CN112693627A - One-rocket multi-satellite stacked launching method - Google Patents
One-rocket multi-satellite stacked launching method Download PDFInfo
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- CN112693627A CN112693627A CN202110007501.2A CN202110007501A CN112693627A CN 112693627 A CN112693627 A CN 112693627A CN 202110007501 A CN202110007501 A CN 202110007501A CN 112693627 A CN112693627 A CN 112693627A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
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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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Abstract
The invention provides a one-arrow multi-star stacked launching method, which comprises the following steps: installing an inter-satellite separation device between a plurality of satellites; sequentially connecting the inter-satellite separation devices on the satellites, and stacking to form a satellite assembly; thereby the satellite assembly can be installed to the rocket through the satellite and rocket separation device and locked; the satellite assembly is conveyed to a preset position through the rocket, the unlocking of the satellite and rocket separating device is controlled, the inter-satellite separating device is controlled to sequentially separate a plurality of satellites, and the satellite launching is completed.
Description
Technical Field
The invention relates to the technical field of satellite launching, in particular to a one-arrow multi-satellite stacked launching method.
Background
When a conventional satellite is launched, a main satellite is preferably considered, a carrier rocket with adaptive carrying capacity is selected, the carrier can utilize the residual space and carrying capacity to provide carrying service for a small satellite, and the space and the weight of the small satellite are always strictly limited.
With the expansion of satellite application, a multi-satellite networking mode is more and more popular, and the traditional one-arrow one-satellite mode for transmitting the small satellite cannot meet the requirements on economy and timeliness. In recent years, a central cylindrical multi-satellite adapter is mostly adopted for one-rocket multi-satellite launching at home and abroad, satellites are hung on the multi-satellite adapter, and although one-rocket multi-satellite launching is realized, the adapter has large mass and volume, occupies the space in a fairing of a carrier rocket and has carrying capacity, and the quantity of satellites launched at one time is small.
Disclosure of Invention
In view of the above, there is a need for a rocket-starry stacking launching method to solve the problem that the space and carrying capacity in the fairing of the carrier rocket cannot meet the requirements when the current small satellites are launched.
The invention provides a one-arrow multi-star stacked launching method, which comprises the following steps:
installing an inter-satellite separation device between a plurality of satellites;
sequentially connecting the inter-satellite separation devices on a plurality of satellites, and stacking to form a satellite assembly;
mounting the satellite assembly to a rocket through a satellite-rocket separation device and locking;
transporting the satellite assembly to a predetermined location by a rocket;
and controlling the satellite-rocket separation device to unlock, and controlling the inter-satellite separation device to sequentially separate the satellites to finish satellite launching.
Optionally, the satellite assembly is formed by stacking a plurality of satellites in sequence in a staggered manner.
Optionally, the inter-satellite separation devices on a plurality of satellites are connected in sequence, and stacking to form a satellite assembly specifically includes:
collecting sailboards and antennas of a plurality of satellites;
connecting an inter-satellite separation device of a satellite to a satellite and rocket separation device;
stacking the inter-satellite separation device of another satellite on the inter-satellite separation device of one satellite, so that the connecting line of the two sailboards of one satellite is vertically crossed with the connecting line of the two sailboards of the other satellite;
and sequentially and alternately stacking a plurality of satellites to form a satellite assembly.
Optionally, the satellite-rocket separation device comprises a plurality of satellite-rocket separation assemblies distributed in an annular mode, each satellite-rocket separation assembly comprises a tension rod, a pressing end cap and an unlocking seat, the fixing seat, the first elastic separation piece and the bolt are used for being connected with the carrier rocket, the unlocking seat is connected with the carrier rocket through the bolt, one end of the tension rod is connected with the unlocking seat, the other end of the tension rod is fixedly connected with the pressing end cap, and one end of the first elastic separation piece is fixedly connected with the fixing seat and the other end of the first elastic separation piece is fixedly connected with the middle of the tension rod.
Optionally, the inter-satellite separation device comprises a plurality of bearing columns and a plurality of second elastic separation pieces, the bearing columns are distributed annularly, and the second elastic separation pieces are fixedly mounted at the bottoms of the bearing columns in a one-to-one correspondence manner; the bearing columns of the inter-satellite separating devices are sequentially connected from top to bottom, and the bearing column of the inter-satellite separating device positioned at the lowest part is abutted against the fixed seats of the separating assemblies in a one-to-one correspondence manner; the bearing columns of the uppermost inter-satellite separating device are butted against the pressing end caps of the separating assemblies in a one-to-one correspondence manner.
Optionally, the mounting and locking the satellite assembly to the rocket through the satellite and rocket separation device specifically includes:
mounting the fixed seat on the rocket;
butting a bearing column of the satellite assembly with the fixed seat;
and controlling the compression end cap to abut against the upper part of the bearing column of the satellite assembly, and applying pretightening force through the bolt to enable the unlocking seat to be installed on the rocket.
The invention has the beneficial effects that:
the invention provides a one-arrow multi-satellite stacked launching method, which is characterized in that inter-satellite separation devices are arranged among a plurality of satellites; sequentially connecting the inter-satellite separation devices on the satellites, and stacking to form a satellite assembly;
mounting the satellite assembly to a rocket through a satellite-rocket separation device and locking;
transporting the satellite assembly to a predetermined location by a rocket;
the satellite and rocket separation device is controlled to unlock, and the inter-satellite separation device is controlled to sequentially separate a plurality of satellites, so that satellite launching is completed, and the satellite and rocket separation device has good practicability.
The invention has the beneficial effects that:
the invention provides a one-arrow multi-satellite stacked launching method, which is characterized in that inter-satellite separation devices are arranged among a plurality of satellites; sequentially connecting the inter-satellite separation devices on the satellites, and stacking to form a satellite assembly; thereby the satellite assembly can be installed to the rocket through the satellite and rocket separation device and locked; transport the satellite assembly to preset position through the rocket, realize the purpose that a transmission just can transport many satellites, and after reacing and predetermineeing the position, control star-arrow separator unblock, separation device makes a plurality of satellites quick separation in proper order between the control star, accomplishes whole satellite launching process, because a plurality of satellites pile up in proper order, abundant utilization the space of rocket radome fairing, a transmission satellite delivery is in large quantity, possesses fine practicality.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
Fig. 1 is a flow chart of a one-arrow-plus-one-star stacked launching method according to a first embodiment of the present invention;
FIG. 2 is a perspective view of a satellite-mounted one-arrow-plus-one separation system in accordance with a first embodiment of the present invention;
FIG. 3 is a perspective view of an inter-satellite separation apparatus with satellites in accordance with a first embodiment of the present invention;
fig. 4 is an enlarged schematic view of a structure at a in fig. 2.
Detailed Description
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate preferred embodiments of the invention and together with the description, serve to explain the principles of the invention and not to limit the scope of the invention.
It will be understood that, although the terms first, second, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another.
Example one
Referring to fig. 1, a one-arrow-multi-star stacked launching method disclosed in an embodiment of the present invention includes the following steps:
and S01, installing inter-satellite separation devices among the satellites. Then, with reference to fig. 2 to 4, the inter-satellite separation device used in this step is part of a one-arrow-and-multi-satellite separation system, which includes a satellite-and-arrow separation device 1 and a plurality of inter-satellite separation devices 2. The satellite and rocket separation device 1 is used for separating the satellite assembly from the rocket; the plurality of inter-satellite separation apparatuses 2 are used to separate a plurality of satellites in a satellite complex from each other.
Specifically, the inter-satellite separation device 2 in this step includes four force-bearing columns 21 and four second elastic separation members 22, and the four force-bearing columns 21 in the inter-satellite separation device 2 are distributed in an annular shape, that is, in this step S01, the four force-bearing columns 21 are respectively and fixedly mounted at four corners of the satellite. It is easy to understand that the connection mode of the satellite and the bearing column 21 can be selected according to the field requirement, and can be one of bonding, welding, bolting or clamping. And the four second elastic separating pieces 22 are fixedly arranged at the bottoms of the four bearing columns 21 in a one-to-one correspondence manner. It is worth noting that a sinking groove is formed at the bottom of each force bearing column 21, and the four second elastic separating members 22 are fixedly installed in the sinking grooves of the four force bearing columns 21 in a one-to-one correspondence manner.
S02, sequentially connecting the inter-satellite separation devices on the satellites, and stacking to form a satellite assembly; with reference to fig. 2 to 4, the inter-satellite separation devices 2 of the present embodiment are sequentially arranged from bottom to top, and the bearing columns 21 of the inter-satellite separation devices 2 are sequentially connected from top to bottom, so that satellites are sequentially stacked. That is, in this step S02, a plurality of satellites are also stacked in sequence. Then, the step of sequentially connecting the inter-satellite separation devices on the plurality of satellites and stacking the inter-satellite separation devices to form the satellite assembly specifically includes the following steps: firstly, folding windsurfing boards and antennas of a plurality of satellites; then connecting an inter-satellite separation device 2 of a satellite to the satellite-rocket separation device 1; and then stacking the inter-satellite separation device 2 of another satellite on the inter-satellite separation device 2 of one satellite, and vertically staggering the connecting line of the two sailboards of one satellite and the connecting line of the two sailboards of the other satellite to complete the stacking. The above steps are repeated to stack a plurality of satellites together to form a satellite assembly. That is, the satellite assembly is formed by stacking a plurality of satellites in a staggered manner.
S03, mounting the satellite assembly to a rocket through a satellite-rocket separation device and locking; the satellite and arrow separating device in the step is the satellite and arrow separating device 1 in the one-arrow-and-multi-satellite separating system. Specifically, the satellite and arrow separating device 1 comprises four satellite and arrow separating assemblies 11 distributed in an annular shape, and the four satellite and arrow separating assemblies 11 distributed in the annular shape are respectively installed on four corners of a satellite. Each satellite-rocket separation assembly 11 comprises a tension rod 111, a pressing end cap 112, an unlocking seat 113, a fixed seat 114, a first elastic separation piece 115 and a plurality of bolts 116, wherein the fixed seat 114 and the unlocking seat 113 are used for connecting a carrier rocket, the unlocking seat 113 is connected with the carrier rocket through the bolts 116, one end of the tension rod 111 is connected with the unlocking seat 113, the other end of the tension rod is fixedly connected with the pressing end cap 112, and one end of the first elastic separation piece 115 is fixedly connected with the fixed seat 114 and the other end of the first elastic separation piece 115 is fixedly connected with the middle part of the tension rod 111. It is easily understood that the bolt 116 in the present embodiment is an explosive bolt. The explosive bolt can be automatically exploded and removed under the control of the rocket to separate the unlocking seat 113 from the rocket. Of course, other kinds of bolts can be selected according to actual needs, and then the bolts can be disassembled through external disassembling equipment. Two tensioning rods 111 and two unlocking seats 113 in each satellite-rocket separation assembly 11 are provided, the two unlocking seats 113 are respectively installed on two sides of the fixed seat 114, the two tensioning rods 111 are respectively and correspondingly connected with the two unlocking seats 113, and one ends of the two tensioning rods 111, which are back to the unlocking seats 113, are both connected with the pressing end caps 112; a plurality of bearing columns 21 which are sequentially connected from top to bottom are arranged between the two tightening rods 111. The star-rocket separation assembly 11 further comprises a third elastic separating member, the third elastic separating member is installed at the bottom of the unlocking seat 113, and one end of the third elastic separating member, which is back to the unlocking seat 113, is used for abutting against the rocket. In this embodiment, the first elastic separating member 115, the second elastic separating member 22 and the third elastic separating member are all springs. It will be readily appreciated that other resilient members, such as spring hinges, springs or rubber, may be used for the first resilient separating member 115, the second resilient separating member 22 and the third resilient separating member.
Then, the step of mounting and locking the satellite assembly to the rocket through the satellite and rocket separation device specifically comprises the following steps: firstly, the fixed seat 114 is installed on the rocket; then the bearing column 21 of the satellite assembly is butted with the fixed seat 114; namely, the force bearing columns 21 of the lowermost inter-satellite separation device 2 are abutted against the fixed seats 114 of the four separation assemblies in a one-to-one correspondence manner. And then the pressing end caps 112 are controlled to abut against the upper parts of the bearing columns 21 of the satellite combination body, namely the bearing columns 21 of the uppermost inter-satellite separation device 2 abut against the pressing end caps 112 of the four separation assemblies in a one-to-one correspondence manner. The pressing end cap 112 is required to abut against the upper part of the bearing column 21 of the satellite assemblyThe first resilient separating element 115 is secured to rotate freely with the tension bar 111. Finally, pretightening force is applied through the bolt 116 to enable the unlocking seat 113 to be installed on the rocket, the pretightening force is mainly generated by deformation of the pressing mechanism, and the deformation is as follows:
wherein F is pretightening force, L is the length of the tensioning rod, E is the elastic modulus of the material, and A is the sectional area of the tensioning rod. When the length L of the tension rod is larger, in order to ensure that the pretightening force is accurately applied, the installation of the hold-down mechanism is carried out according to the following procedures: a) the front end face of the pressing end cap 112 is fitted with the upper end face of the bearing column 21, and the lower end face of the tension rod 111 is approximately parallel to the upper end face of the unlocking seat 113 in a gravity state; b) the gap between the tension rod 111 and the unlocking seat 113 is filled by the mounting cushion block, so that the gap is smaller than a preset value; c) according to the formula
Calculating the deformation of the tension bar, and then taking out a cushion block with the error between the thickness and the calculated value within 20%; d) and installing the bolt 116, and symmetrically screwing the bolt 116 for multiple times to ensure that the lower end surface of the tension rod 111 is attached to the upper end surface of the unlocking seat 113. In order to ensure the safety of the pretightening force, the rotation angles of all the bolts 116 are basically the same each time, and the single rotation angle is not more than 90 degrees, and after the bolts 116 are attached, the bolts are locked according to the torque requirement.
S04, conveying the satellite assembly to a preset position through a rocket; in the step, the satellite is transported to a preset orbit by the rocket, and then the next step of satellite release can be carried out.
And S05, controlling the satellite-rocket separation device to unlock, and controlling the inter-satellite separation device to sequentially separate the satellites to finish satellite launching. After the satellite is conveyed to a preset orbit, a separation signal is sent by the rocket, so that the bolt 116 is removed, because the bolt 116 of the embodiment is an explosive bolt, after the bolt 116 is detonated, the unlocking seat 113 is separated from the rocket, the tension rod 111 and the compression end cap 112 lose pretightening force, the third elastic separating piece releases the elastic force to bounce the unlocking seat, at the moment, the first elastic separating piece 115 contracts, so that the tension rod 111 rotates around the connection point of the tension rod and the first elastic separating piece 115, the compression end cap 112 moves in the direction away from the satellite, after the satellite loses the obstruction of the compression end cap 112, the second elastic separating piece 22 releases the elastic force, the bearing columns 21 among the satellites are separated from each other, and finally the separation of the satellites is realized.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention.
Claims (6)
1. A one-arrow-multi-star stacked launching method is characterized by comprising the following steps:
installing an inter-satellite separation device between a plurality of satellites;
sequentially connecting the inter-satellite separation devices on a plurality of satellites, and stacking to form a satellite assembly;
mounting and locking the satellite assembly to a rocket through a satellite-rocket separation device;
transporting the satellite assembly to a predetermined location by the rocket;
and controlling the satellite-rocket separation device to unlock, and controlling the inter-satellite separation device to sequentially separate a plurality of satellites to finish satellite launching.
2. The stacked one-rocket multi-satellite launching method as claimed in claim 1, wherein the satellite assembly is formed by sequentially and alternately stacking a plurality of satellites.
3. The one-arrow-multi-satellite stacked launching method as claimed in claim 1, wherein the inter-satellite separation devices on the plurality of satellites are sequentially connected, and the stacking to form the satellite assembly specifically comprises:
folding windsurfing boards and antennas of a plurality of satellites;
connecting an inter-satellite separation device of the satellite to the satellite-rocket separation device;
stacking the inter-satellite separation device of another one of the satellites on the inter-satellite separation device of one of the satellites so that the line of the two windsurfing boards of one of the satellites is vertically staggered with the line of the two windsurfing boards of another one of the satellites;
and sequentially and alternately stacking a plurality of satellites to form the satellite assembly.
4. The stacked one-rocket multi-star launching method according to any one of claims 1 to 3, wherein the satellite-rocket separation device comprises a plurality of annularly distributed satellite-rocket separation assemblies, each satellite-rocket separation assembly comprises a tension rod, a pressing end cap, an unlocking seat, a fixed seat, a first elastic separation member and a bolt, the fixed seat and the unlocking seat are used for connecting a carrier rocket, the unlocking seat is connected with the carrier rocket through the bolt, one end of the tension rod is connected with the unlocking seat, the other end of the tension rod is fixedly connected with the pressing end cap, and one end of the first elastic separation member is fixedly connected with the fixed seat, and the other end of the first elastic separation member is fixedly connected with the middle part of the tension rod.
5. The one-arrow-multi-star stacked launching method as claimed in claim 4, wherein the inter-star separating device comprises a plurality of bearing columns and a plurality of second elastic separating pieces, the bearing columns are distributed annularly, and the second elastic separating pieces are fixedly arranged at the bottoms of the bearing columns in a one-to-one correspondence manner; the bearing columns of the inter-satellite separating devices are sequentially connected from top to bottom, and the bearing column of the inter-satellite separating device positioned at the lowest part is abutted against the fixing seats of the separating assemblies in a one-to-one correspondence manner; and the force bearing columns of the uppermost inter-satellite separating device are butted against the pressing end caps of the separating assemblies in a one-to-one correspondence manner.
6. The one-rocket-multi-star stacked launching method as recited in claim 5, wherein said mounting and locking said satellite assembly to said rocket by means of a satellite-rocket separation device specifically comprises:
mounting the holder to the rocket;
butting a bearing column of the satellite assembly with the fixed seat;
and controlling the compression end cap to abut against the upper part of the bearing column of the satellite assembly, and applying pretightening force through a bolt to enable the unlocking seat to be installed on the rocket.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110007501.2A CN112693627A (en) | 2021-01-05 | 2021-01-05 | One-rocket multi-satellite stacked launching method |
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Cited By (3)
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| CN114171882A (en) * | 2021-10-11 | 2022-03-11 | 北京理工大学 | One-rocket multi-satellite SAR satellite flat antenna lamination device |
| CN114537710A (en) * | 2022-01-18 | 2022-05-27 | 上海卫星工程研究所 | Flexible solar cell array pressing device, working method and satellite |
| CN116424570A (en) * | 2023-06-15 | 2023-07-14 | 哈尔滨工业大学 | Foldable and unfolding stacked satellite configuration for launching multiple satellites |
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| CN116424570B (en) * | 2023-06-15 | 2023-08-25 | 哈尔滨工业大学 | Foldable and unfolding stacked satellite configuration for launching multiple satellites |
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Application publication date: 20210423 |