A micro / nano satellite launcher unlocking and separation mechanism

Abstract

This invention discloses a micro / nano satellite-rocket unlocking and separation mechanism, comprising a central rotating wheel structure, N extended sliding arms, and N satellite locking and release structures. Each extended sliding arm is connected at one end to the central rotating wheel structure and at the other end to a satellite locking and release structure. The central rotating wheel structure controls multiple linkages to achieve synchronous opening and closing. The satellite locking and release structures use steel balls for locking and releasing to prevent premature ejection of the satellite and have a high load-bearing capacity. This invention proposes a method for solving the satellite separation speed and separation force values ​​to address the requirements of satellite-rocket separation speed. This unlocking and separation mechanism has high synchronization, high load capacity, light weight, small size, and high reliability, ensuring the safe separation of the satellite from the rocket after entering orbit.

Description

Technical Field

[0001] This invention relates to the field of satellite launch technology, and in particular to a micro / nano satellite launch vehicle unlocking and separation mechanism. Background Technology

[0002] In recent years, with the continuous advancement of aerospace technology, the complexity of spacecraft launch missions and the demands for reliability have been constantly increasing. In various aerospace missions such as satellite launches, manned spaceflight, and deep space exploration, the separation process between the spacecraft and the rocket is crucial. As a key component connecting the rocket and the spacecraft, the spacecraft separator must ensure the safety, accuracy, and smooth separation of the spacecraft, avoiding damage to the spacecraft and its critical equipment. Currently, most existing spacecraft separators on the market employ complex mechanical structures and pyrotechnic devices, achieving separation through explosive bolts, springs, pneumatics, etc. While these traditional separators can complete the separation task in most cases, they have some potential problems, such as: numerous parts, complex structure, use of pyrotechnic devices, non-reusability, and high maintenance and repair difficulty. Therefore, designing a spacecraft separator with a simple structure, fewer parts, no need for pyrotechnic devices, and reusability has become an important direction in modern aerospace technology research. Such a separator can not only reduce manufacturing costs but also improve the reliability and economy of aerospace missions. Summary of the Invention

[0003] This invention proposes a micro / nano satellite launch vehicle unlocking and separation mechanism, which has the following significant advantages: high synchronization, fewer parts, simple structure, reducing complex mechanical and electrical systems; non-pyrotechnic separation, avoiding safety hazards caused by pyrotechnic devices; reusable, effectively reducing the overall cost of space missions and improving the long-term reliability of the equipment.

[0004] To achieve the objectives outlined above, the technical solution adopted in this invention is as follows: a micro / nano satellite launcher unlocking and separation mechanism, comprising a central rotating wheel structure, N extended sliding arms, and N satellite locking and releasing structures, where N ≥ 1. Each extended sliding arm is connected at one end to the central rotating wheel structure and at the other end to a satellite locking and releasing structure. The central rotating wheel structure controls multiple linkages to achieve synchronous opening and closing; the satellite locking and releasing structures use steel balls for locking and releasing, preventing premature ejection of the satellite and possessing a high load-bearing capacity.

[0005] Each extended sliding arm includes a connecting rod and a fixed frame. The top surface of the fixed frame is provided with several slots, and the connecting rod is set in the slots and can slide along the fixed frame. One end of the fixed frame is fixedly connected to the central rotating wheel structure, and the other end is provided with a mounting base for installing the satellite locking and releasing structure.

[0006] The present invention has the following beneficial effects:

[0007] (1) The central rotating wheel structure controls multiple links, which has high synchronization, fewer parts, and simple structure, reducing complex mechanical and electrical systems.

[0008] (2) The separation method adopts a purely mechanical structure for non-pyrotechnic separation, which avoids the safety hazards caused by pyrotechnic devices.

[0009] (3) It is reusable, which effectively reduces the overall cost of space missions and improves the long-term reliability of equipment.

[0010] (4) This structure adopts a center-radiating structure, which has a significant lightweight advantage compared to the traditional slotted structure, such as... Figure 7 As shown, based on the principle that the sum of the two sides of a triangle is greater than the third side, a+b>f, c+d>e, this invention can theoretically use less material.

[0011] The objectives, features, and advantages described above, as well as the working principle of the present invention, will now be described and explained in detail with reference to the accompanying drawings. Attached Figure Description

[0012] Figure 1 This is an overall schematic diagram of the locked state of the micro / nano satellite launcher unlocking and separation mechanism of the present invention.

[0013] Figure 2 This is an exploded schematic diagram of the central rotating wheel structure of the micro / nano satellite launcher unlocking and separation mechanism of the present invention.

[0014] Figure 3 This is a schematic cross-sectional view of the central rotating wheel structure of the micro / nano satellite launcher unlocking and separation mechanism of the present invention.

[0015] Figure 4 This is an exploded schematic diagram of the steel ball locking and unlocking structure of the micro-nano satellite launch vehicle unlocking and separation mechanism of the present invention.

[0016] Figure 5 This is a cross-sectional schematic diagram of the steel ball locking and unlocking structure of the micro-nano satellite launcher unlocking and separation mechanism of the present invention.

[0017] Figure 6 This is an assembly view of the extended sliding arm of the micro / nano satellite launcher unlocking and separation mechanism of the present invention.

[0018] Figure 7 This is a diagram illustrating the lightweight principle of the satellite and rocket unlocking and separation mechanism of this invention. Detailed Implementation

[0019] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0020] Combination Figures 1-6A micro / nano satellite launcher unlocking and separation mechanism includes a central rotating wheel structure, N extended sliding arms, and N satellite locking and releasing structures, where N ≥ 1. Each extended sliding arm is connected to the central rotating wheel structure at one end and to a satellite locking and releasing structure at the other end.

[0021] Each extended sliding arm includes a connecting rod 4-1 and a fixed frame 4-2. The top surface of the fixed frame 4-2 is provided with several slots 4-4. The connecting rod 4-1 is set in the slots 4-4 and can slide along the fixed frame 4-2. One end of the fixed frame 4-2 is fixedly connected to the central rotating wheel structure, and the other end is provided with a mounting base 4-3 for installing the satellite locking and releasing structure.

[0022] Mounting base 4-3 includes a second-stage fixed cylinder 4-3-1 with an increasing outer diameter from top to bottom, and a U-shaped groove 4-3-2 located on the outside of the second-stage fixed cylinder 4-3-1. The two ends of the U-shaped groove 4-3-2 are respectively provided with elongated oblique sliding holes. The second-stage fixed cylinder 4-3-1 is divided into a first fixed cylinder and a second fixed cylinder from top to bottom. The first fixed cylinder has at least 4 through holes distributed in a ring.

[0023] The central rotating wheel structure includes a central cam turntable 1, a main frame base 2, a pin puller 3, a torsion spring 7, and a retaining spring 8. The central cam turntable 1 consists of a turntable and a rotating cylinder set on the bottom surface of the turntable. The turntable has a central hole and N evenly distributed waist holes (1-1, 1-2) around the central hole. The rotating cylinder of the central cam turntable 1 is sleeved on the main frame base 2. The main frame base 2 consists of a base plate and a central cylinder 2-4 on the top surface of the base plate. The torsion spring 7 is sleeved on the central cylinder 2-4 of the main frame base 2 and is connected to the main frame base 2 by means of... The upper and lower end lugs are connected to the main frame base 2 and the central cam turntable 1. The base plate is also provided with a pin puller base 2-2. The top surface of the central cylinder 2-4 extends upward out of the center hole of the turntable and is fixed by a snap ring 8. One end of the connecting rod 4-1 is slidably engaged with the central cam turntable 1 through the waist hole 1-2. The pin puller 3 is connected to the turntable of the central cam turntable 1 through the pin puller base 2-2 to lock the turntable. One end of the fixing bracket 4-2 is fixedly connected to the base plate. The mounting base 4-3, the fixing bracket 4-2 and the base plate are manufactured as a whole.

[0024] The satellite locking and releasing structure includes a sliding sleeve 5, a satellite connecting post 6, a spring 10, a spring retainer 11, and several steel balls 9. The outer wall of the sliding sleeve 5 is provided with a pair of lugs 5-1. The sliding sleeve 5 is concentrically mounted on the outside of the second-stage fixed cylinder 4-3-1. The lugs 5-1 extend into the oblique sliding holes of the U-shaped slot 4-3-2. The top surface of the satellite connecting post 6 has a ring of flanges. The body of the satellite connecting post 6 is provided with a ring of steel ball mounting grooves 6-1. The satellite connecting post 6 is concentrically mounted inside the second-stage fixed cylinder 4-3-1. Each through hole of the first fixed cylinder is provided with a steel ball 9. The steel ball 9 contacts the sliding sleeve 5 and the steel ball mounting grooves 6-1 of the satellite connecting post 6 through the through hole. The spring 10 is installed inside the second-stage fixed cylinder 4-3-1. The top end is kept in a contracted state after being pressed down from top to bottom by the satellite connecting post 6. The bottom end is fixed by the spring retainer 11, which is fixed to the bottom plate of the second-stage fixed cylinder 4-3-1. The connecting rod 4-1 is fixedly connected to the U-shaped slot 4-3-2, and the two are manufactured as a single piece.

[0025] Furthermore, combined Figure 2 The end of the puller 3 is a retractable cylinder 3-1 that extends out and locks the waist hole 1-1.

[0026] Furthermore, combined Figure 2 The torsion spring 7 is installed in a right-hand rotation to ensure that the central cam turntable 1 rotates clockwise during operation.

[0027] Furthermore, combined Figure 2 and Figure 3 The snap ring 8 is fixedly installed in the spring groove 2-1 on the central cylinder 2-4 to limit the movement of the central cam turntable 1.

[0028] Furthermore, combined Figure 2 The top surface of one end of the connecting rod 4-1 is provided with a first boss, which is used to mate with the waist hole 1-2 on the turntable. The curve of the waist hole 1-2 radiates from the inside to the outside, ensuring that the direction of movement of the connecting rod 4-1 is contraction towards the center.

[0029] Furthermore, combined Figure 4 The ear 5-1 is installed in the oblique sliding hole of the U-shaped slot 4-3-2 after being rotated.

[0030] Furthermore, combined Figure 4 and Figure 5 The steel ball 9 is installed in the through hole of the second-order fixed cylinder 4-3-1. The outer side of the steel ball 9 is fixed and limited by the sliding sleeve 5, and the inner side is stuck in the steel ball mounting groove 6-1. The entire satellite locking and release structure is locked and cannot move.

[0031] Furthermore, combined Figure 4 and Figure 5The spring retainer 11 is fixed on the base plate of the second-stage fixed cylinder 4-3-1. The fixing lug 11-1 of the spring retainer 11 is fixed to the first coil of spring at the bottom of the spring 10 to prevent the spring 10 from popping out of the satellite locking and releasing structure after the pressure is released.

[0032] Furthermore, combined Figure 6 The connecting rod 4-1 is made of high-toughness spring steel. Several long grooves 4-5 are opened on the connecting rod 4-1. The grooves 4-5 can be retracted and installed in the slots 4-4 on the top surface of the fixed frame 4-2 after being subjected to upper and lower pressure.

[0033] The working principle of this invention is as follows: In the initial state, the micro-nano satellite launcher unlocking and separation mechanism is in a locked state. The telescopic cylinder 3-1 at the end of the puller 3 is kept extended and stuck in the waist hole 1-1 of the central cam turntable, so that the central cam turntable 1 is fixed and cannot rotate. The connecting rod 4-1 is fixed and cannot move with the central cam turntable 1. The sliding sleeve 5 is fixed and cannot move with the connecting rod 4-1. At the same time, the steel ball 9 fixed by the sliding sleeve 5 is locked and limited inside the through hole of the first fixed cylinder at the upper end of the second-stage fixed cylinder 4-3-1. Meanwhile, the torsion spring 7 and the spring 10 are in a compressed state. The entire micro-nano satellite launcher unlocking and separation mechanism is in a locked state, and all parts cannot move.

[0034] When the pin puller 3 receives the separation signal, the telescopic cylinder 3-1 at the end retracts, the torsion spring 7 is released, and the central cam turntable 1 rotates. The connecting rod 4-1 is limited by the fixing frame 4-2 and can only slide linearly. At the same time, the first protrusion on the top surface of one end of the connecting rod 4-1 retracts towards the center through the waist hole 1-2, and the hanging ear 5-1 moves downward through the oblique sliding hole of the U-shaped slot 4-3-2. The sliding sleeve 5 moves downward, the external limit of the steel ball 9 disappears and it can move outward. The spring 10 acts on the bottom, popping out the satellite connecting post 6. The separated satellites are completely separated through multiple satellite connecting posts 6.

[0035] This invention addresses the requirements for satellite-rocket separation velocity, proposing a relationship between satellite separation velocity and separation force values ​​that satisfies the following formula:

[0036]

[0037] In the formula, v is the satellite velocity, u is the initial velocity of the satellite, S is the displacement of spring 10, F is the force of spring 10, m is the mass of the satellite, and N is the number of extended sliding arms.

[0038] A separation method for a micro / nano satellite launch vehicle unlocking and separation mechanism, comprising the following steps:

[0039] Step 1: After the pin puller 3 receives the separation signal, the telescopic cylinder 3-1 at the end of the pin puller 3 retracts, the limit at the waist hole 1-1 of the central cam turntable disappears, the torsion spring 7 is released, and the central cam turntable 1 rotates counterclockwise.

[0040] Step 2: The connecting rod 4-1 on each extended sliding arm is limited by the fixed frame 4-2 and can only slide in a straight line. At the same time, the first boss on the top surface of one end of the connecting rod 4-1 retracts towards the center through the waist hole 1-2, and the hanging ear 5-1 moves downward through the oblique sliding hole of the U-shaped slot 4-3-2.

[0041] Step 3: In the satellite locking and releasing structure, the sliding sleeve 5 moves downward, the external limit of the steel ball 9 disappears and it can move outward, the spring 10 starts to work and releases pressure upward, popping out the upper satellite connecting column 6. The spring retainer 11 is fixed to the spring 10 to prevent the spring from detaching from the bottom plate of the second-order fixed cylinder 4-3-1. At this time, the separated satellites are completely separated through multiple satellite connecting columns 6.

[0042] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A micro / nano satellite launcher unlocking and separation mechanism, characterized in that: It includes a central rotating wheel structure, N extended sliding arms, and N satellite locking and releasing structures, where N≥1. Each extended sliding arm is connected to the central rotating wheel structure at one end and to a satellite locking and releasing structure at the other end. Each extended sliding arm includes a connecting rod (4-1) and a fixed frame (4-2). The top surface of the fixed frame (4-2) is provided with several slots (4-4). The connecting rod (4-1) is set in the slots (4-4) and can slide along the fixed frame (4-2). One end of the fixed frame (4-2) is fixedly connected to the central rotating wheel structure, and the other end is provided with a mounting base (4-3) for installing the satellite locking and releasing structure. The mounting base (4-3) includes a second-stage fixed cylinder (4-3-1) with an increasing outer diameter from top to bottom, and a U-shaped groove (4-3-2) located on the outside of the second-stage fixed cylinder (4-3-1). The two ends of the U-shaped groove (4-3-2) are respectively provided with elongated oblique sliding holes. The second-stage fixed cylinder (4-3-1) is divided into a first fixed cylinder and a second fixed cylinder from top to bottom. The first fixed cylinder has at least 4 through holes distributed in a ring. The satellite locking and releasing structure includes a sliding sleeve (5), a satellite connecting post (6), a spring (10), a spring retainer (11), and several steel balls (9). The outer wall of the sliding sleeve (5) is provided with a pair of lugs (5-1). The sliding sleeve (5) is concentrically mounted on the outside of the second-order fixed cylinder (4-3-1). The lugs (5-1) extend into the oblique sliding holes of the U-shaped slot (4-3-2). The satellite connecting post (6) has a ring of steel ball mounting grooves (6-1) on its shaft. The satellite connecting post (6) is concentrically mounted on the second-order fixed cylinder (4-3-1). 1) Inside, the spring (10) is installed inside the second-order fixed cylinder (4-3-1). The top end is kept in a contracted state after being pressed down from top to bottom by the satellite connecting column (6). The bottom end is fixed by the spring retainer (11). The spring retainer (11) is fixed to the bottom plate of the second-order fixed cylinder (4-3-1). The steel ball (9) is installed in the through hole of the second-order fixed cylinder (4-3-1). The outer side of the steel ball (9) is fixed and limited by the sliding sleeve (5), and the inner side is stuck in the steel ball mounting groove (6-1). The entire satellite locking and release structure is locked and cannot move.

2. The micro / nano satellite launcher unlocking and separation mechanism according to claim 1, characterized in that: The central rotating structure includes a central cam turntable (1), a main frame base (2), a pin puller (3), a torsion spring (7), and a retaining ring (8). The central cam turntable (1) consists of a turntable and a rotating cylinder set on the bottom surface of the turntable. The turntable has a central hole and N waist holes (1-1, 1-2) evenly distributed around the central hole. The rotating cylinder of the central cam turntable (1) is sleeved on the main frame base (2). The main frame base (2) consists of a base plate and a central cylinder (2-4) on the top surface of the base plate. The torsion spring (7) is sleeved on the central cylinder of the main frame base (2). On column (2-4), both ends of torsion spring (7) are connected to the main frame base (2) and the central cam turntable (1) at the same time. The base plate is also provided with a pin puller base (2-2). The top surface of the central cylinder (2-4) extends upward out of the center hole of the turntable and is fixed by a snap ring (8). One end of the connecting rod (4-1) is slidably engaged with the central cam turntable (1) through the waist hole (1-2). The pin puller (3) is connected to the turntable of the central cam turntable (1) through the pin puller base (2-2) to lock the turntable. One end of the fixing bracket (4-2) is fixedly connected to the base plate.

3. The micro / nano satellite launcher unlocking and separation mechanism according to claim 2, characterized in that: The connecting rod (4-1) is made of high-toughness spring steel. Several long grooves (4-5) are opened on the connecting rod (4-1). The grooves (4-5) can be retracted and installed in the slots (4-4) on the top surface of the fixed frame (4-2) after being subjected to upper and lower pressure.

4. The micro / nano satellite launcher unlocking and separation mechanism according to claim 3, characterized in that: To address the required separation velocity between the satellite and the rocket, the relationship between the satellite separation velocity and the separation force is proposed to satisfy the following formula: In the formula, v is the satellite velocity, u is the initial velocity of the satellite, S is the displacement of the spring (10), F is the force of the spring (10), m is the mass of the satellite, and N is the number of extended sliding arms.

5. The separation method for the micro / nano satellite launch vehicle unlocking and separation mechanism according to any one of claims 1 to 4, characterized in that, The steps are as follows: Step 1: After the pin puller (3) receives the separation signal, the end of the pin puller (3) retracts, the limit at the waist hole (1-1) of the central cam turntable disappears, the torsion spring (7) is released, and the central cam turntable (1) is driven to rotate counterclockwise. Step 2: The connecting rod (4-1) on each extended sliding arm is limited by the fixed frame (4-2) and can only slide in a straight line. At the same time, the first protrusion on the top surface of one end of the connecting rod (4-1) retracts towards the center through the waist hole (1-2), and the hanging ear (5-1) moves downward through the oblique sliding hole of the U-shaped slot (4-3-2). Step 3: In the satellite locking and releasing structure, the sliding sleeve (5) moves downward, the external limit of the steel ball (9) disappears, the steel ball (9) moves outward, the spring (10) starts to work and releases pressure upward, popping out the upper satellite connecting column (6). The spring retainer (11) is fixed to the spring (10) to prevent the spring from detaching from the bottom plate of the second-order fixed cylinder (4-3-1). At this time, the separated satellites are completely separated through multiple satellite connecting columns (6).

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