CN115314066B

CN115314066B - Measurement and control communication device and method for deep space exploration spacecraft

Info

Publication number: CN115314066B
Application number: CN202210872502.8A
Authority: CN
Inventors: 黄江江; 张月婷; 张阔翔
Original assignee: Shanghai Engineering Center for Microsatellites; Innovation Academy for Microsatellites of CAS
Current assignee: Shanghai Engineering Center for Microsatellites; Innovation Academy for Microsatellites of CAS
Priority date: 2022-07-20
Filing date: 2022-07-20
Publication date: 2023-10-27
Anticipated expiration: 2042-07-20
Also published as: CN115314066A

Abstract

The invention relates to a measurement and control communication device and a method for 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 the measurement and control communication device comprises: 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, and the second deep space transponder comprises a Ka wave band transmitting channel and an X wave band receiving channel; a pair of high gain antennas with two ports are respectively connected with the first switch and the second switch; one of the two pairs of low gain antennas is connected with the second switch, and the other pair is connected with the third switch. The invention realizes redundancy of uplink and downlink channels and ensures the reliability of a communication system; by configuring the connection state of the first switch, the downlink transmission of Ka-band high-speed scientific data can be realized; by configuring the connection states of the second switch, the third switch and the fourth switch, the uplink or downlink measurement and control data transmission of the X-band 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 of a deep space exploration spacecraft.

Background

In a deep space exploration task for observing and researching planets such as asteroid, golden star, mars and the like, 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 (Deep Space Network, DSN) on the earth: (1) transmitting scientific data and engineering telemetry data downstream; (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; (3) providing radio frequency signals to the navigation and measurement tracks.

Measurement and control communication systems for deep space exploration tasks are generally composed of the following components: a deep space transponder (Deep Space Transponder, DST); high-power amplifiers (HPAs), including Traveling wave tube amplifiers (Traveling-wave Tube Amplifier, TWTA) or solid state power amplifiers (Solid State Power Amplifier, SSPA); a 3dB bridge; a diplexer; coaxial or waveguide switches; low Gain Antenna (LGA); a medium gain antenna (Medium Gain Antenna, MGA); high gain antennas (High gain antenna, HGA). Different numbers of the components and connection relations thereof form different measurement and control communication system schemes.

Most measurement and control communication systems provide near-omnidirectional beam coverage through two pairs of low-gain wide-beam antennas installed back to back, and high-gain antennas are usually essential items of a spacecraft and are used for high-speed downlink of scientific data.

For a part of deep space exploration spacecraft, the design of a measurement and control communication system is mainly driven by the requirement of high-speed downloading of a large amount of scientific data. Most of the existing deep space measurement and control communication systems have the highest downlink data rate of only hundreds Kbps or even lower, for example, marCO is a spacecraft in a cube star form, no redundant channel exists, and the downlink data rate is only 8Kbps. Some current spacecraft equipped HGAs are only for the downlink and cannot provide high speed uplink in the long range phase. Some typical deep space exploration mission spacecraft have a large number of components, for example, the spacecraft Europa clip contains four transmitting channels (including traveling wave tube amplifiers), seven pairs of antennas, and a relatively complex radio frequency network, so that the system redundancy and complexity are high, and the system is not suitable for a low-cost small spacecraft.

Disclosure of Invention

The application aims to solve the technical problem of providing a measurement and control communication device and method for a deep space exploration spacecraft, which can realize redundant Ka-band downlink and X-band uplink by configuring the connection states of different switches on the premise of minimizing the number of components of a system part, thereby ensuring the reliability of communication between the measurement and control communication device for the deep space exploration spacecraft and a ground station.

The technical scheme adopted by the application for solving the technical problems is that the measurement and control communication device of a deep space exploration spacecraft is provided with a +Z plane pointing to the earth and a-Z plane not pointing to the earth, and comprises the following components: the first deep space transponder comprises a first Ka wave band transmitting channel, an X wave band transmitting channel and a first X wave band receiving channel; the second deep space transponder comprises a second Ka wave band transmitting channel and a second X wave band receiving channel; the high-gain antenna is arranged on the +Z plane, the high-gain antenna comprises a first port and a second port, the high-gain antenna is connected with the first switch through the first port, the connection state of the first switch is configured to selectively establish connection with a first Ka band downlink or a second Ka band downlink for Ka band downlink transmission, the high-gain antenna is connected with the second switch through the second port, the connection state of the second switch is configured to establish connection with an X band transmitting channel, and the connection state of the high-gain antenna is configured to selectively establish 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 plane, is connected with the second switch, establishes connection with the X-band transmitting channel by configuring the connection state of the second switch, and optionally establishes connection with the first X-band receiving channel or the second X-band receiving channel; and the second low-gain antenna is arranged on the-Z surface, is connected with the third switch, establishes connection with the X-band transmitting channel by configuring the connection state of the third switch, and optionally establishes connection with the first X-band receiving channel or the second X-band receiving 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, the bridge includes a first input terminal, a second input terminal, a first output terminal, and a second output terminal, the first Ka-band transmission channel is connected to the first input terminal, the second Ka-band transmission channel is connected to the second input terminal, the first output terminal is connected to the first Ka-band traveling wave tube amplifier, the second output terminal 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 connection state of the first switch is configured to enable the first port of the high-gain antenna to be selectively connected to the first Ka-band traveling wave tube amplifier or the second Ka-band traveling wave tube amplifier.

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 between 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-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, the connection states of the second switch, the third switch and the fourth switch are configured to enable the second low-gain antenna and the second port or the first low-gain antenna of the high-gain antenna to be simultaneously connected with the first X-band receiving channel and the second X-band receiving channel; 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 one 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 communicates the first port of the high gain antenna 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 transmission channel or the second Ka band transmission channel is transmitted to the first port of the high gain antenna through the first Ka band downlink; 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 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.

In one embodiment of the application, the second switch is a single pole double throw switch, the second switch having two connected states, the second switch in the 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.

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 through connection and 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 diplexer 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.

In one embodiment of the present application, the fourth switch is a double pole double throw switch, the fourth switch comprising two connection states, a through connection and a cross connection,

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 X-band receive channel and the second X-band receive channel simultaneously 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; and the second port of the high-gain antenna or the first low-gain antenna is connected with the X-band transmitting 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 X-band receive channel and the second X-band receive channel 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.

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

In an embodiment of the present application, the communication device uses different modes for uplink and downlink signal transmission in different task phases, and when the task phase is any one of emergency situations of a loop phase, an orbit cruising phase and a scientific operation phase, the uplink signal transmission uses an X-band uplink to perform high-speed or low-speed remote control and ranging, and the downlink signal transmission uses an X-band downlink to perform low-speed telemetry 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 measurement and ranging; or the uplink signal transmission uses an X-band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses a Ka-band downlink to carry out high-speed data transmission; when the task phase is a scientific operation phase and the downlink of the Ka wave band fails, the uplink signal transmission uses the uplink of the X wave band to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the downlink of the X wave band to carry out high-speed data transmission.

The application also provides a measurement and control communication method for the deep space exploration spacecraft, which aims to solve the technical problems, and the spacecraft uses a positive Z surface pointing to the earth and a negative Z surface not pointing to the earth, and comprises the following steps: configuring a 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 so as to perform Ka-band high-speed downlink transmission, wherein the high-gain antenna is arranged on a +Z plane, and the high-gain antenna is connected with the first switch through the first port; configuring a connection state of the second switch, so that a second port of the high-gain antenna is connected with the X-band transmitting channel, and optionally, the first X-band receiving channel or the 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 a second switch to enable a first low-gain antenna to be connected with an X-band transmitting channel and optionally connected with a first X-band receiving channel or a second X-band receiving channel, wherein the first low-gain antenna is arranged on a +Z plane, and the first low-gain antenna 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 an X-band transmitting channel and optionally a first X-band receiving channel or a second X-band receiving channel, wherein the second low-gain antenna is arranged on a-Z plane, and the second low-gain antenna is connected with the third switch; the first Ka wave band transmitting channel, the X wave band transmitting channel and the first X wave band receiving channel are arranged in the first deep space transponder, and the second Ka wave band transmitting channel and the second X wave band receiving channel are arranged in the second deep space transponder.

In the technical scheme of the application, 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 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 are connected with the first switch, and high-speed data downlink transmission of a 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 low-gain antennas is connected with the third switch, and by configuring the connection states of the second switch and the third switch, the uplink data transmission of the X-band uplink and the downlink data transmission of the X-band downlink can be realized, and the spacecraft can normally carry out measurement and control communication in all task stages under any posture.

The measurement and control communication device of the deep space exploration spacecraft has fewer components and can reduce the cost. The application realizes the redundancy design of the uplink and the downlink to ensure the reliability of the communication system. The application can realize the link comprising two Ka wave band downlinks, two X wave band uplinks which can work simultaneously and one X wave band downlink by configuring the connection states of the first switch, the second switch, the third switch and the fourth switch, thereby not only realizing the measurement and control communication of all task stages under any posture of the spacecraft, but also realizing the high-speed downlink transmission of a large amount of scientific data. 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, star and Mars exploration tasks, and has the significance of expanding application.

Drawings

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

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

FIG. 2 is a schematic diagram of another exemplary overall structure of a measurement and control communication device for a deep space exploration spacecraft in accordance with an embodiment of the application;

FIG. 3 is an exemplary schematic diagram of the distance and visible duration of a deep space exploration spacecraft from a ground station in accordance with an embodiment of the application;

FIG. 4 is an exemplary schematic diagram of data storage capacity versus mission duration and ground station distance for a deep space exploration spacecraft in accordance with an embodiment of the application.

Detailed Description

In order to make the above objects, features and advantages of the present application more comprehensible, embodiments accompanied with figures 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 as described herein, and therefore the present application is not limited to the specific embodiments disclosed below.

As used in the specification and in the claims, the terms "a," "an," "the," and/or "the" are not specific to a singular, but may include a plurality, unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that the steps and elements are explicitly identified, and they do not constitute an exclusive list, as other steps or elements may be included in a method or apparatus.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

In the description of the present application, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present application and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present application. Furthermore, although terms used in the present application are selected from publicly known and commonly used terms, some terms mentioned in the present specification 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. Furthermore, it is required that the present application is understood, not simply by the actual terms used but by the meaning of each term lying within.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (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 deep space asteroid, star, mars and the like.

The number of components for some typical deep space exploration tasks is shown in table 1, with the exception of MarCO, all measurement and control communication systems provide near omni-directional beam coverage by two pairs of low gain wide beam antennas mounted back-to-back. High gain antennas are generally necessary 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 downstream rates, as shown in table 2.

For a part of deep space exploration spacecraft, the design of a measurement and control communication system is mainly driven by the requirement of high-speed downloading of a large amount of scientific data. Most existing deep space measurement and control communication systems have a maximum downlink data rate of only a few hundred kbps, as shown in table 2. JWST is located at the L2 point of the earth lagrangian, much closer to the earth than other deep space exploration tasks. HGAs are used only for the downlink and cannot provide high speed uplink in the long range phase. The Europa clip contains four transmitting channels (comprising traveling wave tube amplifiers), seven antennae and a relatively complex radio frequency network, and the system has high redundancy and complexity and is not suitable for a low-cost small spacecraft.

TABLE 1 typical spacecraft measurement and control communication System composition

	Deep space transponder	Power amplifier	Bridge	Duplexer	Switch	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
								The application is that	2	3	1	1	4	2	0

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

Table 2 frequency allocation and maximum downlink data rate for some typical tasks

Dawn

MarCO

Cassini

Juno

JWST

Europa

Maximum downlink rate/bps

128K

8K

256K

200K

28M ^a

1M

Frequency band

X

S/Ka

X/Ka

a: JWST is located at the second lagrangian point closer to the earth than other tasks.

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

And (one) frequency design of different links.

Many deep space exploration vehicles carry some payloads with large amounts of data, 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 downstream bandwidth allocated to deep space vehicles is only 50MHz (8400-8450 MHz), and the 50MHz bandwidth is shared by more and more deep space vehicles transmitted by various organizations. To reduce frequency congestion, authorities have objectively provided an X-band bandwidth exceeding 10MHz for one spacecraft. The Ka-band deep space spacecraft allocates a much wider downstream bandwidth than the X-band, up to 500MHz (31.8-32.3 GHz).

For high rate downlink, high gain transmit antennas are employed on spacecraft, and reception by ground stationsThe power (receiving antenna outlet) is P _r ：

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

In the formula (1), P _t For transmitting power on the satellite, G _t Gain, L, of transmitting antenna on spacecraft _s For free space attenuation, L _a For all other attenuation, including atmospheric and cloud attenuation, G _r Gain for terrestrial receive antennas. Antenna gain G (while applying G _t And G _r ) And L _s It 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 frequency of the radio frequency signal, and r is the distance from the spacecraft to the ground station.

Assume that: using Ka band frequency f _Ka =31.9ghz, x band frequency f _X =8425 MHz, using a madrid station. Then L is _a (Ka) < 4dB, the system availability is 99%. Subtracting equation (3) from equation (1), i.e., according to equations (1) - (3), yields:

that is, when η, D and P _t For the same two bands, equation (4) may represent the power difference between the Ka band and the X band, i.e., the link gain of the Ka band is 7.6dB greater than the X band. Even L _a (Ka) increases significantly in cloudiness and rain, and this problem can also be solved by using a link budget design technique based on weather forecast.

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

Based on the analysis, 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 selects Ka wave band. This conclusion is also confirmed by the frequency allocation and maximum downlink data rate of some typical deep space probe tasks in table 2.

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

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

In order to ensure that the uplink and downlink measurement and control links of the spacecraft can work normally under any posture (including the condition of out-of-control posture), two pairs of wide beam receiving and transmitting common antennas LGA which are arranged back to back are adopted to provide omnidirectional beam coverage. The HGA is used for high-speed downlink transmission of a large amount 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, as these two channels are the most common channels throughout the life of the spacecraft. For channels that are only used in a small number of stages, there is no need to provide redundant backups, thereby saving costs and reducing the complexity of the communication system. The X-band uplink is the most important link and should be able to function properly even in the case of out of attitude and unknown, so two deep space transponders should be able to connect to two pairs of LGAs simultaneously without the need for switching. Since the wide-beam X-band downlink is already equipped and applicable to phases of attitude wide range maneuver and even complete runaway, the transmit channels of the two Ka-bands provide high speed downlink through the HGA only when attitude is controlled. The X-band transceiver channel is not only connected to the LGA but also to the HGA to provide a high speed uplink and downlink, such as for injecting big data for repairing or updating software on the spacecraft.

Based on the design principle, the application realizes that 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 describes the specific components of the measurement and control communication device of the deep space exploration spacecraft:

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

Referring to fig. 1, in a measurement and control communication device of a deep space exploration spacecraft of this embodiment, the spacecraft has a +z plane directed to the earth and a-Z plane not directed 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 transmit channel 821 and a second X band receive channel 823; a high gain antenna 100 disposed on 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 the first switch 401 through the first port 101, the high gain antenna 100 being connected to the second switch 402 through the second port 102 by configuring a connection state of the first switch 401 to selectively establish a connection with a first Ka-band downlink or a second Ka-band downlink for Ka-band downlink transmission, the high gain antenna 100 being connected to the X-band transmission channel 812 by configuring a connection state of the second switch 402, and to selectively establish 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 on the +z plane, the first low-gain antenna 200 being connected to the second switch 402, the connection being established with the X-band transmission channel 812 by configuring the connection state of the second switch 402, and optionally with the first X-band reception channel 813 or the second X-band reception channel 823; the second low-gain antenna 300 is disposed on the-Z plane, the second low-gain antenna 300 is connected to the third switch 403, and a connection is established 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 by configuring the 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 transmission path 811 or the second Ka-band transmission path 821 transmits data downstream through the first port 101 of the high-gain antenna 100 to the ground station; when the first switch 401 communicates the first port 101 of the high gain antenna 100 with the second Ka band downlink, the first Ka band transmission path 811 or the second Ka band transmission path 821 transmits data downstream through the first port 101 of the high gain antenna 100 to the ground station. The transmission paths 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 can only communicate with either the first Ka band downlink or the second Ka band downlink at the same time.

When the second switch 402 communicates the second port 102 of the high-gain antenna 100 with the X-band transmit channel 812, the X-band transmit 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 communicates 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 to the first deep space transponder 801 through the first X-band receiving channel 813; when the second switch 402 communicates the second port 102 of the high-gain antenna 100 with the second X-band reception channel 823, the second port 102 of the high-gain antenna 100 transmits data upstream to the second deep space transponder 802 through the second X-band reception channel 823.

The second port 102 of the high gain antenna 100 may communicate simultaneously with the X-band transmit channel 812, the first X-band receive channel 813, or the second X-band receive channel 823. Illustratively, the second port 102 of the high-gain antenna 100 is in simultaneous communication with the X-band transmit channel 812 and the first X-band receive channel 813, i.e., the second port 102 of the high-gain antenna 100 can simultaneously transmit and receive data 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 through the first low gain antenna 200 to the ground station; when the second switch 402 communicates the first low-gain antenna 200 with the first X-band receiving channel 813, the first low-gain antenna 200 transmits data to the first deep space transponder 801 via the first X-band receiving channel 813; when the second switch 402 communicates the first low-gain antenna 200 with the second X-band receive channel 823, the first low-gain antenna 200 transmits data upstream to the second deep space transponder 802 through the second X-band receive channel 823.

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

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

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

In the technical scheme of the application, the first deep space transponder 801 comprises a Ka wave band transmitting channel, an X wave band transmitting channel 812 and an X wave band receiving channel, the second deep space transponder 802 comprises a Ka wave band transmitting channel and an X wave band receiving channel, and the two deep space transponders realize redundancy of an uplink channel and a downlink channel and ensure the reliability of a communication system; a pair of high-gain antennas 100 with two ports are connected with the first switch 401, and by configuring the connection state of the first switch 401, the high-speed data downlink transmission of the 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 of low-gain antennas is connected with the third switch 403, and by configuring the connection states of the second switch 402 and the third switch 403, the uplink data transmission of the X-band uplink and the downlink data transmission of the X-band downlink 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 communication apparatus further includes a first Ka-band traveling-wave tube amplifier 501, a second Ka-band traveling-wave tube amplifier 502, and a bridge 600, where the bridge 600 includes a first input 601, a second input 602, a first output 603, and a second output 604, the first Ka-band transmission channel 811 is connected to the first input 601, the second Ka-band transmission 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, and 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 optionally 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 comprises a 3dB bridge 600, which is configured such that the Ka-band transmit channel of either of the two deep space transponders may drive either 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 transmission channel 821 may drive the first Ka-band traveling-wave tube amplifier 501 or the second Ka-band traveling-wave tube amplifier 502.

The 3dB bridge 600 may implement a cross-connect between the Ka-band transmit channels of two deep space transponders and two Ka-band traveling wave tube amplifiers without the need for switching operations. The switching of the connection state of the first switch 401 connects the first port 101 of the high gain antenna 100 with 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 switches connection to the second Ka-band traveling wave tube amplifier 502. The application does not limit the Ka-band traveling wave tube amplifier connected by default to the first switch 401. The arrangement realizes redundancy of the Ka-band traveling wave tube amplifier, ensures reliability and stability in the downlink transmission process of data through the Ka-band downlink, and avoids failure of data transmission caused by failure of one Ka-band traveling wave tube amplifier.

In some embodiments, referring to fig. 1, the communication apparatus 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 has 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 terminal 405, a second input terminal 406, a first output terminal 407, and a second output terminal 408, the first X-band receiving channel 813 is connected to the first output terminal 407 of the fourth switch 404, the second X-band receiving channel 823 is connected to the second output terminal 408 of the fourth switch 404, the duplexer 700 is connected to the first input terminal 405 of the fourth switch 404, the third switch 403 is connected to the second input terminal 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 receiving channel 813 and the second X-band receiving 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 device 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 over the links between the second port 102, the second switch 402, and the third switch 403 of the high gain antenna 100; when the second switch 402 communicates the first low gain antenna 200 with the third switch 403, data may be transmitted over the links between the first low gain antenna 200, the second switch 402, and the third switch 403.

The second switch 402 can only communicate with the second port 102 of the high gain antenna 100 or the first low gain antenna 200 at the same time.

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

The third switch 403 can 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 most 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 transmit 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 communicates the second port 102 of the high-gain antenna 100 with the first X-band receiving channel 813, data of the ground station is uplink-transmitted to the first deep space transponder 801 through links among the second port 102 of the high-gain antenna 100, the fourth switch 404, and the first X-band receiving channel 813; when the fourth switch 404 communicates the first low-gain antenna 200 with the first X-band receiving channel 813, data of the ground station is uplink-transmitted to the first deep space transponder 801 through links among the first low-gain antenna 200, the fourth switch 404, and the first X-band receiving channel 813; when the fourth switch 404 communicates the second low gain antenna 300 with the first X-band reception channel 813, data of the ground station is uplink-transmitted to the first deep space transponder 801 through links between the second low gain antenna 300, the fourth switch 404, and the first X-band reception channel 813.

The first X-band reception 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 the same time.

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

The second X-band reception 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 the same time.

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

Illustratively, referring to fig. 1, by configuring the connection states of the second switch 402, the third switch 403, and the fourth switch 404, the second ports 102 of the second low-gain antenna 300 and the high-gain antenna 100 may be simultaneously connected with the first X-band receiving channel 813 and the second X-band receiving channel 823, and any one of the second ports 102 of the high-gain antenna 100, the first low-gain antenna 200, and the second low-gain antenna 300 may be connected with the X-band transmitting 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 channel 811 and the second X-band reception channel 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 channel 812. By the arrangement, when the measurement and control communication device of the deep space exploration spacecraft works, the device comprises two X-band uplinks and one X-band downlink which can work simultaneously at the same time, and data transmission and reception are carried out simultaneously.

The measurement and control communication device of the deep space exploration spacecraft can realize the downlink of two Ka wave bands, the uplink of two X wave bands and the downlink of one X wave band which can work simultaneously 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: 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 first Ka-band traveling wave tube amplifier 501; alternatively, the signal transmitted by the first Ka band transmission channel 811 or the second Ka band transmission 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 can operate simultaneously include: a communication link between the second port 102 of the high-gain antenna 100 and the first X-band reception channel 813, and a communication link between the second low-gain antenna 300 and the second X-band reception channel 823; or, a communication link between the first low-gain antenna 200 and the first X-band reception channel 813, and a communication link between the second low-gain antenna 300 and the second X-band reception channel 823.

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

It should be noted that the above-mentioned communication links between the components are only examples, and do not represent that the measurement and control communication device of the deep space exploration spacecraft of the 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 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 so as to ensure the reliability of communication.

FIG. 2 is a schematic diagram of another exemplary overall structure of a measurement and control communication device for a deep space exploration spacecraft in accordance with an embodiment of the 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 communicates the first port 101 of the high gain antenna 100 with 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 transmission channel 811 or the second Ka band transmission 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 communicates the first port 101 of the high-gain antenna 100 with the second Ka-band traveling wave tube amplifier 502 in the second state, and a Ka-band downlink signal transmitted by the first Ka-band transmission channel 811 or the second Ka-band transmission channel 821 is transmitted to the first port 101 of the high-gain antenna 100 through the second Ka-band downlink.

As an example, as shown in fig. 1 and fig. 2, the paths of the downlink signals transmitted by the deep space transponder to the ground station in the downlink of the first Ka band are in turn: a first Ka-band transmission channel 811 or a second Ka-band transmission 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 transmission paths of the downlink signals transmitted to the ground station by the deep space answering machine in the downlink of the second Ka band are as follows: a first Ka-band transmission channel 811 or a second Ka-band transmission channel 821, a bridge 600, a second Ka-band traveling wave tube amplifier 502, a first switch 401, and a first port 101 of a high-gain antenna 100.

The Ka-band transmitting channel is one of the most commonly used channels in the whole life of the spacecraft, and by configuring the connection state of the first switch 401, two Ka-band downlinks can be realized, namely, redundancy of the Ka-band downlinks is realized, when one of the Ka-band downlinks fails, the other Ka-band downlinks can be used, and reliability of downlink transmission of spacecraft data is ensured. When the posture 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 in a high-speed downlink manner 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 connected 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 communicates the first low gain antenna 200 with the third switch 403 in the second state.

The second switch 402 is illustratively configured as a single pole double throw switch that can be switched between two connected states, and in practice, the second switch 402 communicates the second port 102 of the high gain antenna 100 with the third switch 403 or 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, namely a through connection and a cross connection, when the third switch 403 is in the through connection state, the second low gain antenna 300 is connected to 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 to the duplexer 700 through the third switch 403; when the third switch 403 is in the cross-connect 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.

Illustratively, as shown in connection 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 with the fourth switch 404 and connects the second low gain antenna 300 with the duplexer 700 in the cross-connect state.

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

When the third switch 403 is in the cross-connect state, the second low-gain antenna 300 is connected to the duplexer 700 through the third switch 403, and the paths of data transmission between the second low-gain antenna 300 and the duplexer 700 are in order: a second low gain antenna 300, a third switch 403, and a diplexer 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 path of data transmission between the second port 102 of the high gain antenna 100 and the fourth switch 404 is in turn: a second port 102, a second switch 402, a third switch 403, and a fourth switch 404 of the high gain antenna 100; the path of data transmission between the first low gain antenna 200 and the fourth switch 404 is, in order: a first low gain antenna 200, a second switch 402, a third switch 403, and 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 two connection states, a through connection and a cross connection, 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 simultaneously connected with the first X-band receive channel 813 and the second X-band receive channel 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 transmit channel 812; causing the second low-gain antenna 300, and either the second port 102 of the high-gain antenna 100 or the first low-gain antenna 200, to establish a connection simultaneously with the first X-band reception channel 813 and the second X-band reception channel 823 when the third switch 403 is in the cross-connect state and the fourth switch 404 is in the through-connect state, or when the third switch 403 is in the cross-connect state and the fourth switch 404 is in the cross-connect state; and the second low gain antenna 300 establishes a connection with the X-band transmit 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 connection with fig. 1 and 2, the fourth switch 404 connects the diplexer 700 with the first X-band receive channel 813 and the third switch 403 with the second X-band receive channel 823 in the through-connected state; the fourth switch 404 connects the duplexer 700 with the second X-band reception channel 823 and connects the third switch 403 with the first X-band reception channel 813 in the cross-connection 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 that can be operated simultaneously can be realized.

Next, 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 the present application will be described in detail.

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

As an example, as shown in connection with fig. 1 and 2, the paths of the downlink signal transmitted by the first deep space transponder 801 to the ground station in the first X-band downlink are in turn: 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 transmission paths of the downlink signals transmitted by the first deep space transponder 801 to the ground station in the downlink of the second X-band are in turn: 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 transmission paths of the downlink signals transmitted by the first deep space transponder 801 to the ground station in the third X-band downlink are in turn: 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 up to two deep space transponders, including the following twelve uplink transmission paths.

As shown in conjunction with fig. 1 and 2, the paths of the uplink signals transmitted by the ground station to the first deep space transponder 801 in the first X-band uplink are in turn: the second port 102, the second switch 402, the third switch 403, the diplexer 700, the fourth switch 404, the first X-band receive channel 813 of the high gain antenna 100.

The paths of the uplink signals transmitted by the ground station to the second deep space transponder 802 in the second X-band uplink are in turn: the second port 102, the second switch 402, the third switch 403, the diplexer 700, the fourth switch 404, the second X-band receive channel 823 of the high gain antenna 100.

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

The paths of the uplink signals transmitted by the ground station to the second deep space transponder 802 in the fourth X-band uplink are in turn: a second port 102, a second switch 402, a third switch 403, a fourth switch 404, and a second X-band receive channel 823 of the high-gain antenna 100.

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

The uplink signals transmitted by the ground station to the second deep space transponder 802 are transmitted in the sixth X-band uplink in the following sequence: a first low gain antenna 200, a second switch 402, a third switch 403, a diplexer 700, a fourth switch 404, a second X-band receive channel 823.

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

The uplink signals transmitted by the ground station to the second deep space transponder 802 are transmitted in the eighth X-band uplink in the following order: a first low gain antenna 200, a second switch 402, a third switch 403, a fourth switch 404, and a second X-band receive channel 823.

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

The uplink signals transmitted by the ground station to the second deep space transponder 802 are transmitted in the tenth X band uplink in the following order: a second low gain antenna 300, a third switch 403, a diplexer 700, a fourth switch 404, a second X-band receive channel 823.

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

The uplink signals transmitted by the ground station to the second deep space transponder 802 are transmitted in the twelfth X-band uplink in the following sequence: 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 the spacecraft software by an uplink software patch and the like, and can be injected to the spacecraft on any one of the X-band uplink links, so that the low-rate X-band uplink can work normally even if the posture of the spacecraft is abnormal. The X-band receiving channel is one of the most commonly used channels in the whole life of the spacecraft, and by configuring the connection states of the second switch 402, the third switch 403 and the fourth switch 404, two X-band uplinks working simultaneously can be realized, 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, uplink data of the ground station can still be transmitted in two X-band uplinks which can work simultaneously, so that the communication efficiency and reliability of the ground station and the spacecraft are improved.

Illustratively, as shown with reference to fig. 1 and 2, two simultaneously operating X-band uplinks may be as described above: a fifth X-band uplink (the data transmission paths are in turn: the first low-gain antenna 200, the second switch 402, the third switch 403, the duplexer 700, the fourth switch 404, the first X-band reception channel 813) and a twelfth X-band uplink (the data transmission paths are in turn: the second low-gain antenna 300, the third switch 403, the fourth switch 404, the second X-band reception channel 823); the two simultaneous X-band uplinks may also be as described above: the first X-band uplink (the data transmission path is in turn 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) and the twelfth X-band uplink (the data transmission path is in turn the second low gain antenna 300, the third switch 403, the fourth switch 404, the second X-band reception channel 823). The two X-band uplinks operating simultaneously may be selected according to practical circumstances, and the present application is not limited.

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

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

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

Referring to fig. 1, a first digital signal processing component 814 and a second digital signal processing component 824 are used to designate signals for transmission in the various links described above using either a high speed mode or a low speed mode. Preferably, the first digital signal processing component 814 and the second digital signal processing component 824 designate the first Ka band downlink or the 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 that the first Ka band downlink or the second Ka band downlink use a low speed mode for signal transmission, which is not limiting of the present application.

The digital signal processing component sets each uplink, downlink to use either 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, measurement and control communication of the spacecraft in all task stages can be realized, and data can be stably transmitted from the spacecraft to the ground station or stably transmitted from the ground station to the spacecraft in a descending manner no matter whether the operation posture of the spacecraft is normal or abnormal, so that the reliability of data transmission is ensured.

In some embodiments, the communication device uses different modes for uplink and downlink signal transmission in different task phases, and when the task phase is any one of an emergency situation of a loop (early orbit phase, launch and Early Orbit Phase) phase, an orbital cruising phase and a scientific operation phase, 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 measurement and ranging; or the uplink signal transmission uses an X-band uplink to carry out high-speed or low-speed remote control, and the downlink signal transmission uses a Ka-band downlink to carry out high-speed data transmission; when the task phase is a scientific operation phase and the downlink of the Ka wave band fails, the uplink signal transmission uses the uplink of the X wave band to carry out high-speed or low-speed remote control, and the downlink signal transmission uses the downlink of the X wave band to carry out high-speed data transmission.

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

The embodiment of the application also discloses a measurement and control communication method of the deep space exploration spacecraft, which is shown by referring to fig. 1, wherein the spacecraft is provided with a +Z plane pointing to the earth and a-Z plane not pointing to the earth, and comprises the following steps: configuring a connection state of the first switch 401, so that the first port 101 of the high-gain antenna 100 can be selectively connected with a first Ka-band downlink or a second Ka-band downlink to perform Ka-band high-speed downlink transmission, wherein the high-gain antenna 100 is arranged on the +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 is connected to the X-band transmit channel 812 and optionally to the first X-band receive channel 813 or the second X-band receive channel 823, wherein the high gain antenna 100 is connected to 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 channel 812 and optionally with the first X-band reception channel 813 or the second X-band reception channel 823, wherein the first low-gain antenna 200 is disposed on 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 channel 812 and optionally with the first X-band reception channel 813 or the second X-band reception channel 823, wherein the second low-gain antenna 300 is disposed on the-Z plane, and the second low-gain antenna 300 is connected with the third switch 403; wherein a first Ka band transmit channel 811, an X band transmit channel 812 and a first X band receive channel 813 are provided in the first deep space transponder 801 and a second Ka band transmit channel 821 and a second X band receive channel 823 are provided in the second deep space transponder 802.

In the measurement and control communication method of 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 repeated here.

As an example, in the measurement and control communication device of the deep space exploration spacecraft of the application, as shown in fig. 1 and 2, 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 of the X-band is shown in the following table 3.

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

In table 3:

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

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 fails, the first switch is switched to the second Ka-band traveling wave tube amplifier.

3) The uplink and downlink mode 1 of table 4 below requires that each switch of table 3 be in the connected state of sequence number 2 or 4 or 6 or 8; the up-down mode 2 or 3 of table 4 requires the connection state of each switch of table 3 to be in the number 1 or 3 or 5 or 7, and the up-down mode 4 of table 4 requires each switch of table 3 to be in the connection state of number 1 or 5.

According to the foregoing, referring to fig. 1 and 2, the measurement and control communication device of the deep space exploration spacecraft of the application comprises: 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 (Single Pole Double Throw, SPDT) switches (401, 402), two double pole double throw (Double Pole Double Throw, DPDT) switches (403, 404), two Ka band traveling wave tube amplifiers (501, 502), one X band traveling wave tube amplifier 503, one X band duplexer 700, one Ka band 3dB bridge 600, two deep space transponders (801, 802), nine waveguides and nine coaxial cables. Each deep space transponder comprises an X-band receive channel and a Ka-band transmit channel, and the first deep space transponder 801 further comprises an X-band transmit channel 812. The two deep space transponders (801, 802) can not only perform conventional measurement and control communication, but also realize a high-speed data downlink transmission function through a software radio (Software Defination Radio, SDR) technology.

As shown in table 1 described above, the measurement and control communication device of the present application contains a relatively minimum number of components compared to other spacecraft, particularly, JWST and Europa clip, which also have high speed downlink. The most costly component of the communication system is the deep space transponder and the high power amplifier, so the measurement and control communication device is the lowest cost.

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

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

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

3) Through the Ka wave band 3dB bridge, the Ka wave band transmitting channel of any deep space transponder can drive any 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 switching operation is not needed.

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 modes of 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 operation modes are shown in table 4. The X-band uplink operates throughout the life of the spacecraft. The X-band low speed telemetry downlink operates only in emergency situations such as attitude anomalies in the transmit and early orbit phases (Launch and Early Orbit Phase, LEOP), the orbital cruising phase and the scientific operating phase. For the task of a golden or Mars detector, the X-band low-speed telemetry downlink only needs to continuously work for about 6 months and is much shorter than the whole life cycle of a spacecraft (generally at least three years or more, such as more than ten years or even decades), and the X-band low-speed telemetry downlink does not influence the work of a communication system even if damaged, so that the application only configures one X-band transmitting channel and one X-band traveling wave tube amplifier. The Ka-band low-speed telemetry downlink and the X-band uplink realize the conventional telemetry and remote control functions together in the scientific task stage. High-speed data transmission is typically transmitted in the Ka band. The X-band may also provide a data transmission downlink with a data rate <4Mbps through a high gain antenna, as a backup when both ka-band downlinks are totally inactive.

Table 4 up/down mode

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

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

FIG. 3 is an exemplary schematic diagram of the distance and visible duration of a deep space exploration spacecraft from a ground station in accordance with an embodiment of the application; FIG. 4 is an exemplary schematic diagram of data storage capacity versus mission duration and ground station distance for a deep space exploration spacecraft in accordance with an embodiment of the application.

Illustratively, scientists are planning to launch a spacecraft for surrounding observations of the golden star. The basic information of the spacecraft is shown in table 5. On-board loading produces a large amount of scientific data at a speed of about 150 Gb/day. The range of the distance from the gold star to the earth is 4×107km to 2.6X108 km,3 the spacecraft to earth distance change over the year is shown in figure 3. The visibility of a spacecraft to a ground station is shown in fig. 3, assuming that both a ground station and a deep space station within a certain environment are available. The visible duration of each day is greater than 4 hours. Thus, 4 hours/day may be allocated for high-speed scientific data downloads.

TABLE 5 golden star detector basic information (example)

Weight (kg)	2250
		Carrying the articles	****
Time of emission	2026/06
		Cruise orbit time (Tian)	182.48

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

up/down frequency: 71 MHz/31 GHz, forwarding ratio: 749/3328;71 MHz/84 MHz, forwarding ratio: 749/880;

modulation mode: PCM-PSK-PM (remote control and low speed telemetry), BPSK/QPSK (high speed data transmission); wherein the PCM (Pulse Code Modulation ); PSK (Phase Shift Keying ); PM (Phase Modulation); BPSK (Binary Phase Shift Keying ); QPSK (quadrature phase shift keying), quadrature Phase Shift Keying).

Remote control rate: ranging from 7.8125bps to 2,000 bps, increasing by a factor of 2;

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

Low speed telemetry rate: ranging from 8bps to 8192bps, increasing by a factor of 2;

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

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

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

ka band transmit power: 220W;

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

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

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

Table 6 high speed downlink performance for a 35m station

Ground distance/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 volume/Gb	288	230	173	144	115	86	58	43	29	22	14	7

In emergency situations in the loop, cruise orbit phase and scientific operation phase, the X-band low gain antenna is used for low speed telemetry downlink. The link budget for a 75 ° beam coverage based on a certain DSN ground station (35 m) and ground station (66 m) is shown in table 7. When the far-site exceeds the coverage of + -75 DEG beam, 66m ground stations should be used, the data rate is only 8bps, and the calculated link margin is only 0.75dB. The remote uplink budget for a 75 ° beam coverage is shown in table 8. When the far-site exceeds + -75 DEG beam coverage, 66m ground stations 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 distance (low gain antenna @75 DEG beam)

Table 8X band remote uplink data rate and distance (Low gain antenna @75℃Beam)

And when the spacecraft is in a normal posture in the scientific operation stage, adopting a high-gain antenna to carry out X-band uplink remote control and Ka-band downlink remote measurement. Even at the far site, the link margin corresponding to the 35m station is very sufficient, 19.1dB@2000bps is up going, 19.7dB@8192bp is down going.

Based on the prior researches, the application applies the measurement and control communication device of the deep space exploration spacecraft 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 following components: a pair of high gain antennas (two ports, ka band and X band), two pairs of low gain antennas, two Single Pole Double Throw (SPDT) switches, two Double Pole Double Throw (DPDT) switches, two Ka band traveling wave tube amplifiers, an X band traveling wave tube amplifier, an X band duplexer, a Ka band 3dB bridge, two deep space transponders, nine waveguides and nine coaxial cables.

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

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

While the basic concepts have been described above, it will be apparent to those skilled in the art that the foregoing application disclosure is by way of example only and is not intended to be limiting. Although not explicitly described herein, various modifications, improvements and adaptations of the application may occur to one skilled in the art. Such modifications, improvements, and modifications are intended to be suggested within the present disclosure, and therefore, such modifications, improvements, and adaptations are intended to be within the spirit and scope of the exemplary embodiments of the present disclosure.

Some aspects of the application may be performed entirely by hardware, entirely by software (including firmware, resident software, micro-code, etc.) or by a combination of hardware and software. The above hardware or software may be referred to as a "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 application may take the form of a computer product, comprising computer-readable program code, embodied 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, tape … …), optical disk (e.g., compact disk CD, digital versatile disk DVD … …), smart card, and flash memory devices (e.g., card, stick, key drive … …).

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 on a variety of forms, including electro-magnetic, optical, etc., or any suitable combination thereof. A computer readable medium can be any computer readable medium that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code located on a computer readable medium may be propagated through any suitable medium, including radio, cable, fiber optic cable, radio frequency signals, or the like, or a combination of any of the foregoing.

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

In some embodiments, numbers describing the components, number of attributes are used, it being understood that such numbers being used in the description of embodiments are modified in some examples by the modifier "about," approximately, "or" substantially. Unless otherwise indicated, "about," "approximately," or "substantially" indicate that the number allows for a 20% variation. Accordingly, in some embodiments, numerical parameters set forth in the specification and claims are approximations that may vary depending upon the desired properties sought to be obtained by the individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and employ a method for preserving the general number of digits. Although the numerical ranges and parameters set forth herein are approximations in some embodiments for use in determining the breadth of the range, in particular embodiments, the numerical values set forth herein are as precisely as possible.

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

Claims

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

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

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

the high-gain antenna is arranged on the +Z face, comprises a first port and a second port, is connected with a first switch through the first port, establishes connection with a first Ka band downlink or a second Ka band downlink through configuration of a 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 an X band transmitting channel through configuration of a connection state of the second switch, and 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 plane, is connected with the second switch, establishes connection with the X-band transmitting channel by configuring the connection state of the second switch, and establishes connection with the first X-band receiving channel or the second X-band receiving channel;

The second low-gain antenna is arranged on the-Z surface, is connected with the third switch, establishes connection with the X-band transmitting channel by configuring the connection state of the third switch, and establishes connection with the first X-band receiving channel or the second X-band receiving channel.

2. The communication 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, the bridge comprising a first input, a second input, a first output, and a second output, the first Ka-band transmit channel being connected to the first input, the second Ka-band transmit channel being connected to the second input, the first output being connected to the first Ka-band traveling wave tube amplifier, the second output being 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 being disposed between the first switch and the bridge, the first port of the high gain antenna being 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.

3. The communication device of claim 1, further comprising a fourth switch, a diplexer, and an X-band traveling wave tube amplifier, the second switch being connected to the third switch, the second port of the high gain antenna or the first low gain antenna being 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 is provided with 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, 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 communication device of claim 3, wherein the first switch is a single pole double throw switch, the first switch having two connected states, the first switch in a first state placing a first port of the high gain antenna in communication 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 connected 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 comprising two connection states, a pass-through connection and a cross-connect,

when the third switch is in the through connection 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 diplexer 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 device of claim 6, wherein the fourth switch is a double pole double throw switch, the fourth switch comprising two connection states, a pass-through connection and a cross-connect,

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 the first X-band receive channel and the second X-band receive channel simultaneously 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; and a second port of the high gain antenna or the first low gain antenna is connected with the X wave band transmitting channel;

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 the first X-band receive channel and the second X-band receive channel 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 comprise a digital signal processing component configured to: including designating the first Ka-band downlink or the second Ka-band downlink, the X-band uplink, and the X-band downlink for signal transmission using a high-speed mode or a low-speed mode.

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

when the task stage is any one of emergency situations of a LEOP stage, an orbital cruising stage and a scientific operation stage, the uplink signal transmission uses the X-band uplink to carry out high-speed or low-speed remote control and ranging, and the downlink signal transmission uses the X-band downlink to carry out low-speed remote measurement and ranging;

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

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

10. A method of measurement and control communication for a deep space exploration spacecraft using a system having a +z plane pointing to the earth and a-Z plane not pointing to the earth, comprising:

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

Configuring a connection state of a second switch, so that a second port of the high-gain antenna is connected with an X-band transmitting channel and is 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, so that a first low-gain antenna is connected with the X-band transmitting channel and is connected with the first X-band receiving channel or the second X-band receiving channel, wherein the first low-gain antenna is arranged on the +Z plane, and the first low-gain antenna is connected with the second switch;

configuring a connection state of a third switch, so that a second low-gain antenna is connected with the X-band transmitting channel and is connected with the first X-band receiving channel or the second X-band receiving channel, wherein the second low-gain antenna is arranged on the-Z plane, and the second low-gain antenna is connected with the third switch;

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