CN109018450B - Switching method of deep space probe multi-mode measurement and control communication system - Google Patents
Switching method of deep space probe multi-mode measurement and control communication system Download PDFInfo
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- CN109018450B CN109018450B CN201810684288.7A CN201810684288A CN109018450B CN 109018450 B CN109018450 B CN 109018450B CN 201810684288 A CN201810684288 A CN 201810684288A CN 109018450 B CN109018450 B CN 109018450B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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Abstract
The invention provides a switching method of a deep space probe multi-mode measurement and control communication system, which comprises the following working modes: setting a pre-shooting mode; setting an initial separation mode of the device and the arrow; setting a conventional mode of a transition section; setting a first emergency mode; setting a second emergency mode; a sixth mode, a track adjusting mode is set; setting a braking ignition mode; and in the eighth mode, a conventional mode of the surrounding section is set. The invention can be used for deep space exploration tasks such as mars exploration, asteroid exploration and wooden star exploration.
Description
Technical Field
The invention relates to a switching method of a multi-mode measurement and control communication system, in particular to a switching method of a multi-mode measurement and control communication system of a deep space probe.
Background
The deep space probe has the advantages of long flying distance, large space loss, limited data transmission rate, large relative speed of a communication terminal, large Doppler and change rate thereof, and large difficulty in signal acquisition and tracking. Aiming at the characteristics, the deep space probe measurement and control communication system needs to be provided with diversified communication devices (an antenna, a solid-state amplifier, a traveling wave tube amplifier, a deep space transponder and the like), and a plurality of system working modes are constructed through cross combination so as to adapt to the requirements of detection tasks.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a switching method of a multi-mode measurement and control communication system of a deep space probe, which can be used for deep space probe tasks such as Mars probe, asteroid probe, Jupiter probe and the like. Eight working modes are constructed by the cross combination of low, medium and high gain antennas, a transponder, a solid-state amplifier, a traveling wave tube amplifier and other equipment, trigger conditions are set according to ground distance, on-board time, flight programs and the like, and mode switching processes of an active section, a transfer section, a capture section, a ring fire section and other different flight stages are set.
According to one aspect of the invention, a switching method of a deep space probe multi-mode measurement and control communication system is provided, which is characterized by comprising the following working modes:
setting a pre-shooting mode;
setting an initial separation mode of the device and the arrow;
setting a conventional mode of a transition section;
setting a first emergency mode;
setting a second emergency mode;
a sixth mode, a track adjusting mode is set;
setting a braking ignition mode;
and in the eighth mode, a conventional mode of the surrounding section is set.
Compared with the prior art, the invention has the following beneficial effects: the invention can be used for deep space exploration tasks such as mars exploration, asteroid exploration and wooden star exploration. Eight working modes are constructed by the cross combination of low, medium and high gain antennas, a transponder, a solid-state amplifier, a traveling wave tube amplifier and other equipment, trigger conditions are set according to ground distance, on-board time, flight programs and the like, and mode switching processes of an active section, a transfer section, a capture section, a ring fire section and other different flight stages are set.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in tables 1 to 8, the switching method of the deep space probe multi-mode measurement and control communication system of the present invention includes the following working modes:
setting a pre-shooting mode;
setting an initial separation mode of the device and the arrow;
setting a conventional mode of a transition section;
setting a first emergency mode;
setting a second emergency mode;
a sixth mode, a track adjusting mode is set;
setting a braking ignition mode;
and in the eighth mode, a conventional mode of the surrounding section is set.
TABLE 1 Pre-injection mode setup procedure
| Step numbering | Setting content |
| 1 | Deep space transponder transmitter turn-on |
| 3 | Power supply and cut-off of line amplifier stage |
| 4 | Fixed discharge output 1W switch |
| 5 | Solid state power amplifier power supply path |
| 6 | High frequency stabilization source crystal oscillator power supply |
| 7 | Transmitting coaxial switch output line amplifier |
TABLE 2 initial mode setting procedure for device arrow separation
| Step numbering | Setting content |
| 1 | Transponder receiving switch |
| 2 | Transponder transmitter |
| 3 | Fixed output 10W switch |
| 4 | Low gain antenna +/-90 deg receiving and transmitting switch |
| 5 | Transponder a/b receiving switch |
TABLE 3 transition segment conventional mode setup procedure
| Step numbering | Setting content |
| 1 | Transponder receiving switch |
| 2 | Transponder transmitter |
| 3 | Horizontal discharge output switch |
| 4 | High gain antenna transmit-receive |
TABLE 4 first Emergency mode setting step
| Step numbering | Setting content |
| 1 | Transponder receiving switch |
| 2 | Transponder transmitter |
| 3 | Horizontal discharge output switch |
| 4 | Cut low gain antenna + -50 degree receiving and transmitting |
TABLE 5 second Emergency mode setting step
| Step numbering | Setting content |
| 1 | Transponder reception |
| 2 | Transponder transmitter |
| 3 | Horizontal discharge output switch |
| 4 | Low gain antenna reception |
| 5 | Medium gain antenna transmission |
Table 6 track adjustment mode setting procedure
TABLE 7 brake ignition mode setup procedure
| Step numbering | Setting content |
| 1 | Transponder receiving switch |
| 2 | Transponder transmitter |
| 3 | Horizontal discharge output switch |
| 4 | Cut low gain antenna + -50 degree receiving and transmitting |
Table 8 surround section normal mode setting step
| Step numbering | Setting content |
| 1 | Transponder receiving switch |
| 2 | Transponder transmitter |
| 3 | Horizontal discharge output switch |
In conclusion, the method can be used for the design of the spaceflight task remote deep space communication system such as mars detection, asteroid detection and wooden star detection. Eight working modes are constructed through the cross combination of low, medium and high gain antennas, transponders, solid state amplifiers, traveling wave tube amplifiers and other equipment, trigger conditions are set according to the ground distance, the time on the aircraft, flight programs and the like, and mode switching processes of an active section, a transfer section, a capture section, a ring fire section and other different flight stages are set. The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (1)
1. A switching method of a deep space probe multi-mode measurement and control communication system is characterized by comprising the following working modes:
setting a pre-shooting mode;
setting an initial separation mode of the device and the arrow;
setting a conventional mode of a transition section;
setting a first emergency mode;
setting a second emergency mode;
a sixth mode, a track adjusting mode is set;
setting a braking ignition mode;
setting a conventional mode of a surrounding section;
the pre-shooting mode setting step: step A1: the transponder transmitter is on; step A2: the power supply of the power amplifier stage of the line amplifier is cut off; step A3: the output of the solid discharge is 1W; step A4: a solid state power amplifier power supply path; step A5: the high frequency stabilization source crystal oscillator supplies power; step A6: the output of the transmitting coaxial switch is connected with a line amplifier;
the device and arrow separation initial mode setting step: step B1: the responder receives the data; step B2: the transponder is turned on; step B3: the fixed discharge output is 10W; step B4: the low-gain antenna is switched off at +/-90 degrees; step B5: the responder receives the data;
the conventional mode setting step of the transfer section comprises the following steps: step C1: the responder receives the data; step C2: the transponder is turned on; step C3: outputting the line amplifier; step C4: cutting a high-gain antenna for receiving and transmitting;
the first emergency mode setting step: step D1: the responder receives the data; step D2: the transponder is turned on; step D3: outputting the line amplifier; step D4: cutting the low gain antenna to transmit and receive within +/-50 degrees;
the second emergency mode setting step: step E1: the responder receives the data; step E2: the transponder is turned on; step E3: outputting the line amplifier; step E4: receiving by a low-gain antenna; step E5: transmitting by a medium-gain antenna;
the track adjustment mode setting step: step F1: the responder receives the data; step F2: the transponder is turned on; step F3: outputting the line amplifier; step F4: cutting the low gain antenna to transmit and receive within +/-50 degrees;
the brake ignition mode setting step: step G1: the responder receives the data; step G2: the transponder is turned on; step G3: outputting the line amplifier; step G4: cutting the low gain antenna to transmit and receive within +/-50 degrees;
the conventional mode setting step of the surrounding section comprises the following steps: step H1: the responder receives the data; step H2: the transponder is turned on; step H3: and the row discharge output is on.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810684288.7A CN109018450B (en) | 2018-06-28 | 2018-06-28 | Switching method of deep space probe multi-mode measurement and control communication system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810684288.7A CN109018450B (en) | 2018-06-28 | 2018-06-28 | Switching method of deep space probe multi-mode measurement and control communication system |
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| Publication Number | Publication Date |
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| CN109018450A CN109018450A (en) | 2018-12-18 |
| CN109018450B true CN109018450B (en) | 2020-11-24 |
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Citations (5)
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|---|---|---|---|---|
| JP2008183912A (en) * | 2007-01-26 | 2008-08-14 | Mitsubishi Electric Corp | Control device for satellite mounting |
| CN102717902A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Phased multi-rate self-adaptive measurement and control system of mars exploration deep space spacecraft |
| CN102723982A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Full-coverage multi-channel multi-frequency band measuring and control system of deep space electric propulsion asteroid spacecraft |
| CN103034232A (en) * | 2012-11-30 | 2013-04-10 | 北京控制工程研究所 | Automatic failure handling and protection method of deep space probe global navigation chart (GNC) system base on layered structure |
| CN103368638A (en) * | 2012-03-29 | 2013-10-23 | 中国科学院空间科学与应用研究中心 | A measurement and control communication method for a deep space probe and a measurement and control communication system for a deep space probe |
-
2018
- 2018-06-28 CN CN201810684288.7A patent/CN109018450B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008183912A (en) * | 2007-01-26 | 2008-08-14 | Mitsubishi Electric Corp | Control device for satellite mounting |
| CN103368638A (en) * | 2012-03-29 | 2013-10-23 | 中国科学院空间科学与应用研究中心 | A measurement and control communication method for a deep space probe and a measurement and control communication system for a deep space probe |
| CN102717902A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Phased multi-rate self-adaptive measurement and control system of mars exploration deep space spacecraft |
| CN102723982A (en) * | 2012-06-26 | 2012-10-10 | 上海卫星工程研究所 | Full-coverage multi-channel multi-frequency band measuring and control system of deep space electric propulsion asteroid spacecraft |
| CN103034232A (en) * | 2012-11-30 | 2013-04-10 | 北京控制工程研究所 | Automatic failure handling and protection method of deep space probe global navigation chart (GNC) system base on layered structure |
Non-Patent Citations (1)
| Title |
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| 《基于萤火一号技术的自主火星探测器方案》;方宝东等;《上海航天》;20110430;第18-20页 * |
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| CN109018450A (en) | 2018-12-18 |
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