CN117585199B - One-arrow-multi-satellite separation system and method for releasing satellites one by one - Google Patents
One-arrow-multi-satellite separation system and method for releasing satellites one by one Download PDFInfo
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- CN117585199B CN117585199B CN202410069390.1A CN202410069390A CN117585199B CN 117585199 B CN117585199 B CN 117585199B CN 202410069390 A CN202410069390 A CN 202410069390A CN 117585199 B CN117585199 B CN 117585199B
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- 238000000926 separation method Methods 0.000 title claims abstract description 70
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- 238000004804 winding Methods 0.000 claims description 6
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 claims description 4
- 229910052982 molybdenum disulfide Inorganic materials 0.000 claims description 4
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 229910000677 High-carbon steel Inorganic materials 0.000 claims description 3
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/641—Interstage or payload connectors
Abstract
The invention provides an arrow multi-satellite separation system and method for releasing satellites one by one, and belongs to the technical field of satellite launching. Solves the problem that the prior one-arrow multi-star separation is easy to collide with each other. The separating system comprises a star body, a spring device, a separating support, pulleys, locking pins, kevlar pull ropes, pin pullers and carrying adapters, wherein the star body is arranged in a plurality of layers according to each layer, the separating support is arranged in a mode of arranging a plurality of layers along the axial direction of the carrying adapters, the separating support is connected with the spring device, a guide groove is spliced with a guide post, the positions of a first pin hole and a second pin hole coincide, the locking pins are inserted into the first pin hole and the second pin hole, one end of each Kevlar pull rope is connected to one locking pin of the star body, the other end of each Kevlar pull rope penetrates through an auxiliary pulley in the middle and is wound on a fixed pulley at the bottom end of each adjacent star body, all the star bodies are connected in sequence through the Kevlar pull ropes, and the locking pins of the last star body are connected with the pin pullers. It is mainly used for one-arrow multi-star system to release satellites one by one.
Description
Technical Field
The invention belongs to the technical field of satellite launching, and particularly relates to an arrow multi-satellite separation system and method capable of releasing satellites one by one.
Background
In recent years, with the continuous development of the low-orbit broadband internet technology, the construction of a low-orbit constellation system gradually becomes a research focus in the aerospace field. These constellations often require hundreds or even tens of thousands. Aiming at the emission requirement of satellites of the order of magnitude, one arrow and multiple satellites become an important way for reducing the constellation construction cost. The multiple satellites can be sent into space by one rocket, so that the carrying efficiency is remarkably improved, and the launching cost is reduced.
Currently, common one-arrow-multiple-star approaches include: multi-star dispenser and stacked.
A multi-star dispenser is a multi-star dispenser in which a plurality of satellites are mounted to a central carrier or other form of multi-star dispenser. This approach has the following drawbacks: 1. the multi-satellite distributor type central bearing barrel needs to bear the weight of a plurality of satellites, has higher strength and rigidity and correspondingly larger volume and weight, so that the available envelope and weight of the satellites are greatly reduced. 2. The problem of the multiple satellite dispenser, which requires a separate unlocking signal for each satellite, is that the number of satellites that a rocket can carry is directly limited by the large amount of electrical interface resources that are required for carrying. 3. Each satellite of the multi-satellite distributor needs a whole set of separation unlocking devices, and the use of initiating explosive devices in each set of unlocking devices can increase the carrying cost and the ground test cost.
The stacked type multi-satellite distributor is characterized in that a plurality of satellites are stacked and distributed in the fairing, a multi-satellite distributor with large volume and large weight is omitted, the space utilization rate in the fairing is improved, and the following defects exist in the traditional stacked type: 1. by adopting the traditional stacking type of releasing satellites one by one, each satellite also needs to have a separate unlocking signal and a fire-division unlocking device, so that the problems II and III of the multi-satellite distributor are also existed; meanwhile, because satellites are directly stacked, a central bearing cylinder and the like do not penetrate through the upper and lower structures, the unlocking signal cable is difficult to find a layout fixed position, and the cable wiring difficulty is high. 2. The stacking type satellite unlocking and releasing all satellites at one time is adopted to avoid the problems, but the satellites released by the same layer have the risk of extremely collision with each other in the separation process, and the problem greatly limits the layout quantity of the satellites of the same layer, so that the existing stacking type satellite unlocking and releasing device is mainly stacked up and down, the layout quantity of the satellites in the same layer is extremely small, and single satellites or double satellites are usually used as the main satellites; meanwhile, even if a single-layer single-star stacking mode is adopted, satellites stacked one above the other can collide with each other due to spin after being separated on the premise of carrying at a certain angular velocity.
Disclosure of Invention
In view of the above, the present invention aims to provide an arrow multi-satellite separation system and a separation method for releasing satellites one by one, so as to solve the problem that the existing arrow multi-satellite separation is easy to collide with each other.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the utility model provides a many stars of arrow piece-by-piece release satellite's separation system, it includes star body, spring assembly, separation support, pulley, locking pin, kevlar stay cord, pin puller and delivery adapter, spring assembly includes spring, guide holder, inner skleeve and outer sleeve, be provided with the guide post on the guide holder, first pinhole has been seted up to the guide post side, the spring housing is on the guide post, the inner skleeve presses at the spring upper surface, makes the guide post pass the guiding hole on the inner skleeve, the outer sleeve suit is on the inner sleeve, the outer sleeve bottom links to each other with the guide holder, be provided with the guide slot that link up on the separation support, the second pinhole has been seted up to separation support side, the pulley divide into the auxiliary pulley and the fixed pulley that the structure is the same, four spring assembly and two auxiliary pulleys of top surface installation of star body, a plurality of spring assembly and auxiliary pulley of top surface installation of delivery adapter, the star body sets up a plurality of setting up a plurality of according to every layer, and makes the guide post pass the guide slot on the guide post and the inner sleeve, the pin puller is located the guide pin, and the pin puller is in the same with the top surface, the pin puller is located the pin hole with the second, and the same end is kept in the same with the position in succession with the adjacent one end, and the pin puller is kept in the pin hole, and the same.
Further, the star bodies on the same layer are sequentially connected through Kevlar ropes, and the locking pin of the last star body on the same layer is connected with a pin puller.
Further, four auxiliary pulleys are arranged on the side face of the last star body of each layer, two auxiliary pulleys are arranged on the top face of the last star body of each layer, the last star body of the uppermost layer is connected with the locking pin of the last star body of the uppermost layer after the locking pin of the last star body of the same layer is connected with the Kevlar rope.
Still further, the pulley includes pulley wheel body, pulley support, pivot and pivot nut, the pivot passes behind the mounting hole of pulley support, pulley wheel body in succession and passes through the pivot nut fixed, the through-hole has been seted up on the pulley wheel body, the Kjeldahl rope passes through the through-hole fixedly.
Furthermore, the locking pin is made of high-carbon steel, and molybdenum disulfide is smeared on the surfaces of the locking pin, the mounting hole and the rotating shaft.
Still further, the star body includes main frame, roof, bottom plate and four curb plates, roof and bottom plate are installed respectively in the top and the bottom of main frame, four curb plates are installed respectively around the side direction of main frame, the bilateral symmetry of star body is provided with expansion solar wing.
Furthermore, two hinges and two compression points are arranged on the expansion solar wing, the two hinges are connected with the star body, and the two compression points are compressed with the star body.
Furthermore, the main frame comprises two frame plates and four side frames, two ends of the four side frames are respectively connected with four corners of the two frame plates, nuts are stuck to the back surfaces of the frame plates and the side frame mounting holes, and the top plate, the bottom plate and the four side plates are connected to the main frame through the cooperation of screws and the nuts.
Furthermore, the frame plate and the side frames are made of carbon fibers, raised reinforcing ribs are arranged on the frame plate, the side frames are of L-shaped structures, and the top plate, the bottom plate and the side plates are honeycomb plates.
The invention also provides a separation method of the one-arrow-multi-satellite separation system for releasing satellites one by one, which comprises the following steps: applying an unlocking signal to a pin puller positioned at the uppermost layer, unlocking the star body by the pin puller, and enabling the star body to fly upwards as a first released and separated star body under the thrust of a spring device; when the winding part of the Kevlar stay rope is released, the star body continuously flies upwards to pull out a locking pin connected with the tail end of the Kevlar stay rope, and at the moment, the latter star body is unlocked and separated and released; the latter star body is separated upwards and unlocked again, and the last star body is repeatedly moved until all the star bodies are unlocked and separated.
Compared with the prior art, the invention has the beneficial effects that: the invention provides an arrow multi-satellite separation system and a separation method for releasing satellites one by one, which can realize the effects of unlocking once and releasing and separating the satellites one by one, so that the satellites are prevented from collision with each other in the separation process on the premise of reducing the resource requirements of the satellites on a carrying electric interface, the number of the satellites which can be laid out on the same layer is increased, and the carrying efficiency is further improved.
The one-arrow-multiple-star separation system for releasing satellites one by one adopts a satellite stacking mode, so that the waste of carrying available envelopes and weight caused by a multiple-star distributor is avoided.
The one-arrow-multiple-star separation system adopts a mode of releasing satellites one by once unlocking, avoids the waste of electric interface resources caused by providing independent unlocking signals for single satellites, and also avoids the difficult problem of layout of cables for stacking the satellites with complex unlocking signals.
The one-arrow-multiple-satellite separation system adopts a mode of releasing satellites one by once unlocking, and after the previous satellite is far away from the satellite group, the next satellite is separated and unlocked again, so that collision of adjacent released satellites in the separation process is avoided.
According to the one-arrow multi-satellite separation system, only two unlocking devices are needed for unlocking all satellites in a whole layer or the whole system, so that the carrying cost and the ground test cost caused by unlocking a large amount of initiating explosive devices are reduced.
The one-arrow-multiple-star separation system has the advantages of simple design of each component, small size of parts, lower precision requirement, low processing cost and short processing period.
The one-arrow multi-star separation system can be repeatedly unlocked, and the ground test cost is reduced. All parts are mutually independent, secondary design and model selection can be carried out according to specific satellite requirements, and the device has strong adaptability.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of the overall structure of an arrow multi-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 2 is a schematic diagram of a partial construction of an arrow multi-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 3 is a schematic diagram of an explosive structure of a star body assembly according to the present invention;
FIG. 4 is a schematic view of an explosion structure of a main frame assembly according to the present invention;
FIG. 5 is a schematic view of an exploded view of a spring assembly according to the present invention;
FIG. 6 is a schematic cross-sectional view of a spring device in a compressed state according to the present invention;
FIG. 7 is a schematic cross-sectional view of a spring device in a released state according to the present invention;
FIG. 8 is a schematic view of a split support structure according to the present invention;
FIG. 9 is a schematic view of a pulley according to the present invention;
FIG. 10 is a schematic diagram of a single star body assembly according to the present invention;
FIG. 11 is a schematic diagram II of a single star body composition according to the present invention;
FIG. 12 is a schematic diagram showing an assembly process of an arrow-to-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 13 is a schematic diagram showing a second process for assembling an one-arrow-multiple-satellite separation system according to the present invention, wherein the satellites are released one by one;
FIG. 14 is a schematic diagram III illustrating an assembly process of an one-arrow-multiple-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 15 is a schematic diagram showing a process for assembling an one-arrow-multiple-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 16 is a schematic diagram showing an assembly process of an one-arrow-multiple-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 17 is a schematic diagram of an assembly process of an one-arrow-multiple-satellite separation system for releasing satellites one by one according to the present invention;
FIG. 18 is a schematic diagram of a single-layer all-star connection according to the present invention;
FIG. 19 is a schematic diagram of a first satellite in flight unlocking a second satellite according to the present invention;
FIG. 20 is a schematic illustration of a one-by-one release separation of satellites according to the present invention;
FIG. 21 is a schematic view of the connection and fixation of the upper and lower satellites according to the present invention;
FIG. 22 is a schematic diagram illustrating the overall composition of an one-arrow-multiple-satellite separation system for releasing satellites layer by layer in one-time unlocking according to the present invention;
Fig. 23 is a schematic diagram of an unlocking lower satellite in the upper satellite flying process according to the present invention.
In the figure: 1: star body, 2: spring device, 3: separation support, 4: pulley, 5: locking pin, 6: kevlar rope, 7: pin puller, 8: carrying adapter, 1-1: main frame, 1-1-1: frame plate, 1-1-2: side frame, 1-1-3: nut, 1-2: top plate, 1-3: bottom plate, 1-4: side plates, 1-5: expansion solar wing, 1-5-1: hinge, 1-5-2: compression point, 2-1: spring, 2-2: guide holder, 2-2-1: guide post, 2-2-2: first pin hole, 2-3: an inner sleeve, 2-3-1: guide port, 2-4: outer sleeve, 3-1: guide slot, 3-2: second pin hole, 4-1: pulley wheel body, 4-1-1: mounting holes, 4-1-2: through hole, 4-2: pulley support, 4-3: rotating shaft, 4-4: and a spindle nut.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, in the case of no conflict, embodiments of the present invention and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.
Example 1: referring to fig. 1-2, a one-arrow-multiple-satellite separation system for releasing satellites one by one is described, which comprises a satellite body 1, a spring device 2, a separation support 3, a pulley 4, a locking pin 5, a kevlar rope 6, a pin puller 7 and a carrying adapter 8.
As shown in fig. 3, the star body 1 includes a main frame 1-1, a top plate 1-2, a bottom plate 1-3, and four side plates 1-4, wherein the top plate 1-2 and the bottom plate 1-3 are respectively mounted at the top and bottom of the main frame 1-1, the four side plates 1-4 are respectively mounted around the lateral direction of the main frame 1-1, and each cabin plate can be used for mounting and fixing equipment and load, and comprises mounting and fixing of each mechanism so as to realize a corresponding separation release function. The two sides of the star body 1 are symmetrically provided with expansion solar wings 1-5, each expansion solar wing 1-5 is provided with two hinges 1-5-1 and two compression points 1-5-2, the two hinges 1-5-1 are connected with the star body 1, the two compression points 1-5-2 are compressed with the star body 1, the installation and fixation of the whole one-arrow multi-star separation system are not affected under the furling state, and sufficient energy is provided after the satellite is released and enters the orbit.
As shown in fig. 4, the main frame 1-1 includes two frame plates 1-1-1 and four side frames 1-1-2, and the frame plates 1-1 and the side frames 1-1-2 are made of carbon fibers, so that the weight reduction effect is achieved on the premise of improving the rigidity and strength of the star body 1. Two ends of the four side frames 1-1-2 are respectively connected with four corners of the two frame plates 1-1, nuts 1-1-3 are adhered to the back surfaces of mounting holes of the frame plates 1-1-1 and the side frames 1-1-2, and the top plate 1-2, the bottom plate 1-3 and the four side plates 1-4 are connected to the main frame 1-1 through the cooperation of screws and the nuts 1-1-3. The frame plate 1-1 is provided with raised reinforcing ribs, and the side frame 1-1-2 is of an L-shaped structure, so that the bearing effect of the main frame 1-1 can be improved. The surfaces of the frame plate 1-1-1 and the side frame 1-1-2 are provided with mounting through holes for mutual mounting and fixing and mounting and fixing with the cabin plate. All the cabin boards are made of honeycomb boards, and counter bores are formed in the surfaces of the cabin boards and are used for installing screws so as to be fixed with the main frame 1-1.
The installation process of the star body 1 is as follows:
the first step: pasting nuts 1-1-3 at corresponding positions of mounting holes on the backs of the frame plates 1-1-1 and the side frames 1-1-2 for subsequent mounting and fixing;
And a second step of: the two frame plates 1-1-1 and the four side frames 1-1-2 are stuck together to realize the pre-fixing effect;
and a third step of: the top plate 1-2, the bottom plate 1-3 and the four side plates 1-4 are arranged on the outer side of the main frame 1-1 through screws, and the screws are screwed and fixed with nuts 1-1-3 stuck on the back of the main frame 1-1, so that the frame plate 1-1-1 and the side frames 1-1-2 and all cabin plates and the main frame 1-1 are fixed.
The installed satellite body 1 has higher rigidity and strength, after the satellites are stacked, the weight generated by the satellites above is transferred to the main frame 1-1 below through the spring device 2, the force transfer path is short, and the dynamic load and the static load generated by the carrying ascending section can be borne; at the same time, the star body 1 can bear the acting force of the spring device 2 in the compressed state and the separation process through the high-strength main frame 1-1.
As shown in FIG. 5, the spring device 2 comprises a spring 2-1, a guide seat 2-2, an inner sleeve 2-3 and an outer sleeve 2-4, wherein a guide post 2-2-1 is arranged on the guide seat 2-2, a first pin hole 2-2-2 is formed in the side surface of the guide post 2-2-1, the spring 2-1 is sleeved on the guide post 2-2-1, the inner sleeve 2-3 is pressed on the upper surface of the spring 2-1, so that the guide post 2-2-1 passes through a guide opening 2-3-1 in the inner sleeve 2-3, the outer sleeve 2-4 is sleeved on the inner sleeve 2-3, and the bottom end of the outer sleeve 2-4 is connected with the guide seat 2-2.
As shown in fig. 6, the inner sleeve 2-3 is pressed down until its top is flush with the top of the outer sleeve 2-4, the spring device 2 is in a compressed state, and at this time, the first pin hole 2-2-2 on the guide seat 2-2 is exposed outside the device; as shown in FIG. 7, when the pressing of the inner sleeve 2-3 is released and the spring 2-1 pushes the inner sleeve 2-3 to move upward, the spring device 2 is locked and in a released state when the lower edge of the inner sleeve 2-3 contacts with the upper edge of the outer sleeve 2-4, and at this time, the first pin hole 2-2-2 on the guide seat 2-2 is hidden inside the device. The guiding column 2-2-1 and the outer sleeve 2-4 play a guiding role in the upward movement of the inner sleeve 2-3 in the whole process of the spring device 2 from the compressed state to the released state, so that the thrust direction of the spring device 2 is vertical to the mounting surface.
As shown in fig. 8, the separation support 3 is provided with a through guide groove 3-1, the size of which is matched with the design of a guide post 2-2-1 of the guide seat 2-2, and the two can be inserted and combined; the side surface of the separation support 3 is provided with a second pin hole 3-2, and the size of the second pin hole is consistent with that of the first pin hole 2-2-2.
As shown in fig. 9, the pulley 4 includes a pulley body 4-1, a pulley bracket 4-2, a rotating shaft 4-3 and a rotating shaft nut 4-4, the rotating shaft 4-3 passes through the pulley bracket 4-2 and a mounting hole 4-1-1 of the pulley body 4-1 in sequence and then is fixed by the rotating shaft nut 4-4, a through hole 4-1-2 is formed in the pulley body 4-1, the kevlar rope 6 is fixed by the through hole 4-1-2, and molybdenum disulfide is smeared on the surfaces of the mounting hole 4-1-1 and the rotating shaft 4-3 so as to reduce friction force when the pulley rotates.
The locking pin 5 is preferably made of high-carbon steel, and molybdenum disulfide is coated on the surface of the locking pin, so that the miniaturization design can be realized on the premise of ensuring the locking effect and not deforming the locking pin, and the friction force during unlocking is reduced.
As shown in fig. 10 and 11, the pulley 4 is divided into an auxiliary pulley and a fixed pulley which have the same structure, and the auxiliary pulley plays a guiding role when the kevlar rope 6 is pulled, so that the pulling direction of the locking pin 5 is kept consistent with the pin hole, and the blocking is avoided; the fixed pulley is used for fixing one end of the Kevlar rope 6.
The whole assembly scheme and the separation scheme of the embodiment are as follows: four spring devices 2 and two auxiliary pulleys are arranged on the top surface of the star body 1, four separation supports 3 and two fixed pulleys are arranged on the bottom surface of the star body 1, a plurality of spring devices 2 and two auxiliary pulleys are arranged on the top surface of the carrying adapter 8, the star body 1 is arranged in a plurality of layers according to each layer, the separation supports 3 are arranged in a multi-layer mode along the axial direction of the carrying adapter 8, the spring devices 2 are connected with the separation supports 3, the guide grooves 3-1 are spliced with the guide posts 2-2-1, the positions of the first pin holes 2-2-2 and the second pin holes 3-2 are overlapped, the springs 2-1 are in a compression state, the locking pins 5 are inserted into the first pin holes 2-2 and the second pin holes 3-2, one end of each Kevlar pull rope 6 is connected to one locking pin 5, the other end of each Kevlar pull rope passes through the middle auxiliary pulley, the Kevlar pull rope 6 is wound on the fixed pulley at the bottom end of the adjacent star body 1, all the star bodies 1 are sequentially connected through Kevlar pull ropes 6, and finally the locking pins 5 of the star body 1 are connected with the locking pins 7.
The separation is as follows: an unlocking signal is applied to a pin puller 7 positioned at the uppermost layer, the pin puller 7 releases the locking of the star body 1, and the star body 1 flies upwards as a first released and separated star body 1 under the thrust of the spring device 2; when the winding part of the Kevlar stay rope 6 is released, the star body 1 continues to fly upwards to pull out the locking pin 5 connected with the tail end of the Kevlar stay rope 6, and at the moment, the next star body 1 is unlocked and separated for release; the latter star body 1 is separated upwards and then unlocked, and the latter star body 1 is repeatedly moved until all the star bodies 1 are unlocked and separated.
The more specific scheme is as follows: in this embodiment, the multiple star bodies 1 on the same layer are sequentially connected through kevlar ropes 6, and the locking pin 5 of the last star body 1 on the same layer is connected with a pin puller 7, i.e. each layer is provided with a pin puller 7. The assembly method is as follows:
The first step: as shown in fig. 12, a corresponding number of spring devices 2 and pulleys 4 are mounted on the surface of the carrying adapter 8 according to the number of star bodies 1 arranged in a single layer.
And a second step of: as shown in fig. 13, a single star body 1 is mounted on four spring devices 2, guide posts 2-2-1 of the four spring devices 2 are inserted into guide grooves 3-1 of four separation supports 3, the star body 1 is pressed down to enable the four spring devices 2 to be in a compressed state, at this time, a first pin hole 2-2-2 of the guide seat 2-2 coincides with a second pin hole 3-2 of the separation support 3 in position, and locking of the four positions is completed by using locking pins 5 to pass through the coinciding pin holes, as shown in fig. 14.
And a third step of: the installation and fixation of the adjacent one star body 1 are completed by referring to the second step, then one end of a Kevlar rope 6 is connected to one locking pin 5 of the first star body 1, the other end passes through an auxiliary pulley in the middle and is connected to a pulley 4 at the bottom end of the second star body 1, and the pulley 4 is rotated to wind the Kevlar rope 6 on the surface of the pulley wheel body 4-1 so as to straighten the rest part of the Kevlar rope 6, as shown in fig. 15; according to the operation, the connection of the Kevlar rope 6 at the other side is completed, and then the two locking pins 5 which are not connected with the Kevlar rope 6 are pulled out, so that the installation of the first star body 1 is completed.
Fourth step: referring to the second step and the third step, the installation of all the star bodies 1 in the same layer can be executed, after the installation is completed, the locking pins 5 of all the star bodies 1 in the same layer are all fixed on the pulley 4 of the next star body 1 through the Kevlar rope 6, as shown in fig. 16, and the finally installed star body 1 is locked through the two pin extractors 7, as shown in fig. 17, namely the installation and the fixation of all the star bodies 1 in the same layer are completed; the connection and fixation relation of all the single-layer star bodies 1 is shown in fig. 18, wherein overlapping positions of the Kevlar ropes 6 are shown in the drawing, and the Kevlar ropes 6 installed later are lapped above the Kevlar ropes 6 installed before so as to meet the requirement of a release sequence.
Fifth step: according to the total number of the stars of the arrow, the stacking installation of all the stars 1 can be continuously completed above the first layer of stars 1 according to the second, third and fourth steps, as shown in fig. 1.
The separation mode of this embodiment is: an unlocking signal is applied to a pin puller 7 of the last installed star body 1, the pin puller 7 releases the lock of the star body 1, and the star body 1 flies upwards as a first released and separated star body 1 under the thrust of a spring device 2; in the upward flight process of the star body 1, the tension force of the Kevlar stay rope 6 preferentially releases the part wound on the surface of the pulley wheel body 4-1, when the winding part of the Kevlar stay rope 6 is released, the star body 1 continues to fly upwards to pull out the locking pin 5 connected with the tail end of the Kevlar stay rope 6 from the pin hole, as shown in fig. 19, and at the moment, the next star body 1 is unlocked and separated and released; the latter star body 1 is separated upwards and then unlocked, as shown in fig. 20, the next star body 1 is cycled until all the star bodies 1 in one layer are unlocked and separated. An unlocking signal is applied to the pin puller 7 of the last installed star body 1 of the next layer, so that all the star bodies 1 of the next layer are released, and the cyclic operation can finish the release of all the star bodies 1.
In this embodiment, the length of the kevlar rope 6 is preferably about twice the height of the satellite body 1, and in the upward flight of one satellite body 1, since the kevlar rope 6 preferentially releases the portion wound on the surface of the pulley wheel body 4-1, when the locking pin 5 is pulled out to release the next satellite body 1, the previous satellite body 1 is far away from the satellite group, thereby forming the effect of releasing satellites one by one, and the satellites released adjacently will not collide in the separation process.
Example 2: based on embodiment 1, four auxiliary pulleys are arranged on the side face of the last star body 1 of each layer, two auxiliary pulleys are arranged on the top face, the locking pin 5 of the last star body 1 of the same layer is connected with the Kevlar rope 6 and then connected with the star body 1 of the last layer, the locking pin 5 of the last star body 1 of the uppermost layer is connected with the pin puller 7, namely, the pin puller 7 is only arranged on the star body 1 installed last in the uppermost layer, the effect that all satellites are released one by one layer after one unlocking can be realized in the mode that:
The first step: the first, second, third and fourth steps of the assembly mode in the embodiment 1 are referred to complete the installation and fixation of all star bodies 1 in one layer; when the fourth step is performed, the last star body 1 of the layer is locked without the use of the pin puller 7, and is still locked with the use of the locking pin 5.
And a second step of: six pulleys 4 are additionally arranged on the side face and the top of the last star body 1 arranged at the bottom layer, as shown by the broken line in the figure 21, the first star body 1 at the upper layer is arranged at the top, one end of a Kevlar pull rope 6 is connected to a locking pin 5 of the last star body 1 at the lower layer, the other end of the Kevlar pull rope passes through the middle four auxiliary pulleys 4 and is connected to the pulley 4 at the bottom end of the last star body 1, and the Kevlar pull rope 6 is wound on the surface of the pulley wheel body 4-1 by rotating the pulley 4 so as to straighten the rest part of the Kevlar pull rope 6, namely, the installation and fixation of the last star body 1 at the bottom layer are completed.
And a third step of: referring to the assembly step of embodiment 1 and the assembly step of this embodiment, the assembly of the remaining satellite bodies 1 is completed, and one of all the satellite bodies 1 which is finally installed is locked by the two pin extractors 7, and the installed satellite group is shown in fig. 22.
The separation mode of this embodiment is: the single layer satellite release process was consistent with that described in example 1; in the release process of the last star body 1 of the layer, the star body 1 flies upwards, the tension force of the Kevlar rope 6 preferentially releases the part wound on the surface of the pulley wheel body 4-1, when the winding part of the Kevlar rope 6 is released, the star body 1 continues to fly upwards to pull out the locking pin 5 connected with the tail end of the Kevlar rope 6 from the pin hole, as shown in fig. 23, and at the moment, the first star body 1 at the lower layer is unlocked and separated and released; and the unlocking and releasing of all the satellite bodies 1 are sequentially and circularly performed in a reciprocating way, so that the effect of releasing all satellites layer by layer at one time is achieved.
In this embodiment, the length of the kev rope 6 connected to the same layer of the star body 1 is preferably about twice the height of the star body 1, and the length of the kev rope 6 connected to the upper and lower layers of the star body 1 is preferably about three times the height of the star body 1, and in the upward flight process of one star body 1, since the kev rope 6 preferentially releases the part wound on the surface of the pulley wheel body 4-1, when the locking pin 5 is pulled out to release the next star body 1, the previous star body 1 is far away from the satellite group, thereby forming the effect of releasing satellites one by one, and the satellites released adjacently cannot collide in the separation process.
The embodiments of the invention disclosed above are intended only to help illustrate the invention. The examples are not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention.
Claims (10)
1. An arrow multi-satellite separation system for releasing satellites one by one, which is characterized in that: the novel planet carrier comprises a star body (1), a spring device (2), a separation support (3), a pulley (4), a locking pin (5), a Kevlar pull rope (6), a pin puller (7) and a carrying adapter (8), wherein the spring device (2) comprises a spring (2-1), a guide seat (2-2), an inner sleeve (2-3) and an outer sleeve (2-4), a guide column (2-2-1) is arranged on the guide seat (2-2), a first pin hole (2-2-2) is formed in the side surface of the guide column (2-2-1), the spring (2-1) is sleeved on the guide post (2-2-1), the inner sleeve (2-3) is pressed on the upper surface of the spring (2-1), the guide post (2-2-1) passes through the guide opening (2-3-1) on the inner sleeve (2-3), the outer sleeve (2-4) is sleeved on the inner sleeve (2-3), the bottom end of the outer sleeve (2-4) is connected with the guide seat (2-2), the separation support (3) is provided with a through guide groove (3-1), the side surface of the separation support (3) is provided with a second pin hole (3-2), the pulley (4) is divided into an auxiliary pulley and a fixed pulley which are the same in structure, four spring devices (2) and two auxiliary pulleys are arranged on the top surface of the star body (1), four separation supports (3) and two fixed pulleys are arranged on the bottom surface of the star body (1), a plurality of spring devices (2) and auxiliary pulleys are arranged on the top surface of the carrying adapter (8), the star body (1) is provided with a plurality of layers according to each layer, the plurality of auxiliary pulleys are axially arranged along the carrying adapter (8), the separation supports (3) are connected with the spring devices (2), the guide grooves (3-1) are connected with the guide posts (2-2-1) in an inserting mode, the first pin holes (2-2-2) and the second pin holes (3-2) are overlapped in position, the springs (2-1) are in a compression state, one end of a pull rope (6) is connected to one locking pin (5) of the star body (1) in a multi-layer mode, the other end of the pull rope (6) penetrates through the adjacent auxiliary pulleys (1) and penetrates through the star body (6) to be connected with the other end of the star body (6) in sequence, the locking pin (5) of the last star body (1) is connected with a pin puller (7).
2. An archery multi-satellite separation system for individually releasing satellites according to claim 1 wherein: the star bodies (1) on the same layer are sequentially connected through the Kevlar pull ropes (6), and the locking pin (5) of the last star body (1) on the same layer is connected with the pin puller (7).
3. An archery multi-satellite separation system for individually releasing satellites according to claim 1 wherein: four auxiliary pulleys are arranged on the side face of the last star body (1) of each layer, two auxiliary pulleys are arranged on the top face of the last star body, the last star body (1) of the upper layer is connected with the locking pin (5) of the last star body (1) of the upper layer after being connected with the Kevlar rope (6), and the locking pin (5) of the last star body (1) of the uppermost layer is connected with the pin puller (7).
4. An archery multi-satellite separation system for individually releasing satellites according to claim 1 wherein: the pulley (4) comprises a pulley body (4-1), a pulley support (4-2), a rotating shaft (4-3) and a rotating shaft nut (4-4), wherein the rotating shaft (4-3) sequentially penetrates through the pulley support (4-2) and the mounting hole (4-1-1) of the pulley body (4-1) and then is fixed through the rotating shaft nut (4-4), the pulley body (4-1) is provided with a through hole (4-1-2), and the Kevlar rope (6) is fixed through the through hole (4-1-2).
5. An archery multiple-satellite separation system for individually releasing satellites according to claim 4 wherein: the locking pin (5) is made of high-carbon steel, and molybdenum disulfide is smeared on the surfaces of the locking pin (5), the mounting hole (4-1-1) and the rotating shaft (4-3).
6. An archery multi-satellite separation system for individually releasing satellites according to claim 1 wherein: the star body (1) comprises a main frame (1-1), a top plate (1-2), a bottom plate (1-3) and four side plates (1-4), wherein the top plate (1-2) and the bottom plate (1-3) are respectively arranged at the top and the bottom of the main frame (1-1), the four side plates (1-4) are respectively arranged around the lateral direction of the main frame (1-1), and expansion solar wings (1-5) are symmetrically arranged on the two sides of the star body (1).
7. An archery multiple-satellite separation system for individually releasing satellites according to claim 6 wherein: two hinges (1-5-1) and two compression points (1-5-2) are arranged on the expansion solar wing (1-5), the two hinges (1-5-1) are connected with the star body (1), and the two compression points (1-5-2) are compressed with the star body (1).
8. An archery multiple-satellite separation system for individually releasing satellites according to claim 6 wherein: the main frame (1-1) comprises two frame plates (1-1-1) and four side frames (1-1-2), two ends of the four side frames (1-1-2) are respectively connected with four corners of the two frame plates (1-1-1), nuts (1-1-3) are adhered to the back surfaces of mounting holes of the frame plates (1-1-1-1) and the side frames (1-1-2), and the top plate (1-2), the bottom plate (1-3) and the four side plates (1-4) are connected to the main frame (1-1) through the cooperation of screws and the nuts (1-1-3).
9. An archery multiple-satellite separation system for individually releasing satellites according to claim 8 wherein: the frame plate (1-1-1) and the side frame (1-1-2) are made of carbon fibers, raised reinforcing ribs are arranged on the frame plate (1-1-1), the side frame (1-1-2) is of an L-shaped structure, and the top plate (1-2), the bottom plate (1-3) and the side plate (1-4) are honeycomb plates.
10. A method of separating an archery multi-satellite separation system for individually releasing satellites as defined in claim 1 wherein: an unlocking signal is applied to a pin puller (7) positioned at the uppermost layer, the pin puller (7) releases the locking of the star body (1), and the star body (1) flies upwards as a first release separated star body (1) under the thrust of the spring device (2); in the upward flight process of the star body (1), the winding part is released by the tension force of the Kevlar pull rope (6), when the winding part of the Kevlar pull rope (6) is released, the star body (1) continuously flies upward to pull out the locking pin (5) connected with the tail end of the Kevlar pull rope (6), and at the moment, the next star body (1) is unlocked and separated to be released; the latter star body (1) is separated upwards and then unlocked, and the next star body (1) is repeatedly moved until all the star bodies (1) are unlocked and separated.
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| JPS6433000A (en) * | 1987-07-28 | 1989-02-02 | Nec Corp | Separating mechanism |
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
| WO2022095599A1 (en) * | 2020-11-03 | 2022-05-12 | 四川航天川南火工技术有限公司 | Shape-memory alloy-driven connecting and unlocking structure |
| CN116022364A (en) * | 2022-12-30 | 2023-04-28 | 航天科工火箭技术有限公司 | Multi-star arrow separation device |
| CN117262242A (en) * | 2023-11-17 | 2023-12-22 | 哈尔滨工大卫星技术有限公司 | Planar unfolding three-dimensional cabin door device applied to primary and secondary stars and working method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230192325A1 (en) * | 2021-12-17 | 2023-06-22 | Maxar Space Llc | Dispenserless multi-satellite launch configuration with simple adapter interface |
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| JPS6433000A (en) * | 1987-07-28 | 1989-02-02 | Nec Corp | Separating mechanism |
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
| WO2022095599A1 (en) * | 2020-11-03 | 2022-05-12 | 四川航天川南火工技术有限公司 | Shape-memory alloy-driven connecting and unlocking structure |
| CN116022364A (en) * | 2022-12-30 | 2023-04-28 | 航天科工火箭技术有限公司 | Multi-star arrow separation device |
| CN117262242A (en) * | 2023-11-17 | 2023-12-22 | 哈尔滨工大卫星技术有限公司 | Planar unfolding three-dimensional cabin door device applied to primary and secondary stars and working method |
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