CN114572425A - Multi-satellite separation controller - Google Patents
Multi-satellite separation controller Download PDFInfo
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- CN114572425A CN114572425A CN202210381358.8A CN202210381358A CN114572425A CN 114572425 A CN114572425 A CN 114572425A CN 202210381358 A CN202210381358 A CN 202210381358A CN 114572425 A CN114572425 A CN 114572425A
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- separation
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- memory alloy
- control signal
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- 238000000926 separation method Methods 0.000 title claims abstract description 102
- 229910001285 shape-memory alloy Inorganic materials 0.000 claims abstract description 56
- HBBGRARXTFLTSG-UHFFFAOYSA-N Lithium ion Chemical compound [Li+] HBBGRARXTFLTSG-UHFFFAOYSA-N 0.000 claims description 6
- 229910001416 lithium ion Inorganic materials 0.000 claims description 6
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 238000012360 testing method Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 2
- 238000011031 large-scale manufacturing process Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000006870 function Effects 0.000 description 3
- 230000001934 delay Effects 0.000 description 2
- 238000012827 research and development Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
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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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- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a multi-satellite separation controller, which comprises a power supply part, a separation delay part, a separation control signal output part and a memory alloy unlocking part, wherein the power supply part is connected with the separation delay part; the power supply part is electrically connected with the separation delay part, the separation control signal output part and the memory alloy unlocking part respectively; the separation delay part is also electrically connected with the separation control signal output part, and when the separation delay time is up, the separation control signal is directly output; the separation control signal output part is also electrically connected with the memory alloy unlocking part, and after the separation control signal is output, the memory alloy is directly heated until the memory alloy is unlocked, so that the satellite is safely released. Compared with the existing satellite release separation deployment system, the satellite release separation deployment system has the advantages that the autonomy, the flexibility and the reliability of satellite release are improved, the complexity of a satellite-rocket interface is reduced, the universality is good, a plurality of satellites can be released in orbit, and the large-scale production is facilitated.
Description
Technical Field
The invention relates to the technical field of spacecraft satellite-rocket docking, in particular to a multi-satellite separation controller.
Background
After the last stage rocket finishes the work task, the last stage rocket and the satellite must be separated in a specified time. And sending an instruction by the ground before the star and arrow are separated, so that the explosion bolt connected with the belt is detonated, the star and arrow unlocking system is unlocked, the belt is loosened, and the star and arrow are separated. After the carrier rocket flies to a preset height and speed and is subjected to attitude adjustment, the satellite is separated from the rocket at a certain relative speed, and a spring and a reverse rocket are generally adopted for separation. The last-stage carrier rocket connected with the satellite is separated, the separation mode has higher working efficiency and reliability, and the separation mode has the function of enabling the satellite to enter a preset orbit.
At present, there are 3 ways for separating stars and arrows, which are: the ejection separation, the satellite and the final rocket have force along the direction of the feeding shaft. The urging means for such a manner is generally constituted by a compression coil spring, an ejector, a gas actuator, and the like. Braking separation, which is usually achieved by a final stage assisted reverse thrust rocket or by the reverse thrust generated by the pressurized gas discharged from the propellant tank, brakes the final stage rocket. It has the advantages that: in the separation process, the satellite does not generate disturbance motion, and the orbit entering precision is high. The rotary multi-satellite separation is characterized in that two or more satellites which are symmetrically arranged in parallel in the axial direction of the longitudinal axis of the satellite are driven by a final distributor at the fixed end of the satellite to rotate around the longitudinal axis of the satellite, the separated satellites are unlocked, and the satellites can be separated out simultaneously under the action of axial spring separation force and rotary centrifugal force. In the above several satellite-rocket separation modes, generally, the power output is provided by the carrying end, i.e. the rocket side, and the output current is large, so as to ensure reliability, so that a designer has to consider more problems about safety and reliability during designing, and the satellite-rocket interface is relatively complex.
Disclosure of Invention
The present invention is directed to a reliable, safe, convenient, short-cycle, and relatively simple multi-satellite separation controller, which solves the above-mentioned problems.
In order to achieve the purpose, the invention provides the following technical scheme: a multi-satellite separation controller comprises a power supply part, a separation delay part, a separation control signal output part and a memory alloy unlocking part; the power supply part is respectively electrically connected with the separation delay part, the separation control signal output part and the memory alloy unlocking part; the separation delay part is also electrically connected with the separation control signal output part, and when the separation delay time is up, the separation control signal is directly output; the separation control signal output part is also electrically connected with the memory alloy unlocking part, and directly heats the memory alloy after the separation control signal is output until the memory alloy is unlocked, so that the satellite is safely released.
Further, the carrier terminal of the separation controller provides a set of passive contacts as a separation indication signal, and the power supply section starts to be powered up autonomously after the set of passive contacts of the carrier terminal is closed.
Still further, the power supply section includes a battery charging circuit and a ground battery voltage detection test circuit.
Furthermore, the power supply part consists of 18650 single lithium ion storage batteries which are connected in an M-series-N-parallel mode, and the using number and the capacity of the lithium batteries are determined according to the magnitude of working current flowing through the memory alloy.
Furthermore, the separation delay part comprises an RC charging delay circuit, the on-orbit release can be carried out at different moments aiming at different satellites, and the delay circuit can reach 100 paths at most.
Further, the starting time of the delay time of the RC charging delay circuit is counted from the closing time of the passive contact at the carrying end until the separation release delay time meets the satellite release requirement.
Furthermore, the separated control signal output part comprises a high-power tube driving output circuit, and the high-power tube driving output circuit can reach 100 paths at most.
Furthermore, the memory alloy unlocking part is unlocked through the memory alloy pin puller unlocking device, and the number of the memory alloy pin puller unlocking devices can reach 100 at most.
Furthermore, the unlocking device of the memory alloy pin extractor adopts memory alloy as a drive and is completed through the memory alloy pin extractor, one end of the memory alloy pin extractor is connected with the pin, the other end of the memory alloy pin extractor is provided with a movable heavy hammer, and the pin is extracted by utilizing the impact generated by the movable heavy hammer.
Compared with the prior art, the invention has the beneficial effects that:
1. the multi-satellite separation controller provided by the invention can be used for simultaneously deploying and separating a plurality of cuboids with different models, is provided with a power system and a control system, only needs a carrying end to provide a group of passive contact signals, and has the remarkable characteristics that: because the power supply system is arranged, the carrying end is not required to provide power supply voltage, and the output pressure of the power supply of the carrying end is reduced; meanwhile, when the satellite and the arrow are separated, only one group of passive contact signals are required to be provided by the carrying end to serve as command signals for separating the satellite and the arrow, so that the satellite and the arrow interface is simpler and more convenient to operate.
2. The multi-satellite separation controller provided by the invention adopts a memory alloy unlocking mode, is a pure resistive load, has no inductive reactance and capacitive reactance, has the total current requirement of 2A-30A, and has a wide working current range, so that a power supply system is more flexible to design; because the on-orbit release device is provided with a control system and has different time delay functions, the on-orbit release device can separate the star and the arrow of the cube stars with different types according to different time sequences when separating the star and the arrow, is suitable for the on-orbit release of a single satellite, is also suitable for 2 stars, 4 stars, 8 stars and even more stars, can release 100 stars on-orbit at most, and solves the problems existing in the prior art: the problem of the need for the carrying terminal to provide the supply voltage; the problem of complex, safe and reliable satellite-rocket interface; the unlocking part has large volume and heavy weight; the research and development period is long; the research and development cost is high.
Drawings
FIG. 1 is a schematic diagram of the overall framework of the present invention;
FIG. 2 is a flow chart of the present invention;
FIG. 3 is a battery charging circuit according to the present invention;
FIG. 4 is a circuit diagram of a battery voltage ground interface of the present invention;
FIG. 5 is a circuit diagram of the separation delay of the present invention;
FIG. 6 is a circuit diagram of the separation control output circuit of the present invention;
FIG. 7 is a flowchart illustrating the operation of the unlocking device of the memory alloy of the present invention.
In the figure: 1. a power supply section; 2. a separation delay part; 3. a separation control signal output section; 4. a memory alloy unlocking part.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-2, an embodiment of the invention provides a multi-satellite separation controller, which includes a power supply portion 1, a separation delay portion 2, a separation control signal output portion 3, and a memory alloy unlocking portion 4; the power supply part 1 is respectively electrically connected with the separation delay part 2, the separation control signal output part 3 and the memory alloy unlocking part 4; the separation delay part 2 is also electrically connected with the separation control signal output part 3, and when the separation delay time is up, the separation control signal is directly output; the separation control signal output part 3 is also electrically connected with the memory alloy unlocking part 4, the memory alloy is directly heated after the separation control signal is output, when the heat reaches 10J, the memory alloy is unlocked, the satellite is safely released, wherein the carrying end of the separation controller provides a group of passive contacts as separation indication signals, and when the group of passive contacts of the carrying end is closed, the power supply part 1 starts to be powered on automatically.
The power supply part 1 in the embodiment of the invention comprises batteries and power supply management, wherein the power supply part mainly comprises 18650 single lithium ion storage batteries, and because the memory alloy is a pure resistive load, the use number and the capacity of the lithium batteries are mainly determined according to the magnitude of working current flowing through the memory alloy; the working temperature range of the lithium ion battery pack is required to meet 0-40 ℃, parameters are required to be unchanged in thermal vacuum, vibration and impact environments, the lithium ion battery pack is placed for 30 days at normal temperature, namely 20 +/-5 ℃, and the capacity of the battery is ensured to be not less than 90% of the capacity before placement. The power management part includes functions of charging, protecting, testing the ground and the like of the battery, as shown in fig. 3-4.
The separation delay part 2 in the embodiment of the invention is mainly completed by adopting an RC charging circuit, can carry out on-orbit release at different moments aiming at different satellites, the delay circuit can reach 100 paths at most, the release of each satellite can be carried out by a user according to different time sequences of on-orbit release of different cubic satellites in sequence, the separation release delay time starting point of each satellite is timed from the moment when the passive contact of the carrying end is closed until the separation release delay time meets the satellite release requirement, and the separation delay of a single satellite is shown in figure 5.
The separation control signal output part 3 in the embodiment of the invention comprises a high-power tube driving output circuit, and the high-power tube driving output circuit can reach 100 paths at most: when a passive contact signal of a carrying end travel switch is closed, the multi-satellite separation controller starts to be powered on autonomously, according to a multi-satellite release delay time sequence diagram, when a charging circuit of a first released satellite meets a plurality of delays, a first path of high-power tube is directly connected to output a separation control signal, the first path of memory alloy starts to be heated, and when the heat reaches 10J, the first path of memory alloy is unlocked, and meanwhile, the first satellite is released reliably. And then, in the same step, after the charging circuit of the second released satellite meets a plurality of delays, the second high-power tube is directly connected to output a separation control signal, the second path of memory alloy is heated, and after the heat reaches 10J, the second path of memory alloy is unlocked, and meanwhile, the second satellite is reliably released. And by analogy, the deployment and separation release work of other paths of satellites is completed, the controller output of 100 paths of satellite separation release can be met at most, and namely the separation release of 100 satellites can be completed at most. Wherein each individual split release output control circuit is shown below in fig. 6.
The memory alloy unlocking part 4 in the embodiment of the invention is unlocked by a memory alloy pin extractor unlocking device, the number of the memory alloy pin extractor unlocking devices can reach 100 at most, the memory alloy pin extractor adopts memory alloy as drive and is completed by a memory alloy pin extractor, the memory alloy pin extractor is a facility specially used for pulling out a positioning pin, one end of the memory alloy pin extractor is connected with a pin, the other end of the memory alloy pin extractor is provided with a movable heavy hammer, the pin is pulled out by utilizing the impact generated by the movable heavy hammer, and the use process is as follows: after the power is switched on, the purpose of achieving the purpose of being universal is achieved by calculating the current and the power-on time and receiving a command for separating the satellite to release and open the separator and judging whether the satellite is released; the specific use flow is shown in fig. 7.
In summary, the following steps: the invention provides a multi-satellite separation controller, which comprises: the system comprises a power supply part 1, a separation delay part 2, a separation control signal output part 3 and a memory alloy unlocking part 4, when the separation delay time reaches, the separation control signal is directly heated for the memory alloy after being output, when the heat reaches 10J, the memory alloy is unlocked, the satellite is safely released, compared with the existing satellite release separation deployment system, the autonomy, the flexibility and the reliability of satellite release are improved, the complexity of a satellite-rocket interface is reduced, the universality is good, a plurality of satellites can be released in an on-orbit manner, and the large-scale production is facilitated.
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 person skilled in the art should be able to cover the technical solutions and the inventive concepts of the present invention within the technical scope of the present invention.
Claims (9)
1. The multi-satellite separation controller is characterized by comprising a power supply part (1), a separation delay part (2), a separation control signal output part (3) and a memory alloy unlocking part (4); the power supply part (1) is electrically connected with the separation delay part (2), the separation control signal output part (3) and the memory alloy unlocking part (4) respectively; the separation delay part (2) is also electrically connected with the separation control signal output part (3), and when the separation delay time is up, the separation control signal is directly output; the separation control signal output part (3) is also electrically connected with the memory alloy unlocking part (4), and after the separation control signal is output, the memory alloy is directly heated until the memory alloy is unlocked, so that the satellite is safely released.
2. A multi-satellite separation controller according to claim 1, wherein: the carrying end of the separation controller provides a group of passive contacts as a separation indicating signal, and when the group of passive contacts of the carrying end is closed, the power supply part (1) starts to be powered on automatically.
3. A multi-satellite separation controller according to claim 2, wherein: the power supply part (1) comprises a battery charging circuit and a ground battery voltage detection test circuit.
4. A multi-satellite separation controller according to claim 3, wherein: the power supply part (1) consists of 18650 single lithium ion storage batteries, the lithium ion storage batteries are connected in an M-series-N-parallel mode, and the using number and capacity of lithium batteries are determined according to the magnitude of working current flowing through the memory alloy.
5. A multi-satellite separation controller according to claim 1, wherein: the separation delay part (2) comprises an RC charging delay circuit, the on-orbit release can be carried out at different moments aiming at different satellites, and the delay circuit can reach 100 paths at most.
6. The multi-satellite separation controller of claim 5, wherein the delay time of the RC charging delay circuit starts from the moment the carrier passive contact is closed until the separation release delay time meets the satellite release requirement.
7. A multi-satellite separation controller according to claim 1, wherein the separation control signal output section (3) comprises a high power tube driving output circuit, and the high power tube driving output circuit can reach 100 paths at most.
8. A multiple satellite separation controller according to claim 1, wherein the memory alloy unlocking part (4) is unlocked by memory alloy pin puller unlocking means, and the number of the memory alloy pin puller unlocking means is up to 100.
9. The multi-satellite separation controller of claim 8, wherein the unlocking means of the memory alloy pin extractor is driven by a memory alloy pin extractor having one end connected to the pin and the other end with a movable weight, and the pin is extracted by the impact of the movable weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210381358.8A CN114572425A (en) | 2022-04-12 | 2022-04-12 | Multi-satellite separation controller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210381358.8A CN114572425A (en) | 2022-04-12 | 2022-04-12 | Multi-satellite separation controller |
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| CN114572425A true CN114572425A (en) | 2022-06-03 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115498431A (en) * | 2022-07-15 | 2022-12-20 | 大连理工大学 | Separation control box suitable for long-time on-orbit operation satellite deployer |
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| CN106542127A (en) * | 2016-12-27 | 2017-03-29 | 哈尔滨工业大学 | One kind receive skin satellite orbit deployment device |
| CN110789742A (en) * | 2019-09-23 | 2020-02-14 | 上海空间电源研究所 | Accurate time delay separation circuit for satellite |
| US20200270001A1 (en) * | 2019-02-22 | 2020-08-27 | The Boeing Company | Systems And Methods For Launching A Plurality Of Spacecraft |
| WO2020205174A1 (en) * | 2019-04-01 | 2020-10-08 | Ensign-Bickford Aerospace & Defense Company | Multipoint payload release system |
| CN112596443A (en) * | 2020-12-21 | 2021-04-02 | 星众空间(北京)科技有限公司 | Control system and method for multi-satellite deployer |
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2022
- 2022-04-12 CN CN202210381358.8A patent/CN114572425A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106542127A (en) * | 2016-12-27 | 2017-03-29 | 哈尔滨工业大学 | One kind receive skin satellite orbit deployment device |
| US20200270001A1 (en) * | 2019-02-22 | 2020-08-27 | The Boeing Company | Systems And Methods For Launching A Plurality Of Spacecraft |
| WO2020205174A1 (en) * | 2019-04-01 | 2020-10-08 | Ensign-Bickford Aerospace & Defense Company | Multipoint payload release system |
| CN110789742A (en) * | 2019-09-23 | 2020-02-14 | 上海空间电源研究所 | Accurate time delay separation circuit for satellite |
| CN112596443A (en) * | 2020-12-21 | 2021-04-02 | 星众空间(北京)科技有限公司 | Control system and method for multi-satellite deployer |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115498431A (en) * | 2022-07-15 | 2022-12-20 | 大连理工大学 | Separation control box suitable for long-time on-orbit operation satellite deployer |
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