CN102829857A - Monitoring method of satellite air transportation vibration response - Google Patents
Monitoring method of satellite air transportation vibration response Download PDFInfo
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- CN102829857A CN102829857A CN2012102855698A CN201210285569A CN102829857A CN 102829857 A CN102829857 A CN 102829857A CN 2012102855698 A CN2012102855698 A CN 2012102855698A CN 201210285569 A CN201210285569 A CN 201210285569A CN 102829857 A CN102829857 A CN 102829857A
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Abstract
The invention discloses a monitoring method of satellite air transportation vibration response. The monitoring method comprises the following steps: charge type acceleration sensors are stuck on a satellite, a connecting face of a packing case and the satellite, and the upper part and the lower part of a packing case shock absorber, wherein a DC-DC power converter and a charge amplifier are arranged in the packing case; a three-direction accelerometer and a data collector are connected to the charge amplifier; two DC storage batteries for a vehicle are respectively connected to the DC-DC power converter and the data collector to power up; a lead is connected with an inlet-outlet packing case through a flange; and the data collector can allow the DC storage batteries for the vehicle to power up and a lithium battery of a notebook computer to power up. The invention has the following advantages that: (1) the monitoring method of the satellite air transportation vibration response is provided; (2) the monitoring method provides a reference for making an air transportation scheme of a subsequent specification; and (3) the monitoring method is suitable for monitoring satellite roadway transportation vibration response at short time.
Description
Technical field
The present invention relates to the satellite monitoring method, the especially air transport vibratory response of certain platform satellite of this institute monitoring is equally applicable to the satellite air transport vibratory response monitoring of all other platforms, as: certain platform etc. are specifically related to a kind of satellite air transport vibratory response monitoring method.
Background technology
Transportation is an important component part in the lifetime of satellite section, and the excitation of transportation is different from the excitation of noise and sinusoidal vibration, and it is the excitation-basic excitation of kinematic parameter.Same satellite may run into multiple transportation environment, like land transport, marine transportation or air transport etc.Generally speaking, in the transportation, the vibration of land transportation is than marine or even more serious in the air, and land transportation comprises highway and two kinds of environment of transportation by railroad, and the mechanical environment of transport by road is more abominable than transportation by railroad.Can find out from several kinds of transportation measurement data of certain satellite of this institute: the vibration peak of transport by road is 2～5 times of transportation by railroad, and in 3～5 day time of whole transportation by railroad, vibration peak maintains higher level always.Air transport does not have any vibration basically at inflight phase, and significantly response all concentrates on the short period of taking off and landing.So, adopt the air transport vibration condition to be much better than transportation by railroad.
Certain satellite is confirmed to enter the orbit in the emission of certain cosmodrome, satellite adopt certain type aircraft from the somewhere air transport to certain airport.Owing to be that the whole star of this institute satellite adopts air transport first; For guaranteeing certain satellite " safe and reliable, perfectly safe " in transportation; Also in order to obtain first hand response data; Simultaneously for the formulation of follow-up model traffic program provides reference, this is marched into the arena and the whole process of satellite and packing case transportation thereof has been carried out vibratory response measures in real time.
When satellite adopted the land transportation mode, the number of vibratory response measuring system was adopted, the powerup issue of constant current source and computer all solves than being easier to.And the incoming end of not supplying power in the transporter cabin, the consideration from secure context does not allow cabin on the inflammable articles band.Can carry the accumulator (storage battery) that is wrapped in the iron sheet case and board, for signal is fitted power supplies such as transferring device, Dynamic Data Acquiring device.The power supply of notebook computer is provided by own lithium battery, is with several battery of the same type that are full of electricity according to time and distance needs more.
Because the not power supply of packing case air-conditioning can't be opened in the air transport process, for satisfying environmental requirement in the case in the transportation, the sealing of packing case must be got well.So, to consider sealing problem when test cable is drawn in packing case.
The present invention relates to satellite air transport vibratory response monitoring system, comprise the supporting charge amplifier of cabling, acceleration transducer and the number power supply modes of adopting of test cable etc.Do not have at present to find explanation or report, do not collect both at home and abroad similarly data as yet yet with similar techniques of the present invention.
Summary of the invention
According to preamble, in order to satisfy the requirement of satellite vibratory response monitoring, the object of the present invention is to provide a kind of practicable method that is used for satellite air transport vibration monitoring.Utilize the present invention, on the basis of existing satellite vibratory response test, carry out optimal design, can effectively solve the problem of the each side such as power supply, sealing and security of air transport monitoring.
According to an aspect of the present invention, a kind of satellite air transport vibratory response monitoring method is provided, comprises the steps:
On satellite, packing case and satellite joint face, packing case vibration damper these local charge type acceleration transducers of pasting up and down;
DC-DC supply convertor and charge amplifier are installed in packing case;
Three-dimensional accelerometer, data acquisition unit are connected to charge amplifier;
Connect the DC-DC supply convertor respectively and data acquisition unit is supplied power with two DC car batteries;
Lead is connected the turnover packing case through flange;
Make data acquisition unit allow power supply of DC car battery and notebook to carry lithium battery power supply.
Preferably, the DC car battery is specially DC 12V car battery, and wherein a DC car battery is placed on by the packing case nearby, and an other DC car battery is placed near data acquisition unit.
Preferably, charge amplifier use ± 15V power supply, adopting the DC-DC supply convertor is its power supply.
Preferably, also comprise step: combine from the acceleration signal line of charge amplifier output, and be welded on the flange, this flange connects with the inner corresponding pre-buried flange of packing case and tightens.
Preferably, also comprise step: the test cable that packing case is outside, be connected with the pre-buried flange in packing case outside and tighten through flange, the other end of cable is connected with data acquisition unit.
Preferably, the other end of cable and the type of attachment between the data acquisition unit are BNC.
Preferably, charge amplifier, DC-DC supply convertor are installed in satellite packing case bottom.
Preferably, service cable separates with the acceleration signal cable, and is placed on the packing case next door nearby.
This method is satisfying under the prerequisite of satellite air transport about the requirement of aspects such as sealing, safety; Be installed in packing case inside to the instrument of participating in the experiment as much as possible; Reduce that the satellite packing case goes on or off the plane and the airport carrying object of truck (flat-bed trailer) up and down, also more favourable to the reliability and stability of monitoring system.The present invention has obtained following beneficial effect:
⑴ provide a kind of monitoring method of satellite air transport vibratory response;
⑵ provide reference to the formulation of the air transport monitoring scheme of follow-up model;
⑶ equally also can be applicable to the satellite transport by road vibration monitoring of short time.
Description of drawings
Fig. 1 is a satellite air transport vibration monitor system synoptic diagram.
Fig. 2 is satellite air transport response measurement system signal and power supply link process flow diagram.
Fig. 3 is charge amplifier power supply process flow diagram.
Among the figure: 1 is acceleration transducer; 2 is shock-absorbing spring; 41 is first plug; 42 is second plug; 43 is the 3rd plug; 44 is the 4th plug; 3 is pocket computer.
Embodiment
On satellite, packing case and satellite joint face, packing case vibration damper wait the place that reference value is relatively arranged to paste the charge type acceleration transducer up and down.Be installed in satellite packing case bottom to DC-DC supply convertor and charge amplifier, and connect lead by shown in Figure 2.Combine from the acceleration signal line of charge amplifier output, and be welded on the flange, this flange connects with the inner corresponding pre-buried flange of packing case and tightens.The test cable that packing case is outside is connected and tightens through the outside pre-buried flange of flange and packing case equally, and the other end of cable is connected with data acquisition unit, and common type of attachment is BNC.Data acquisition unit and computer all are placed on the working position.
Acceleration signal comes out to insert charge amplifier from sensor, after the charge amplifier conditioning, is output as voltage signal, inserts data acquisition unit, is transferred to computer through 1394 live wires, like Fig. 1, shown in 2.
In order to guarantee the sealing of packing case, the vibratory response test cable connects through the aviation plug flange, and is as shown in Figure 1, and the plug model is looked how many selections of signalling channel number, like specifications such as 65 cores, 55 cores, 31 cores.Charge amplifier, DC-DC supply convertor are installed in satellite packing case bottom.
System adopts the DC 12V car battery power supply that allows usefulness on the aircraft, and general charge amplifier needs use ± 15V power supply, thus can only adopt the DC-DC supply convertor, like Fig. 2, shown in 3.When the difference between current when instrument power supply starts because of usual Switching Power Supply seldom is operate as normal 10 times are so the starting current of DC-DC is very big when system has just switched on.If the cable of power supply usefulness is longer, then the pressure drop on the lead is bigger, may be lower than normal working voltage because of the DC-DC input terminal voltage, and cause DC-DC normally not start.So in this programme, service cable separates with the acceleration signal cable, and be placed on the packing case next door nearby,, guarantee that supply convertor and charge amplifier can operate as normal to reduce the influence that long lead resistance brings.Because the data acquisition unit supply current is bigger, for guaranteeing 5 hours continous-stable power-supplyings, so adopted 2 accumulators to supply power respectively.
Accumulator all is placed in the iron sheet case of customization, places one near packing case, receives the both positive and negative polarity of accumulator to positive and negative two ends of 1 meter long supply lines respectively, and inner supply convertor and the charge amplifier of packing case this moment is just in running order.An other accumulator is placed near data acquisition unit, connects power lead, and number was adopted also and started working this moment.
Be connected to computer to data line (being preferably 1394 live wires, USB2.0 line) by counting to adopt, open computer, log-on data acquisition and recording program.
In sum; This method is as the vibratory response monitoring method of satellite air transport; Satisfying under the prerequisite of air transportation about the secure context requirement, can guarantee the vibratory response monitoring that the satellite transportation is omnidistance simultaneously, the Transport Safety of marching into the arena for satellite provides the force data support.
Claims (8)
1. a satellite air transport vibratory response monitoring method is characterized in that, comprises the steps:
On satellite, packing case and satellite joint face, packing case vibration damper these local charge type acceleration transducers of pasting up and down;
DC-DC supply convertor and charge amplifier are installed in packing case;
Three-dimensional accelerometer, data acquisition unit are connected to charge amplifier;
Connect the DC-DC supply convertor respectively and data acquisition unit is supplied power with two DC car batteries;
Lead is connected the turnover packing case through flange;
Make data acquisition unit allow power supply of DC car battery and notebook to carry lithium battery power supply.
2. satellite air transport vibratory response monitoring method according to claim 1; It is characterized in that; The DC car battery is specially DC 12V car battery, and wherein a DC car battery is placed on by the packing case nearby, and an other DC car battery is placed near data acquisition unit.
3. satellite air transport vibratory response monitoring method according to claim 2 is characterized in that, charge amplifier use ± 15V power supply, and adopting the DC-DC supply convertor is its power supply.
4. satellite air transport vibratory response monitoring method according to claim 1; It is characterized in that; Also comprise step: combine from the acceleration signal line of charge amplifier output, and be welded on the flange, this flange connects with the inner corresponding pre-buried flange of packing case and tightens.
5. satellite air transport vibratory response monitoring method according to claim 1 is characterized in that, also comprises step: the test cable that packing case is outside, and be connected with the pre-buried flange in packing case outside and tighten through flange, the other end of cable is connected with data acquisition unit.
6. satellite air transport vibratory response monitoring method according to claim 5 is characterized in that the other end of cable and the type of attachment between the data acquisition unit are BNC.
7. satellite air transport vibratory response monitoring method according to claim 1 is characterized in that, charge amplifier, DC-DC supply convertor are installed in satellite packing case bottom.
8. satellite air transport vibratory response monitoring method according to claim 1 is characterized in that service cable separates with the acceleration signal cable, and is placed on the packing case next door nearby.
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| CN2012102855698A CN102829857A (en) | 2012-08-10 | 2012-08-10 | Monitoring method of satellite air transportation vibration response |
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| CN2012102855698A CN102829857A (en) | 2012-08-10 | 2012-08-10 | Monitoring method of satellite air transportation vibration response |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500833A (en) * | 2016-10-21 | 2017-03-15 | 上海卫星工程研究所 | Spaceborne vibration monitoring device based on vibrating sensor |
| CN108986436A (en) * | 2018-06-19 | 2018-12-11 | 上海卫星工程研究所 | A kind of communication system for the transmission of Satellite Vibration data |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101419442A (en) * | 2008-12-08 | 2009-04-29 | 浙江大学 | Portable elevator dynamic characteristic data acquisition unit based on USB interface |
| CN101493355A (en) * | 2009-02-18 | 2009-07-29 | 长沙全程数字机电科技有限公司 | Integration oscillation monitoring instrument |
| CN201378174Y (en) * | 2008-11-28 | 2010-01-06 | 上海宝钢工业检测公司 | Digital vibration acceleration sensor |
| CN202075034U (en) * | 2011-05-10 | 2011-12-14 | 江门机械设备（轴承）有限公司 | Rolling bearing vibration acceleration and abnormal sound detection device |
| CN102331547A (en) * | 2011-07-12 | 2012-01-25 | 江苏镇安电力设备有限公司 | Transformer winding vibration on-line monitoring and fault diagnosis method |
-
2012
- 2012-08-10 CN CN2012102855698A patent/CN102829857A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201378174Y (en) * | 2008-11-28 | 2010-01-06 | 上海宝钢工业检测公司 | Digital vibration acceleration sensor |
| CN101419442A (en) * | 2008-12-08 | 2009-04-29 | 浙江大学 | Portable elevator dynamic characteristic data acquisition unit based on USB interface |
| CN101493355A (en) * | 2009-02-18 | 2009-07-29 | 长沙全程数字机电科技有限公司 | Integration oscillation monitoring instrument |
| CN202075034U (en) * | 2011-05-10 | 2011-12-14 | 江门机械设备（轴承）有限公司 | Rolling bearing vibration acceleration and abnormal sound detection device |
| CN102331547A (en) * | 2011-07-12 | 2012-01-25 | 江苏镇安电力设备有限公司 | Transformer winding vibration on-line monitoring and fault diagnosis method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500833A (en) * | 2016-10-21 | 2017-03-15 | 上海卫星工程研究所 | Spaceborne vibration monitoring device based on vibrating sensor |
| CN108986436A (en) * | 2018-06-19 | 2018-12-11 | 上海卫星工程研究所 | A kind of communication system for the transmission of Satellite Vibration data |
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Owner name: SHANGHAI SATELLITE EQUIPMENT INSTITUTE Free format text: FORMER OWNER: SHANGHAI SATELLITE ENGINEERING RESEARCH INSTITUTE Effective date: 20130826 |
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Effective date of registration: 20130826 Address after: 200240 Shanghai city Minhang District Huaning Road No. 251 Applicant after: Shanghai Institute of Satellite Equipment Address before: 200240 Shanghai city Minhang District Huaning Road No. 251 Applicant before: Shanghai Satellite Engineering Research Institute |
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Application publication date: 20121219 |