CN211824087U - Missile-borne data chain system and missile provided with data chain system - Google Patents
Missile-borne data chain system and missile provided with data chain system Download PDFInfo
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- CN211824087U CN211824087U CN202020369991.1U CN202020369991U CN211824087U CN 211824087 U CN211824087 U CN 211824087U CN 202020369991 U CN202020369991 U CN 202020369991U CN 211824087 U CN211824087 U CN 211824087U
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Abstract
The utility model provides a missile-borne data chain system and missile provided with the same, belonging to the technical field of data chain, comprising a missile-borne terminal and a ground terminal, wherein the missile-borne terminal is connected with a missile body, and the missile-borne terminal is used for transmitting a target image acquired by a missile upper seeker and the working state information of a missile to the ground terminal in real time and receiving a remote control instruction from the ground terminal; and the missile-borne terminal is provided with a signal processing module for realizing a wireless same-frequency two-way transmission technology. The utility model provides a pair of missile-borne data chain system and install guided missile of data chain system has the advantage that interference killing feature is strong and dynamic behavior is high.
Description
Technical Field
The utility model belongs to the technical field of the data link, more specifically say, relate to a missile of missile-borne data chain system and installation data chain system.
Background
The missile-borne data link technology is an information technology. With the arrival of informatization war, the development and research of various countries and military parties on data chain technology are greatly stimulated. The system can realize information exchange among various platforms such as sea, land, air and the like, share situation perception, facilitate the cooperative operation of a command control system and a fire unit in each war zone, and obtain a first opportunity on a battlefield. Missile-borne data link technology has been paid high attention in various countries and has become a key technology for future missile development towards intellectualization, informatization and networking.
The existing missile-borne data link technology has the problems of low frequency spectrum utilization rate, poor anti-jamming capability and poor dynamic performance.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a missile-borne data chain system and install guided missile of data chain system aim at solving current missile-borne data chain technical spectrum low utilization, interference killing feature poor, and the relatively poor technical problem of dynamic behavior.
In order to achieve the above object, the utility model adopts the following technical scheme: there are provided a missile-borne data link system and a missile having the data link system installed therein, including:
the missile-borne terminal is connected with the missile body and is used for transmitting a target image acquired by the missile upper seeker and the working state information of the missile in real time and receiving a remote control command from the ground terminal; and the missile-borne terminal is provided with a signal processing module for realizing a wireless same-frequency two-way transmission technology.
As another embodiment of the present application, the missile-borne terminal further includes a missile-borne antenna designed in a common form of a missile body, and the missile-borne antenna is fixedly connected to the missile body and is configured to transmit a signal to the ground terminal or receive an instruction transmitted by the ground terminal.
As another embodiment of the present application, the signal processing module includes:
the main machine frame is positioned in the bomb body and is fixedly connected with the bomb body;
the image processing module is connected with the host frame and used for converting a target image into a data signal and transmitting the data signal;
the baseband module is connected with the host frame and used for receiving the data signals transmitted by the image processing module, and functional components for realizing a wireless same-frequency bidirectional transmission technology and an LDPC (low density parity check) error correction code technology are integrated on the baseband module;
and the power amplifier module is connected with the host frame and is used for amplifying or/and bidirectionally transmitting the data signal between the missile-borne antenna and the baseband module.
As another embodiment of the present application, the host frame includes a rectangular frame.
As another embodiment of the present application, the image processing module, the baseband module, and the power amplifier module are respectively disposed on any one side of the host frame.
As another embodiment of the present application, a radio frequency component is further separately disposed on the baseband module; and an independent cavity for accommodating the radio frequency assembly is arranged on the main machine frame.
As another embodiment of the application, the main frame is provided with a containing cavity for containing the power amplifier module independently.
As another embodiment of the present application, the missile-borne antenna includes:
the base is used for being connected and fixed with the projectile body;
the missile-borne antenna radiation sheet is used for receiving the signal transmitted by the signal processing module; and
and the missile-borne antenna housing is fixedly connected with the base and is used for connecting and protecting the missile-borne antenna radiating piece with the base.
As another embodiment of the present application, the curvature of the missile-borne radome shape is the same as the curvature of the missile body.
The utility model also provides an install guided missile of data link, its characterized in that: the missile provided with the data chain is applied with the missile-borne data chain system.
The utility model provides a pair of missile-borne data chain system and missile of installing data chain system's beneficial effect lies in: compared with the prior art, the utility model relates to a missile-borne data chain system and install guided missile of data chain system, signal processing module adopt same frequency two-way wireless transmission technique, can realize two-way communication through single frequency point, and frequency spectrum utilization is high. The signal processing module can also sense whether external interference exists in a certain frequency range, and automatically and preferably selects a frequency without interference or with less interference for transmission. The signal processing module has the capacity of resisting channel fading and multipath interference. The utility model discloses still have transmission distance far away, characteristics that the mobility is high.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic perspective view of a missile-borne data chain system according to an embodiment of the present invention installed in a missile body;
fig. 2 is a schematic side view of a missile-borne data chain system according to an embodiment of the present invention installed in a missile body;
fig. 3 is a schematic perspective view of a signal processing module in a missile-borne data chain system according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a three-dimensional structure of a signal processing module in a missile-borne data chain system according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a baseband module in a missile-borne data chain system according to an embodiment of the present invention;
fig. 6 is an exploded view of a missile-borne antenna structure in a missile-borne data chain system according to an embodiment of the present invention;
fig. 7 is a schematic view of an operation flow of a missile-borne terminal in a missile-borne data chain system according to an embodiment of the present invention;
fig. 8 is a schematic diagram of an antenna standing-wave ratio in a missile-borne data link system according to an embodiment of the present invention.
In the figure: 1. a missile-borne antenna; 11. a base; 12. a missile-borne antenna radiating patch; 13. a missile-borne radome; 14. a radio frequency connector; 2. a signal processing module; 21. a main machine frame; 211. an independent cavity; 22. an image processing module; 23. a baseband module; 231. a functional component; 232. a radio frequency component; 24. a power amplifier module; 3. and (3) a projectile body.
Detailed Description
In order to make the technical problem, technical solution and advantageous effects to be solved by the present invention more clearly understood, the following description is given in conjunction with the accompanying drawings and embodiments to illustrate the present invention in further detail. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1 to 8, a description will now be given of a data link system for missile-borne applications according to the present invention. The missile-borne data chain system comprises a missile-borne terminal, wherein the missile-borne terminal is connected with a missile body 3 and is used for transmitting a target image acquired by a missile upper seeker and the working state information of a missile in real time and receiving a remote control command from a ground terminal; and the missile-borne terminal is provided with a signal processing module 2 for realizing a wireless same-frequency two-way transmission technology.
The seeker acquires a target image and the working state information of the missile, transmits the target image and the working state information of the missile to the missile-borne terminal, and transmits a radio frequency signal to the ground terminal in a wireless mode after the target image and the working state information of the missile are processed by a signal processing module 2 on the missile-borne terminal; the ground terminal can also transmit the remote control command input by the user to the signal processing module 2.
The utility model provides a pair of missile-borne data chain system compares with prior art, and signal processing module 2 adopts same frequency two-way wireless transmission technique, can realize two-way communication through single frequency point, and frequency spectrum utilization is high. The signal processing module 2 can also sense whether there is external interference in a certain frequency range, and automatically prefers to transmit at a frequency with no interference or less interference. The signal processing module 2 has the capability of resisting channel fading and multipath interference. The utility model discloses still have transmission distance far away, characteristics that the mobility is high.
It should be noted that the velocity of the missile during the flight is about 200m/s, and the signal transmitted by the missile-borne terminal 1 received by the ground terminal will generate the doppler shift effect. The doppler difference due to the projectile velocity is (doppler difference, light velocity 3.0 × 1e8, flight velocity 200 m/s).
The frequency point of the data chain system is 580MHz, and the Doppler frequency difference is calculated according to the formula and is fd＝386Hz。
The data link communication system adopts a time division duplex technology, an orthogonal frequency division multiplexing technology and an orthogonal phase shift keying modulation mode, frequency points are 580MHz, subcarrier intervals are 15KHz, receiving and transmitting are distinguished by adopting different time slots in a time division mode in the time division duplex technology, the bandwidth set by an uplink (from a ground terminal to a missile-borne terminal 1) is 2MHz, and the bandwidth of a downlink (from the missile-borne terminal 1 to the ground terminal) is 4 MHz. An increase in the doppler difference of the signals received by the terrestrial terminal results in a deterioration of the received signal-to-noise ratio. According to the result of simulation calculation, the relationship between the Doppler shift/subcarrier spacing and the signal-to-noise ratio loss in the quadrature phase shift keying modulation mode is as follows: when the doppler shift/subcarrier spacing is 0.002, 0.05, 0.1, the signal-to-noise ratio loss (dB) is 0.1, 1, 3 in this order. I.e., the loss of signal-to-noise ratio is below 1dB when the doppler shift and subcarrier spacing are less than 0.05 and 3dB when the doppler shift/subcarrier spacing is equal to 0.1.
In a data chain system, when the speed of a projectile is 200m/s, the Doppler frequency shift is equal to 386Hz, the ratio between the Doppler frequency difference and the subcarrier spacing of 15KHz is 386/15000-0.025, and the signal-to-noise ratio is degraded by less than 1 dB.
As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 and fig. 6 together, the missile-borne terminal further includes a missile-borne antenna 1 designed in a common form of a missile body, and the missile-borne antenna 1 is fixedly connected to the missile body 3 for transmitting signals to the ground terminal or receiving instructions transmitted by the ground terminal.
Missile-borne antenna 1 is the front end of data chain system, and the quality of data chain system depends on the performance of missile-borne antenna 1, and projectile 3 also can become a part of antenna radiator under specific circumstances, the utility model provides a missile-borne antenna 1 adopts the conformal formula design of projectile, has not only increased position and the radiating area that projectile 3 can install the antenna, still reduces projectile 3 greatly because the pneumatic resistance that the antenna produced, and the normal gain of the standing wave of furthest optimization antenna and increase antenna in flight process.
As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to 5, wherein the signal processing module 2 includes a main frame 21, an image processing module 22, a baseband module 23, and a power amplifier module 24, the main frame 21 is located in the projectile body 3 and is connected and fixed with the projectile body 3; the image processing module 22 is connected to the host frame 21, and is configured to convert the target image into a data signal, and transmit the data signal to the power amplifier module 24 through the baseband module 23. The baseband module 23 is connected with the main frame 21, the baseband module 23 is electrically connected with the image processing module 22, and a functional component 231 for realizing the wireless same-frequency bidirectional transmission technology and the LDPC error correction code technology is integrated on the baseband module 23; the power amplifier module 24 is connected with the main frame 21 and is used for amplifying or/and bidirectionally transmitting the data signal between the missile-borne antenna 1 and the baseband module 23.
The seeker transmits image information to the image processing module 22 for processing, the image processing module 22 transmits signals to the baseband module 23, the signals are processed by the functional component 231 in the baseband module 23 and then transmitted to the power amplifier module 24, the power amplifier module 24 transmits the signals to the missile-borne antenna 1, and then the missile-borne antenna 1 sends out signals which can be received by a ground terminal. The main machine frame 21 is used for realizing the connection and fixation with the projectile body 3 and the fixation of the image processing module 22, the baseband 23 module and the power amplifier module 24.
It should be noted that the signal transmission process between the baseband module 23, the power amplifier module 24 and the missile-borne antenna 1 is bidirectional. One transmission process is as follows: the signal is transmitted to a power amplifier module 24 by a baseband module 23, then transmitted to a path of the missile-borne antenna 1 and then transmitted to a ground terminal; the other transmission process is as follows: the signal is transmitted to the power amplifier module 24 by the missile-borne antenna 1 and then transmitted to the path of the baseband module 23.
In the present embodiment, the main frame 21 includes a rectangular frame body, and the shape of the connecting position of the rectangular frame body and the projectile body 3 depends on the shape of the connecting position of the projectile body 3. The stability of the connection relation between the main frame 21 and the projectile body 3 is effectively improved, the structural stress distribution is improved, local stress is prevented, stress concentration is eliminated, the self high overload resistance of the connection structure of the main frame 21 and the projectile body 3 is improved, and the missile-borne data chain system is improved in the capacity (such as vibration resistance, impact resistance and the like) of adapting to the missile overload environment.
In this embodiment, the connection part of the projectile body 3 and the main frame 21 is added with a reinforcing rib structure. Correspondingly, the position where the main frame 21 is correspondingly connected with the reinforcing rib is set to be a plane structure, so that the main frame 21 is prevented from being damaged due to local stress.
In this embodiment, the image processing module 22, the baseband module 23, and the power amplifier module 24 are respectively disposed on any side of the main frame 21.
The image processing module 22, the baseband module 23, the power amplifier module 24 and the missile-borne antenna 1 are respectively corresponding to one side of the host frame 21, for example, the image processing module 22 is connected with the left side of the host frame 21, the baseband module 23 is connected with the upper side of the host frame 21, and the power amplifier module 24 is connected with the right side of the host frame 21. The structure has shielding effect and isolation effect, and reduces the influence generated among the image processing module 22, the baseband module 23, the power amplifier module 24 and the missile-borne antenna 1.
In the present embodiment, the modules of the signal processing module 2 are connected by vias or connectors.
In this embodiment, the board card structure and the module structure in the signal processing module 2 both adopt a surface contact mounting structure, so that damage to the board card structure and the module structure when stressed is avoided, and the structural firmness of the signal processing module 2 is improved.
As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to 5, the baseband module 23 is further provided with a radio frequency assembly 232; the main frame 21 is provided with a separate cavity 211 for receiving the rf assembly 232. An independent cavity 211 is designed on the radio frequency assembly 232 on the main machine frame 21, so that the influence of external equipment on the radio frequency assembly 232 is effectively isolated, and the interference of the radio frequency assembly 232 on other external equipment is weakened.
In this embodiment, the baseband module 23 and the power amplifier module 24 are respectively shielded. The system adopts module shielding, all components adopt module design, the module design can weaken mutual interference of the components per se, can prevent external equipment from electromagnetic interference to the components per se to a greater extent, and in the mutual connection between the modules, the aviation plug and radio frequency connector structure with good shielding effect is adopted, so that the shielding effect is improved.
As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to 5, a containing cavity for separately containing the power amplifier module 24 is disposed on the main frame 21. The power amplifier module 24 is one of the core parts in the host, an independent cavity structure is designed, the power amplifier module 24 is used as an independent module to effectively isolate the influence of external equipment on the power amplifier module, and the interference of the power amplifier module on other external equipment is weakened.
As a specific implementation manner of the embodiment of the present invention, please refer to fig. 6 and fig. 7, the missile-borne antenna 1 includes a base 11, a missile-borne antenna radiation sheet 12 and a missile-borne antenna housing 13, wherein the base 11 is used for being connected and fixed with the missile body 3; the missile-borne antenna radiation piece 12 is used for receiving signals transmitted by the signal processing module 2; the missile-borne antenna housing 13 is fixedly connected with the base 11 and used for being connected with the base 11 and protecting the missile-borne antenna radiation piece 12.
In this embodiment, a patch layer for controlling the wavelength is provided on the missile-borne antenna radiation patch 12.
In the present embodiment, the missile-borne antenna radiation piece 12 is electrically connected with the signal processing module 2 through the radio frequency connector 14.
In the present embodiment, the curvature of the shape of the missile-borne radome 13 is the same as the curvature of the projectile body 3.
The antenna is a broadband antenna with the bandwidth of 10M. The projectile body 3 launches in the ground launching cabin, and the missile-borne antenna 1 needs to be integrated with the carrier in the design process, so the missile-borne antenna cover 13 needs to be made to be the same as the curvature of the projectile body 3, the velocity of time of the projectile body 3 in the flight process is lower than Mach 1, and the base 11 adopts a smooth rigid structure in consideration of factors such as vibration impact. The missile-borne radome 13 is made of a teflon glass cloth plate.
The missile-borne antenna 1 is conformal with the missile body 3, so that the requirements of the appearance and the frequency band of the missile body 3 can be met. The center frequency of the missile-borne antenna 1 is 580MHz, the vertical polarization is realized, the normal gain is 3.7dbi, and the standing-wave ratio is 1.5. The standing-wave ratio of the antenna is measured by a scalar network analyzer, and the test result (please refer to fig. 8) shows that the standing-wave ratio of the antenna is less than 1.5 within the bandwidth of +/-5 MHz, so that the design requirement of the antenna is met.
In the embodiment, the structural components of the system are all made of aluminum-magnesium alloy materials, so that the structural members can be effectively ensured to meet the requirements on quality and strength. In the design process, the system equipment and the capsule section 3 of the projectile body are integrally processed, and a part of unnecessary structures are reduced, so that the overall weight of the equipment is reduced.
In the embodiment, a power supply is one of the cores of the system, and the input end and the output end of a power supply module used by the system adopt a power supply ground isolation design mode, so that the design realizes isolation of ground noise and high common mode voltage. The power input also adopts an ultra-wide voltage design, so that the terminal equipment can be normally started to work within the input voltage requirement range, and measures such as input under-voltage and overvoltage protection, output overcurrent protection, short-circuit protection and the like are designed.
The utility model also provides an install guided missile of data link, its characterized in that: the missile provided with the data chain is applied with any missile-borne data chain system.
The utility model provides a pair of install guided missile of data chain system compares with prior art, and the signal processing module 2 of this guided missile adopts same frequency two-way wireless transmission technique, can realize two-way communication through single frequency point, and frequency spectrum utilization is high. The missile also has the characteristics of long transmission distance, high mobility, strong anti-interference performance and high dynamic performance.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A system for a data link for missile-borne applications, comprising:
the missile-borne terminal is connected with the missile body (3), and is used for transmitting a target image acquired by the missile upper seeker and the working state information of the missile in real time and receiving a remote control command from the ground terminal; and the missile-borne terminal is provided with a signal processing module (2) for realizing a wireless same-frequency two-way transmission technology.
2. The missile-borne data link system of claim 1, wherein: the missile-borne terminal further comprises a missile-borne antenna (1) which is designed in a missile-body common form, wherein the missile-borne antenna (1) is fixedly connected with the missile body (3) and is used for transmitting signals to the ground terminal or receiving instructions transmitted by the ground terminal.
3. A system of missile-borne data link as claimed in claim 2 wherein the signal processing module (2) comprises:
the main machine frame (21) is positioned in the projectile body (3) and is fixedly connected with the projectile body (3);
the image processing module (22) is connected with the main machine frame (21) and is used for converting a target image into a data signal and transmitting the data signal;
the baseband module (23) is connected with the host frame (21), the baseband module (23) is used for receiving the data signal transmitted by the image processing module (22), and a functional component (231) for realizing a wireless same-frequency bidirectional transmission technology and an LDPC (low density parity check) error correction code technology is integrated on the baseband module (23); and
and the power amplifier module (24) is connected with the main frame (21) and is used for amplifying or/and bidirectionally transmitting the data signals between the missile-borne antenna (1) and the baseband module (23).
4. A system of missile-borne data link system as in claim 3 wherein the host frame (21) comprises a rectangular frame.
5. The missile-borne data link system of claim 4, wherein: the image processing module (22), the baseband module (23) and the power amplifier module (24) are respectively arranged on any side surface of the main machine frame (21).
6. A data link system as claimed in claim 3, wherein: the baseband module (23) is also provided with a radio frequency component (232) independently; and an independent cavity (211) for accommodating the radio frequency assembly (232) is arranged on the main machine frame (21).
7. A system of missile-borne data link according to claim 3, in which the host frame (21) is provided with a housing for separately housing the power amplifier module (24).
8. A system of missile-borne data link as claimed in claim 2 wherein the missile antenna (1) comprises:
the base (11) is used for being connected and fixed with the projectile body (3);
the missile-borne antenna radiation sheet (12) is used for receiving the signals transmitted by the signal processing module (2); and
and the missile-borne antenna housing (13) is fixedly connected with the base (11) and is used for connecting and protecting the missile-borne antenna radiating sheet (12) with the base (11).
9. The missile-borne data link system of claim 8, wherein: the curvature of the shape of the missile-borne radome (13) is the same as the curvature of the projectile body (3).
10. A missile provided with a data link is characterized in that: the missile provided with the data chain is applied with the missile-borne data chain system as claimed in any one of claims 1 to 9.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202020369991.1U CN211824087U (en) | 2020-03-23 | 2020-03-23 | Missile-borne data chain system and missile provided with data chain system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202020369991.1U CN211824087U (en) | 2020-03-23 | 2020-03-23 | Missile-borne data chain system and missile provided with data chain system |
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| CN211824087U true CN211824087U (en) | 2020-10-30 |
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| CN202020369991.1U Active CN211824087U (en) | 2020-03-23 | 2020-03-23 | Missile-borne data chain system and missile provided with data chain system |
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