CN113682499B - Spacecraft multi-space separation method - Google Patents
Spacecraft multi-space separation method Download PDFInfo
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- CN113682499B CN113682499B CN202110914915.3A CN202110914915A CN113682499B CN 113682499 B CN113682499 B CN 113682499B CN 202110914915 A CN202110914915 A CN 202110914915A CN 113682499 B CN113682499 B CN 113682499B
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Abstract
The invention relates to a method for separating multiple spacecrafts, which is suitable for spacecraft ground test and design of separation signals of on-orbit crafts. The method comprises the following steps: the method comprises the steps of designing separation signals among ground simulators, designing electrical separation signals and mechanical separation signals among railers, and designing safety of command power signals after separation among railers. Testability, integrity and power supply safety of the separation signal are guaranteed from three aspects. The method realizes the accuracy of judging from ground simulation separation to on-orbit real separation and the safety of use from before on-orbit separation to after on-orbit separation.
Description
Technical Field
The invention relates to a method for separating multiple spacecrafts, belongs to the field of spacecraft design, and is particularly suitable for the separation design of a deep space probe with a three-craft multi-combination body and a four-craft multi-combination body.
Background
At present, spacecrafts of remote sensing models and navigation models only have a satellite-rocket separation mode, and have no separation mode between the spacecrafts. Only the deep space probe has an on-track multi-device separation mode besides a device-arrow separation mode. Taking a certain deep space probe as an example, according to different flight stages, a separation mode between multiple devices such as separation between two devices, separation between a outsole and a platform, separation between a back cover and the platform, separation between a cabin and a vehicle and the like is carried out.
At present, when a deep space probe drills a flight program on the ground, the separation of a separation electric connector among multiple devices needs to be simulated, and in addition, the problem that the separation electric connector instructs a power supply to consume electric energy all the time after the separation of a track exists.
Disclosure of Invention
The invention solves the technical problems that: the defects of the prior art are overcome, and a method for separating a plurality of spacecraft is provided. The method can ensure the integrity and redundancy of the electrical separation signals and the mechanical separation signals among the multiple devices; the testability and the coverage of the ground simulation flight test are solved; the potential safety hazard that the end surface of the separated electric connector is exposed in the space environment after the rail device is separated is solved. The method realizes the accuracy of judgment from ground separation to on-track separation and the safety of use from before on-track separation to after on-track separation.
The technical scheme adopted by the invention is as follows:
a method for separating multiple spacecrafts comprises the following steps:
designing a ground separation system among the spacecrafts, and carrying out ground simulation on the separation among the spacecrafts to realize the ground simulation separation among the spacecrafts; and judging the separation signal;
designing an on-orbit separation system among the spacecrafts, realizing on-orbit electrical separation and mechanical separation among a plurality of spacecrafts, and judging separation signals;
and step three, protecting the power supply contact of the separation instruction after the multiple devices of the spacecraft are separated during the on-orbit period.
Furthermore, the ground separation system between the spacecrafts specifically comprises a first spacecraft, a second spacecraft, a first switching test device, a second switching test device, a first cable A1, a second cable A2, a third cable A3, a first switching electric connector, a second switching electric connector, a first separation electric connector and a second separation electric connector;
the first spacecraft is provided with expansion unit equipment, first GNC unit equipment and management unit equipment, and the second spacecraft is provided with second GNC unit equipment and comprehensive electronic equipment;
two paths are arranged between the first spacecraft and the second spacecraft, and one path is that the extension unit equipment of the first spacecraft is connected to the second GNC unit equipment of the second spacecraft through the first transfer electric connector and the first separation electric connector; the other path is that the first GNC unit equipment of the first spacecraft is connected to the integrated electronic equipment of the second spacecraft through the second switching electric connector and the second separation electric connector; the first spacecraft transmits a power supply signal, a charging signal, a remote control command signal, a remote measurement parameter signal and other signals to the second spacecraft through the two paths;
setting switch action through a first switching test device to generate four circuit separation signals which are respectively an analog circuit separation signal 1-1, an analog circuit separation signal 1-2, an analog circuit separation signal 2-1 and an analog circuit separation signal 2-2, sending the signals into expansion unit equipment in a first spacecraft through a first cable A1, and judging whether a first separation electric connector and a second separation electric connector are successfully separated or not by the expansion unit equipment by four-out judgment of the received four circuit separation signals;
setting a switch action through a second switching test device, generating a simulated mechanical separation signal 1-2 and a simulated mechanical separation signal 2-2, respectively sending the signals into a first management unit device and a first GNC unit device through a third cable A3 and a second cable A2, and performing mechanical separation judgment;
when the ground separation simulation between the spacecrafts is carried out, after the first spacecraft and the second spacecraft are successfully separated electrically or mechanically, the flight procedure is continued, and signals transmitted between the first spacecraft and the second spacecraft are uninterrupted.
Further, the expansion unit device performs a fourth-to-third judgment on the received four circuit separation signals, and then determines whether the first separation electrical connector and the second separation electrical connector are successfully separated, specifically: when the values of any three signals among the received analog electrical separation signal 1-1, the analog electrical separation signal 1-2, the analog electrical separation signal 2-1 and the analog electrical separation signal 2-2 are 1, the two spacecrafts are successfully electrically separated, namely the first electrical separation connector and the second electrical separation connector are successfully separated.
Further, the mechanical separation judgment specifically includes: and when the value of the simulated mechanical separation signal 1-2 received by the management unit equipment is 0 or the value of the simulated mechanical separation signal 2-2 received by the first GNC unit equipment is 0, the mechanical separation between the first spacecraft and the second spacecraft is represented to be successful.
Furthermore, the first switching test device is connected with contacts at two ends of the electrical separation signal through a jumper and a switch, and the on-off of the electrical separation signal is realized through the on-off of the switch, so that four circuits of electrical separation signals are generated; the second switching test device is connected with contacts at two ends of the mechanical separation signal through a crossover wire and a switch, and the on-off of the mechanical separation signal is realized through the on-off of the switch, so that two paths of mechanical separation signals are generated, and meanwhile, the two paths of mechanical separation signals are in a parallel relation.
Furthermore, the inter-spacecraft in-orbit separation system specifically comprises a first spacecraft, a second spacecraft, a first separation electric connector, a second separation electric connector, a first mechanical separation signal device and a second mechanical separation signal device;
the first spacecraft is provided with an expansion unit device, a first GNC unit device and a management unit device, and the second spacecraft is provided with a second GNC unit device and an in-orbit integrated electronic device;
the method comprises the steps that a socket and a plug of a first separation electric connector are in short circuit with a separation signal contact through a lead to generate an on-track electric separation signal 1-1 and an on-track electric separation signal 1-2, a socket and a plug of a second separation electric connector are in short circuit with a separation signal contact through a lead to generate an on-track electric separation signal 2-1 and an on-track electric separation signal 2-2, and the four on-track electric separation signals are simultaneously sent to equipment on a first spacecraft and a second spacecraft to be collected and subjected to four-out-of-three judgment;
the method comprises the steps that mechanical separation signal contacts are in short circuit through a short circuit piece on a first mechanical separation signal device to generate an on-rail mechanical separation signal 1-1 and an on-rail mechanical separation signal 1-2, the mechanical separation signal contacts are in short circuit through the short circuit piece on a second mechanical separation signal device to generate an on-rail mechanical separation signal 2-1 and an on-rail mechanical separation signal 2-2, and the four on-rail mechanical separation signals are simultaneously sent to equipment on a first spacecraft and a second spacecraft to be collected and judged in a four-out-of-three mode.
Further, the on-rail electrical separation signal 1-1 is in short circuit with the positive line of the on-rail electrical separation signal 1-1 and the return line of the on-rail electrical separation signal 1-1 at the socket end of the first separation electrical connector through a conducting wire; the on-rail electrical separation signal 1-2 is in short circuit with the on-rail electrical separation signal 1-2 positive line and the on-rail electrical separation signal 1-2 return line at the plug end of the first separation electrical connector through a conducting wire; the on-rail electrical split signals 2-1 and 2-2 generated by the second split electrical connector are similarly available.
Further, the first mechanical separation signal device comprises a separation socket A1, a short-circuit piece A1, a separation socket B1 and a short-circuit piece B1; the second mechanical separation signal device comprises a separation socket A2, a short-circuit piece A2, a separation socket B2 and a short-circuit piece B2;
the on-rail mechanical separation signal 1-1 is formed by short-circuiting the positive line of the on-rail mechanical separation signal 1-1 and the return line of the on-rail mechanical separation signal 1-1 through a short-circuit piece A1 at a pin end at a separation socket A1 in a first mechanical separation signal device; the positive line of the on-rail mechanical separation signal 1-2 and the return line of the on-rail mechanical separation signal 1-2 are in short circuit through a short circuit piece B1 at a pin end at a separation socket B1 in the first mechanical separation signal device;
the positive line of the on-rail mechanical separation signal 2-1 and the return line of the on-rail mechanical separation signal 2-1 are in short circuit through a short circuit piece A2 at a pin end at a separation socket A2 in a second mechanical separation signal device; the pin end of the rail mechanical separation signal 2-2 at the separation socket B2 in the second mechanical separation signal device is in short circuit connection between the positive line of the rail mechanical separation signal 2-2 and the return line of the rail mechanical separation signal 2-2 through a short circuit piece B2.
Further, the extension unit device on the first spacecraft performs a four-out-of-three judgment on the received four-circuit separation signal, and then determines whether the first separation electrical connector and the second separation electrical connector in the in-orbit separation system between the spacecraft are successfully separated, specifically: when the values of any three of the received on-track electrical separation signal 1-1, the received on-track electrical separation signal 1-2, the received on-track electrical separation signal 2-1 and the received on-track electrical separation signal 2-2 are 1, representing that the two spacecrafts are successfully separated on-track, namely the first separation electrical connector and the second separation electrical connector are successfully separated on-track;
the on-orbit mechanical separation signal 1-2 and the on-orbit mechanical separation signal 2-2 are respectively sent to GNC unit equipment and management unit equipment of a first spacecraft, and the on-orbit mechanical separation signal 1-1 and the on-orbit mechanical separation signal 2-1 are respectively sent to integrated electronic equipment of a second spacecraft;
the rail mechanical separation signal 1-1 is connected in parallel in the integrated electronic equipment through a contact to generate two mechanical separation signals 1-1 and 1-1', and the rail mechanical separation signal 2-1 is connected in parallel in the integrated electronic equipment through a contact to generate two mechanical separation signals 2-1 and 2-1'; the four mechanical separation signals are judged in a four-out-of-three mode, and whether the first mechanical separation signal device and the second mechanical separation signal device are successfully separated is judged; when the value of any three signals is 1, the on-orbit mechanical separation of the two spacecrafts is represented to be successful, namely the first mechanical separation signal device and the second mechanical separation signal device are successfully mechanically separated in an on-orbit mode.
Furthermore, after the plurality of devices are separated during the on-orbit period of the spacecraft, the contact of a separation instruction power supply is protected, the separation electric connector wire is wrapped on the socket, and the instruction power supply is provided by equipment in the socket end cabin instead of equipment in the plug end cabin of the separation electric connector;
1) A contact 77 and a contact 125 are respectively designed in the separated electric connector socket and are respectively in short circuit with wiring terminals A and B;
2) The instruction power supply contact 44 and the instruction line contact 150 designed in the socket are respectively led to the contact 44 and the contact 150 corresponding to the plug end of the separation electric connector, and when the plug of the separation electric connector is in butt joint with the socket, the instruction power supply and the instruction line are respectively in short circuit through the plug to form an instruction loop; when a disconnect command for disconnecting the electrical connector is sent, the power supply is commanded to open within the receptacle, i.e., to a passive state at the receptacle end.
Compared with the prior art, the invention has the advantages that:
(1) The invention solves the redundant design of the electrical separation signal and the mechanical separation signal after the spacecraft multi-device separation, and even if 1 circuit of electrical separation signal or 1 circuit of mechanical separation signal is not acquired, the criterion of electrical separation and mechanical separation of the spacecraft is not influenced. The two types of separation signals are conveniently and simply designed, namely, signal short circuits are respectively designed on the separation electric connector and the mechanical separation signal device, namely, the separation signals after separation are generated and are changed from '0' to '1'.
(2) The invention solves the problem of simulating electrical separation signals and mechanical separation signals during the ground multi-device test of the spacecraft, replaces the requirement of real separation action of the device separation electric connector in the test power-up process, and has reasonable and effective test and comprehensive coverage.
(3) The invention solves the problem that the power supply is in a cut-off state, namely a passive state, when the spacecraft is separated from the orbit device and the socket end face of the electric connector is separated, and avoids the hidden trouble of electrification of the socket end face after separation. Meanwhile, when the ground has a multi-connector separation mode, the end face of the socket of the electric connector is separated, so that the hidden trouble of power supply short circuit caused by redundant materials is avoided.
(4) The invention relates to an inter-device electrical separation signal, which is designed by carrying out short circuit of a separation signal contact on a plug or a socket of a separation electric connector, and an inter-device mechanical separation signal is designed by carrying out short circuit of the separation signal contact on a contact pin end of a mechanical separation signal device. After receiving the separation signal, the control subsystem may start a program control flight program; the design of on-orbit separation signals is simulated through the test switching device, so that the separation action of the whole ground uninterruptible power supply is solved, and the on-orbit flight task is simulated; after the spacecraft is separated, the separated instruction power supply is directly cut off at the socket end of the separated electric connector, so that the safe and reliable use of the separated spacecraft instruction power supply is ensured.
Drawings
FIG. 1 is a schematic diagram of the design of an analog separation signal between two devices on the ground;
FIG. 2 is a schematic diagram of the design of mechanical separation signals and electrical separation signals between two on-track devices;
FIG. 3 is a schematic diagram of a power contact design for a disconnection command of the disconnection electrical connector.
Detailed Description
The invention provides a method for designing a separation signal between multiple spacecraft, which is suitable for separation of on-orbit spacecraft of a spacecraft and testing of a ground multiple component. And judging whether the separator is successfully separated or not through a design strategy of selecting three from four electrical separation signals and mechanical separation signals. Upon receipt of a successful separation criterion, the control subsystem may initiate a program control flight procedure. In addition, the deep space probe is in a complex space environment with moon dust or fire star dust, and a fault of short circuit of a separation power supply signal can be caused, so that the design that the command power supply signal is in an open circuit state after the separation of the separation electric connector ensures that the command power supply of the spacecraft can be reliably and safely used after the separation.
At present, when a deep space probe conducts flight procedure drilling on the ground, the separation of a separation electric connector among multiple devices needs to be simulated, and if the separation electric connector among the devices is actually disconnected during ground testing, the flight procedure is interrupted. Thus, a device designed on the ground allows the separation of the signals between the simulators without interrupting the continuation of the flight sequence. In addition, the separated electric connector instructs the power supply to be directly led to the socket wire package after the rail is separated, and the socket is electrified after the separation, so that electric energy is always consumed. In order to avoid the design, the design of short circuit with the socket is skillfully realized through the design of plug contacts, so that the separated electric connector socket after the rail separation is in a passive state. The reliability and safety design of the separated electric connector is improved.
The invention provides a method for separating a plurality of spacecrafts, which comprises the following steps:
designing a ground separation system among the spacecrafts, and carrying out ground simulation on the separation among the spacecrafts so as to realize the ground simulation separation among the spacecrafts; and determining the separation signal;
designing an on-orbit separation system among the spacecrafts, realizing on-orbit electrical separation and mechanical separation among a plurality of spacecrafts, and judging separation signals;
and step three, protecting the power supply contact of the separation instruction after the multiple devices of the spacecraft are separated during the on-orbit period.
As shown in fig. 1, the ground separation system between spacecrafts specifically includes a first spacecraft, a second spacecraft, a first switching test device, a second switching test device, a first cable A1, a second cable A2, a third cable A3, a first switching electrical connector, a second switching electrical connector, a first separation electrical connector, and a second separation electrical connector;
the first spacecraft is provided with an expansion unit device, a first GNC unit device and a management unit device, and the second spacecraft is provided with a second GNC unit device and a comprehensive electronic device;
two paths are arranged between the first spacecraft and the second spacecraft, and one path is that the expansion unit equipment of the first spacecraft is connected to the second GNC unit equipment of the second spacecraft through the first transfer electric connector and the first separation electric connector; the other path is that the first GNC unit device of the first spacecraft is connected to the integrated electronic equipment of the second spacecraft through the second switching electric connector and the second separation electric connector; the first spacecraft transmits a power supply signal, a charging signal, a remote control command signal, a remote measurement parameter signal and other signals to the second spacecraft through the two paths;
setting a switching action through a first switching test device to generate four paths of electric separation signals which are respectively an analog electric separation signal 1-1, an analog electric separation signal 1-2, an analog electric separation signal 2-1 and an analog electric separation signal 2-2, sending the signals into extension unit equipment in a first spacecraft through a first cable A1, and judging whether a first separation electric connector and a second separation electric connector are successfully separated or not by the extension unit equipment by four-out-of-three judgment of the received four paths of electric separation signals;
setting a switch action through a second switching test device to generate a simulated mechanical separation signal 1-2 and a simulated mechanical separation signal 2-2, sending the signals into the first management unit device and the first GNC unit device through a third cable A3 and a second cable A2 respectively, and performing mechanical separation judgment;
when the ground separation simulation between the spacecrafts is carried out, after the first spacecraft and the second spacecraft are successfully separated electrically or mechanically, the flight procedure is continued, and signals transmitted between the first spacecraft and the second spacecraft are uninterrupted.
Further, the expansion unit device performs a four-out-of-three judgment on the received four-circuit separation signal, and further determines whether the first separation electric connector and the second separation electric connector are successfully separated, specifically: when the values of any three signals among the received analog electrical separation signal 1-1, the analog electrical separation signal 1-2, the analog electrical separation signal 2-1 and the analog electrical separation signal 2-2 are 1, the two spacecrafts are successfully electrically separated, namely the first electrical separation connector and the second electrical separation connector are successfully separated.
Further, the mechanical separation judgment specifically includes: and when the value of the simulated mechanical separation signal 1-2 received by the management unit equipment is 0 or the value of the simulated mechanical separation signal 2-2 received by the first GNC unit equipment is 0, the mechanical separation between the first spacecraft and the second spacecraft is represented to be successful.
The first switching test device is connected with contacts at two ends of the electrical separation signal through a jumper and a switch, and the on-off of the electrical separation signal is realized through the on-off of the switch, so that four circuits of electrical separation signals are generated; the second switching test device is connected with contacts at two ends of the mechanical separation signal through the overline and the switch, and the on-off of the mechanical separation signal is realized through the on-off of the switch, so that two paths of mechanical separation signals are generated, and meanwhile, the two paths of mechanical separation signals are in a parallel connection relation.
As shown in fig. 2, the in-orbit separation system between spacecrafts specifically includes a first spacecraft, a second spacecraft, a first separation electrical connector, a second separation electrical connector, a first mechanical separation signal device, and a second mechanical separation signal device;
the first spacecraft is provided with expansion unit equipment, first GNC unit equipment and management unit equipment, and the second spacecraft is provided with second GNC unit equipment and on-orbit integrated electronic equipment;
in fact, the on-orbit analysis system is that two mechanical signal separation devices are added on the basis of a ground analog separation system, and the switching test device is removed, so that analog signals are not needed any more, and on-orbit separation signals are directly collected.
The socket and the plug of the first separation electric connector generate an on-rail electric separation signal 1-1 and an on-rail electric separation signal 1-2 by short-circuiting separation signal contacts through wires, the socket and the plug of the second separation electric connector generate an on-rail electric separation signal 2-1 and an on-rail electric separation signal 2-2 by short-circuiting separation signal contacts through wires, and the four on-rail electric separation signals are simultaneously transmitted to equipment on a first spacecraft and a second spacecraft for collection and judgment;
the method comprises the steps that a mechanical separation signal contact is in short circuit on a first mechanical separation signal device through a short circuit piece to generate an on-rail mechanical separation signal 1-1 and an on-rail mechanical separation signal 1-2, a mechanical separation signal contact is in short circuit on a second mechanical separation signal device through the short circuit piece to generate an on-rail mechanical separation signal 2-1 and an on-rail mechanical separation signal 2-2, and the four on-rail mechanical separation signals are simultaneously sent to equipment on a first spacecraft and a second spacecraft to be collected and make a judgment of four-out-of-three.
The positive line of the on-rail electrical separation signal 1-1 is in short circuit with the return line of the on-rail electrical separation signal 1-1 through a conducting wire at the socket end of the first separation electrical connector by the on-rail electrical separation signal 1-1; the positive line of the on-rail electrical separation signal 1-2 is in short circuit with the return line of the on-rail electrical separation signal 1-2 at the plug end of the first separation electrical connector through a conducting wire; the on-rail electrical split signals 2-1 and 2-2 generated by the second split electrical connector are obtained in the same manner.
As shown in fig. 2, the first mechanical isolation signaling device includes an isolation socket A1, a short-circuit component A1, an isolation socket B1 and a short-circuit component B1; the second mechanical separation signal device comprises a separation socket A2, a short-circuit piece A2, a separation socket B2 and a short-circuit piece B2;
the on-rail mechanical separation signal 1-1 is formed by short-circuiting the positive line of the on-rail mechanical separation signal 1-1 and the return line of the on-rail mechanical separation signal 1-1 through a short-circuit piece A1 at a pin end at a separation socket A1 in a first mechanical separation signal device; the positive line of the on-rail mechanical separation signal 1-2 and the return line of the on-rail mechanical separation signal 1-2 are in short circuit through a short circuit piece B1 at a pin end at a separation socket B1 in the first mechanical separation signal device;
the positive line of the on-rail mechanical separation signal 2-1 and the return line of the on-rail mechanical separation signal 2-1 are in short circuit through a short circuit piece A2 at a pin end at a separation socket A2 in a second mechanical separation signal device; the pin end of the rail mechanical separation signal 2-2 at the separation socket B2 in the second mechanical separation signal device is in short circuit connection between the positive line of the rail mechanical separation signal 2-2 and the return line of the rail mechanical separation signal 2-2 through a short circuit piece B2.
The method comprises the following steps that extension unit equipment on a first spacecraft carries out four-out-of-three judgment on received four-circuit electric separation signals, and then whether a first separation electric connector and a second separation electric connector in an on-orbit separation system between the spacecrafts are successfully separated is judged, and the method specifically comprises the following steps: when the values of any three of the received on-track electrical separation signal 1-1, the received on-track electrical separation signal 1-2, the received on-track electrical separation signal 2-1 and the received on-track electrical separation signal 2-2 are 1, representing that the two spacecrafts are successfully separated on-track, namely the first separation electrical connector and the second separation electrical connector are successfully separated on-track;
the on-orbit mechanical separation signal 1-2 and the on-orbit mechanical separation signal 2-2 are respectively sent to GNC unit equipment and management unit equipment of a first spacecraft, and the on-orbit mechanical separation signal 1-1 and the on-orbit mechanical separation signal 2-1 are respectively sent to integrated electronic equipment of a second spacecraft;
the rail mechanical separation signal 1-1 is connected in parallel in the integrated electronic equipment through a contact to generate two mechanical separation signals 1-1 and 1-1', and the rail mechanical separation signal 2-1 is connected in parallel in the integrated electronic equipment through a contact to generate two mechanical separation signals 2-1 and 2-1'; the four mechanical separation signals are judged in a four-out-of-three mode, and whether the first mechanical separation signal device and the second mechanical separation signal device are successfully separated is judged; when the value of any three signals is 1, the on-orbit mechanical separation of the two spacecrafts is represented to be successful, namely the first mechanical separation signal device and the second mechanical separation signal device are successfully mechanically separated in an on-orbit mode.
As shown in fig. 3, during the on-orbit period of the spacecraft, after the multiple devices are separated, the contacts of the separation command power supply are protected, the separation electric connector wire is wrapped on the socket, and the command power supply is provided not by the devices in the plug end cabin of the separation electric connector but by the devices in the socket end cabin;
1) A contact 77 and a contact 125 are respectively designed in the separated electric connector socket and are respectively in short circuit with the coil wiring terminals A and B;
2) The instruction power supply contact 44 and the instruction line contact 150 designed in the socket are respectively led to the contact 44 and the contact 150 corresponding to the plug end of the separation electric connector, and when the plug of the separation electric connector is in butt joint with the socket, the instruction power supply and the instruction line are respectively in short circuit through the plug to form an instruction loop; when the disconnection command of the disconnection electric connector is sent, the power supply is commanded to form an open circuit in the socket, namely, the socket end is in a passive state.
Taking a certain type of deep space probe as an example, the protection of the command power supply contact between the two devices is explained.
Terminal a is shorted to contact 77 and terminal B is shorted to contact 125 at both ends of the split electrical connector receptacle terminal package. The command power is directed to in-receptacle contact 44 and the command line is directed to in-receptacle contact 150. When the plug is mated with the receptacle, the command power contacts 44 and the command line contacts 150 are directed into the plug. Contact 77 is then shorted to contact 44, contact 125 is shorted to contact 150 in the plug, and the command power is looped through the short. When the on-orbit sending in-cabin and mars vehicle separation command is sent, the socket and the plug of the separation electric connector are separated, namely the command power supply is in a direct open circuit state at the socket end, so that the hidden danger that the command power supply is unsafe and unreliable is avoided in the space environment.
In order to simulate the separation action of the on-orbit device, the separation operation of the electric connector and the mechanical separation signal device between the devices can not be carried out under the condition of power failure during the ground test of the spacecraft, so that a mechanical separation signal and an electric separation signal generated after the separation of a characterizer are simulated, the testability of the ground separation signal is ensured, and the surround device continues to fly after receiving the separation signal; and sequentially receiving the electrical separation signal and the mechanical separation signal on track, and designing a criterion strategy for successful separation to ensure the validity and integrity of the collected separation signal. After receiving the successful separation criterion, the control subsystem starts a program control flight program; after the rail device is separated, the separating electric connector is exposed in a space environment, namely, a separating instruction power supply signal is exposed in space, so that a power supply is directly cut off at the socket end of the separating electric connector, and the hidden danger that the instruction power supply of the spacecraft equipment fails due to the short circuit of the separating electric connector instruction power supply is avoided after the rail device is separated.
The method belongs to the technical field of electrical design of spacecrafts. The invention can realize the effectiveness of the ground simulation separation test among the spacecraft and the on-orbit multi-device separation correctness and the reliability and the safety of the command power supply used after the on-orbit multi-device separation of the spacecraft.
Claims (6)
1. A spacecraft multi-space separation method is characterized by comprising the following steps:
designing a ground separation system among the spacecrafts, and carrying out ground simulation on the separation among the spacecrafts to realize the ground simulation separation among the spacecrafts; and determining the separation signal;
designing an on-orbit separation system among the spacecrafts, realizing on-orbit electrical separation and mechanical separation among a plurality of spacecrafts, and judging separation signals;
step three, protecting a separation instruction power supply contact after a plurality of spacecrafts are separated in an on-orbit period;
the ground separation system between the spacecrafts specifically comprises a first spacecraft, a second spacecraft, a first switching test device, a second switching test device, a first cable A1, a second cable A2, a third cable A3, a first switching electric connector, a second switching electric connector, a first separation electric connector and a second separation electric connector;
the first spacecraft is provided with an expansion unit device, a first GNC unit device and a management unit device, and the second spacecraft is provided with a second GNC unit device and a comprehensive electronic device;
two paths are arranged between the first spacecraft and the second spacecraft, and one path is that the extension unit equipment of the first spacecraft is connected to the second GNC unit equipment of the second spacecraft through the first transfer electric connector and the first separation electric connector; the other path is that the first GNC unit device of the first spacecraft is connected to the integrated electronic equipment of the second spacecraft through the second switching electric connector and the second separation electric connector; the first spacecraft transmits a power supply signal, a charging signal, a remote control command signal, a remote measurement parameter signal and other signals to the second spacecraft through the two paths;
setting a switching action through a first switching test device to generate four paths of electric separation signals which are respectively an analog electric separation signal 1-1, an analog electric separation signal 1-2, an analog electric separation signal 2-1 and an analog electric separation signal 2-2, sending the signals into extension unit equipment in a first spacecraft through a first cable A1, and judging whether a first separation electric connector and a second separation electric connector are successfully separated or not by the extension unit equipment by four-out-of-three judgment of the received four paths of electric separation signals;
setting a switch action through a second switching test device to generate a simulated mechanical separation signal 1-2 and a simulated mechanical separation signal 2-2, sending the signals into the first management unit device and the first GNC unit device through a third cable A3 and a second cable A2 respectively, and performing mechanical separation judgment;
during the ground separation simulation between the spacecrafts, when the first spacecraft and the second spacecraft are simulated to be successfully separated electrically or mechanically, the flight procedure is continued, and signals transmitted between the first spacecraft and the second spacecraft are uninterrupted;
the expansion unit equipment performs four-to-three judgment on the received four-circuit separation signal so as to judge whether the first separation electric connector and the second separation electric connector are successfully separated, and the method specifically comprises the following steps: when the values of any three signals of the received analog electrical separation signal 1-1, the analog electrical separation signal 1-2, the analog electrical separation signal 2-1 and the analog electrical separation signal 2-2 are 1, representing that the electrical separation of the two spacecrafts is successful, namely that the first electrical separation connector and the second electrical separation connector are successfully separated;
the mechanical separation judgment specifically comprises the following steps: when the value of the simulated mechanical separation signal 1-2 received by the management unit equipment is 0 or the value of the simulated mechanical separation signal 2-2 received by the first GNC unit equipment is 0, representing that the mechanical separation between the first spacecraft and the second spacecraft is successful;
the on-orbit separation system between the spacecrafts specifically comprises a first spacecraft, a second spacecraft, a first separation electric connector, a second separation electric connector, a first mechanical separation signal device and a second mechanical separation signal device;
the first spacecraft is provided with an expansion unit device, a first GNC unit device and a management unit device, and the second spacecraft is provided with a second GNC unit device and an in-orbit integrated electronic device;
the socket and the plug of the first separation electric connector generate an on-rail electric separation signal 1-1 and an on-rail electric separation signal 1-2 by short-circuiting separation signal contacts through wires, the socket and the plug of the second separation electric connector generate an on-rail electric separation signal 2-1 and an on-rail electric separation signal 2-2 by short-circuiting separation signal contacts through wires, and the four on-rail electric separation signals are simultaneously transmitted to equipment on a first spacecraft and a second spacecraft for collection and judgment;
the method comprises the steps that mechanical separation signal contacts are in short circuit through a short circuit piece on a first mechanical separation signal device to generate an on-rail mechanical separation signal 1-1 and an on-rail mechanical separation signal 1-2, the mechanical separation signal contacts are in short circuit through the short circuit piece on a second mechanical separation signal device to generate an on-rail mechanical separation signal 2-1 and an on-rail mechanical separation signal 2-2, and four on-rail mechanical separation signals are simultaneously sent to equipment on a first spacecraft and a second spacecraft to be collected and judged in a four-out-of-three mode.
2. A spacecraft space-to-space separation method according to claim 1, comprising: the first switching test device is connected with contacts at two ends of the electrical separation signal through a jumper and a switch, and the on-off of the electrical separation signal is realized through the on-off of the switch, so that four circuits of electrical separation signals are generated; the second switching test device is connected with contacts at two ends of the mechanical separation signal through the overline and the switch, and the on-off of the mechanical separation signal is realized through the on-off of the switch, so that two paths of mechanical separation signals are generated, and meanwhile, the two paths of mechanical separation signals are in a parallel connection relation.
3. A spacecraft space-to-space separation method according to claim 1, comprising: the positive line of the on-rail electrical separation signal 1-1 is in short circuit with the return line of the on-rail electrical separation signal 1-1 through a conducting wire at the socket end of the first separation electrical connector by the on-rail electrical separation signal 1-1; the positive line of the on-rail electrical separation signal 1-2 is in short circuit with the return line of the on-rail electrical separation signal 1-2 at the plug end of the first separation electrical connector through a conducting wire; the on-rail electrical split signals 2-1 and 2-2 generated by the second split electrical connector are obtained in the same manner.
4. A spacecraft space-splitting method according to claim 3, wherein: the first mechanical separation signal device comprises a separation socket A1, a short-circuit piece A1, a separation socket B1 and a short-circuit piece B1; the second mechanical separation signal device comprises a separation socket A2, a short-circuit piece A2, a separation socket B2 and a short-circuit piece B2;
when the rail mechanical separation signal 1-1 is a pin end at a separation socket A1 in a first mechanical separation signal device, a positive line of the rail mechanical separation signal 1-1 is in short circuit with a return line of the rail mechanical separation signal 1-1 through a short circuit piece A1; the positive line of the on-rail mechanical separation signal 1-2 and the return line of the on-rail mechanical separation signal 1-2 are in short circuit through a short circuit piece B1 at a pin end at a separation socket B1 in the first mechanical separation signal device;
the positive line of the on-rail mechanical separation signal 2-1 and the return line of the on-rail mechanical separation signal 2-1 are in short circuit through a short circuit piece A2 at a pin end at a separation socket A2 in a second mechanical separation signal device; the pin terminal at the split socket B2 in the second mechanical split signaling device shorts the positive in-track mechanical split signal 2-2 line with the return in-track mechanical split signal 2-2 line through a shorting member B2 at the in-track mechanical split signal 2-2.
5. A spacecraft space-to-space separation method according to claim 3, wherein: the method comprises the following steps that the expansion unit equipment on the first spacecraft judges whether four-out-of-three received four-circuit separation signals are received so as to judge whether a first separation electric connector and a second separation electric connector in the on-orbit separation system between the spacecrafts are successfully separated, and specifically comprises the following steps: when the values of any three signals among the received on-track electrical separation signal 1-1, the received on-track electrical separation signal 1-2, the received on-track electrical separation signal 2-1 and the received on-track electrical separation signal 2-2 are 1, the successful on-track electrical separation of the two spacecrafts is represented, namely the first separation electrical connector and the second separation electrical connector are successfully separated in an on-track manner;
the on-orbit mechanical separation signal 1-2 and the on-orbit mechanical separation signal 2-2 are respectively sent to GNC unit equipment and management unit equipment of a first spacecraft, and the on-orbit mechanical separation signal 1-1 and the on-orbit mechanical separation signal 2-1 are respectively sent to integrated electronic equipment of a second spacecraft;
the rail mechanical separation signal 1-1 is connected in parallel in the integrated electronic equipment through a contact to generate two paths of mechanical separation signals 1-1 and 1-1', and the rail mechanical separation signal 2-1 is connected in parallel in the integrated electronic equipment through a contact to generate two paths of mechanical separation signals 2-1 and 2-1'; the four mechanical separation signals are judged in a four-out-of-three mode, and whether the first mechanical separation signal device and the second mechanical separation signal device are successfully separated is judged; when the value of any three signals is 1, the on-orbit mechanical separation of the two spacecrafts is represented to be successful, namely the first mechanical separation signal device and the second mechanical separation signal device are successfully and mechanically separated in orbit.
6. A spacecraft space-to-space separation method according to claim 1, comprising: during the on-orbit period of the spacecraft, after a plurality of devices are separated, the contacts of a separation instruction power supply are protected, the separation electric connector is wrapped on a socket, and the instruction power supply is provided by equipment in a socket end cabin instead of equipment in a plug end cabin of the separation electric connector;
1) A contact 77 and a contact 125 are respectively designed in the separated electric connector socket and are respectively in short circuit with wiring terminals A and B;
2) The instruction power supply contact 44 and the instruction line contact 150 designed in the socket are respectively led to the contact 44 and the contact 150 corresponding to the plug end of the separation electric connector, and when the plug of the separation electric connector is in butt joint with the socket, the instruction power supply and the instruction line are respectively in short circuit through the plug to form an instruction loop; when the disconnection command of the disconnection electric connector is sent, the power supply is commanded to form an open circuit in the socket, namely, the socket end is in a passive state.
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