided, and the shaft seat is fixed with a hatch door rotation shaft. The hatch door rotates and cooperates with the hatch door rotation shaft through the rotation seat at the inner bottom end of the hatch door. The position is provided with anti-recovery pin installation hole, and anti-recovery pin is arranged in it, and the side of anti-recovery pin and the rotating seat of cabin door are vertical, and in the initial section position of hatch door rotation, anti-recovery pin is positioned at the side of rotating seat in the axial direction. Within the range of the side, limited by the rotating seat, after the door rotates to leave the initial position, the return pin is axially located outside the range of the side of the rotating seat, and the shaft seat of the door baffle is in the direction of rotation of the door Plane limit protrusions are set; transport safety holes are provided at the upper corners of the hatch and corresponding to the door baffle, transport safety pins are arranged in the transport safety holes, and boss structures are arranged on the inner side of the hatch; the spring mechanism includes a push Plate, pressure spring, push plate and frame internal slide rail form a sliding pair, and the two ends of the pressure spring are respectively stuck in the slots on the push plate and the rear cover; the unlocking mechanism includes an electromagnet and an electromagnet adsorption piece, and the electromagnet is set The top of the upper cover plate is close to the door baffle, and the electromagnet absorbing part is arranged on the hatch, and its position is opposite to that of the electromagnet. Among them, the maximum compression height of the compression spring + the length of the satellite + the thickness of the boss structure behind the hatch = The total internal length of the launcher.

Compared with the prior art, the present invention has significant advantages:

(1) The transportation safety pin of the present invention can lock the cabin door during transportation to ensure the safety of the transportation process.

(2) In the present invention, the bolt connection on both sides of the bottom plate is used for mechanical connection with the reliable mechanical connection of the carrying, so as to ensure the stability of the carrying process.

(3) The anti-restoring pin of the present invention is set in cooperation with the rotating seat of the cabin door, which can prevent the recovery of the cabin door during the release of the microsatellite, and avoid affecting the release of the microsatellite and causing damage to the microsatellite.

(4) The position-limiting protrusion provided on the shaft seat of the door baffle plate in the direction of rotation of the hatch can prevent excessive rotation after the hatch is opened, and avoid collision with the carrying platform, causing unnecessary damage.

(5) The present invention is provided with lugs on both symmetrical sides of the push plate, which can prevent the push plate from falling out of the release device under the action of inertia after the small satellite is completely released.

(6) In the present invention, the maximum compression height of the clip spring+the length of the satellite+the thickness of the boss structure behind the cabin door=the total length inside the launching device, which can limit the axial freedom of the small satellite in the device, so that the small satellite will not be in the middle of the transportation process. movement within the device, causing damage.

(7) Both the push plate and the rear cover of the present invention have round holes, and the size of the round holes is relatively large, which increases the applicability of the device and can accommodate the protruding part of the tail of the satellite.

The present invention will be described in further detail below in conjunction with the accompanying drawings.

Description of drawings

Fig. 1 is a schematic diagram of the appearance and structure of the integral orbiting CubeSat launching device of the present invention.

Fig. 2 is a schematic diagram of the overall structure of the integral orbiting CubeSat launching device of the present invention.

Fig. 3 is a schematic diagram of the internal structure of the integral orbiting CubeSat launching device of the present invention.

Fig. 4 is a structural schematic diagram of the transportation safety pin of the integral orbiting CubeSat launching device of the present invention.

Fig. 5 is a schematic structural view of the push plate of the integral orbiting cubesat launching device of the present invention.

Fig. 6 is a schematic structural view of the rear cover of the integral orbiting cubesat launching device of the present invention.

Fig. 7 is a schematic structural view of the door baffle of the integral orbiting CubeSat launching device of the present invention.

Fig. 8 is a schematic diagram of the hatch limit structure of the integral orbiting CubeSat launching device of the present invention.

Fig. 9 is a schematic diagram of the door anti-recovery structure of the integral orbiting cubesat launching device of the present invention.

Fig. 10 is a schematic diagram of the reverse recovery pin being limited in the integral orbiting cubesat launching device of the present invention.

Fig. 11 is a schematic diagram of the unrestricted return pin of the integral orbiting cubesat launching device of the present invention.

Fig. 12 is a schematic structural view of the door rotating seat of the integral orbiting cubesat launching device of the present invention.

Fig. 13 is a structural schematic diagram of the reverse return pin of the integral orbiting cubesat launching device of the present invention.

Fig. 14 is a structural schematic diagram of the sliding rail and the mechanical interface for bolt connection of the integral orbital cubesat launcher of the present invention.

detailed description

Combined with Figure 1 to Figure 14:

The present invention is an integral track type cube star launching device, comprising a main body frame, a spring mechanism, and an unlocking mechanism; the main body frame includes a cabin door 1, a door stopper 2, a bottom plate 3, a side plate 4, an upper cover plate 5 and a rear cover 6, The side plates 4 are symmetrically installed on both sides of the bottom plate 3, and the upper cover plate 5 is installed on the top of the side plates 4. Thin bosses 11 are symmetrically distributed along the long axis of the four plates, and two pairs form slide rails. The front and rear of the frame are respectively fixed with door baffles 2 With the rear cover 6, the bottom end of the door baffle plate 2 exceeds the position of the bottom plate 3 to set the shaft seat, and the shaft seat is fixedly provided with the hatch rotation shaft, and the hatch door 1 rotates and cooperates with the hatch door rotation shaft through the rotation seat at the bottom end of the hatch inner side , the shaft seat on the bottom edge of the door baffle plate 2 is parallel to the rotation axis and staggered to be provided with an anti-recovery pin installation hole, which is provided with an anti-recovery pin, and the anti-recovery pin is perpendicular to the side of the rotary seat of the cabin door 1, At the initial section position of the hatch door 1 rotation, the anti-restoration pin is located in the range of the side of the rotary seat in the axial direction, and is limited by the rotary seat. Located outside the range of the side of the rotating seat, the shaft seat of the door baffle 2 is provided with a plane limit protrusion 12 in the direction of rotation of the door; Holes, transport safety pins 10 are provided in the transport safety holes, and the inner side of the cabin door 1 is provided with a boss structure; the spring mechanism includes a push plate 7 and a compression spring 8. The two ends are respectively stuck in the card slots on the push plate 7 and the rear cover 6; the unlocking mechanism includes an electromagnet 9 and an electromagnet adsorption piece, the electromagnet 9 is arranged on the top of the upper cover 5, close to the door baffle 2, The electromagnet absorbing part is arranged on the cabin door 1, and its position is opposite to the electromagnet 9 positions, wherein, stage clip 8 maximum compression height+satellite length+cabin door 1 backside boss structure thickness=total length inside the launching device.

The anti-reversing pin is composed of a pin shaft, a pin head, a movable pin seat, a fixed pin seat and a spring. The two ends of the pin shaft are respectively fixed with a pin head and a fixed pin seat, and a movable pin seat is slid on the pin shaft. On the pin shaft, the two ends are in contact with the pin head and the movable pin seat respectively, and the movable pin seat is fixedly arranged in the installation hole of the reverse return pin.

Transport insurance pin 10 is made of bolt and nut, utilizes threaded connection to overcome the thrust that stage clip 8 produces to cabin door.

There are mechanical interfaces 13 for bolt connection on both sides of the bottom plate 3, which are used for mechanical connection between the device and the platform.

Have a circular hole on the push plate 7 and the back cover 6, and the size of the circular hole is larger than the protruding part of the satellite.

The push plate 7 is provided with lugs on the symmetrical sides, and the lugs are limited by the door stop plate 2 in the sliding direction of the push plate 7. The support ears do not affect the sliding of the push plate 7 in the device, but they exceed the door stop plate 2. Opening part, can be blocked by door stopper 2 when moving further.

The hatch 1 is normally closed, and before receiving an unlocking instruction, it is ensured that the hatch 1 is completely closed during the transportation of the rocket. Micro-satellites slide along the integral track in the device, and cuboid protruding structures 11 are designed on the four panels of up, down, left, and right, and two by two constitute satellite slide rails.

The hatch door 1 is provided with a torsion spring in the direction of rotation. The torsion spring is a spring that works under torsion. When the hatch door 1 is opened, the torsion spring needs to have a certain pretightening force to ensure that the hatch door remains open reliably and absorbs A certain amount of resilience.

During the slide launch of the CubeSat, the hatch 1 is subject to a large force and is easy to hit the launch vehicle platform. In order to prevent possible collisions, the hatch limit structure is designed. Promptly utilize the plane limit protrusion 12 at the rear part of the lower shaft seat of the door baffle plate 2, when the hatch door 1 rotates, the lower plane will coincide with the plane limit protrusion 12 raised plane, thereby blocking the further rotation of the hatch door 1. In order to ensure stability, four plane protrusions are designed, and the angle between the plane of the protrusions and the vertical direction is 30 degrees, so as to ensure that the maximum rotation angle of the hatch door 1 is 150 degrees.

When the door 1 moves in place but the cubestar is not completely ejected, in order to prevent the door 1 from rotating under the action of inertia and hitting the cubestar, thereby affecting its performance and movement, the door anti-restoration structure is designed, as shown in Figure 9～ 11. The anti-recovery door structure includes an axle seat provided at the bottom end of the cabin door 1 and an anti-recovery pin structure door. The top of the axle seat is provided with a flat edge, and the rest is arc-shaped; Composed of fixed pin seat and spring, the two ends of the pin shaft are respectively fixed with pin head and fixed pin seat, and the movable pin seat is slid on the pin shaft. Fixed, the movable pin seat is fixedly arranged in the mounting hole of the reverse return pin. Utilize the rotation track of the rotating seat around the rotation axis of the hatch door, that is, when the hatch door starts to open to the angle corresponding to the flat side of the rotation, the flat side of the rotating seat coincides with the round hole where the reverse return pin is placed, and the reverse return pin is blocked , the spring is compressed, and when the door turns over the angle corresponding to the flat side, the arc part of the rotating seat no longer blocks the anti-recovery pin, but is always tangent to the anti-recovery pin mounting hole on the baffle plate 2, and the anti-recovery pin is in the Stretch out under spring action, block rotating seat, make cabin door 1 unable to return. At this time, if you want to manually close the door, you only need to pinch the fixed pin seat and pull out the reverse recovery pin.

Since the CubeSat needs to be protected inside the main frame, its structural strength, impact resistance requirements, thermal requirements, and mechanical requirements are strictly designed, and it needs to go through a series of ground verifications such as positive selection vibration, random vibration, impact, and thermal cycle. test. In addition, the spring mechanism and unlocking mechanism are all attached to the main frame, which increases the complexity of the main structure design, so the requirements for the safety factor and reliability indicators of the main structure design are very high.

The spring mechanism mainly includes a push plate 7 for ejecting the satellite, a clip spring 8 and two torsion springs for opening the hatch, which are the power behind the unlocking of the hatch of the entire satellite launching device. Stage clip 8 is the spring of pressurized work, will guarantee that the speed that CubeSat is ejected is in a certain range, and the acceleration of satellite in the ejection process is in a certain range, guarantees the stability when satellite is ejected. The torsion spring is a spring that works under torsion. After the unlocking device is unlocked, when the hatch 1 is opened, the torsion spring also needs a certain pre-tightening force to ensure that the hatch remains open reliably and absorbs a certain rebound force.

In order to prevent small satellites from scurrying around during the flight of the carrier rocket, its movement in the launch device must be restricted. Since the small satellite is in a frame structure, its degrees of freedom in the x and y directions are limited by the frame, and the z direction, that is, the satellite direction of ejection, other measures are required. The present invention adopts the mode that clip spring 8 and cabin door are jointly restricted, and when designing clip spring 8, just considered the problem of the degree of freedom of the tiny satellite, that is, after the small satellite was put into the launching device, clip spring 8 was basically crushed to death, and then A raised platform is designed at the rear of the hatch 1. When the hatch 1 is closed, the compression spring 8 is further compressed, that is, the maximum compression height of the compression spring 8 + the length of the tiny satellite + the raised thickness behind the hatch 1 = the total internal length of the launching device, In this way, the degree of freedom limitation of the micro-satellite during the launching process is realized.

For the existing satellite release device, the surface length and width of the push plate 7 are consistent with the length and width of the section of the micro-satellite. When the micro-satellite is completely pushed out by the compression spring 8, the push plate 7 may also come out under the action of inertia, causing a certain impact. Therefore, the present invention designs push plate lugs, and the lugs exceed the opening of the door baffle 2, that is, when the push plate 7 moves to the hatch 1, the lugs will be blocked by the door baffle 2, so that the push plate 7 cannot escape from the door. device.

Unlocking mechanism is mainly made up of sucker electromagnet 9 and electromagnet adsorption part, controls the opening and closing of cabin door. The unlocking mechanism is controlled by the control circuit to ensure reliable locking of the hatch before receiving the unlocking command; when the unlocking command is received, the electromagnet 9 is energized and the magnetic force is eliminated, and the restriction on the hatch 1 is reliably released. The unlocking method is simple and reliable.

In order to increase the applicability of the device, when the push plate 7 and the rear cover 6 are designed, circular holes are left respectively, so that the device is suitable for 3U+ series cube stars. The 3U+ series cube star is based on the original 3-unit cube star with some devices added at the rear, such as lenses.

Bolt connection mechanical interfaces 13 are designed on both sides of the bottom plate 3, which means that the satellite launching device is fixed together with the carrier installation platform with several M6 bolts. The mechanical interface 13 for bolt connection needs to enable the device to be stably fixed on the carrying installation platform to ensure mechanical requirements such as strength and shock resistance.

Example:

Combined with Figure 1 to Figure 14

In the following, for convenience, the 1-unit CubeSat is referred to as 1U, the 2-unit CubeSat is referred to as 2U, and the 3-unit CubeSat is referred to as 3U.

An integral orbital cubesat launching device, comprising a main frame, a spring mechanism, and an unlocking mechanism; the main frame includes a cabin door 1, a door baffle plate 2, a bottom plate 3, a side plate 4, an upper cover plate 5 and a rear cover 6, and the side plate 4 are symmetrically installed on both sides of the bottom plate 3, and the upper cover plate 5 is installed on the top of the side plate 4. The four plates are symmetrically distributed along the long axis with thin bosses 11, and the slide rails are formed in pairs. Cover 6, the bottom end of the door baffle plate 2 exceeds the position of the bottom plate 3 to set the shaft seat, and the shaft seat is fixedly provided with the hatch rotating shaft, and the hatch door 1 rotates and cooperates with the hatch rotating shaft through the rotating seat at the inner bottom end of the hatch door, and the door On the shaft seat on the edge of the bottom end of the baffle plate 2, parallel to the rotation axis and staggered, there is a mounting hole for a reverse recovery pin, in which a reverse recovery pin is arranged. At the initial position of the door 1 rotation, the reverse return pin is located in the range of the side of the rotating seat in the axial direction, and is limited by the rotating seat. After the door 1 rotates to leave the initial position, the reverse return pin is located in the axial direction Outside the range of the side of the seat, the shaft seat of the door baffle 2 is provided with a plane limit protrusion 12 in the direction of rotation of the hatch; the upper corner of the hatch 1 and the corresponding position of the door baffle 2 are provided with a transportation insurance hole, A transport safety pin 10 is provided in the transport safety hole, and a boss structure is provided on the inner side of the cabin door 1; the spring mechanism includes a push plate 7 and a compression spring 8, and the push plate 7 and the internal slide rail of the frame form a sliding pair, and the two ends of the compression spring 8 Respectively stuck in the draw-in slots on the push plate 7 and the rear cover 6; the unlocking mechanism includes an electromagnet 9 and an electromagnet adsorption piece, the electromagnet 9 is arranged on the top of the upper cover 5, close to the door baffle 2, and the electromagnet The adsorption part is arranged on the cabin door 1, and its position is opposite to that of the electromagnet 9;

The anti-reversing pin is composed of a pin shaft, a pin head, a movable pin seat, a fixed pin seat and a spring. The two ends of the pin shaft are respectively fixed with a pin head and a fixed pin seat, and a movable pin seat is slid on the pin shaft. On the pin shaft, the two ends are respectively in contact with the pin head and the movable pin seat, and the movable pin seat is fixedly arranged in the mounting hole of the reversing return pin;

Transport insurance pin 10 is made of bolt and nut, utilizes threaded connection to overcome the thrust that stage clip 8 produces to cabin door;

There are mechanical interfaces 13 for bolt connection on both sides of the bottom plate 3, which are used for mechanical connection between the device and the platform;

There are round holes on the push plate 7 and the back cover 6, and the size of the round holes is larger than the protruding part of the satellite;

The push plate 7 is provided with lugs on the symmetrical sides, and the lugs are limited by the door stop plate 2 in the sliding direction of the push plate 7. The support ears do not affect the sliding of the push plate 7 in the device, but they exceed the door stop plate 2. The opening part will be blocked by the door stopper 2 during further movement;

The device is connected to the launch vehicle platform through a mechanical interface, and can undertake the carrying and launching of three 1Us or a combination of a single 1U and 2U or one 3U or 3U+;

In order to adapt to the carrying capacity of the rocket carrier platform, in the present embodiment, the maximum compression height of stage clip 8+lengths of three 1U satellites+the thickness of the boss structure behind the cabin door 1=the internal total length of the launching device, the internal width of the launching device and a 1U satellite The width of the launching device matches the height of a 1U satellite.

Claims (7)

1. a kind of integral track formula cube star launcher, it is characterized in that: comprise main frame, spring mechanism, unlocking mechanism; Main frame comprises cabin door (1), door catch plate (2), base plate (3), side plate ( 4), the upper cover (5) and the rear cover (6), the side plates (4) are symmetrically installed on both sides of the bottom plate (3), the upper cover (5) is installed above the side plate (4), and the four plates are Thin bosses (11) are symmetrically distributed on the long axis, and slide rails are formed in pairs, and door baffles (2) and rear cover plates (6) are fixedly arranged at the front and back of the frame, and the bottom ends of the door baffles (2) exceed the bottom plate (3 ) is provided with a shaft seat, the shaft seat is fixedly provided with a door rotation shaft, the door (1) rotates through the rotation seat at the inner bottom end of the door and the door rotation shaft, and the shaft at the bottom edge of the door baffle (2) The position parallel to the rotation axis and staggered on the seat is provided with an anti-recovery pin installation hole, which is provided with an anti-recovery pin, and the anti-recovery pin is perpendicular to the side of the rotary seat of the hatch (1) In the initial section position, the anti-return pin is axially located within the range of the side of the rotating seat, and is limited by the rotating seat. Outside the scope of the side, the shaft seat of the door baffle (2) is provided with a plane limit protrusion (12) in the direction of rotation of the hatch; A transportation safety hole is provided, and a transportation safety pin (10) is arranged in the transportation safety hole, and a boss structure is arranged on the inner side of the cabin door (1); the spring mechanism includes a push plate (7), a clip spring (8), and the push plate ( 7) It forms a sliding pair with the slide rail inside the frame, and the two ends of the compression spring (8) are respectively stuck in the slots on the push plate (7) and the rear cover (6); the unlocking mechanism includes an electromagnet (9) and an electromagnet The adsorption part, the electromagnet (9) is arranged on the top of the upper cover (5), close to the door baffle (2), the electromagnet adsorption part is arranged on the cabin door (1), and its position is the same as that of the electromagnet (9). Relatively, wherein, stage clip (8) maximum compression height+satellite length+cabin door (1) the thickness of the boss structure=launcher internal total length, the width inside the launcher matches the width of satellite. 2. The integral orbital cubesat launching device according to claim 1, characterized in that: the reverse return pin is made up of a pin shaft, a pin head, a movable pin seat, a fixed pin seat and a spring, and the two ends of the pin shaft The pin head and the fixed pin seat are fixed respectively, the movable pin seat is slid on the pin shaft, the spring is sleeved on the pin shaft, and the two ends are respectively in contact with the pin head and the movable pin seat, and the movable pin seat is fixedly arranged on the anti-restoration pin installation. inside the hole. 3. The integral orbiting cubesat launching device according to claim 1, characterized in that: the transportation safety pin (10) is made of bolts and nuts. 4. The integral orbiting cubesat launching device according to claim 1, characterized in that: there are mechanical interfaces (13) for bolt connection on both sides of the base plate (3). 5. The integral orbiting CubeSat launching device according to claim 1, characterized in that: said push plate (7) and the back cover (6) are provided with round holes, and the size of the round holes is larger than the protruding part of the satellite . 6. The integral orbital cubesat launching device according to claim 1, characterized in that: said push plate (7) is provided with lugs on symmetrical sides, and the lugs are on the sliding direction of push plate (7) It is limited by the door baffle (2). 7. The integral orbiting CubeSat launching device according to claim 1, characterized in that: the hatch (1) is provided with a torsion spring in the direction of rotation.