Star-rocket unlocking and separating mechanism for micro-nano satellite

Abstract

The invention discloses a micro-nano satellite and rocket unlocking and separating mechanism which comprises a center rotating wheel structure, N extension sliding arms and N satellite locking and releasing structures, one end of each extension sliding arm is connected with the center rotating wheel structure, and the other end of each extension sliding arm is connected with one satellite locking and releasing structure; the central runner structure controls the plurality of connecting rods to realize synchronous opening and closing; the satellite locking and releasing structure adopts a steel ball for locking and releasing, so that the satellite is prevented from popping up in advance, and the satellite locking and releasing structure has higher loading capacity; the invention provides a satellite separation speed and separation force value solving method aiming at a satellite and rocket separation speed requirement; the unlocking separation mechanism is high in synchronism, large in load, light in weight, small in size, high in reliability and capable of ensuring that a satellite is safely separated from a rocket after entering an orbit.

Description

Technical Field

[0001] The present invention relates to the field of satellite launch technology, and in particular to a micro-nano satellite rocket unlocking and separation mechanism. Background Art

[0002] In recent years, with the continuous advancement of aerospace technology, the complexity of spacecraft launch missions and the requirements for reliability have continued to increase. In various aerospace missions such as satellite launch, manned space flight, and deep space exploration, the satellite-rocket separation process is crucial. As a key component connecting the rocket and the spacecraft, the satellite-rocket separator must ensure the safety, accuracy, and smoothness of the spacecraft during separation to avoid damage to the spacecraft and its key equipment. At present, most of the satellite-rocket separators available on the market use complex mechanical structures and pyrotechnic devices to achieve separation through explosive bolts, springs, pneumatics, etc. Although these traditional separators can complete the separation task in most cases, there are some potential problems, such as: more parts, complex structure, use of pyrotechnic devices, non-reusability, and difficulty in maintenance and overhaul. Therefore, how to design a satellite-rocket separator with a simple structure, few parts, no need for pyrotechnic devices, and reusable has become an important direction of modern spacecraft 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] The present invention proposes a micro-nano satellite rocket unlocking and separation mechanism, which has the following significant advantages: high synchronization, few parts, simple structure, and reduction of complex mechanical and electrical systems; non-pyrotechnic separation, avoiding the safety hazards caused by pyrotechnic devices; reusable, effectively reducing the overall cost of space missions, and improving the long-term use reliability of the equipment.

[0004] In order to achieve the above-outlined purpose, the technical solution adopted by the present invention is as follows: a micro-nano satellite rocket unlocking and separation mechanism, including a central rotating wheel structure, N extended sliding arms and N satellite locking and releasing structures, N ≥ 1, each extended sliding arm is connected to the central rotating wheel structure at one end, and connected to a satellite locking and releasing structure at the other end. The central rotating wheel structure controls multiple connecting rods to achieve synchronous opening and closing; the satellite locking and releasing structure uses steel balls for locking and releasing to prevent the satellite from being ejected prematurely, and has a high load capacity.

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

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

[0007] (1) The center wheel structure controls multiple connecting rods, has high synchronization, few parts, simple structure, and reduces complex mechanical and electrical systems.

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

[0009] (3) Reusability effectively reduces the overall cost of space missions and improves the long-term reliability of equipment.

[0010] (4) This structure adopts a central radial structure, which has a higher lightweight advantage than the traditional slot-type structure. Figure 7 As shown, according to the principle that the sum of two sides of a triangle is greater than the third side, a+b>f, c+d>e, the present invention can use less material in principle.

[0011] The above-described objects, features and advantages as well as the working principle of the present invention will be described and explained in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0013] Figure 2 It is a schematic diagram of the explosion of the central rotor structure of the micro-nano satellite rocket unlocking and separation mechanism of the present invention.

[0014] Figure 3 It is a schematic cross-sectional view of the central rotor structure of the micro-nano satellite rocket unlocking and separation mechanism of the present invention.

[0015] Figure 4 It is a schematic diagram of the explosion of the steel ball locking and unlocking structure of the micro-nano satellite rocket unlocking and separation mechanism of the present invention.

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

[0018] Figure 7 It is an explanatory diagram of the lightweight principle of the satellite and rocket unlocking and separation mechanism of the present invention. DETAILED DESCRIPTION

[0019] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0020] Combination Figure 1 to Figure 6A micro-nano satellite rocket unlocking and separation mechanism includes a central rotating wheel structure, N extended sliding arms and N satellite locking and releasing structures, N ≥ 1, and 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 fixing frame 4-2. A plurality of slots 4-4 are provided on the top surface of the fixing frame 4-2. The connecting rod 4-1 is arranged in the slot 4-4 and can slide along the fixing frame 4-2. One end of the fixing frame 4-2 is fixedly connected to the central rotating wheel structure, and the other end is provided with a mounting seat 4-3 for installing the satellite locking and releasing structure.

[0022] The mounting seat 4-3 includes a second-order fixed cylinder 4-3-1 with an outer diameter increasing from top to bottom, and a U-shaped slot 4-3-2 located on the outside of the second-order fixed cylinder 4-3-1, and long inclined sliding holes are respectively provided at both ends of the U-shaped slot 4-3-2. The second-order fixed cylinder 4-3-1 is divided into a first fixed cylinder and a second fixed cylinder from top to bottom, and at least 4 through holes are distributed in a ring shape on the first fixed cylinder.

[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 includes a turntable and a rotating cylinder arranged on the bottom surface of the turntable. The turntable is provided with a central hole and N waist holes 1-1 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 is composed of a bottom plate and a central cylinder 2-4 on the top surface of the bottom plate. The torsion spring 7 is sleeved on the central cylinder 2-4 of the main frame base 2 and is connected to the central cylinder 2-4 of the main frame base 2 through the upper and lower ends. The hanging ear is connected to the main frame base 2 and the center cam turntable 1 at the same time. A pin puller base 2-2 is also provided on the bottom plate. The top surface of the center cylinder 2-4 extends upward from the center hole of the turntable and is fixed by a retaining spring 8. One end of the connecting rod 4-1 slides with the center cam turntable 1 through the waist hole 1-1. The pin puller 3 is connected to the turntable of the center cam turntable 1 through the pin puller base 2-2 and is used to lock the turntable. One end of the fixing frame 4-2 is fixedly connected to the bottom plate, and the mounting seat 4-3, the fixing frame 4-2 and the bottom plate are manufactured integrally.

[0024] The satellite locking and releasing structure comprises a sleeve 5, a satellite connecting column 6, a spring 10, a spring retainer 11 and a plurality of steel balls 9. A pair of ears 5-1 are provided on the outer wall of the sleeve 5. The sleeve 5 is concentrically installed on the outer side of the second-order fixed cylinder 4-3-1. The ears 5-1 extend into the oblique sliding hole of the U-shaped slot 4-3-2. The top surface of the satellite connecting column 6 has a circle of flanges. A circle of steel ball mounting grooves 6-1 are provided on the column body of the satellite connecting column 6. The satellite connecting column 6 is concentrically installed in the second-order fixed cylinder 4-3-1. A steel ball 9 is provided in each through hole of the first fixed cylinder. The steel ball 9 contacts with the sleeve 5 and the steel ball mounting groove 6-1 of the satellite connecting column 6 through the through hole at the same time. The spring 10 is installed in the second-order fixed cylinder 4-3-1. The top end is kept in a contracted state after being subjected to the pressure from the satellite connecting column 6 from top to bottom. 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 connecting rod 4-1 is fixedly connected to the U-shaped slot 4-3-2, and the two are manufactured in one piece.

[0025] Furthermore, combined with Figure 2 The telescopic cylinder 3-1 at the end of the pin puller 3 extends out to clamp the waist hole 1-1.

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

[0027] Furthermore, combined with Figure 2 and Figure 3 The retaining spring 8 is fixedly installed at the spring groove 2-1 on the central cylinder 2-4 to limit the central cam turntable 1.

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

[0029] Furthermore, combined with Figure 4 The hanging ear 5-1 is installed in the inclined sliding hole of the U-shaped card slot 4-3-2 by rotation.

[0030] Furthermore, combined with 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 installation groove 6-1. The entire satellite locking and release structure is locked and cannot move.

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

[0032] Furthermore, combined with Figure 6 The connecting rod 4-1 is made of high-toughness spring steel, and a plurality of long strip waist grooves 4-5 are formed on the connecting rod 4-1. The waist grooves 4-5 can be contracted and installed in the card slots 4-4 on the top surface of the fixing frame 4-2 after being subjected to upper and lower pressures.

[0033] The working principle of the present invention is as follows: in the initial state, the micro-nano satellite rocket unlocking and separation mechanism is in a locked state, and the retractable cylinder 3-1 at the end of the pin puller 3 remains 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 and the central cam turntable 1 are fixed and cannot move, the sliding sleeve 5 and the connecting rod 4-1 are fixed and cannot move, and at the same time, the sliding sleeve 5 fixes the steel ball 9 in the through hole of the first fixed cylinder at the upper end of the second-order fixed cylinder 4-3-1 to lock the limiting satellite connecting column 6, and at the same time, the torsion spring 7 and the spring 10 are in a compressed state, and the entire micro-nano satellite rocket 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 contracts, 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 boss on the top surface of one end of the connecting rod 4-1 contracts toward the center through the waist hole 1-1, and the hanging ear 5-1 moves downward through the oblique sliding hole of the U-shaped card slot 4-3-2. The sliding sleeve 5 moves downward, the external limit of the steel ball 9 disappears and can move outward, and the spring 10 acts on the bottom to pop out the satellite connection column 6. The separated satellite is completely separated through multiple satellite connection columns 6.

[0035] In view of the separation speed requirement of the satellite and the rocket, the present invention proposes that the relationship between the satellite separation speed and the separation force value satisfies the following formula:

[0036]

[0037] Wherein, 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 satellite mass, and N is the number of extended sliding arms.

[0038] A separation method of a micro-nano satellite rocket unlocking and separation mechanism, the steps are as follows:

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

[0040] Step 2: The connecting rod 4-1 on each extended sliding arm is limited by the fixing 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 shrinks toward the center through the waist hole 1-1, and the hanging ear 5-1 moves downward through the inclined sliding hole of the U-shaped slot 4-3-2.

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

[0042] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments. The above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A micro-nano satellite rocket unlocking and separation mechanism, characterized by: It includes a central rotating wheel structure, N extended sliding arms and N satellite locking and releasing structures, N ≥ 1, and 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 comprises a connecting rod (4-1) and a fixing frame (4-2); a plurality of slots (4-4) are provided on the top surface of the fixing frame (4-2); the connecting rod (4-1) is arranged in the slots (4-4) and can slide along the fixing frame (4-2); one end of the fixing frame (4-2) is fixedly connected to the central rotating wheel structure, and the other end is provided with a mounting seat (4-3) for mounting a satellite locking and releasing structure.

2. The micro-nano satellite rocket unlocking and separation mechanism according to claim 1 is characterized in that: The mounting seat (4-3) comprises a second-order fixed cylinder (4-3-1) whose outer diameter increases from top to bottom, and a U-shaped slot (4-3-2) located outside the second-order fixed cylinder (4-3-1), and long strip-shaped oblique sliding holes are respectively arranged at both ends of the U-shaped slot (4-3-2). The second-order fixed cylinder (4-3-1) is divided into a first fixed cylinder and a second fixed cylinder from top to bottom, and at least four through holes are distributed in an annular shape on the first fixed cylinder.

3. The micro-nano satellite rocket unlocking and separation mechanism according to claim 2 is characterized by: The central rotating wheel structure comprises a central cam rotating table (1), a main frame base (2), a pin puller (3), a torsion spring (7), and a retaining spring (8). The central cam rotating table (1) comprises a rotating disk and a rotating cylinder arranged on the bottom surface of the rotating disk. The rotating disk is provided with a central hole and N waist holes (1-1) evenly distributed around the central hole. The rotating cylinder of the central cam rotating table (1) is sleeved on the main frame base (2). The main frame base (2) is composed of a bottom plate and a central cylinder (2-4) on the top surface of the bottom plate. The torsion spring (7) is sleeved on the central cylinder (2-4) of the main frame base (2). 2-4), both ends of the torsion spring (7) are connected to the main frame base (2) and the center cam turntable (1) at the same time, a pin puller base (2-2) is also provided on the bottom plate, the top surface of the center cylinder (2-4) extends upward from the center hole of the turntable and is fixed by a retaining ring (8), one end of the connecting rod (4-1) is slidably matched with the center cam turntable (1) through the waist hole (1-1), the pin puller (3) is connected to the turntable of the center cam turntable (1) through the pin puller base (2-2) for locking the turntable, and one end of the fixing frame (4-2) is fixedly connected to the bottom plate.

4. The micro-nano satellite rocket unlocking and separation mechanism according to claim 3 is characterized by: The satellite locking and releasing structure comprises a sliding sleeve (5), a satellite connecting column (6), a spring (10), a spring fixer (11) and a plurality of steel balls (9). A pair of hanging ears (5-1) are arranged on the outer wall of the sliding sleeve (5). The sliding sleeve (5) is coaxially mounted on the outer side of a second-order fixed cylinder (4-3-1). The hanging ears (5-1) extend into the oblique sliding hole of the U-shaped card slot (4-3-2). A circle of steel ball mounting grooves (6-1) are arranged on the column body of the satellite connecting column (6). The satellite connecting column (6) is coaxially mounted on the second-order fixed cylinder (4-3-1). 1), a spring (10) is installed in a second-order fixed cylinder (4-3-1), the top end is kept in a contracted state after being subjected to pressure from the satellite connecting column (6) from top to bottom, the bottom end is fixed by a spring fixer (11), the spring fixer (11) is fixed to the bottom plate of the second-order fixed cylinder (4-3-1), a steel ball (9) is installed in a through hole of the second-order fixed cylinder (4-3-1), the outer side of the steel ball (9) is fixed and limited by a sliding sleeve (5), and the inner side is stuck in the steel ball installation groove (6-1), so that the entire satellite locking and releasing structure is locked and cannot move.

5. The micro-nano satellite rocket unlocking and separation mechanism according to claim 4 is characterized in that: The connecting rod (4-1) is made of high-toughness spring steel. A plurality of long strip waist grooves (4-5) are formed on the connecting rod (4-1). The waist grooves (4-5) can be contracted and installed in the clamping grooves (4-4) on the top surface of the fixing frame (4-2) under the pressure from the upper and lower sides.

6. The micro-nano satellite rocket unlocking and separation mechanism according to claim 1 is characterized by: According to the separation speed requirement of satellite and rocket, the relationship between satellite separation speed and separation force value satisfies the following formula: Where 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 satellite mass, and N is the number of extended sliding arms.

7. The separation method of the micro-nano satellite rocket unlocking and separation mechanism according to any one of claims 1 to 6, characterized in that: Here are the steps: Step 1: After the pin puller (3) receives the separation signal, the end of the pin puller (3) contracts, the limit at the waist hole (1-1) of the central cam turntable disappears, and the torsion spring (7) is released, driving the central cam turntable (1) to rotate counterclockwise; Step 2: The connecting rod (4-1) on each extended sliding arm is limited by the fixing 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) shrinks toward the center through the waist hole (1-1), and the hanging ear (5-1) moves downward through the inclined sliding hole of the U-shaped slot (4-3-2); Step 3: The sliding sleeve (5) in the satellite locking and releasing structure moves downward, the external limit of the steel ball (9) disappears, the steel ball (9) moves outward, and the spring (10) starts to work to release the pressure upward, popping out the upper satellite connecting column (6). The spring fixer (11) and the spring (10) are fixed to prevent the spring from detaching from the bottom plate of the second-stage fixed cylinder (4-3-1). At this time, the separated satellite is completely separated through multiple satellite connecting columns (6).

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