CN204925668U - A control system with close on spacecraft for closing on spacecraft - Google Patents
A control system with close on spacecraft for closing on spacecraft Download PDFInfo
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- CN204925668U CN204925668U CN201520646984.0U CN201520646984U CN204925668U CN 204925668 U CN204925668 U CN 204925668U CN 201520646984 U CN201520646984 U CN 201520646984U CN 204925668 U CN204925668 U CN 204925668U
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Abstract
The utility model discloses a control system with close on spacecraft for closing on spacecraft. Should be used for the control system who closes on spacecraft to include: communication terminal sets up in the utricule surface of closing on spacecraft, establishs the communication with the ground basic station and is connected to be controlled by the ground basic station, and the controller, set up in the utricule surface of closing on spacecraft, be connected with communication terminal for establish the communication through communication terminal with the ground basic station and be connected, close on the target device's among the spacecraft operation with control. Through the utility model discloses, solved and flown to control the great problem of computer load burden when spacecraft carries out the emergency control to closing on.
Description
Technical field
The utility model relates near space vehicle field, in particular to a kind of control system near space vehicle and near space vehicle.
Background technology
Near space vehicle can make aircraft that is long-term, follow-on mission near space, in communication support, information acquisition, electronic suppress, early warning etc., have great development potentiality.Near space vehicle flight is aerial at the height of 24km, belong to the environment of low temperature, low pressure, minimum temperature is about-70 DEG C, air pressure is about 3000Pa, therefore, in order to ensure the safe operation of near space vehicle in high altitude environment, gathering high altitude environment data and carrying out accurately controlling to seem particularly important to flight control system.
Under normal circumstances, near space vehicle utilizes flight control computer to carry out the collection of high altitude environment data and the control of flight control system.This proposes high requirement to flight control computer, needs flight control computer to possess enough large resource space, with while execution is to tasks such as the control of flight control system, the computings of task load, carries out other TT&C tasks.Meanwhile, the control of the collection and flight control system that utilize flight control computer to realize high altitude environment data needs the cost of input higher.
For the problem that flight control computer load burden when carrying out security control near space vehicle in correlation technique is larger, at present effective solution is not yet proposed.
Utility model content
Fundamental purpose of the present utility model is to provide a kind of control system near space vehicle and near space vehicle, the problem that when carrying out security control to solve near space vehicle, flight control computer load burden is larger.
To achieve these goals, according to an aspect of the present utility model, a kind of control system near space vehicle is provided.This system comprises: communicating terminal, is arranged at the utricule surface of near space vehicle, sets up communication and be connected, and be controlled by ground base station with ground base station; And controller, be arranged at the utricule surface of near space vehicle, be connected with communicating terminal, be connected for setting up communication by communicating terminal and ground base station, to control the operation of the target device near space vehicle.
Further, this system also comprises: flight control computer, is arranged in the gondola of near space vehicle, is connected respectively with communicating terminal with controller, sets up communication be connected for controlling controller by communicating terminal and ground base station.
Further, this system also comprises: measuring equipment, being arranged at the utricule surface of near space vehicle, being connected, for measuring the flight environment of vehicle data of near space vehicle with flight control computer.
Further, measuring equipment, is connected with communicating terminal, and sets up communication by communicating terminal and ground base station and be connected.
Further, this system also comprises: measuring equipment, being arranged at the utricule surface of near space vehicle, being connected, for measuring the flight environment of vehicle data of near space vehicle with controller.
Further, this system also comprises: energy supply subsystem, and the gondola utricule that is interior or near space vehicle being arranged near space vehicle is surperficial, is connected with measuring equipment, controller and any one in communicating terminal or multiple equipment.
Further, energy supply subsystem comprises primary power cource and standby power supply, and wherein, primary power cource is arranged in the gondola of near space vehicle, and standby power supply is arranged at the utricule surface of near space vehicle.
Further, this system also comprises: measuring equipment, be arranged near space vehicle utricule surface, be connected with communicating terminal, be connected to set up communication by communicating terminal and ground base station.
Further, measuring equipment comprises following any one or plurality of devices: multiple temperature sensing device, is evenly arranged on the equatorial line of the outer surface of near space vehicle; Humidity sensor equipment, is arranged at the top of the outer surface of near space vehicle; Differential pressure of atmospheric pressure sensing equipment, is arranged at the top of the outer surface of near space vehicle; Barometric surveying equipment, is arranged at the top of the outer surface of near space vehicle; Wind speed and direction sensing equipment, is arranged at the top of the outer surface of near space vehicle; And GPS receiving equipment, be arranged at the top of the outer surface of near space vehicle.
Further, communicating terminal comprises iridium satellite transparent transmission terminal.
Further, controller comprises following any one or various controller: priming system Blasting Control device, is connected with the priming system of near space vehicle, performs explosion for controlling priming system; Valve positioner, is connected with the valve of near space vehicle, opens or close for by-pass valve control; Load heavy burden controller, is connected with the target load of near space vehicle, and depart near space vehicle for control objectives load, wherein, target load is arranged in the gondola of near space vehicle; And boat lamp controller, be connected with the boat lamp of near space vehicle, open for controlling boat lamp or close, wherein, on the utricule that boat lamp is arranged near space vehicle or in the gondola of near space vehicle.
To achieve these goals, according to another aspect of the present utility model, provide a kind of near space vehicle.This near space vehicle comprises any one control system near space vehicle that the utility model provides.
By the utility model, this control system being used near space vehicle is owing to comprising: communicating terminal, is arranged at the utricule surface of near space vehicle, sets up communication and be connected, and be controlled by ground base station with ground base station, and controller, be arranged at the utricule surface of near space vehicle, be connected with communicating terminal, be connected for setting up communication by communicating terminal and ground base station, to control the operation of the target device near space vehicle, solve the problem that when carrying out security control near space vehicle, flight control computer load burden is larger, and then the controller on utricule surface being positioned near space vehicle is set up communication by communicating terminal and ground base station and is connected, to control the operation of the target device near space vehicle, reach the effect reducing flight control computer load burden.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the schematic diagram of the control system near space vehicle according to the utility model first embodiment; And
Fig. 2 is the schematic diagram of the control system near space vehicle according to the utility model second embodiment.
Embodiment
It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.Below with reference to the accompanying drawings and describe the utility model in detail in conjunction with the embodiments.
The application's scheme is understood better in order to make those skilled in the art person, below in conjunction with the accompanying drawing in the embodiment of the present application, technical scheme in the embodiment of the present application is clearly and completely described, obviously, described embodiment is only the embodiment of the application's part, instead of whole embodiments.Based on the embodiment in the application, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all should belong to the scope of the application's protection.
It should be noted that, term " first ", " second " etc. in the instructions of the application and claims and above-mentioned accompanying drawing are for distinguishing similar object, and need not be used for describing specific order or precedence.Should be appreciated that the data used like this can be exchanged, in the appropriate case so that the embodiment of the application described herein.In addition, term " comprises " and " having " and their any distortion, and intention is to cover not exclusive comprising.
According to embodiment of the present utility model, provide a kind of control system near space vehicle.
Fig. 1 is the schematic diagram of the control system near space vehicle according to the utility model first embodiment.As shown in Figure 1, this control system being used near space vehicle comprises: communicating terminal 10 and controller 20.
Communicating terminal 10, is arranged at the utricule surface of near space vehicle, sets up communication and be connected, and be controlled by ground base station with ground base station.
Controller 20, is arranged at the utricule surface of near space vehicle, is connected, is connected for setting up communication by communicating terminal 10 and ground base station, to control the operation of the target device near space vehicle with communicating terminal 10.
Communicating terminal 10 achieves the communication between near space vehicle and ground base station.Also possess the communicating terminal corresponding with it in ground base station, be connected by wireless network between high-altitude and the communicating terminal on ground, thus realize the communication between near space vehicle and ground base station.Ground base station can send command information to controller 20, and the communicating terminal that is conveyed through of command information realizes.Command information is used to indicate controller 20 and controls target device near space vehicle and run.Controller 20 inside is integrated with control chip, by control chip controls transfer to the current signal of target device or voltage signal, with the operation of control objectives equipment.
Such as, communicating terminal 10 receives the instruction of the lifting flying height that ground base station sends, then communicating terminal 10 by this command to controller 20, controller 20 controls some load near space vehicle, it is made to depart near space vehicle, and then alleviating the heavy burden of near space vehicle, flying height is promoted.
Preferably, above-mentioned communicating terminal 10 can be iridium satellite transparent transmission terminal.Complete the passback with the communication of ground base station, control and measurement data by iridium satellite transparent transmission terminal, effectively can increase the contact scope of communication.
According to the control system near space vehicle of this embodiment, owing to being provided with communicating terminal 10 and controller 20 on the utricule surface of near space vehicle, set up communication by communicating terminal 10 and ground base station to be connected, and then the target device that controller 20 controls near space vehicle runs, under ensureing that ground base station realizes the prerequisite controlled near space vehicle security of operation, increase any burden to the flight control computer configured near space vehicle, thus make flight control computer can reserve more space to perform other TT&C task.
In a kind of optional embodiment, this control system being used near space vehicle can also comprise: flight control computer, be arranged in the gondola of near space vehicle, be connected with controller 20 with communicating terminal 10 respectively, set up communication by communicating terminal 10 and ground base station be connected for controlling controller 20, ground base station can realize based on flight control computer the control of controller 20.
This embodiment realizes the control of ground base station to controller 20 by flight control computer, and flight control computer can hold the state of flight of near space vehicle on the whole, thus improves the security of near space vehicle flight.In flight control computer temporary derangement or when cannot normally work, directly can realize the control of ground base station to controller 20 by communicating terminal 10, the generation of the situation of whole near space vehicle and ground base station lost contact when effectively prevent flight control computer fault, and then ensure that the security control near space vehicle.
In the above-described embodiments, this control system being used near space vehicle can also comprise: measuring equipment, being arranged at the utricule surface of near space vehicle, being connected, for measuring the flight environment of vehicle data of near space vehicle with flight control computer.
This measuring equipment, under the control of flight control computer, performs measurement task.Such as, ground base station have sent the instruction of the environment temperature detecting current near space vehicle, then receive this instruction by communicating terminal 10, this instruction is sent to flight control computer by communicating terminal 10, and flight control computer will control the detection being arranged at the temperature sensor execution environment temperature of near space vehicle.Above-mentioned flight environment of vehicle data comprise environment temperature, wind direction, air pressure etc. residing near space vehicle.The utility model does not carry out concrete restriction to flight environment of vehicle data.
This embodiment realizes the control of ground base station to measuring equipment by flight control computer, to measure flight environment of vehicle data.When base station returns flight environment of vehicle data earthward, also need via flight control computer.Flight control computer can carry out otherwise safe observing and controlling in conjunction with flight environment of vehicle data near space vehicle, and then ensure that the safety in operation of near space vehicle better.
In the above-described embodiments, measuring equipment is connected with communicating terminal 10, and sets up communication by communicating terminal 10 and ground base station and be connected.
Specifically, between measuring equipment and ground base station, data transmission, can realize based on flight control computer.Also namely, measuring equipment is connected with communicating terminal 10, and flight environment of vehicle data are transferred to communicating terminal 10 by flight control computer control survey equipment, and flight environment of vehicle data are transferred to ground base station by communicating terminal 10 again.
In a kind of preferred embodiment, this system can also comprise: measuring equipment, being arranged at the utricule surface of near space vehicle, being connected, for measuring the flight environment of vehicle data of near space vehicle with controller 20.
In this embodiment, measuring equipment is connected with controller 20, and the control of direct controlled device 20 performs the detection of flight environment of vehicle data.This embodiment, when flight control computer normally runs, can reserve more free space for flight control computer, and promotes travelling speed when flight control computer performs other tasks; In flight control computer temporary derangement or when cannot normally work, the detection independently realizing flight environment of vehicle data in flight control computer can be departed from, and carry out with ground base station the transmission detecting data.In addition, controller 20 can obtain flight environment of vehicle data, and the operation of other equipment with reference to this flight environment of vehicle Data Control near space vehicle.Such as, when flight environment of vehicle data display flying height is on the low side, controller 20 can bear a heavy burden to the load of near space vehicle and regulate, and such as, can control certain load and depart near space vehicle.
In a kind of optional embodiment, this system can also comprise: energy supply subsystem, the gondola utricule that is interior or near space vehicle being arranged near space vehicle is surperficial, is connected with measuring equipment, controller 20 and any one in communicating terminal 10 or multiple equipment.
Energy supply subsystem in this embodiment, for providing energy for any one in measuring equipment, controller 20 and communicating terminal 10 or multiple equipment.As an independently energy delivery system, go wrong at the energy source of near space vehicle, or during depleted of energy, still energy can be provided for measuring equipment, controller 20 and communicating terminal 10, and then the communication between guarantee near space vehicle and ground base station, realize ground base station and the security of operation of near space vehicle is controlled.
In the above-described embodiments, energy supply subsystem can comprise primary power cource and standby power supply, and wherein, primary power cource is arranged in the gondola of near space vehicle, and standby power supply is arranged at the utricule surface of near space vehicle.Under normal circumstances, be the supplying energies such as measuring equipment, controller 20 and communicating terminal 10 by primary power cource; When primary power cource lost efficacy, be the supplying energies such as measuring equipment, controller 20 and communicating terminal 10 by standby power supply.Primary power cource can be main battery, and standby power supply can be reserve battery.
In a kind of optional embodiment, this system can also comprise: measuring equipment, be arranged near space vehicle utricule surface, be connected with communicating terminal 10, be connected to set up communication by communicating terminal 10 and ground base station.
Particularly, in this embodiment, measuring equipment can carry out the transmission of data by communicating terminal 10 and ground base station, comprising: ground base station directly can send the instruction of measuring by communicating terminal 10 to measuring equipment; The data (flight environment of vehicle data) measuring gained can be transferred to ground base station by communicating terminal 10 by measuring equipment.This measuring equipment is independent of flight control computer and controller 20, and the data realized between ground base station are transmitted.When flight control computer and controller 20 break down, can ensure that ground base station can get the flight environment of vehicle data of near space vehicle.
In a kind of optional embodiment, measuring equipment can comprise following any one or plurality of devices: multiple temperature sensing device (such as, 4 temperature sensors), is evenly arranged on the equatorial line of the outer surface of near space vehicle; Humidity sensor equipment, is arranged at the top of the outer surface of near space vehicle; Differential pressure of atmospheric pressure sensing equipment, is arranged at the top of the outer surface of near space vehicle; Barometric surveying equipment, is arranged at the top of the outer surface of near space vehicle; Wind speed and direction sensing equipment, is arranged at the top of the outer surface of near space vehicle; And GPS receiving equipment, be arranged at the top of the outer surface of near space vehicle.
Above-mentioned temperature sensing device, humidity sensor equipment, differential pressure of atmospheric pressure sensing equipment, barometric surveying equipment, wind speed and direction sensing equipment, GPS receiving equipment can be respectively temperature sensor, humidity sensor, differential pressure of atmospheric pressure sensor, wind speed wind direction sensor, GPS.Multiple temperature sensing device is evenly arranged on the equatorial line of the outer surface of near space vehicle, more accurately can detects the environment temperature of near space vehicle all sidedly; Humidity sensor equipment, differential pressure of atmospheric pressure sensing equipment, barometric surveying equipment, wind speed and direction sensing equipment, GPS receiving equipment are arranged at the top of the outer surface of near space vehicle, corresponding environmental data can be detected more exactly.
In a kind of optional embodiment, controller 20 comprises following any one or various controller: priming system Blasting Control device, is connected with the priming system of near space vehicle, performs explosion for controlling priming system; Valve positioner, is connected with the valve of near space vehicle, opens or close for by-pass valve control; Load heavy burden controller, is connected with the target load of near space vehicle, and depart near space vehicle for control objectives load, wherein, target load is arranged in the gondola of near space vehicle; And boat lamp controller, be connected with the boat lamp of near space vehicle, open for controlling boat lamp or close, wherein, on the utricule that boat lamp is arranged near space vehicle or in the gondola of near space vehicle.
Specifically, the Blasting Control of priming system is the consideration for aircraft flight safety, for the recovery of near space vehicle; Load bear a heavy burden control for adjusting the weight of near space vehicle, to control the flying height of near space vehicle; The control of valve is carried out when near space vehicle lands usually; The opening of boat lamp can as near space vehicle a kind of indicator signal outwardly.Above-mentioned controller may be used for the switch of control objectives equipment, such as, and can the switch of by-pass valve control by valve positioner.
Fig. 2 is the schematic diagram of the control system near space vehicle according to the utility model second embodiment.This embodiment can as a kind of preferred implementation embodiment illustrated in fig. 1.As shown in Figure 2, this system comprises: the flight control computer 50 being positioned at the gondola B of near space vehicle, be positioned at the communicating terminal 10 on the surface of the utricule A of near space vehicle, controller 20, measuring equipment 30 and energy supply subsystem 40 (except primary power cource), wherein, be connected by cable between communicating terminal 10, controller 20, measuring equipment 30 and energy supply subsystem 40, flight control computer 50 can respectively be positioned at the communicating terminal 10 on utricule surface, controller 20, measuring equipment 30 be connected by cable.
Specifically, communicating terminal 10 can be iridium satellite equipment transparent transmission terminal.Iridium satellite equipment transparent transmission terminal can be connected with flight control computer 50, completes and the communication of ground base station (comprising the transmission of steering order and the passback etc. of measurement data).Or also can depart from the control of flight control computer 50, independent and ground base station carries out communication.Iridium satellite equipment transparent transmission terminal can ensure larger communication context.When this system and flight control computer 50 lost contact, by iridium satellite equipment transparent transmission terminal, realize ground base station to the data acquisition of aircraft and the control to controller 20.This communicating terminal 10 with embodiment illustrated in fig. 1 in identical, repeat no more here.
The equipment that controller 20 can control comprises: 10 tunnel explosion priming systems, load, valve and boat lamp etc.Controller 20 inside is integrated with control chip, and controller 20 is connected with valve, priming system, load, boat lamp etc. by cable.After controller 20 receives steering order, generated voltage signal or the current signal of control objectives equipment (such as, valve) by control chip, to realize the control to this equipment.Controller 20 can be controlled by flight control computer 50, performs control to target device.Controller 20 can receive the control information that flight control computer 50 sends, to perform control to target device.Meanwhile, controller 20 also can depart from the control of flight control computer 50, independently performs control to target device.This controller 20 with embodiment illustrated in fig. 1 in identical, repeat no more here.
Measuring equipment 30 can comprise: No. 4 temperature sensors, humidity sensor, differential pressure of atmospheric pressure sensor, pressure altimeter, wind speed wind direction sensor and GPS etc.No. 4 temperature sensors are arranged on the equatorial line on utricule A surface respectively, and evenly arrange.Humidity sensor, differential pressure of atmospheric pressure sensor, pressure altimeter, wind speed wind direction sensor and GPS are arranged at the top of utricule A outside surface respectively.In normal operation, this system the data that measuring equipment 30 obtains can be transferred to flight control computer 50 carry out data analysis and passback ground base station.When flight control computer 50 breaks down, measuring equipment 30 can depart from the control of flight control computer 50, independently performs Detection task.
Energy supply subsystem 40 comprises main battery and reserve battery.Reserve battery used when main battery loses efficacy, and main battery can automatically switch to reserve battery, thus reserve battery continues as controller 20, measuring equipment 30, communicating terminal 10 supplying energy, enhances the reliability of this system.Wherein, (not shown) in the gondola that main battery is arranged near space vehicle, reserve battery is arranged on the utricule surface of near space vehicle.
Because near space vehicle flight is aerial at stratospheric height, be in the environment of low-temp low-pressure, minimum temperature is-70 DEG C, and air pressure is about 3000Pa, therefore ensures that the reliability of this system in high altitude environment is of crucial importance.The control system near space vehicle according to this embodiment comprises: communicating terminal 10, controller 20, measuring equipment 30, energy supply subsystem 40 and flight control computer 50, wherein, communicating terminal 10, controller 20, measuring equipment 30, energy supply subsystem 40 possesses the ability of independent operating, the control that can depart from flight control computer 50 is independently executed the task, effectively improve the reliability of near space vehicle, and alleviate the observing and controlling burden of flight control computer 50, can be flight control computer 50 and save more resource space for work such as the control of aircraft flight control system and the computings of mission payload.In addition, communicating terminal 10, controller 20, measuring equipment 30, energy supply subsystem 40 and flight control computer 50 can reasonably coordinate to perform inter-related task, effectively improve the safety running control efficiency of near space vehicle.
In addition, embodiment still provides a kind of near space vehicle according to of the present utility model, this near space vehicle comprises any one control system near space vehicle that the utility model provides.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (12)
1. for a control system near space vehicle, it is characterized in that, comprising:
Communicating terminal, is arranged at the utricule surface of near space vehicle, sets up communication and be connected, and be controlled by described ground base station with ground base station; And
Controller, is arranged at the utricule surface of described near space vehicle, is connected, is connected for setting up communication by described communicating terminal with described ground base station, to control the operation of the target device in described near space vehicle with described communicating terminal.
2. system according to claim 1, is characterized in that, described system also comprises:
Flight control computer, is arranged in the gondola of described near space vehicle, is connected respectively with described communicating terminal with described controller, sets up communication be connected for controlling described controller by described communicating terminal with described ground base station.
3. system according to claim 2, is characterized in that, described system also comprises:
Measuring equipment, being arranged at the utricule surface of described near space vehicle, being connected, for measuring the flight environment of vehicle data of described near space vehicle with described flight control computer.
4. system according to claim 3, is characterized in that,
Described measuring equipment, is connected with described communicating terminal, and sets up communication by described communicating terminal with described ground base station and be connected.
5. system according to claim 1, is characterized in that, described system also comprises:
Measuring equipment, being arranged at the utricule surface of described near space vehicle, being connected, for measuring the flight environment of vehicle data of described near space vehicle with described controller.
6. system according to claim 5, is characterized in that, described system also comprises:
Energy supply subsystem, the gondola utricule that is interior or described near space vehicle being arranged at described near space vehicle is surperficial, is connected with described measuring equipment, described controller and any one in described communicating terminal or multiple equipment.
7. system according to claim 6, it is characterized in that, described energy supply subsystem comprises primary power cource and standby power supply, wherein, described primary power cource is arranged in the gondola of described near space vehicle, and described standby power supply is arranged at the utricule surface of described near space vehicle.
8. system according to claim 1, is characterized in that, described system also comprises:
Measuring equipment, be arranged at described near space vehicle utricule surface, be connected with described communicating terminal, be connected to set up communication by described communicating terminal with described ground base station.
9. system according to claim 8, is characterized in that, described measuring equipment comprises following any one or plurality of devices:
Multiple temperature sensing device, is evenly arranged on the equatorial line of the outer surface of described near space vehicle;
Humidity sensor equipment, is arranged at the top of the outer surface of described near space vehicle;
Differential pressure of atmospheric pressure sensing equipment, is arranged at the top of the outer surface of described near space vehicle;
Barometric surveying equipment, is arranged at the top of the outer surface of described near space vehicle;
Wind speed and direction sensing equipment, is arranged at the top of the outer surface of described near space vehicle; And
GPS receiving equipment, is arranged at the top of the outer surface of described near space vehicle.
10. system according to claim 1, is characterized in that, described communicating terminal comprises iridium satellite transparent transmission terminal.
11. systems according to claim 1, is characterized in that, described controller comprises following any one or various controller:
Priming system Blasting Control device, is connected with the priming system of described near space vehicle, performs explosion for controlling described priming system;
Valve positioner, is connected with the valve of described near space vehicle, for controlling described valve open or closedown;
Load heavy burden controller, is connected with the target load of described near space vehicle, departs from described near space vehicle for controlling described target load, and wherein, described target load is arranged in the gondola of described near space vehicle; And
Boat lamp controller, is connected with the boat lamp of described near space vehicle, opens for controlling described boat lamp or closes, wherein, on the utricule that described boat lamp is arranged on described near space vehicle or in the gondola of described near space vehicle.
12. 1 kinds of near space vehicles, is characterized in that, comprise the control system near space vehicle according to any one of claim 1 to claim 11.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520646984.0U CN204925668U (en) | 2015-08-25 | 2015-08-25 | A control system with close on spacecraft for closing on spacecraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520646984.0U CN204925668U (en) | 2015-08-25 | 2015-08-25 | A control system with close on spacecraft for closing on spacecraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106940537A (en) * | 2017-04-17 | 2017-07-11 | 北京航空航天大学 | A kind of near space aerostatics method of controlling security |
| CN109828321A (en) * | 2019-02-28 | 2019-05-31 | 中国科学院国家空间科学中心 | A kind of active expansion falling sphere near space atmospheric environment in-situ investigation |
| CN111122045A (en) * | 2019-12-19 | 2020-05-08 | 中国科学院光电研究院 | Tethered balloon differential pressure monitoring system |
-
2015
- 2015-08-25 CN CN201520646984.0U patent/CN204925668U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106940537A (en) * | 2017-04-17 | 2017-07-11 | 北京航空航天大学 | A kind of near space aerostatics method of controlling security |
| CN109828321A (en) * | 2019-02-28 | 2019-05-31 | 中国科学院国家空间科学中心 | A kind of active expansion falling sphere near space atmospheric environment in-situ investigation |
| CN111122045A (en) * | 2019-12-19 | 2020-05-08 | 中国科学院光电研究院 | Tethered balloon differential pressure monitoring system |
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Effective date of registration: 20230630 Address after: Room 501, Building D2, Songshan Lake International Innovation and Entrepreneurship Community, Songshan Lake High tech Industrial Development Zone, Dongguan City, Guangdong Province, 523000 Patentee after: Dongguan Dongguan Institute of Science and Technology Innovation Address before: 523000 Room 502, 5th floor, building 1, innovation and Technology Park, Songshanhu high tech Industrial Development Zone, Dongguan City, Guangdong Province Patentee before: DONGGUAN FRONTIER TECHNOLOGY INSTITUTE Patentee before: SHENZHEN KUANG-CHI SPACE TECH. Co.,Ltd. |