CN101938076A - Microsatellite unplugged cable network - Google Patents
Microsatellite unplugged cable network Download PDFInfo
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- CN101938076A CN101938076A CN 201010253646 CN201010253646A CN101938076A CN 101938076 A CN101938076 A CN 101938076A CN 201010253646 CN201010253646 CN 201010253646 CN 201010253646 A CN201010253646 A CN 201010253646A CN 101938076 A CN101938076 A CN 101938076A
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Abstract
The invention relates to a microsatellite unplugged cable network, which solves the problem that the design of a star catalogue plug is difficult due to structural characteristics of the microsatellite of small volume, body-mounted solar cell array and the like. In the prior art, in order to preserve the star catalogue plug, only a star catalogue plug interface is arranged on the body-mounted solar cell array, which necessarily damages the integral structure of the satellite body-mounted solar cell array. In order to meet the task requirement of the microsatellite and overcome the defects in the prior art, the microsatellite unplugged cable network integrates the satellite star catalogue and the microsatellite unplugged cable, maintains satellite power supply of the traditional unplugged cable, a satellite task test computer interface and controlled quantity, state quantity and analog quantity contacts of a wired station, reasonably utilizes limited pin resources of the unplugged cable, and successfully integrates the traditional star catalogue plug and star catalogue cable into the unplugged cable network according to the electromagnetic compatibility of strong and weak current and pin multiplexing of an electric connector.
Description
Technical field
The present invention relates to a kind of microsatellite and take off plug in cable system, can be applicable in the test of space industry microsatellite.
Background technology
In the integration test process of satellite, the wireline interface of ground checkout equipment and satellite comprises two kinds: a kind of is satellite star catalogue plug interface, and connected cable is called the star catalogue cable; Another kind is a satellite pull-off plug interface, and coupled cable is called and takes off the plug-in cable.In the traditional design of satellite, test assignments such as storage battery equalizing charge, satellite emergency-off and primary power source measurement are finished by the star catalogue cable; The tasks such as controlled quentity controlled variable, quantity of state and analog measurement of satellite power supply, Star Service test computer interface and wired TV station are finished by the cable that comes off.When the satellite volume was big, it is less relatively that wireline interface takies the ratio of satellite structure resource; But when the satellite volume is less, the ratio that wireline interface takies the satellite structure resource will become bigger.In the wireline interface design of large satellite and moonlet, because the solar array of large satellite and moonlet mainly adopts the form of the sun wing, and the satellite volume is bigger, and enough spatial design star catalogue plugs are arranged.But in the design of microsatellite wireline interface, because design features such as the microsatellite volume is little, body dress solar battery array make the satellite structure resource very valuable, design star catalogue plug has difficulties.Prior art can only design the star catalogue plug interface in order to keep the star catalogue plug of microsatellite on body packed battery battle array, but this must destroy the overall structure of satelloid dress solar battery array, will have a strong impact on the function and the performance of solar battery array.Because star catalogue plug/star catalogue cable only uses when ground test, the overall structure of therefore destroying solar battery array in order to design the star catalogue plug will lose more than gain.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of plug in cable system that takes off is provided, this takes off plugs in cable system and has solved the problem that can't design the star catalogue plug in the microsatellite, has realized in the traditional design star catalogue cable and has taken off all functions that the plug-in cable will be realized.
Technical solution of the present invention is:
A kind of microsatellite takes off plug in cable system, comprising eight cables and 15 plug connectors, is respectively first cable, second cable, the 3rd cable, the 4th cable, the 5th cable, the 6th cable, the 7th cable, the 8th cable, first plug connector, second plug connector, the 3rd plug connector, the 4th plug connector, the 5th plug connector, the 6th plug connector, the 7th plug connector, the 8th plug connector, the 9th plug connector, the tenth plug connector, the 11 plug connector, the 12 plug connector, the 13 plug connector, the 14 plug connector and the 15 plug connector;
Wherein, one end of first cable is connected with satellite by first plug connector, and first plug connector is fixed on the satellite base plate, and the other end of first cable is divided into four the tunnel, be respectively the first via, the second tunnel, Third Road and the four tunnel, wherein the first via is connected with an end of the 5th cable by second plug connector; The second the tunnel passes through the 3rd plug connector is connected with an end of the 4th cable; Third Road is connected with an end of the 3rd cable by the 4th plug connector; The four the tunnel passes through the 5th plug connector is connected with an end of second cable; The 5th cable transmission satellite and the rocket separation command signal and its other end are connected with carrier rocket by the 6th plug connector; The 4th cable transmission satellite and the rocket released state signal and its other end also are connected with carrier rocket by the 7th plug connector; The 3rd cable is that service cable and its other end are connected with an end of the 7th cable by the 8th plug connector, and the 7th cable is connected with ground power supply and distribution test equipment by the tenth plug connector for prolonging cable and its other end; The second cable transmission test signal and its other end are connected with an end of the 6th cable by the 9th plug connector, the 6th cable is one minute three cable, three road cables that are divided into are respectively the first sub-road, the second sub-road and the 3rd sub-road, and wherein the transmission of the first sub-road is connected with ground power supply and distribution test equipment by the 11 plug connector for controlled quentity controlled variable, quantity of state and the analog quantity of distribution and its; The second sub-road is connected with the emergency protection for power-cut plug by the 13 plug connector, is used for the emergency-off of satellite; The 3rd sub-road is connected with an end of the 8th cable by the 12 plug connector, the 8th cable is the one-to-two cable, the two-way cable that is divided into respectively the transfer management control signal with the Star Service scheduling signals and be connected with the Star Service test computer with the 15 plug connector by the 14 plug connector respectively;
Described second plug connector, the 3rd plug connector, the 4th plug connector and the 5th plug connector are fixed on the moonlet adapter lower plate; The 6th plug connector, the 7th plug connector, the 8th plug connector and the 9th plug connector are fixed on the delivery instrument room disk.
Described the 4th plug connector, the 5th plug connector, the 8th plug connector, the 9th plug connector, the tenth plug connector and the 11 plug connector are Y2-50 type plug connector;
Described second plug connector, the 3rd plug connector, the 6th plug connector, the 7th plug connector, the 12 plug connector, the 14 plug connector and the 15 plug connector are Y2-10 type plug connector;
Described the 13 plug connector is a J36A-9ZK type plug connector.
Described first plug connector is a YF8-64TD type plug connector, and stitch is distributed as 14 parts, is defined as follows:
The Part A of first: use stitch 1 and stitch 2 as the used stitch of primary power source;
Second portion Part B: use stitch 3, stitch 4, stitch 5, stitch 6 and stitch 11 as the used stitch of Star Service 422 supervisory control signals;
Third part Part C: use stitch 7, stitch 8, stitch 9, stitch 10 and stitch 20 as the used stitch of Star Service 422 Star Service scheduling signals;
The 4th part Part D: use stitch 13～stitch 18 as the used stitch of battery discharging command signal;
The 5th part Part E: use stitch 12, stitch 22 and stitch 23 to insert the used stitch of separation command positive signal as taking off;
The 6th part Part F: use stitch 19, stitch 24 and stitch 25 to insert the used stitch of separation command negative signal as taking off;
The 7th part Part G: use stitch 27 and stitch 31 to insert the used stitch of released state signal as taking off;
The 8th part Part H: use stitch 28 and stitch 32 as the used stitch of bus voltage signal;
The tenth part Part J: use stitch 36 and stitch 40 as the used stitch of load current signal;
The tenth a part of Part K: use stitch 21 and stitch 29 as the used stitch of simulator shunting positive signal;
The 12 part Part L: use stitch 33 and stitch 37 to divide the battle array positive signal used stitch as simulator;
The 13 part Part M: use stitch 26, stitch 30, stitch 34 and stitch 38 to divide the battle array negative signal used stitch as simulator.
The 14 part Part N: use stitch 41～stitch 64 as the used stitch of storage battery activation signals.
The two-way cable that the 8th cable and the 8th cable are told uses twisted-pair feeder to disturb to reduce.
The present invention's beneficial effect compared with prior art is:
(1) prior art is placed on signals such as emergency-off, storage battery equalizing charge in the star catalogue cable, but because the microsatellite volume is little and adopted the mode of body packed battery battle array, causes designing the star catalogue plug and have difficulties.Tradition is taken off the plug-in cable in the present invention and the star catalogue cable has carried out the integral fusion design, only keep and take off plug, take off the problem that cable system has solved microsatellite design star catalogue plug difficulty of inserting with microsatellite, the problem of having avoided destroying body dress solar battery array overall structure and having influenced solar battery array function and performance has been saved the infrastructure resource of microsatellite;
(2) integrated design integrated level of the present invention is high, 64 none wastes of stitch of YF8-64TD type pull-off plug, reduced as much as possible and taken off the number of cables of plugging in cable system, make test environment cleaner and tidier, simultaneously, taken into full account the Electro Magnetic Compatibility of taking off strong and weak electricity in the plug-in cable in the design, taked forceful electric power to separate and mode such as cable multiple twin reduces electromagnetic interference, improved the reliability and the fail safe of satellite test with light current;
(3) the present invention is by carrying out integrated design to the wired test network of microsatellite, cancelled the star catalogue plug, make design and the simplification of star ground interface on the star, make the satellite comprehensive testing system step essential step to integrated and miniaturization, design cost and production cost have been saved, have good social benefit and economic benefit, have the market competitiveness.
Description of drawings
Fig. 1 plugs in the cable system schematic diagram for the present invention takes off;
Fig. 2 is the stitch distribution map of the present invention first plug connector XT-1.
Embodiment
Below in conjunction with accompanying drawing the specific embodiment of the present invention is further described in detail.
The present invention keeps the designs such as controlled quentity controlled variable, quantity of state and analog quantity contact that tradition is taken off satellite power supply, Star Service test computer interface and the wired TV station of plug-in cable, rationally utilize the limited contact resource of taking off the plug-in cable, the contact that takes into full account the electromagnetic compatibility of strong and weak electricity and electric connector is multiplexing, with tradition take off plug-in cable and the equalizing charge of star catalogue storage battery, satellite emergency-off, bus is measured and functions such as delivery separation command and state acquisition are carried out integral fusion, finally realizes the plug in cable system of taking off of integrated design.
As shown in Figure 1, the present invention takes off and plugs in cable system to form structure as follows: comprising eight cables and 15 plug connectors, is respectively the first cable W01, the second cable W02, the 3rd cable W03, the 4th cable W04, the 5th cable W05, the 6th cable W06, the 7th cable W07, the 8th cable W08, the first plug connector XT-1, the second plug connector XTFb1, the 3rd plug connector XTYb1, the 4th plug connector TC11, the 5th plug connector TC21, the 6th plug connector XTFb, the 7th plug connector XTYb, the 8th plug connector TC1, the 9th plug connector TC2, the tenth plug connector XD-01, the 11 plug connector XD-02, the 12 plug connector XD-03, the 13 plug connector XD-04, the 14 plug connector XD-GL and the 15 plug connector XD-DD;
A is a satellite as shown in Figure 1, b is the satellite base plate, c is a moonlet adapter lower plate, d is delivery instrument room disk, and e is a ground power supply and distribution test equipment, and f is Star Service 422 test computers, above-mentioned this several sections is a general knowledge known in this field, why identifying this several parts, mainly is in order more clearly to give expression to the position that each plug connector is installed, promptly to be fixed on the residing above-mentioned a certain parts.For example: plug connector XT-1 is fixed on the b, promptly is fixed on the satellite base plate, and all the other are similar with it.
Transmission comprises all wire signals that satellite and ground exchange among the first cable W01, the end of the first cable W01 is connected with satellite by the first plug connector XT-1, the first plug connector XT-1 is YF8-64TD type plug connector and is fixed on the satellite base plate, has 64 stitch.The other end of the first cable W01 is divided into four the tunnel, is respectively first via A1, the second road A2, Third Road A3 and the four road A4, and wherein first via A1 is connected with the end of the 5th cable W05 by the second plug connector XTFb1; The second road A2 is connected with the end of the 4th cable W04 by the 3rd plug connector XTYb1; Third Road A3 is connected with the end of the 3rd cable W03 by the 4th plug connector TC11; The four road A4 is connected with the end of the second cable W02 by the 5th plug connector TC21; The 5th cable W05 transmission satellite and the rocket separation command signal and its other end are connected with carrier rocket by the 6th plug connector XTFb; The 4th cable W04 transmission satellite and the rocket released state signal and its other end also are connected with carrier rocket by the 7th plug connector XTYb; Because transmission is the signal that the satellite and the rocket separate, so the 4th cable W04 and the 3rd cable W03 need not to consider the problem of Electro Magnetic Compatibility.The 3rd cable W03 is that service cable and its other end are connected with the end of the 7th cable W07 by the 8th plug connector TC1, and all supply lines all are integrated among the 3rd cable W03; The 7th cable W07 is connected with ground power supply and distribution test equipment by the tenth plug connector XD-01 for prolonging cable and its other end; The second cable W02 transmitted test signal and its other end are connected with the end of the 6th cable W06 by the 9th plug connector TC2, the 6th cable W06 is one minute three cable, three road cables that are divided into are respectively the first sub-road B1, the second sub-road B2 and the 3rd sub-road B3, and wherein first sub-road B1 transmission is connected with ground power supply and distribution test equipment by the 11 plug connector XD-02 for controlled quentity controlled variable, quantity of state and the analog quantity of distribution and its; The second sub-road B2 is connected with the emergency protection for power-cut plug by the 13 plug connector XD-04, is used for the emergency-off of satellite; The 3rd sub-road B3 is connected with the end of the 8th cable W08 by the 12 plug connector XD-03, the 8th cable W08 is the one-to-two cable, the transfer management control signal is with the Star Service scheduling signals and be connected with the Star Service test computer with the 15 plug connector XD-DD by the 14 plug connector XD-GL respectively respectively for the two-way cable that is divided into, and the two-way cable that the 8th cable W08 is divided into all is that twisted-pair cable is with the minimizing interference.The 13 plug connector XD-04 need not to fix; be in ground test if need be with the satellite emergency-off; then enable this second sub-road B2 cable; using method is about to the second sub-road B2 cable and is connected with the emergency protection for power-cut plug by the 13 plug connector XD-04 and realizes; described emergency protection for power-cut plug is a short circuit plug; its objective is to make the satellite test network short, thereby reach the function of forcing the satellite outage
The second plug connector XTFb1, the 3rd plug connector XTYb1, the 4th plug connector TC11 and the 5th plug connector TC21 are fixed on the moonlet adapter lower plate; The 6th plug connector XTFb, the 7th plug connector XTYb, the 8th plug connector TC1 and the 9th plug connector TC2 are fixed on the delivery instrument room disk.
Described the 4th plug connector TC11, the 5th plug connector TC21, the 8th plug connector TC1, the 9th plug connector TC2, the tenth plug connector XD-01 and the 11 plug connector XD-02 are Y2-50 type plug connector;
The described second plug connector XTFb1, the 3rd plug connector XTYb1, the 6th plug connector XTFb, the 7th plug connector XTYb, the 12 plug connector XD-03,, the 14 plug connector XD-GL and the 15 plug connector XD-DD be Y2-10 type plug connector;
Described the 13 plug connector XD-04 is a J36A-9ZK type plug connector.
The first plug connector XT-1 is a YF8-64TD type plug connector, stitch is distributed as 14 parts, as shown in Figure 2: YF8-64TD type plug connector is totally 64 stitch, put in order and the present position of 64 stitch is fixing and known, in view of the present invention with star catalogue plug and the incorporate design of patch cable plug, so 64 stitch of all of the first plug connector XT-1 all are used, and specifically are divided into 14 parts, are defined as follows:
The Part A of first: use stitch 1 and stitch 2 as the used stitch of primary power source;
Second portion Part B: use stitch 3, stitch 4, stitch 5, stitch 6 and stitch 11 as the used stitch of Star Service test computer supervisory control signals;
Third part Part C: use stitch 7, stitch 8, stitch 9, stitch 10 and stitch 20 as the used stitch of Star Service test computer Star Service scheduling signals;
The 4th part Part D: use stitch 13～stitch 18 as the used stitch of battery discharging command signal;
The 5th part Part E: use stitch 12, stitch 22 and stitch 23 to insert the used stitch of separation command positive signal as taking off;
The 6th part Part F: use stitch 19, stitch 24 and stitch 25 to insert the used stitch of separation command negative signal as taking off;
The 7th part Part G: use stitch 27 and stitch 31 to insert the used stitch of released state signal as taking off;
The 8th part Part H: use stitch 28 and stitch 32 as the used stitch of bus voltage signal;
The tenth part Part J: use stitch 36 and stitch 40 as the used stitch of load current signal;
The tenth a part of Part K: use stitch 21 and stitch 29 as the used stitch of simulator shunting positive signal;
The 12 part Part L: use stitch 33 and stitch 37 to divide the battle array positive signal used stitch as simulator;
The 13 part Part M: use stitch 26, stitch 30, stitch 34 and stitch 38 to divide the battle array negative signal used stitch as simulator.
The 14 part Part N: use stitch 41～stitch 64 as the used stitch of storage battery activation signals.
The 6th cable W06 is one minute three cable, three cables that are divided into are respectively the first sub-road B1, the second sub-road B2 and the 3rd sub-road B3, weak electric signal is further segmented, and wherein the signal that transmits among the first sub-road B1 comprises the signal that above-mentioned the 4th part Part D, the 7th part Part G, the 8th part Part H, Session 9 Part I and the tenth part Part J stitch carry and transmit; The signal that transmits among the 3rd sub-road B3 is the signal that carries and transmit in second portion Part B and the pairing stitch of third part Part C, be two kinds of signals of Star Service test computer, Star Service scheduling signals and supervisory control signals, the first sub-road B1, the second sub-road B2 and the 3rd sub-road B3 still need use twisted-pair feeder to disturb to reduce; The second sub-road B2 is used for the measurement of satellite emergency-off and above-mentioned first primary power source; the emergency-off function makes the second sub-road B2 be connected with the emergency protection for power-cut plug by the 13 plug connector XD-04 and realizes; described emergency protection for power-cut plug is a short circuit plug; its objective is to make the satellite test network short, thereby reach the function of forcing the satellite outage.
64 signal contacts of the first plug connector XT-1 distribute and should take into full account the electromagnetic compatibility of strong and weak electricity, should be separated from each other between forceful electric power and the weakness, and same signal contact should be tried one's best close; Weak electric signal comprises the Part A of first～the tenth part Part J among Fig. 2, and the forceful electric power signal comprises the tenth a part of Part K～the 14 part Part N among Fig. 2.
Should as far as possible putting together of the similar contact of signal type, second portion Part B and third part PartC are Star Service test computer signal, and distance is close, and the lead of these two groups of signals all should adopt the form of twisted-pair feeder to reduce interference; The 4th part Part D, the 5th part Part E and the 6th part Part F are command signal, and distance is close; The 7th part Part G, the 8th part Part H, Session 9 Part I and the tenth part Part J are the analog acquisition signal, and distance is close; The 14 part Part N is a storage battery equalizing charge usefulness, will flow through big electric current during test, these contacts should near and away from weak electric signal.
Because the contact of forceful electric power signal correspondence will flow through high-power electric current, so the forceful electric power signal should use thicker capillary among the first plug connector XT-1 as far as possible, as the Part A of first among Fig. 2, the tenth a part of Part K, the 12 part Part L and the pairing stitch of the 13 part Part M.
In order further to reduce electromagnetic interference, whole power supply signal the tenth a part of Part K, the 12 part Part L, the 13 part Part M and the 14 part Part N are designed among the 3rd cable W03, with other Design of Signal in the second cable W02.
Technical solution of the present invention has obtained application on microsatellite of hope of China's emission, and respond well.
The content that is not described in detail in the specification of the present invention belongs to this area professional and technical personnel's known technology.
Claims (4)
1. a microsatellite takes off plug in cable system, it is characterized in that: comprising eight cables and 15 plug connectors, is respectively the first cable W01, the second cable W02, the 3rd cable W03, the 4th cable W04, the 5th cable W05, the 6th cable W06, the 7th cable W07, the 8th cable W08, the first plug connector XT-1, the second plug connector XTFb1, the 3rd plug connector XTYb1, the 4th plug connector TC11, the 5th plug connector TC21, the 6th plug connector XTFb, the 7th plug connector XTYb, the 8th plug connector TC1, the 9th plug connector TC2, the tenth plug connector XD-01, the 11 plug connector XD-02, the 12 plug connector XD-03, the 13 plug connector XD-04, the 14 plug connector XD-GL and the 15 plug connector XD-DD;
Wherein, the end of the first cable W01 is connected with satellite by the first plug connector XT-1, the first plug connector XT-1 is fixed on the satellite base plate, the other end of the first cable W01 is divided into four the tunnel, be respectively first via A1, the second road A2, Third Road A3 and the four road A4, wherein first via A1 is connected with the end of the 5th cable W05 by the second plug connector XTFb1; The second road A2 is connected with the end of the 4th cable W04 by the 3rd plug connector XTYb1; Third Road A3 is connected with the end of the 3rd cable W03 by the 4th plug connector TC11; The four road A4 is connected with the end of the second cable W02 by the 5th plug connector TC21; The 5th cable W05 transmission satellite and the rocket separation command signal and its other end are connected with carrier rocket by the 6th plug connector XTFb; The 4th cable W04 transmission satellite and the rocket released state signal and its other end also are connected with carrier rocket by the 7th plug connector XTYb; The 3rd cable W03 is that service cable and its other end are connected with the end of the 7th cable W07 by the 8th plug connector TC1, and the 7th cable W07 is connected with ground power supply and distribution test equipment by the tenth plug connector XD-01 for prolonging cable and its other end; The second cable W02 transmitted test signal and its other end are connected with the end of the 6th cable W06 by the 9th plug connector TC2, the 6th cable W06 is one minute three cable, three road cables that are divided into are respectively the first sub-road B1, the second sub-road B2 and the 3rd sub-road B3, and wherein first sub-road B1 transmission is connected with ground power supply and distribution test equipment by the 11 plug connector XD-02 for controlled quentity controlled variable, quantity of state and the analog quantity of distribution and its; The second sub-road B2 is connected with the emergency protection for power-cut plug by the 13 plug connector XD-04, is used for the emergency-off of satellite; The 3rd sub-road B3 is connected with the end of the 8th cable W08 by the 12 plug connector XD-03, the 8th cable W08 is the one-to-two cable, the two-way cable that is divided into respectively the transfer management control signal with the Star Service scheduling signals and be connected with the Star Service test computer with the 15 plug connector XD-DD by the 14 plug connector XD-GL respectively;
The described second plug connector XTFb1, the 3rd plug connector XTYb1, the 4th plug connector TC11 and the 5th plug connector TC21 are fixed on the moonlet adapter lower plate; The 6th plug connector XTFb, the 7th plug connector XTYb, the 8th plug connector TC1 and the 9th plug connector TC2 are fixed on the delivery instrument room disk.
2. a kind of microsatellite according to claim 1 takes off plug in cable system, it is characterized in that: described the 4th plug connector TC11, the 5th plug connector TC21, the 8th plug connector TC1, the 9th plug connector TC2, the tenth plug connector XD-01 and the 11 plug connector XD-02 are Y2-50 type plug connector;
The described second plug connector XTFb1, the 3rd plug connector XTYb1, the 6th plug connector XTFb, the 7th plug connector XTYb, the 12 plug connector XD-03,, the 14 plug connector XD-GL and the 15 plug connector XD-DD be Y2-10 type plug connector;
Described the 13 plug connector XD-04 is a J36A-9ZK type plug connector.
3. a kind of microsatellite according to claim 1 takes off plug in cable system, it is characterized in that: the described first plug connector XT-1 is a YF8-64TD type plug connector, and stitch is distributed as 14 parts, is defined as follows:
The Part A of first: use stitch 1 and stitch 2 as the used stitch of primary power source;
Second portion Part B: use stitch 3, stitch 4, stitch 5, stitch 6 and stitch 11 as the used stitch of Star Service 422 supervisory control signals;
Third part Part C: use stitch 7, stitch 8, stitch 9, stitch 10 and stitch 20 as the used stitch of Star Service 422 Star Service scheduling signals;
The 4th part Part D: use stitch 13～stitch 18 as the used stitch of battery discharging command signal;
The 5th part Part E: use stitch 12, stitch 22 and stitch 23 to insert the used stitch of separation command positive signal as taking off;
The 6th part Part F: use stitch 19, stitch 24 and stitch 25 to insert the used stitch of separation command negative signal as taking off;
The 7th part Part G: use stitch 27 and stitch 31 to insert the used stitch of released state signal as taking off;
The 8th part Part H: use stitch 28 and stitch 32 as the used stitch of bus voltage signal;
Session 9 Part I: use stitch 35 and stitch 39 as the used stitch of battery tension signal;
The tenth part Part J: use stitch 36 and stitch 40 as the used stitch of load current signal;
The tenth a part of Part K: use stitch 21 and stitch 29 as the used stitch of simulator shunting positive signal;
The 12 part Part L: use stitch 33 and stitch 37 to divide the battle array positive signal used stitch as simulator;
The 13 part Part M: use stitch 26, stitch 30, stitch 34 and stitch 38 to divide the battle array negative signal used stitch as simulator.
The 14 part Part N: use stitch 41～stitch 64 as the used stitch of storage battery activation signals.
4. a kind of microsatellite according to claim 1 takes off plug in cable system, it is characterized in that: the two-way cable that described the 8th cable W08 and the 8th cable W08 tell, use twisted-pair feeder to disturb to reduce.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102536462A CN101938076B (en) | 2010-08-13 | 2010-08-13 | Microsatellite unplugged cable network |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010102536462A CN101938076B (en) | 2010-08-13 | 2010-08-13 | Microsatellite unplugged cable network |
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| CN101938076A true CN101938076A (en) | 2011-01-05 |
| CN101938076B CN101938076B (en) | 2012-11-14 |
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| CN2010102536462A Active CN101938076B (en) | 2010-08-13 | 2010-08-13 | Microsatellite unplugged cable network |
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| CN102738866A (en) * | 2012-06-18 | 2012-10-17 | 航天东方红卫星有限公司 | Satellite storage battery pack control circuit with ground emergency power-off protection function |
| CN104477414A (en) * | 2014-10-31 | 2015-04-01 | 北京兴华机械厂 | Single-needle separable power supply device |
| CN105984594A (en) * | 2015-01-28 | 2016-10-05 | 中国科学院空间科学与应用研究中心 | Low-orbit satellite power supply device |
| CN110034607A (en) * | 2019-04-25 | 2019-07-19 | 北京航天自动控制研究所 | Based on de- survey hair control power-off protection method, system and the storage medium for plugging off and falling |
| CN113156252A (en) * | 2021-04-26 | 2021-07-23 | 中国人民解放军国防科技大学 | Quick response satellite test system and method supporting segmental recombination and satellite and rocket quick docking test |
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|---|---|---|---|---|
| CN102738866A (en) * | 2012-06-18 | 2012-10-17 | 航天东方红卫星有限公司 | Satellite storage battery pack control circuit with ground emergency power-off protection function |
| CN104477414A (en) * | 2014-10-31 | 2015-04-01 | 北京兴华机械厂 | Single-needle separable power supply device |
| CN104477414B (en) * | 2014-10-31 | 2017-02-15 | 北京兴华机械厂 | Single-needle separable power supply device |
| CN105984594A (en) * | 2015-01-28 | 2016-10-05 | 中国科学院空间科学与应用研究中心 | Low-orbit satellite power supply device |
| CN110034607A (en) * | 2019-04-25 | 2019-07-19 | 北京航天自动控制研究所 | Based on de- survey hair control power-off protection method, system and the storage medium for plugging off and falling |
| CN113156252A (en) * | 2021-04-26 | 2021-07-23 | 中国人民解放军国防科技大学 | Quick response satellite test system and method supporting segmental recombination and satellite and rocket quick docking test |
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| Publication number | Publication date |
|---|---|
| CN101938076B (en) | 2012-11-14 |
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