CN115314066A - Measurement and control communication device and method for deep space exploration spacecraft - Google Patents

Abstract

The invention relates to a measurement and control communication device and method for a deep space exploration spacecraft, wherein the spacecraft has a + Z surface pointing to the earth and a-Z surface not pointing to the earth, and the measurement and control communication device comprises: the first deep space transponder comprises a Ka-band transmitting channel, an X-band transmitting channel and an X-band receiving channel, and the second deep space transponder comprises a Ka-band transmitting channel and an X-band receiving channel; a pair of high-gain antennas with two ports is respectively connected with the first switch and the second switch; one of the two pairs of low gain antennas is connected to the second switch, and the other pair is connected to the third switch. The invention realizes the redundancy of the uplink and downlink channels and ensures the reliability of the communication system; by configuring the connection state of the first switch, the Ka-band high-speed scientific data downlink transmission can be realized; by configuring the connection states of the second switch, the third switch and the fourth switch, the transmission of the X-band uplink or downlink measurement and control data can be realized, and the spacecraft can normally perform measurement and control communication in all task stages.

Description

Measurement and control communication device and method for deep space exploration spacecraft

Technical Field

The invention mainly relates to the technical field of deep space exploration, in particular to a measurement and control communication device and method for a deep space exploration spacecraft.

Background

In a deep space exploration task for observing and researching celestial bodies such as asteroid, venus and Mars, a measurement and control communication device is usually arranged on a deep space exploration spacecraft to realize a deep space measurement and control communication system. The Deep Space measurement and control communication system is an information transmission channel between a Deep Space spacecraft and the earth, and provides three basic functions by combining a Deep Space Network (DSN) on the earth: (1) transmitting scientific data and engineering telemetering data in a downlink manner; (2) The uplink transmission remote control instruction is used for controlling the spacecraft, and the uplink software patch is used for repairing or updating the spacecraft software; and (3) providing radio frequency signals for the navigation and measuring tracks.

The measurement and control communication system for the deep space exploration task generally comprises the following components: deep Space Transponders (DST); a High-Power Amplifier (HPA) including a Traveling-wave Tube Amplifier (TWTA) or a Solid State Power Amplifier (SSPA); a 3dB bridge; a duplexer; a coaxial or waveguide switch; low Gain Antenna (LGA); medium Gain Antenna (MGA); high Gain Antenna (HGA). Different component numbers and connection relations form different measurement and control communication system schemes.

Most of measurement and control communication systems provide near-omnidirectional beam coverage through two pairs of low-gain wide-beam antennas which are arranged back to back, and the high-gain antennas are usually indispensable items of spacecrafts and are used for high-speed downlink of scientific data.

For a part of deep space exploration spacecrafts, the design of a measurement and control communication system of the spacecraft is mainly driven by the requirement of high-speed downloading of a large amount of scientific data. The highest downlink data rate of most existing deep space measurement and control communication systems is only a few hundred Kbps or even lower, for example, marCO is a cube star type spacecraft, redundant channels are not provided, and the downlink rate is only 8Kbps. At present, some spacecraft are equipped with HGAs only for the downlink and cannot provide high speed uplinks at long distance stages. The number of parts of some typical deep space mission spacecraft is large, for example, the Europa Clipper comprises four transmitting channels (including traveling wave tube amplifiers), seven pairs of antennas, and a relatively complex radio frequency network, the system redundancy and complexity are high, and the spacecraft is not suitable for a small-sized spacecraft with low cost.

Disclosure of Invention

The communication device and the method can realize redundant Ka-band downlink and X-band uplink by configuring the connection states of different switches on the premise of minimizing the quantity of system components, and ensure the reliability of communication between the measurement and control communication device of the deep space exploration spacecraft and a ground station.

The technical scheme adopted by the application for solving the technical problems is a measurement and control communication device of a deep space exploration spacecraft, wherein the spacecraft is provided with a + Z surface pointing to the earth and a-Z surface not pointing to the earth, and comprises: the first deep space transponder comprises a first Ka waveband transmitting channel, an X waveband transmitting channel and a first X waveband receiving channel; the second deep space transponder comprises a second Ka-band transmitting channel and a second X-band receiving channel; the high-gain antenna is arranged on a + Z plane and comprises a first port and a second port, the high-gain antenna is connected with the first switch through the first port, optionally establishes connection with a first Ka-band downlink or a second Ka-band downlink by configuring the connection state of the first switch so as to perform Ka-band downlink transmission, is connected with the second switch through the second port, establishes connection with the X-band transmitting channel by configuring the connection state of the second switch, and optionally establishes connection with a first X-band receiving channel or a second X-band receiving channel; the first low-gain antenna is arranged on the + Z surface, is connected with the second switch, is connected with the X-band transmitting channel by configuring the connection state of the second switch, and is optionally connected with the first X-band receiving channel or the second X-band receiving channel; and a second low-gain antenna disposed on the-Z plane, the second low-gain antenna being connected to the third switch, establishing a connection with the X-band transmit channel by configuring a connection state of the third switch, and optionally establishing a connection with the first X-band receive channel or the second X-band receive channel.

In an embodiment of the present application, the communication device further includes a first Ka-band traveling wave tube amplifier, a second Ka-band traveling wave tube amplifier, and a bridge, where the bridge includes a first input end, a second input end, a first output end, and a second output end, the first Ka-band transmitting channel is connected to the first input end, the second Ka-band transmitting channel is connected to the second input end, the first output end is connected to the first Ka-band traveling wave tube amplifier, the second output end is connected to the second Ka-band traveling wave tube amplifier, the first Ka-band traveling wave tube amplifier and the second Ka-band traveling wave tube amplifier are disposed between the first switch and the bridge, and the first port of the high-gain antenna is selectively connected to the first Ka-band traveling wave tube amplifier or the second Ka-band traveling wave tube amplifier by configuring a connection state of the first switch.

In an embodiment of the present application, the communication device further includes a fourth switch, a duplexer, and an X-band traveling-wave tube amplifier, the second switch is connected to the third switch, and the second port of the high-gain antenna or the first low-gain antenna is connected to the third switch by configuring a connection state of the second switch; the X-band traveling wave tube amplifier is provided with an input end and an output end, an X-band transmitting channel is connected with the input end, and the output end of the X-band traveling wave tube amplifier is connected with the first end of the duplexer; the duplexer is arranged among the third switch, the X-band traveling wave tube amplifier and the fourth switch; the fourth switch is provided with a first input end, a second input end, a first output end and a second output end, the first X waveband receiving channel is connected with the first output end of the fourth switch, the second X waveband receiving channel is connected with the second output end of the fourth switch, the duplexer is connected with the first input end of the fourth switch, the third switch is connected with the second input end of the fourth switch, and the second low-gain antenna and the second port of the high-gain antenna or the first low-gain antenna are simultaneously connected with the first X waveband receiving channel and the second X waveband receiving channel by configuring the connection states of the second switch, the third switch and the fourth switch; and any one of the second port of the high-gain antenna, the first low-gain antenna and the second low-gain antenna is connected with the X-band transmitting channel.

In an embodiment of the present application, the first switch is a single-pole double-throw switch, the first switch has two connection states, the first switch enables the first port of the high-gain antenna to communicate with the first Ka-band traveling wave tube amplifier in the first state, and the Ka-band downlink signal transmitted by the first Ka-band transmitting channel or the second Ka-band transmitting channel is transmitted to the first port of the high-gain antenna through the first Ka-band downlink; and the first switch enables the first port of the high-gain antenna to be communicated with the second Ka-band traveling wave tube amplifier in the second state, and the Ka-band downlink signal transmitted by the first Ka-band transmitting channel or the second Ka-band transmitting channel is transmitted to the first port of the high-gain antenna through the second Ka-band downlink.

In an embodiment of the present application, the second switch is a single-pole double-throw switch, the second switch has two connection states, and the second switch connects the second port of the high-gain antenna to the third switch in the first state; the second switch connects the first low-gain antenna to the third switch in the second state.

In an embodiment of the present application, the third switch is a double-pole double-throw switch, the third switch includes two connection states of a through connection and a cross connection, when the third switch is in the through connection state, the second low-gain antenna is connected to the fourth switch through the third switch, and the second port of the high-gain antenna or the first low-gain antenna is connected to the duplexer through the third switch; when the third switch is in the cross-connect state, the second low-gain antenna is connected to the duplexer via the third switch, and the second port of the high-gain antenna or the first low-gain antenna is connected to the fourth switch via the third switch.

In one embodiment of the present application, the fourth switch is a double pole double throw switch, the fourth switch includes both through-connected and cross-connected connection states,

when the third switch is in the through-connection state and the fourth switch is in the through-connection state, or when the third switch is in the through-connection state and the fourth switch is in the cross-connection state, simultaneously establishing a connection with the first low-gain antenna, and the second port of the high-gain antenna or the first low-gain antenna, with the first X-band receive path and the second X-band receive path; and the second port of the high-gain antenna or the first low-gain antenna is connected with the X-band transmitting channel;

when the third switch is in a cross-connected state and the fourth switch is in a through-connected state, or when the third switch is in a cross-connected state and the fourth switch is in a cross-connected state, causing the second low-gain antenna, and either the second port of the high-gain antenna or the first low-gain antenna, to establish a connection with both the first X-band receive path and the second X-band receive path; and the second low gain antenna establishes a connection with the X-band transmit channel.

In an embodiment of the present application, the first deep space transponder and the second deep space transponder each comprise a digital signal processing component configured to: including designating a first or second Ka-band downlink, an X-band uplink, and an X-band downlink for signal transmission using a high speed mode or a low speed mode.

In an embodiment of the application, the communication device uses different modes for uplink and downlink signal transmission in different task stages, when the task stage is any one of emergency situations of an LEOP stage, an orbital transfer cruise stage and a scientific operation stage, the uplink signal transmission uses an X-waveband uplink to perform high-speed or low-speed remote control and ranging, and the downlink signal transmission uses an X-waveband downlink to perform low-speed remote control and ranging; when the task stage is a scientific operation stage, the uplink signal transmission uses an X-band uplink to carry out high-speed remote control and ranging, and the downlink signal transmission uses a Ka-band downlink to carry out low-speed remote control and ranging; or the uplink signal transmission uses an X wave band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses a Ka wave band downlink to carry out high-speed data transmission; when the task stage is a scientific operation stage and the Ka-band downlink fails, the uplink signal transmission uses the X-band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the X-band downlink to carry out high-speed data transmission.

The present application further provides a measurement and control communication method for a deep space exploration spacecraft, in order to solve the above technical problems, where the spacecraft uses a + Z plane pointing to the earth and a-Z plane not pointing to the earth, and the method includes: configuring the connection state of a first switch, and enabling a first port of a high-gain antenna to be optionally connected with a first Ka-band downlink or a second Ka-band downlink to perform high-speed Ka-band downlink transmission, wherein the high-gain antenna is arranged on a + Z plane and is connected with the first switch through the first port; configuring a connection state of a second switch to enable a second port of the high-gain antenna to be connected with the X-band transmitting channel and optionally to be connected with the first X-band receiving channel or a second X-band receiving channel, wherein the high-gain antenna is connected with the second switch through the second port; configuring the connection state of a second switch to enable a first low-gain antenna to be connected with an X-waveband transmitting channel and optionally connected with a first X-waveband receiving channel or a second X-waveband receiving channel, wherein the first low-gain antenna is arranged on a + Z plane and is connected with the second switch; configuring a connection state of a third switch to enable a second low-gain antenna to be connected with the X-band transmitting channel and optionally with the first X-band receiving channel or a second X-band receiving channel, wherein the second low-gain antenna is arranged on the-Z plane and is connected with the third switch; the first Ka-band transmitting channel, the X-band transmitting channel and the first X-band receiving channel are arranged in the first deep space transponder, and the second Ka-band transmitting channel and the second X-band receiving channel are arranged in the second deep space transponder.

In the technical scheme, the first deep space transponder comprises a Ka wave band transmitting channel, an X wave band transmitting channel and an X wave band receiving channel, the second deep space transponder comprises a Ka wave band transmitting channel and an X wave band receiving channel, and the two deep space transponders realize the redundancy of an uplink channel and a downlink channel and ensure the reliability of a communication system; a pair of high-gain antennas with two ports is connected with the first switch, and the high-speed data downlink transmission of the Ka-band downlink can be realized by configuring the connection state of the first switch; one of the two pairs of low-gain antennas is connected with the second switch, the other pair of the two pairs of low-gain antennas is connected with the third switch, and by configuring the connection states of the second switch and the third switch, the data uplink transmission of an X-band uplink and the data downlink transmission of an X-band downlink can be realized, and the spacecraft can normally carry out measurement and control communication at all task stages under any postures.

The measuring and controlling communication device component number of the deep space exploration spacecraft is small, and cost can be reduced. The method and the device realize the redundancy design of the uplink and the downlink to ensure the reliability of the communication system. By configuring the connection states of the first switch, the second switch, the third switch and the fourth switch, the link which can be realized comprises two Ka-band downlinks, two X-band uplinks which can work simultaneously and one X-band downlink, so that measurement and control communication at all task stages of the spacecraft in any postures can be realized, and high-speed downlink transmission of a large amount of scientific data can be realized. The measurement and control communication device of the deep space exploration spacecraft can also be applied to other deep space exploration spacecraft, such as asteroid, wooden star and mars exploration tasks, and has significance for expanding application.

Drawings

In order to make the aforementioned objects, features and advantages of the present application more comprehensible, embodiments accompanying figures are described in detail below, wherein:

fig. 1 is a schematic overall structure diagram of a measurement and control communication device of a deep space exploration spacecraft according to an embodiment of the present application;

fig. 2 is another exemplary overall structural diagram of a measurement and control communication device of a deep space exploration spacecraft according to an embodiment of the present application;

FIG. 3 is an exemplary schematic diagram of the distance and visibility duration of a deep space exploration spacecraft to a ground station according to an embodiment of the present application;

fig. 4 is an exemplary diagram of data storage capacity, mission duration and ground station distance of the deep space exploration spacecraft according to an embodiment of the application.

Detailed Description

In order to make the aforementioned objects, features and advantages of the present application more comprehensible, embodiments accompanying the present application are described in detail below.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, but the present application may be practiced in other ways than those described herein and thus is not limited to the specific embodiments disclosed below.

As used in this application and the appended claims, the terms "a," "an," "the," and/or "the" are not intended to be inclusive in the singular, but rather are intended to be inclusive in the plural unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that steps and elements are included which are explicitly identified, that the steps and elements do not form an exclusive list, and that a method or apparatus may include other steps or elements.

The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present application, it is to be understood that the directions or positional relationships indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the directions or positional relationships shown in the drawings, and are for convenience of description and simplicity of description only, and in the case of not making a reverse description, these directional terms do not indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be construed as limiting the scope of the present application; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of protection of the present application is not to be construed as being limited. Further, although the terms used in the present application are selected from publicly known and used terms, some of the terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Further, it is required that the present application is understood not only by the actual terms used but also by the meaning of each term lying within.

For ease of description, spatially relative terms such as "over 8230 \ 8230;,"' over 8230;, \8230; upper surface "," above ", etc. may be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary terms "at 8230; \8230; 'above" may include both orientations "at 8230; \8230;' above 8230; 'at 8230;' below 8230;" above ". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

The measurement and control communication device of the deep space exploration spacecraft is mainly applied to exploration tasks of medium and small planets, venus, mars and the like in the deep space.

The number of components of some typical deep space exploration tasks is shown in table 1, and except for MarCO, all measurement and control communication systems provide near-omni-directional beam coverage through two pairs of low-gain wide-beam antennas installed back-to-back. High gain antennas are usually a mandatory item for high speed downlink of scientific data and are not listed in table 1. MarCO is a cubic star spacecraft with no redundant channels and very low down velocities as shown in table 2.

For a part of deep space exploration spacecrafts, the design of a measurement and control communication system of the spacecraft is mainly driven by the requirement of high-speed downloading of a large amount of scientific data. The maximum downlink data rate of most existing deep space measurement and control communication systems is only a few hundred kbps, as shown in table 2. The JWST is positioned at a Lagrangian L2 point and is far closer to the earth than other deep space exploration tasks. The HGA is used only for the downlink and cannot provide a high speed uplink during long distance phases. The Europa Clipper comprises four transmitting channels (including traveling wave tube amplifiers), seven pairs of antennas and a relatively complex radio frequency network, has high system redundancy and complexity, and is not suitable for a small-sized spacecraft with low cost.

TABLE 1 typical spacecraft measurement and control communication system composition

	Deep space answering machine	Power amplifier	Electric bridge	Duplexer	Switch with a switch body	Low gain antenna	Medium gain antenna
								Dawn
	2	2	1	2	5	3	0
								MarCO	1	3	0	0	0	2	2
Cassini	2	2	1	2	4	1	0
								Juno	2	2	2	2	5	3	0
JWST	4 a	4	/ b	/ b	/ b	2	0
								Europa	2	4	2	2	8	5	1
This application is a	2	3	1	1	4	2	0

a: a high-speed modulator comprising 2 independent Ka bands; b: no details are found.

TABLE 2 frequency assignment and maximum downlink data Rate for some exemplary tasks

Dawn

MarCO

Cassini

Juno

JWST

Europa

Maximum downlink rate/bps

128K

8K

256K

200K

28M a

1M

Frequency band

X

X

X

X

S/Ka

X/Ka

a: the JWST is located at the second Lagrangian point, closer to the Earth than other tasks.

First, the analysis and design of a low cost communication system with a high speed downlink is described.

Frequency design of different links.

Many deep space exploration spacecraft carry some data heavy payloads such as radar and cameras. Therefore, the design of the measurement and control communication system scheme is mainly driven by the requirement of high-speed downlink transmission of a large amount of scientific data. The X-band downlink bandwidth allocated for deep space spacecraft is only 50MHz (8400-8450 MHz), and the 50MHz bandwidth is shared by more and more deep space spacecraft launched by various organizations. To reduce frequency congestion, the official object is to provide a spacecraft with an X-band bandwidth in excess of 10 MHz. The downlink bandwidth allocated by the Ka-band deep space spacecraft is much wider than that of the X-band, and the maximum bandwidth can reach 500MHz (31.8-32.3 GHz).

For high-speed downlink, a high-gain transmitting antenna is adopted on the spacecraft, and the receiving power (receiving antenna outlet) of the ground station is P _r ：

P _r ＝P _t +G _t -L _s -L _a +G _r (1)

In the formula (1), P _t Is the on-satellite transmit power, G _t For transmitting antenna gain, L, on spacecraft _s For free space attenuation, L _a For all other attenuations, including atmospheric and cloud rain attenuations, G _r Gain for terrestrial receive antennas. Antenna gain G (applicable to G at the same time) _t And G _r ) And L _s Can be calculated as:

L _s ＝20log(r)+20log(f)+92.44 (3)

where η, D are the aperture efficiency and diameter of the antenna, respectively. C is the speed of light, f is the radio frequency signal frequency, and r is the distance of the spacecraft from the ground station.

Suppose that: using Ka-band frequencies f _Ka =31.9ghz, x band frequency f _X =8425MHz, madrid station was used. Then L _a (Ka) < 4dB, and the system availability is 99%. Subtracting the formula (3) from the formula (1), that is, obtaining the following equations (1) - (3):

that is, when η, D and P _t Equation (4) may represent the power difference between Ka-band and X-band for two bands being the same, i.e., the link gain of Ka-band is 7.6dB greater than X-band. Even though L is _a (Ka) increases significantly in cloudy and rainy weather conditions, and this problem can also be solved by using link budget design techniques based on weather forecasts.

In addition, power consumption, size and weight are also very important for communication systems. Illustratively, according to the public data of the traveling wave tube amplifier (the component with the largest power consumption in the system), the power efficiency of the X-band is about 65%, and the power efficiency of the Ka-band is about 63%, so that the power consumption of the Ka-band component is only slightly larger than that of the X-band. However, because of the short wavelength of the Ka band, the size and weight of the Ka band assembly is much smaller than the X band. Illustratively, taking the waveguide as an example, the size of the Ka band component (WR-28/WR-34) is only about 1/3 of that of the X band component (WR-112). The total weight of the X-band waveguide in a project is 6.3kg, and if the X-band waveguide is replaced by Ka-band, about 5.1kg of weight is saved (equivalent to 1.7 times the weight of the deep space transponder), because the density (kg/m) of the Ka-band waveguide is only 18% of the X-band. In addition, the influence of a dispersion noise source is inversely proportional to the wavelength, so that the Ka band can improve the precision of distance measurement, speed measurement and angle measurement.

Based on the analysis, the Ka waveband is selected for the high-speed downlink of the measurement and control communication system formed by the measurement and control communication device of the deep space exploration spacecraft. This conclusion is also confirmed by the frequency allocation and maximum downlink data rate of some typical deep space sounding tasks in table 2.

Even in the case of an abnormal attitude pointing of the spacecraft, for example, when the attitude pointing of the spacecraft deviates from a preset value, the low-rate uplink (remote control) link and the downlink (remote measurement) link should be able to operate normally, and therefore, the transceiver antenna on the spacecraft is designed as a low-gain antenna with wide beam coverage, and therefore, the formula (4) for performing calculation based on a high-gain antenna is not applicable. On the other hand, the Ka-band beam width of the ground antenna is much narrower than that of the X-band, and the high dynamic characteristics of the spacecraft in the launching and early operation stage and the orbit-changing cruising stage bring serious difficulty to the tracking of the spacecraft in the Ka-band deep space station. Therefore, the low-speed uplink and downlink telemetering remote control links of the observing and controlling communication system formed by the observing and controlling communication device of the deep space exploration spacecraft select X wave bands.

And (II) designing the composition and connection relation of a spacecraft communication system.

In order to ensure that an uplink and downlink measurement and control link of a spacecraft can work normally under any attitude (including the condition of out-of-control attitude), two pairs of wide beam transceiving shared antennas LGA which are arranged back to back are adopted to provide omnidirectional beam coverage. The HGA is used for high-speed downstream transmission of large amounts of scientific data. In order to ensure the reliability of the system, redundant X-band receive channels and Ka-band transmit channels (including TWTA) need to be provided, since these two channels are the most commonly used channels in the full life of the spacecraft. For channels that are used only at a small fraction of the time, there is no need to provide redundant backups, thereby saving cost and reducing the complexity of the communication system. The X-band uplink is the most important link and should be able to work properly even in the case of attitude runaway and unknown, so two deep space transponders should be able to connect to two LGAs simultaneously without the need for switching. Since the wide beam X-band downlink is already equipped and can be applied in the phase of attitude wide maneuver or even complete runaway, the two Ka-band transmit channels provide the high-speed downlink through the HGA only when the attitude is controlled. The transceiving channel of the X-band is not only connected with the LGA, but also connected with the HGA to provide a high-speed uplink and downlink, for example, the uplink data is used for repairing or updating software on a spacecraft.

Based on the design principle, the measurement and control communication device of the deep space exploration spacecraft is used for forming an improved low-cost measurement and control communication system with a high-speed downlink. The following introduces specific components of the measurement and control communication device of the deep space exploration spacecraft of the application:

fig. 1 is an overall structural schematic diagram of a measurement and control communication device of a deep space exploration spacecraft according to an embodiment of the present application. In fig. 1, parts of the components are connected by coaxial cables, and parts of the components are connected by waveguides 903. The pointing direction of the arrow of the transmitting coaxial cable 901 indicates that the spacecraft transmits a downlink signal to the ground station; the direction of the arrow pointing to receive coaxial cable 902 indicates that the spacecraft receives the uplink signal transmitted from the ground station; tx denotes a transmitting end, rx denotes a receiving end, and Tx/Rx denotes simultaneous transmission and reception.

Referring to fig. 1, in the measurement and control communication device for a deep space exploration spacecraft of the embodiment, the spacecraft has a + Z surface pointing to the earth and a-Z surface not pointing to the earth, the measurement and control communication device includes: a first deep space transponder 801 comprising a first Ka band transmit channel 811, an X band transmit channel 812, and a first X band receive channel 813; a second deep space transponder 802 including a second Ka band transmission channel 821 and a second X band reception channel 823; a high gain antenna 100 disposed in the + Z plane, the high gain antenna 100 including a first port 101 and a second port 102, the high gain antenna 100 being connected to a first switch 401 through the first port 101, optionally establishing a connection with a first Ka-band downlink or a second Ka-band downlink by configuring a connection state of the first switch 401 for Ka-band downlink transmission, the high gain antenna 100 being connected to a second switch 402 through the second port 102, establishing a connection with an X-band transmission channel 812 by configuring a connection state of the second switch 402, and optionally establishing a connection with a first X-band reception channel 813 or a second X-band reception channel 823; a first low-gain antenna 200 disposed in the + Z plane, the first low-gain antenna 200 being connected to the second switch 402, establishing a connection with the X-band transmission path 812 by configuring a connection state of the second switch 402, and optionally establishing a connection with the first X-band reception path 813 or the second X-band reception path 823; a second low-gain antenna 300 disposed in the-Z plane, the second low-gain antenna 300 being connected to the third switch 403, establishing a connection with the X-band transmission channels 812 and optionally with the first X-band reception channels 813 or the second X-band reception channels 823 by configuring a connection state of the third switch 403.

Illustratively, referring to fig. 1, when the first switch 401 communicates the first port 101 of the high-gain antenna 100 with the first Ka-band downlink, the first Ka-band transmit channel 811 or the second Ka-band transmit channel 821 transmits data downstream through the first port 101 of the high-gain antenna 100 to the ground station; when the first switch 401 connects the first port 101 of the high-gain antenna 100 to the second Ka-band downlink, the first Ka-band transmit channel 811 or the second Ka-band transmit channel 821 transmits data downstream to the ground station through the first port 101 of the high-gain antenna 100. The transmission path of data in the first Ka-band downlink and the second Ka-band downlink will be described in detail below.

The first port 101 of the high gain antenna 100 may only be in communication with either the first Ka-band downlink or the second Ka-band downlink at one time.

When the second switch 402 connects the second port 102 of the high-gain antenna 100 with the X-band transmitting channel 812, the X-band transmitting channel 812 transmits data downstream to the ground station through the second port 102 of the high-gain antenna 100; when the second switch 402 connects the second port 102 of the high-gain antenna 100 with the first X-band receiving channel 813, the second port 102 of the high-gain antenna 100 transmits data uplink to the first deep space transponder 801 through the first X-band receiving channel 813; when the second switch 402 connects the second port 102 of the high-gain antenna 100 to the second X-band receiving channel 823, the second port 102 of the high-gain antenna 100 transmits data uplink to the second deep space transponder 802 through the second X-band receiving channel 823.

The second port 102 of the high gain antenna 100 may be in simultaneous communication with the X-band transmit path 812, the first X-band receive path 813, or the second X-band receive path 823. Illustratively, the second port 102 of the high-gain antenna 100 is in simultaneous communication with the X-band transmit path 812 and the first X-band receive path 813, i.e., the second port 102 of the high-gain antenna 100 may transmit and receive data simultaneously at the same time.

When the second switch 402 communicates the first low-gain antenna 200 with the X-band transmit channel 812, the X-band transmit channel 812 transmits data downstream to the ground station via the first low-gain antenna 200; when the second switch 402 communicates the first low-gain antenna 200 with the first X-band reception channel 813, the first low-gain antenna 200 transmits data upstream to the first deep space transponder 801 through the first X-band reception channel 813; when the second switch 402 connects the first low-gain antenna 200 to the second X-band reception channel 823, the first low-gain antenna 200 transmits data upstream to the second deep space transponder 802 through the second X-band reception channel 823.

The first low gain antenna 200 may be in simultaneous communication with the X-band transmit path 812, the first X-band receive path 813, or the second X-band receive path 823. Illustratively, the first low gain antenna 200 is in simultaneous communication with the X-band transmit path 812 and the first X-band receive path 813, i.e., the first low gain antenna 200 may transmit and receive data simultaneously at the same time.

When the third switch 403 connects the second low-gain antenna 300 with the X-band transmitting channel 812, the X-band transmitting channel 812 transmits data downstream to the ground station through the second low-gain antenna 300; when the third switch 403 connects the second low-gain antenna 300 with the first X band reception channels 813, the second low-gain antenna 300 transmits data uplink to the first deep space transponder 801 through the first X band reception channels 813; when the third switch 403 connects the second low-gain antenna 300 with the second X-band reception channel 823, the second low-gain antenna 300 transmits data upstream to the second deep space transponder 802 through the second X-band reception channel 823.

The second low gain antenna 300 may be in simultaneous communication with the X-band transmit path 812, the first X-band receive path 813, or the second X-band receive path 823. Illustratively, the second low-gain antenna 300 is in simultaneous communication with the X-band transmit path 812, the first X-band receive path 813, i.e., the second low-gain antenna 300 may transmit and receive data simultaneously at the same time.

In the technical scheme of the application, the first deep space transponder 801 comprises a Ka-band transmitting channel, an X-band transmitting channel 812 and an X-band receiving channel, and the second deep space transponder 802 comprises a Ka-band transmitting channel and an X-band receiving channel, so that the redundancy of an uplink channel and a downlink channel is realized by the two deep space transponders, and the reliability of a communication system is ensured; a pair of high-gain antennas 100 with two ports is connected to the first switch 401, and by configuring the connection state of the first switch 401, high-speed data downlink transmission of a Ka-band downlink can be realized; one of the two pairs of low-gain antennas is connected with the second switch 402, the other pair is connected with the third switch 403, and by configuring the connection states of the second switch 402 and the third switch 403, the data uplink transmission of the uplink of the X wave band and the data downlink transmission of the downlink of the X wave band can be realized, and the spacecraft can normally perform measurement and control communication in all task stages under any posture.

In some embodiments, referring to fig. 1, the communications device further comprises a first Ka-band traveling wave tube amplifier 501, a second Ka-band traveling wave tube amplifier 502, and a bridge 600, wherein the bridge 600 comprises a first input 601, a second input 602, a first output 603, and a second output 604, wherein the first Ka-band transmit channel 811 is connected to the first input 601, the second Ka-band transmit channel 821 is connected to the second input 602, the first output 603 is connected to the first Ka-band traveling wave tube amplifier 501, the second output 604 is connected to the second Ka-band traveling wave tube amplifier 502, the first Ka-band traveling wave tube amplifier 501 and the second Ka-band traveling wave tube amplifier 502 are disposed between the first switch 401 and the bridge 600, and the first port 101 of the high-gain antenna 100 is selectively connected to the first Ka-band traveling wave tube amplifier 501 or the second Ka-band traveling wave tube amplifier 502 by configuring a connection state of the first switch 401.

Illustratively, the bridge 600 includes a 3dB bridge 600 configured such that the Ka-band transmit channel of any one of the two deep space transponders can drive any one of the Ka-band traveling wave tube amplifiers by connecting the first Ka-band transmit channel 811, the second Ka-band transmit channel 821, and the bridge 600, and connecting the bridge 600 to the first Ka-band traveling wave tube amplifier 501 and the second Ka-band traveling wave tube amplifier 502. For example, the first Ka-band transmit channel 811 may drive the first Ka-band traveling-wave tube amplifier 501 or the second Ka-band traveling-wave tube amplifier 502; the second Ka-band transmit channel 821 may drive either the first Ka-band traveling wave tube amplifier 501 or the second Ka-band traveling wave tube amplifier 502.

The 3dB bridge 600 can implement cross-connection between Ka-band transmit channels of two deep space transponders and two Ka-band traveling wave tube amplifiers, and does not require switching operations. The first switch 401 is switched to connect the first port 101 of the high-gain antenna 100 to the first Ka-band traveling wave tube amplifier 501 or the second Ka-band traveling wave tube amplifier 502. Illustratively, the first switch 401 is connected to the first Ka-band traveling wave tube amplifier 501 by default, and when the first Ka-band traveling wave tube amplifier 501 fails, the first switch 401 is switched to be connected to the second Ka-band traveling wave tube amplifier 502. The application does not limit the Ka band traveling wave tube amplifier to which the first switch 401 is connected by default. The configuration realizes the redundancy of the Ka-band traveling wave tube amplifier, ensures the reliability and stability of data in the downlink transmission process through the Ka-band downlink, and avoids data transmission failure caused by the failure of a certain Ka-band traveling wave tube amplifier.

In some embodiments, referring to fig. 1, the communication device further includes a fourth switch 404, a duplexer 700, and an X-band traveling wave tube amplifier 503, the second switch 402 is connected to the third switch 403, and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200 is connected to the third switch 403 by configuring a connection state of the second switch 402; the X-band traveling wave tube amplifier 503 is provided with an input end 504 and an output end 505, an X-band transmitting channel 812 is connected with the input end 504, and the output end 505 of the X-band traveling wave tube amplifier 503 is connected with the first end 701 of the duplexer 700; the duplexer 700 is arranged among the third switch 403, the X-band traveling-wave tube amplifier 503 and the fourth switch 404; the fourth switch 404 has a first input 405, a second input 406, a first output 407 and a second output 408, the first X-band reception channel 813 is connected to the first output 407 of the fourth switch 404, the second X-band reception channel 823 is connected to the second output 408 of the fourth switch 404, the duplexer 700 is connected to the first input 405 of the fourth switch 404, the third switch 403 is connected to the second input 406 of the fourth switch 404, and the second low-gain antenna 300, and the second port 102 or the first low-gain antenna 200 of the high-gain antenna 100 are simultaneously connected to the first X-band reception channel 813 and the second X-band reception channel 823 by configuring the connection states of the second switch 402, the third switch 403 and the fourth switch 404; and any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 establishes a connection with the X-band transmission channel 812.

In the communication apparatus of the present application, two X-band reception channels (the first X-band reception channel 813 and the second X-band reception channel 823) can simultaneously receive signals, and two X-band reception channels and the X-band transmission channel 812 can also be simultaneously established.

Illustratively, when the second switch 402 communicates the second port 102 of the high-gain antenna 100 with the third switch 403, data may be transmitted in a link between the second port 102 of the high-gain antenna 100, the second switch 402, and the third switch 403; when the second switch 402 connects the first low-gain antenna 200 and the third switch 403, data may be transmitted in the link between the first low-gain antenna 200, the second switch 402, and the third switch 403.

The second switch 402 can only be connected to the second port 102 of the high gain antenna 100 or the first low gain antenna 200 at a time.

When the third switch 403 connects the second port 102 of the high-gain antenna 100 with the X-band transmitting channel 812, the X-band transmitting channel 812 transmits data downstream to the ground station through the second port 102 of the high-gain antenna 100; when the third switch 403 connects the first low-gain antenna 200 with the X-band transmitting channel 812, the X-band transmitting channel 812 transmits data downstream to the ground station through the first low-gain antenna 200; when the third switch 403 communicates the second low-gain antenna 300 with the X-band transmit channel 812, the X-band transmit channel 812 transmits data downstream through the second low-gain antenna 300 to the ground station.

The third switch 403 can communicate with at most the second port 102 of the high-gain antenna 100, any one of the first low-gain antennas 200, and the second low-gain antenna 300 at the same time. For example, at the same time, the third switch 403 can communicate with the second port 102 of the high-gain antenna 100 and the second low-gain antenna 300 at most; alternatively, the third switch 403 can communicate with the first low-gain antenna 200 and the second low-gain antenna 300 at most.

The X-band transmitting channel 812 can only communicate with any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 at the same time.

When the fourth switch 404 connects the second port 102 of the high gain antenna 100 with the first X band reception channel 813, the data of the ground station is transmitted to the first deep space transponder 801 through the link among the second port 102 of the high gain antenna 100, the fourth switch 404, and the first X band reception channel 813; when the fourth switch 404 connects the first low gain antenna 200 and the first X-band receiving channel 813, the data of the ground station is transmitted to the first deep space transponder 801 through the uplink among the first low gain antenna 200, the fourth switch 404, and the first X-band receiving channel 813; when the fourth switch 404 connects the second low gain antenna 300 and the first X band reception channel 813, the data of the ground station is transmitted to the first deep space transponder 801 through the link between the second low gain antenna 300, the fourth switch 404, and the first X band reception channel 813.

The first X-band receiving channel 813 can only communicate with any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 at a time.

When the fourth switch 404 connects the second port 102 of the high-gain antenna 100 to the second X-band receiving channel 823, the data of the ground station is uplink-transmitted to the second deep space transponder 802 through the link among the second port 102 of the high-gain antenna 100, the fourth switch 404, and the second X-band receiving channel 823; when the fourth switch 404 connects the first low-gain antenna 200 with the second X-band receiving channel 823, the data of the ground station is uplink-transmitted to the second deep space transponder 802 through the link among the first low-gain antenna 200, the fourth switch 404, and the second X-band receiving channel 823; when the fourth switch 404 connects the second low gain antenna 300 with the second X-band receiving channel 823, the data of the ground station is uplink-transmitted to the second deep space transponder 802 through the link between the second low gain antenna 300, the fourth switch 404, and the second X-band receiving channel 823.

The second X-band receiving channel 823 can only communicate with any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 at a time.

The fourth switch 404 can communicate with at most the second port 102 of the high gain antenna 100, any one of the first low gain antenna 200, and the second low gain antenna 300 at the same time. For example, at the same time, the fourth switch 404 can be connected to the second port 102 of the high-gain antenna 100 and the second low-gain antenna 300 at most; alternatively, the fourth switch 404 can communicate with the first low gain antenna 200 and the second low gain antenna 300 at most.

Exemplarily, referring to fig. 1, by configuring the connection states of the second switch 402, the third switch 403, and the fourth switch 404, it is possible to make the second low-gain antenna 300 and the second port 102 of the high-gain antenna 100 establish a connection with the first X-band reception channel 813 and the second X-band reception channel 823 at the same time, and make any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 establish a connection with the X-band transmission channel 812; alternatively, the second low-gain antenna 300 and the first low-gain antenna 200 may be connected to the first X-band reception path 811 and the second X-band reception path 823 at the same time, and any one of the second port 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 may be connected to the X-band transmission path 812. By the arrangement, when the measurement and control communication device of the deep space exploration spacecraft works, two X-waveband uplink chains and one X-waveband downlink chain which can work simultaneously are included at the same time, and data transmission and data reception are carried out simultaneously.

The measurement and control communication device for the deep space exploration spacecraft can realize that the device comprises two Ka-band downlinks, two X-band uplinks capable of working simultaneously and one X-band downlink by configuring the connection states of the first switch 401, the second switch 402, the third switch 403 and the fourth switch 404.

For example, two Ka-band downlinks include: a signal transmitted by the first Ka-band transmitting channel 811 or the second Ka-band transmitting channel 821 is transmitted to a communication link between the first ports 101 of the high-gain antenna 100 through the first Ka-band traveling wave tube amplifier 501; alternatively, the signal transmitted by the first Ka-band transmitting channel 811 or the second Ka-band transmitting channel 821 is transmitted to the communication link between the first ports 101 of the high-gain antenna 100 through the second Ka-band traveling wave tube amplifier 502.

For example, two X band uplinks that may operate simultaneously include: a communication link between the second port 102 of the high gain antenna 100 and the first X band reception path 813, and a communication link between the second low gain antenna 300 and the second X band reception path 823; or a communication link between the first low-gain antenna 200 and the first X band reception path 813, and a communication link between the second low-gain antenna 300 and the second X band reception path 823.

For example, an X band downlink includes: a communication link between the X-band transmit path 812 and the second port 102 of the high gain antenna 100; or, a communication link between the X-band transmit path 812 and the first low-gain antenna 200; or the X-band transmit path 812 and the second low gain antenna 300.

It should be noted that the communication links between the above components are only used as examples, and do not represent that the measurement and control communication device of the deep space exploration spacecraft of the present application only has these communication links. The transmission path of the communication link of data between the components will be described in detail below.

The measurement and control communication device of the deep space exploration spacecraft can realize measurement and control communication of the spacecraft in all task stages and can also realize high-speed downlink transmission of a large amount of scientific data. The measurement and control communication device of the deep space exploration spacecraft has the advantages of less component number and lower cost, and can provide redundancy of uplink and downlink data transmission channels to ensure the reliability of communication.

Fig. 2 is another exemplary overall structural schematic diagram of the measurement and control communication device of the deep space exploration spacecraft according to an embodiment of the present application.

In some embodiments, referring to fig. 2, the first switch 401 is a single-pole double-throw switch, the first switch 401 has two connection states, the first switch 401 connects the first port 101 of the high-gain antenna 100 to the first Ka-band traveling wave tube amplifier 501 in the first state, and the Ka-band downlink signal transmitted by the first Ka-band transmitting channel 811 or the second Ka-band transmitting channel 821 is transmitted to the first port 101 of the high-gain antenna 100 through the first Ka-band downlink; the first switch 401, in the second state, connects the first port 101 of the high-gain antenna 100 with the second Ka-band traveling wave tube amplifier 502, and the Ka-band downlink signal transmitted by the first Ka-band transmitting channel 811 or the second Ka-band transmitting channel 821 is transmitted to the first port 101 of the high-gain antenna 100 through the second Ka-band downlink.

Illustratively, as shown in fig. 1 and fig. 2, the path of the downlink signal transmitted by the deep space transponder to the ground station in the first Ka-band downlink is sequentially: a first Ka-band transmitting channel 811 or a second Ka-band transmitting channel 821, a bridge 600, a first Ka-band traveling wave tube amplifier 501, a first switch 401, and a first port 101 of the high-gain antenna 100;

the path of the downlink signal transmitted by the deep space transponder to the ground station in the second Ka-band downlink is as follows in sequence: a first Ka-band transmit channel 811 or a second Ka-band transmit channel 821, a bridge 600, a second Ka-band traveling wave tube amplifier 502, a first switch 401, and a first port 101 of the high gain antenna 100.

The Ka-band transmitting channel is one of the most commonly used channels in the full life cycle of the spacecraft, two Ka-band downlinks can be realized by configuring the connection state of the first switch 401, namely, the redundancy of the Ka-band downlinks is realized, when one Ka-band downlink fails, the other Ka-band downlink can be used, and the reliability of data downlink transmission of the spacecraft is ensured. When the attitude of the spacecraft is controlled, any one of the two Ka-band downlinks can transmit a large amount of scientific data on the spacecraft to the ground station at high speed through the first port 101 of the high-gain antenna 100, so that the efficiency of data downlink transmission is improved.

In some embodiments, referring to fig. 2, the second switch 402 is a single-pole double-throw switch, the second switch 402 has two connection states, the second switch 402 communicates the second port 102 of the high-gain antenna 100 with the third switch 403 in the first state; the second switch 402 puts the first low-gain antenna 200 in communication with the third switch 403 in the second state.

For example, the second switch 402 is set as a single-pole double-throw switch, which can be switched between two connection states, and in practical applications, the second switch 402 communicates the second port 102 of the high-gain antenna 100 with the third switch 403 or communicates the first low-gain antenna 200 with the third switch 403 in different states.

In some embodiments, referring to fig. 2, the third switch 403 is a double-pole double-throw switch, the third switch 403 includes two connection states of through connection and cross connection, when the third switch 403 is in the through connection state, the second low-gain antenna 300 is connected with the fourth switch 404 through the third switch 403, and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200 is connected with the duplexer 700 through the third switch 403; when the third switch 403 is in the cross-connected state, the second low-gain antenna 300 is connected to the duplexer 700 through the third switch 403, and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200 is connected to the fourth switch 404 through the third switch 403.

Exemplarily, as shown in conjunction with fig. 1 and 2, the third switch 403 connects the second switch 402 with the duplexer 700 and connects the second low-gain antenna 300 with the fourth switch 404 in the through-connection state; the third switch 403 connects the second switch 402 and the fourth switch 404, and connects the second low gain antenna 300 and the duplexer 700 in the cross-connected state.

When third switch 403 is in the through-connected state, second low-gain antenna 300 is connected to fourth switch 404 through third switch 403, and the path for data transmission between second low-gain antenna 300 and fourth switch 404 is, in order: a second low gain antenna 300, a third switch 403, a fourth switch 404; and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200 is connected to the duplexer 700 through the third switch 403, and the paths through which data is transmitted between the second port 102 of the high-gain antenna 100 and the duplexer 700 are, in order: the second port 102, the second switch 402, the third switch 403, and the duplexer 700 of the high-gain antenna 100; the path for data transmission between the first low-gain antenna 200 and the duplexer 700 is, in order: a first low gain antenna 200, a second switch 402, a third switch 403, and a duplexer 700.

When the third switch 403 is in the cross-connection state, the second low-gain antenna 300 is connected to the duplexer 700 through the third switch 403, and the paths through which data is transmitted between the second low-gain antenna 300 and the duplexer 700 are, in order: a second low-gain antenna 300, a third switch 403, a duplexer 700; and the second port 102 of the high gain antenna 100 or the first low gain antenna 200 is connected to the fourth switch 404 through the third switch 403, the paths through which data is transmitted between the second port 102 of the high gain antenna 100 and the fourth switch 404 are, in turn: second port 102, second switch 402, third switch 403, fourth switch 404 of high gain antenna 100; the path for data transmission between the first low gain antenna 200 and the fourth switch 404 is in turn: a first low gain antenna 200, a second switch 402, a third switch 403, a fourth switch 404.

In some embodiments, referring to fig. 2, the fourth switch 404 is a double pole double throw switch, the fourth switch 404 includes both through connection and cross connection states, and when the third switch 403 is in the through connection state and the fourth switch 404 is in the through connection state, or when the third switch 403 is in the through connection state and the fourth switch 404 is in the cross connection state, the second low gain antenna 300, and the second port 102 of the high gain antenna 100 or the first low gain antenna 200, are connected simultaneously with the first X band receive path 813 and the second X band receive path 823; and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200 establishes a connection with the X-band transmission channel 812; when the third switch 403 is in the cross-connected state and the fourth switch 404 is in the through-connected state, or when the third switch 403 is in the cross-connected state and the fourth switch 404 is in the cross-connected state, the second low-gain antenna 300, and the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200, are simultaneously connected with the first X-band reception path 813 and the second X-band reception path 823; and the second low-gain antenna 300 establishes a connection with the X-band transmission channel 812.

The communication device of the present application may have two X band uplinks and one X band downlink at the same time.

Illustratively, as shown in conjunction with fig. 1 and 2, the fourth switch 404, in a through-connection state, connects the duplexer 700 with the first X-band reception channel 813 and the third switch 403 with the second X-band reception channel 823; the fourth switch 404 connects the duplexer 700 to the second X band reception path 823 and the third switch 403 to the first X band reception path 813 in the cross-connected state.

By configuring the connection states of the second switch 402, the third switch 403, and the fourth switch 404, two X-band uplinks and one X-band downlink can be implemented, which can operate simultaneously.

Next, a detailed description will be given of a specific path through which data can be transmitted in each link by configuring the connection states of the second switch 402, the third switch 403, and the fourth switch 404 in this application.

The X-band transmit channel 812 transmits data downstream to the ground station, including the following three downlink transmission paths.

Illustratively, as shown in fig. 1 and fig. 2, the downlink signal transmitted by the first deep space transponder 801 to the ground station is transmitted in the first X-band downlink by the following paths: an X-band transmitting channel 812, an X-band traveling wave tube amplifier 503, a duplexer 700, a third switch 403, a second switch 402, and a second port 102 of the high gain antenna 100.

The paths of the downlink signals transmitted by the first deep space transponder 801 to the ground station in the second X-band downlink are as follows: an X-band transmitting channel 812, an X-band traveling wave tube amplifier 503, a duplexer 700, a third switch 403, a second switch 402, and a first low-gain antenna 200.

The path of the downlink signal transmitted by the first deep space transponder 801 to the ground station in the third X-band downlink is sequentially: an X-band transmitting channel 812, an X-band traveling wave tube amplifier 503, a duplexer 700, a third switch 403 and a second low-gain antenna 300.

The ground station transmits data to two deep space transponders in an uplink mode, and the ground station comprises the following twelve uplink transmission paths.

As shown in fig. 1 and fig. 2, the path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the first X-band uplink is sequentially: the second port 102 of the high gain antenna 100, the second switch 402, the third switch 403, the duplexer 700, the fourth switch 404, the first X band reception channel 813.

The path of the uplink signal transmitted by the ground station to the second deep space transponder 802 in the uplink of the second X band is sequentially as follows: the second port 102 of the high gain antenna 100, the second switch 402, the third switch 403, the duplexer 700, the fourth switch 404, the second X-band reception channel 823.

The path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the third X-band uplink is as follows: the second port 102, the second switch 402, the third switch 403, the fourth switch 404, the first X-band receive channel 813 of the high gain antenna 100.

The path of the uplink signal transmitted by the ground station to the second deep space transponder 802 in the fourth X band uplink is sequentially: second port 102, second switch 402, third switch 403, fourth switch 404, second X-band receive channel 823 of high gain antenna 100.

The path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the fifth X band uplink is as follows: a first low gain antenna 200, a second switch 402, a third switch 403, a duplexer 700, a fourth switch 404, a first X-band receive path 813.

The path of the uplink signal transmitted by the ground station to the second deep space transponder 802 in the sixth X band uplink is sequentially: a first low gain antenna 200, a second switch 402, a third switch 403, a duplexer 700, a fourth switch 404, a second X-band reception channel 823.

The path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the seventh X band uplink is as follows: a first low gain antenna 200, a second switch 402, a third switch 403, a fourth switch 404, a first X band receive via 813.

The path of the uplink signal transmitted by the ground station to the second deep space transponder 802 in the eighth X band uplink is sequentially: a first low gain antenna 200, a second switch 402, a third switch 403, a fourth switch 404, a second X-band receive channel 823.

The path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the ninth X band uplink is sequentially: a second low gain antenna 300, a third switch 403, a duplexer 700, a fourth switch 404, a first X band receive path 813.

The path of the uplink signal transmitted by the ground station to the second deep space transponder 802 in the tenth X band uplink is sequentially: a second low gain antenna 300, a third switch 403, a duplexer 700, a fourth switch 404, a second X-band receive channel 823.

The path of the uplink signal transmitted by the ground station to the first deep space transponder 801 in the eleventh X band uplink is as follows: a second low gain antenna 300, a third switch 403, a fourth switch 404, a first X-band receive path 813.

The uplink signal transmitted by the ground station to the second deep space transponder 802 is transmitted in the twelfth band X uplink by the following paths: a second low gain antenna 300, a third switch 403, a fourth switch 404, a second X-band receive channel 823.

The uplink transmission remote control instruction of the ground station is used for controlling the spacecraft, repairing or updating spacecraft software through an uplink software patch, and the like, and the uplink transmission remote control instruction can be injected to the spacecraft through any one of the X-band uplink links, so that the low-speed X-band uplink can work normally even if the attitude of the spacecraft points abnormally. The X-band receiving channel is one of the most common channels in the life cycle of the spacecraft, and two X-band uplinks which work simultaneously can be realized by configuring the connection states of the second switch 402, the third switch 403 and the fourth switch 404, namely the redundancy of the X-band uplinks is realized, and the measurement and control communication of the spacecraft in all task stages can be realized. Under the normal condition, even under the condition that the attitude of the spacecraft is out of control and unknown, the uplink data of the ground station can still be simultaneously transmitted in two X-waveband uplink links which can work simultaneously, and the communication efficiency and reliability of the ground station and the spacecraft are improved.

Illustratively, referring to fig. 1 and 2, the two simultaneously operating X-band uplinks may be as described above: a fifth X band uplink (the path for data transmission is, in order, the first low-gain antenna 200, the second switch 402, the third switch 403, the duplexer 700, the fourth switch 404, and the first X band receive path 813) and a twelfth X band uplink (the path for data transmission is, in order, the second low-gain antenna 300, the third switch 403, the fourth switch 404, and the second X band receive path 823); the two simultaneously operating X-band uplinks may also be as described above: a first X band uplink (the path of data transmission is, in order, the second port 102, the second switch 402, the third switch 403, the duplexer 700, the fourth switch 404, and the first X band receiving channel 813 of the high gain antenna 100), and a twelfth X band uplink (the path of data transmission is, in order, the second low gain antenna 300, the third switch 403, the fourth switch 404, and the second X band receiving channel 823). The two simultaneously operating X-band uplinks may be selected according to actual conditions, and the application is not limited.

For example, referring to fig. 1, when the attitude of the spacecraft is abnormal, the first low-gain antenna 200 and the second low-gain antenna 300 may be used to perform X-band uplink data transmission and X-band downlink data transmission. Under the condition that the attitude of the spacecraft is abnormal, the measurement and control communication device can ensure normal communication between the ground station and the spacecraft.

When two X-band uplink links are not required to work simultaneously, any one of the first X-band uplink link to the twelfth X-band uplink link can be selected for transmitting data, and when a certain X-band uplink link fails, the rest X-band uplink links can be used for transmitting the data of the ground station to the deep space transponder in an uplink mode, so that the reliability of spacecraft data uplink transmission is guaranteed.

In some embodiments, as illustrated with reference to fig. 1, the first deep space transponder 801 and the second deep space transponder 802 each include digital signal processing components configured to: including designating a first or second Ka-band downlink, an X-band uplink, and an X-band downlink for signal transmission using a high speed mode or a low speed mode.

Referring to fig. 1, the first dsp component 814 and the second dsp component 824 are used to designate signals to be transmitted in the high-speed mode or the low-speed mode in each link as described above. Preferably, the first and second digital signal processing components 814 and 824 designate either the first or second Ka-band downlink for signal transmission using the high speed mode. Illustratively, the first digital signal processing component 814 and the second digital signal processing component 824 may also specify whether the first Ka-band downlink or the second Ka-band downlink is to be signaled using a low speed mode, which is not limited in this application.

The digital signal processing component sets each uplink and downlink to use a high-speed mode or a low-speed mode for signal transmission. In a high-speed mode, high-speed downlink transmission of a large amount of scientific data on a spacecraft can be realized, and the data transmission efficiency is improved; under the low-speed mode, the measurement and control communication of the spacecraft in all task stages can be realized, no matter whether the operation posture of the spacecraft is normal or abnormal, data can be stably transmitted from the spacecraft to the ground station in a downlink mode, or stably transmitted from the ground station to the spacecraft in an uplink mode, and the reliability of data transmission is guaranteed.

In some embodiments, the communication device uses different modes for uplink and downlink signal transmission in different task stages, when the task stage is any one of emergency situations of an LEOP (Early Orbit stage), an orbital transfer cruise stage and a scientific operation stage, the uplink signal transmission uses an X-band uplink for high-speed or low-speed remote control and ranging, and the downlink signal transmission uses an X-band downlink for low-speed remote control and ranging; when the task stage is a scientific operation stage, the uplink signal transmission uses an X-band uplink to carry out high-speed remote control and ranging, and the downlink signal transmission uses a Ka-band downlink to carry out low-speed remote control and ranging; or the uplink signal transmission uses an X wave band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses a Ka wave band downlink to carry out high-speed data transmission; when the task stage is a scientific operation stage and the Ka-band downlink fails, the uplink signal transmission uses the X-band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the X-band downlink to carry out high-speed data transmission.

The mode used by the communication device of the present application in the transmission of uplink and downlink signals at different task stages is shown in table 4 below.

The embodiment of the present application further discloses a measurement and control communication method for a deep space exploration spacecraft, as shown in fig. 1, the spacecraft uses a + Z plane pointing to the earth and a-Z plane not pointing to the earth, and includes: configuring a connection state of a first switch 401, so that a first port 101 of a high-gain antenna 100 can optionally establish connection with a first Ka-band downlink or a second Ka-band downlink to perform Ka-band high-speed downlink transmission, where the high-gain antenna 100 is arranged on a + Z plane, and the high-gain antenna 100 is connected with the first switch 401 through the first port 101; configuring a connection state of the second switch 402 such that the second port 102 of the high-gain antenna 100 establishes a connection with the X-band transmission channel 812 and optionally with the first X-band reception channel 813 or the second X-band reception channel 823, wherein the high-gain antenna 100 is connected with the second switch 402 through the second port 102; configuring a connection state of the second switch 402 such that the first low-gain antenna 200 establishes a connection with the X-band transmission path 812 and optionally with the first X-band reception path 813 or the second X-band reception path 823, wherein the first low-gain antenna 200 is disposed at the + Z plane and the first low-gain antenna 200 is connected with the second switch 402; configuring a connection state of the third switch 403 such that the second low-gain antenna 300 establishes a connection with the X-band transmission path 812 and optionally with the first X-band reception path 813 or the second X-band reception path 823, wherein the second low-gain antenna 300 is disposed in the-Z plane and the second low-gain antenna 300 is connected with the third switch 403; among them, a first Ka-band transmission channel 811, an X-band transmission channel 812, and a first X-band reception channel 813 are provided in the first deep space transponder 801, and a second Ka-band transmission channel 821 and a second X-band reception channel 823 are provided in the second deep space transponder 802.

In the measurement and control communication method for the deep space exploration spacecraft, the setting mode and the communication process of each component are described in detail in the foregoing, and are not described again.

For example, as shown in fig. 1 and fig. 2, in the measurement and control communication device of the deep space exploration spacecraft of the present application, the second switch is a single-pole double-throw switch, the third switch is a double-pole double-throw switch, and the fourth switch is a double-pole double-throw switch, and by configuring the states of the switches, the connection relationship between the uplink and the downlink in the X-band is as shown in table 3 below.

TABLE 3 connection relationship between second, third and fourth switch states and X-band uplink and downlink

In table 3:

1) A state 1 of the single-pole double-throw switch (second switch) indicates that the left upper port is connected with the right port, and a state 2 indicates that the left lower port is connected with the right port; the double pole double throw switch has a through connection state 1 and a cross connection state 2.

2) The first switch connects the first port of the high-gain antenna to the first Ka-band traveling wave tube amplifier by default, and only when the first Ka-band traveling wave tube amplifier breaks down, the first switch can be switched to the second Ka-band traveling wave tube amplifier.

3) In the following, the uplink and downlink mode 1 of table 4 requires that each switch of table 3 is in a connection state of serial number 2 or 4 or 6 or 8; the uplink and downlink mode 2 or 3 of table 4 requires the connection state of each switch of table 3 by number 1 or 3 or 5 or 7, and the uplink and downlink mode 4 of table 4 requires the connection state of each switch of table 3 by number 1 or 5.

According to the foregoing, referring to fig. 1 and fig. 2, the measurement and control communication device of the deep space exploration spacecraft of the present application includes: a pair of high gain antennas 100 (two ports, ka band and X band), two pairs of low gain antennas (200, 300), two Single Pole Double Throw (SPDT) switches (401, 402), two Double Pole Double Throw (DPDT) switches (403, 404), two Ka band traveling wave tube amplifiers (501, 502), an X band traveling wave tube amplifier 503, an X band duplexer 700, a Ka band 3dB bridge 600, two deep space transponders (801, 802), nine waveguides and nine coaxial cables. Each deep space transponder includes an X-band receive channel and a Ka-band transmit channel, and the first deep space transponder 801 further includes an X-band transmit channel 812. The two deep space answering machines (801 and 802) can not only carry out conventional measurement and control communication, but also realize a high-speed data downlink transmission function through Software Defined Radio (SDR) technology.

As shown in table 1, the measurement and control communication device of the present application contains a relatively minimal number of components compared to other spacecraft, particularly compared to JWST and Europa Clipper, which also have a high speed downlink. Because the most expensive components in the communication system are a deep space transponder and a high-power amplifier, the measurement and control communication device is the lowest cost.

In the measurement and control communication device, one of the two pairs of low-gain antennas and the high-gain antenna are arranged at the same position of the spacecraft (the low-gain antenna is arranged on a feed source of the high-gain antenna), the two low-gain antennas are arranged on the + Z surface (pointing to the earth) of the spacecraft, and the other low-gain antenna is arranged on the-Z surface. By configuring the connection state of four microwave switches:

1) The X-band traveling wave tube amplifier (together with the X-band transmit channel in the first deep space transponder) may be connected to any of three antennas (one high gain antenna, two low gain antennas);

2) Any one of the two pairs of + Z-plane antennas (a pair of high-gain antennas, a pair of low-gain antennas) and the-Z-plane low-gain antenna can be simultaneously connected to the two X-band receiving channels respectively;

3) Through a Ka wave band 3dB electric bridge, a Ka wave band transmitting channel of any one deep space transponder can drive any one Ka wave band traveling wave tube amplifier. The 3dB bridge realizes the cross connection between the Ka-band transmitting channels of the two transponders and the two Ka-band traveling wave tube amplifiers, and does not need switching operation.

Therefore, by configuring the connection states of the four microwave switches, two Ka-band downlinks, two X-band uplinks that can operate simultaneously, and one X-band downlink can be realized.

The design of the working mode of the uplink and downlink data transmission of the measurement and control communication device of the deep space exploration spacecraft is carried out below.

The uplink and downlink operating modes are shown in table 4. The X-band uplink operates throughout the life cycle of the spacecraft. The X-band low-speed telemetry downlink only works in emergencies (such as attitude anomaly) during Launch and Early Orbit Phase (LEOP), orbital transfer cruise Phase, and scientific operation Phase. For a mission of a Venus or Mars detector, the X-band low-speed telemetering downlink only needs to continuously work for about 6 months, which is much shorter than the whole life cycle of a spacecraft (generally at least three years, such as more than ten years and even dozens of years), and even if the X-band low-speed telemetering downlink is damaged, the work of a communication system is not influenced, so that only one X-band transmitting channel and one X-band traveling wave tube amplifier are configured. The Ka-band low-speed telemetry downlink and the X-band uplink jointly realize a conventional telemetry and remote control function in a scientific task stage. High speed data transmission is typically carried out in the Ka band. The X band may also provide a data transfer downlink with a data rate <4Mbps through a high gain antenna as a backup when both ka band downlinks are fully failed.

TABLE 4 Up/Down mode

TC: remote control; r: ranging, including two-way tone ranging, or differential one-way ranging; "()" represents optional.

The following exemplifies the application of the measurement and control communication device of the deep space exploration spacecraft of the present application.

FIG. 3 is an exemplary schematic diagram of the distance and visibility duration of a deep space exploration spacecraft to a ground station according to an embodiment of the present application; fig. 4 is an exemplary diagram of data storage capacity, mission duration and ground station distance of the deep space exploration spacecraft according to an embodiment of the application.

Illustratively, scientists are planning to launch a spacecraft to perform a surround view of Venus. The spacecraft basic information is shown in table 5. The on-board load produces a large amount of scientific data at a rate of about 150 Gb/day. The range of the distance from the star to the earth is 4 x 107km to 2.6 x 108km, and the distance between the spacecraft and the earth within 3 years is shown in figure 3. Assuming that both a ground station and deep space stations within a certain environment are available, the visibility of the spacecraft to the ground station is shown in fig. 3. The visible time period is greater than 4 hours per day. Therefore, 4 hours/day can be allocated for high-speed scientific data download.

TABLE 5 Starter Detector basic information (example)

Weight (kg)	2250
		Carrying is carried	****
Time of transmission	2026/06
		Cruise track transfer time (sky)	182.48

Based on the constraint conditions, the main indexes of the measurement and control communication system are as follows:

uplink/downlink frequency: 71 MHz/31 GHz, forward ratio: 749/3328; 71/84 MHz, transfer ratio: 749/880;

modulation mode: PCM-PSK-PM (remote and low speed telemetry), BPSK/QPSK (high speed data transmission); PCM (Pulse Code Modulation); PSK (Phase Shift Keying); PM (Phase Modulation); BPSK (Binary Phase Shift Keying); QPSK (Quadrature Phase Shift Keying).

Remote control rate: ranging from 7.8125bps to 2,000 bps, multiplied by 2;

remote control channel coding: BCH (63, 56); the BCH code is proposed by r.c. bose, d.k.chaudhuri and a.hocquenghem, and is a cyclic check code suitable for random error correction.

Low speed telemetry rate: ranging from 8bps to 8192bps, multiplied by 2;

high speed data transfer rate: 200kbps (far site and when the weather is very bad), and the rates in table 6; the data transmission data comprises telemetry information;

telemetry channel coding: RS concatenated (7, 1/2) convolutional coding, LDPC; among them, RS (Reed-Solomon Codes); LDPC (Low Density Parity Check Code).

X-band transmit power: 10W/220W (10W for initial transmission);

ka-band transmission power: 220W;

low gain antenna gain: 0-65 degrees, G is more than or equal to 1dB; 65-75 degrees, G is more than or equal to 0dB; 75-90 degrees, and G is more than or equal to-5 dB;

high gain antenna gain: the X wave band emission gain is more than or equal to 41.5dB @ plus or minus 0.5 degrees, and the X wave band receiving gain is more than or equal to 40.5dB @ plus or minus 0.5 degrees; the Ka wave band emission gain is more than or equal to 52.5dB @ +/-0.2 degrees.

Illustratively, the high speed data transmission link performance based on a certain deep space network ground station (35 m) is shown in table 6. Therefore, the data quantity stored on the satellite can be calculated, and as shown in fig. 4, the scientific data on the satellite can be downloaded all at each near place.

TABLE 6 HIGH-SPEED DOWNLINK PERFORMANCE FOR A35 m station

Distance between ground and vessel/10 7 km	4	5	5.5	6	7	8	10	11	13	16	20	26
													Data rate/Mbps	20	16	12	10	8	6	4	3	2	1.5	1	0.5
4h downlink data amount/Gb	288	230	173	144	115	86	58	43	29	22	14	7

In emergency situations, such as LEOP, cruise orbital transfer phase, and scientific operational phase, the X-band low gain antenna is used for low speed telemetry downlink. The link budget over a + -75 deg. beam coverage based on a certain DSN ground station (35 m) and ground station (66 m) is shown in table 7. When the far spot is out of the + -75 deg. beam coverage, a 66m ground station should be used, the data rate is only 8bps, and the link margin is calculated to be only 0.75dB. The remote uplink budget for + -75 beam coverage is shown in table 8. When the far spot exceeds + -75 deg. beam coverage, a 66m ground station should be used, the data rate is only 7.8125bps, and the link margin is only 1.65dB.

TABLE 7X band Low speed telemetry data Rate and Range (Low gain antenna @75 ° Beam in)

Table 8X band remote control uplink data rate and distance (low gain antenna @75 ° beam inside)

And when the spacecraft is in a normal posture in the scientific operation stage, the high-gain antenna is adopted to carry out X-band uplink remote control and Ka-band downlink remote control. Even in remote sites, the link margin corresponding to 35m stations is quite sufficient, with 19.1dB @2000bps for the uplink and 19.7dB @8192bps for the downlink.

In summary, based on the existing research, the measurement and control communication device of the deep space exploration spacecraft is applied to the spacecraft to form an improved low-cost measurement and control communication system scheme with a high-speed downlink, and the communication system comprises: the antenna comprises a pair of high-gain antennas (two ports, a Ka wave band and an X wave band), two pairs of low-gain antennas, two single-pole double-throw (SPDT) switches, two double-pole double-throw (DPDT) switches, two Ka wave band traveling wave tube amplifiers, an X wave band traveling wave tube amplifier, an X wave band duplexer, a Ka wave band 3dB electric bridge, two deep space answering machines, nine wave tubes and nine coaxial cables.

Compared with some typical deep space detection tasks, the measurement and control communication device has the advantages that the number of components is minimum, the redundancy design of an uplink link and a downlink link is realized, and the reliability of a communication system is guaranteed; the measurement and control communication device is provided with two Ka-band downlinks, two X-band uplinks capable of working simultaneously and one X-band downlink, measurement and control communication of the spacecraft in all task stages can be achieved, and high-speed downlink transmission of a large amount of scientific data can be achieved.

Exemplarily, the application example of the aforementioned Venus probe shows that 150Gb scientific data can be downloaded by a 35m ground station on average every day, and uplink and downlink measurement and control communication under any posture can be realized. The remote measurement and remote control communication of the spacecraft in all task stages and the high-speed downlink of a large amount of scientific data (the maximum data rate is 20 Mbps) can be reliably ensured. The measurement and control communication device, the measurement and control communication method and the design idea of the deep space exploration spacecraft can provide reference significance for the design of other measurement and control communication systems of the deep space exploration spacecraft.

Having thus described the basic concept, it should be apparent to those skilled in the art that the foregoing disclosure is by way of example only, and is not intended to limit the present application. Various modifications, improvements and adaptations to the present application may occur to those skilled in the art, though not expressly described herein. Such modifications, improvements and adaptations are proposed in the present application and thus fall within the spirit and scope of the exemplary embodiments of the present application.

Aspects of the present application may be embodied entirely in hardware, entirely in software (including firmware, resident software, micro-code, etc.) or in a combination of hardware and software. The above hardware or software may be referred to as "data block," module, "" engine, "" unit, "" component, "or" system. The processor may be one or more Application Specific Integrated Circuits (ASICs), digital Signal Processors (DSPs), digital signal processing devices (DAPDs), programmable Logic Devices (PLDs), field Programmable Gate Arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or a combination thereof. Furthermore, aspects of the present application may be represented as a computer product, including computer readable program code, in one or more computer readable media. For example, computer-readable media can include, but are not limited to, magnetic storage devices (e.g., hard disk, floppy disk, magnetic tape \8230;), optical disks (e.g., compact disk CD, digital versatile disk DVD \8230;), smart cards, and flash memory devices (e.g., card, stick, key drive \8230;).

The computer readable medium may comprise a propagated data signal with the computer program code embodied therein, for example, on a baseband or as part of a carrier wave. The propagated signal may take any of a variety of forms, including electromagnetic, optical, and the like, or any suitable combination. The computer readable medium can be any computer readable medium that can communicate, propagate, or transport the program for use by or in connection with an instruction execution system, apparatus, or device. Program code on a computer readable medium may be propagated over any suitable medium, including radio, electrical cable, fiber optic cable, radio frequency signals, or the like, or any combination of the preceding.

Also, this application uses specific language to describe embodiments of the application. Reference throughout this specification to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic described in connection with at least one embodiment of the present application is included in at least one embodiment of the present application. Therefore, it is emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, some features, structures, or characteristics of one or more embodiments of the present application may be combined as appropriate.

Numerals describing the number of components, attributes, etc. are used in some embodiments, it being understood that such numerals used in the description of the embodiments are modified in some instances by the use of the modifier "about", "approximately" or "substantially". Unless otherwise indicated, "about", "approximately" or "substantially" indicates that the number allows a variation of ± 20%. Accordingly, in some embodiments, the numerical parameters set forth in the specification and claims are approximations that may vary depending upon the desired properties sought to be obtained by a particular embodiment. In some embodiments, the numerical parameter should take into account the specified significant digits and employ a general digit preserving approach. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of the range are approximations, in the specific examples, such numerical values are set forth as precisely as possible within the scope of the application.

Although the present application has been described with reference to the present specific embodiments, it will be appreciated by those skilled in the art that the above embodiments are merely illustrative of the present application and that various equivalent changes or substitutions may be made without departing from the spirit of the application, and therefore, it is intended that all changes and modifications to the above embodiments within the spirit of the application fall within the scope of the claims of the application.

Claims (10)

1. A measurement and control communication device for a deep space exploration spacecraft, the spacecraft having a + Z plane pointing towards the earth and a-Z plane not pointing towards the earth, comprising:

the first deep space transponder comprises a first Ka waveband transmitting channel, an X waveband transmitting channel and a first X waveband receiving channel;

the second deep space transponder comprises a second Ka-band transmitting channel and a second X-band receiving channel;

a high-gain antenna disposed on the + Z plane, the high-gain antenna including a first port and a second port, the high-gain antenna being connected to a first switch through the first port, optionally establishing a connection with a first Ka-band downlink or a second Ka-band downlink by configuring a connection state of the first switch to perform Ka-band downlink transmission, the high-gain antenna being connected to a second switch through the second port, optionally establishing a connection with the X-band transmit channel by configuring a connection state of the second switch, and optionally establishing a connection with the first X-band receive channel or the second X-band receive channel;

a first low-gain antenna disposed on the + Z plane, the first low-gain antenna being connected to the second switch, establishing a connection with the X-band transmit channel by configuring a connection state of the second switch, and optionally establishing a connection with the first X-band receive channel or the second X-band receive channel;

a second low-gain antenna disposed at the-Z plane, the second low-gain antenna being connected to a third switch, establishing a connection with the X-band transmit channel by configuring a connection state of the third switch, and optionally establishing a connection with the first X-band receive channel or the second X-band receive channel.

2. The communications device of claim 1 further comprising a first Ka-band traveling wave tube amplifier, a second Ka-band traveling wave tube amplifier, and a bridge comprising a first input, a second input, a first output, and a second output, the first Ka-band transmit channel connected to the first input, the second Ka-band transmit channel connected to the second input, the first output connected to the first Ka-band traveling wave tube amplifier, the second output connected to the second Ka-band traveling wave tube amplifier, the first and second Ka-band traveling wave tube amplifiers disposed between the first switch and the wave tube, the first port of the high gain antenna selectively connectable to either the first Ka-band traveling wave tube amplifier or the second Ka-band traveling wave tube amplifier by configuring a connection state of the first switch.

3. The communications apparatus according to claim 1, further comprising a fourth switch, a duplexer, and an X-band traveling wave tube amplifier, wherein the second switch is connected to the third switch, and wherein the second port of the high-gain antenna or the first low-gain antenna is connected to the third switch by configuring a connection state of the second switch; the X-band traveling wave tube amplifier is provided with an input end and an output end, the X-band transmitting channel is connected with the input end, and the output end of the X-band traveling wave tube amplifier is connected with the first end of the duplexer; the duplexer is arranged among the third switch, the X-band traveling wave tube amplifier and the fourth switch; the fourth switch has a first input end, a second input end, a first output end and a second output end, the first X band receiving channel is connected with the first output end of the fourth switch, the second X band receiving channel is connected with the second output end of the fourth switch, the duplexer is connected with the first input end of the fourth switch, the third switch is connected with the second input end of the fourth switch, and the second low-gain antenna, and the second port of the high-gain antenna or the first low-gain antenna are simultaneously connected with the first X band receiving channel and the second X band receiving channel by configuring the connection states of the second switch, the third switch and the fourth switch; and any one of the second port of the high-gain antenna, the first low-gain antenna and the second low-gain antenna establishes a connection with the X-band transmission channel.

4. The communications device of claim 3, wherein the first switch is a single-pole double-throw switch, the first switch having two connection states, the first switch in a first state communicating the first port of the high-gain antenna with the first Ka-band traveling-wave tube amplifier, the Ka-band downlink signal transmitted by the first Ka-band transmit channel or the second Ka-band transmit channel being transmitted through the first Ka-band downlink to the first port of the high-gain antenna; and the first switch enables the first port of the high-gain antenna to be communicated with the second Ka-band traveling wave tube amplifier in a second state, and Ka-band downlink signals transmitted by the first Ka-band transmitting channel or the second Ka-band transmitting channel are transmitted to the first port of the high-gain antenna through the second Ka-band downlink.

5. The communications device of claim 4, wherein the second switch is a single pole double throw switch, the second switch having two connection states, the second switch in a first state placing the second port of the high gain antenna in communication with the third switch; the second switch communicates the first low-gain antenna with the third switch in a second state.

6. The communication device of claim 5, wherein the third switch is a double pole double throw switch, the third switch including both through-connection and cross-connection states,

when the third switch is in the through-connected state, connecting the second low-gain antenna with the fourth switch through the third switch, and connecting the second port of the high-gain antenna or the first low-gain antenna with the duplexer through the third switch;

when the third switch is in the cross-connect state, the second low-gain antenna is connected to the duplexer through the third switch, and the second port of the high-gain antenna or the first low-gain antenna is connected to the fourth switch through the third switch.

7. The communications apparatus of claim 6 wherein the fourth switch is a double pole double throw switch, the fourth switch comprising both through connection and cross connection states,

causing the second low-gain antenna, and the second port of the high-gain antenna or the first low-gain antenna, to establish a connection with the first and second X-band receive channels simultaneously when the third switch is in the through-connected state and the fourth switch is in the through-connected state or when the third switch is in the through-connected state and the fourth switch is in the cross-connected state; and a second port of the high-gain antenna or the first low-gain antenna establishes a connection with the X-band transmit channel;

causing the second low-gain antenna, and the second port of the high-gain antenna or the first low-gain antenna, to establish a connection with the first and second X-band receive channels simultaneously when the third switch is in the cross-connect state and the fourth switch is in the through-connect state, or when the third switch is in the cross-connect state and the fourth switch is in the cross-connect state; and the second low-gain antenna establishes a connection with the X-band transmit channel.

8. The communication device of claim 1, wherein the first deep space transponder and the second deep space transponder each include a digital signal processing component configured to: including designating the first or second Ka-band downlink, X-band uplink, X-band downlink to use a high speed mode or a low speed mode for signaling.

9. The communications apparatus of claim 8, wherein the communications apparatus uses different modes for uplink and downlink signaling during different task phases,

when the task stage is any one of emergency situations of an LEOP stage, an orbital transfer cruise stage and a scientific operation stage, uplink signal transmission uses the X-waveband uplink to perform high-speed or low-speed remote control and ranging, and downlink signal transmission uses the X-waveband downlink to perform low-speed remote control and ranging;

when the task stage is a scientific operation stage, uplink signal transmission uses the X-band uplink to carry out high-speed remote control and ranging, and downlink signal transmission uses the Ka-band downlink to carry out low-speed remote control and ranging; or the uplink signal transmission uses the X wave band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the Ka wave band downlink to carry out high-speed data transmission;

and when the task stage is a scientific operation stage and the Ka-band downlink fails, the uplink signal transmission uses the X-band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the X-band downlink to carry out high-speed data transmission.

10. A measurement and control communication method for a deep space exploration spacecraft, wherein the spacecraft uses a + Z surface pointing to the earth and a-Z surface not pointing to the earth, and the method comprises the following steps:

configuring a connection state of a first switch, so that a first port of a high-gain antenna can be selectively connected with a first Ka-band downlink or a second Ka-band downlink to perform high-speed Ka-band downlink transmission, wherein the high-gain antenna is arranged on the + Z plane and is connected with the first switch through the first port;

configuring a connection state of a second switch to enable a second port of the high-gain antenna to be connected with an X-band transmitting channel and optionally to be connected with a first X-band receiving channel or a second X-band receiving channel, wherein the high-gain antenna is connected with the second switch through the second port;

configuring a connection state of the second switch to enable a first low-gain antenna to establish a connection with the X-band transmitting channel and optionally with the first X-band receiving channel or the second X-band receiving channel, wherein the first low-gain antenna is disposed on the + Z plane and the first low-gain antenna is connected with the second switch;

configuring a connection state of a third switch such that a second low-gain antenna is connected to the X-band transmit channel and optionally to the first X-band receive channel or the second X-band receive channel, wherein the second low-gain antenna is disposed at the-Z plane and the second low-gain antenna is connected to the third switch;

the first Ka-band transmitting channel, the X-band transmitting channel and the first X-band receiving channel are arranged in a first deep space transponder, and the second Ka-band transmitting channel and the second X-band receiving channel are arranged in a second deep space transponder.

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