CN215067790U - Multifunctional wireless ground control system for rocket - Google Patents
Multifunctional wireless ground control system for rocket Download PDFInfo
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- CN215067790U CN215067790U CN202120832045.0U CN202120832045U CN215067790U CN 215067790 U CN215067790 U CN 215067790U CN 202120832045 U CN202120832045 U CN 202120832045U CN 215067790 U CN215067790 U CN 215067790U
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Abstract
The application discloses a multifunctional wireless ground control system for a rocket. The method comprises the following steps: the ground control unit is arranged in the controller shell; the ground control system is convenient to carry and carry; the wireless communication module receives a control instruction sent by the ground command end, is processed by the central processor module and then is transmitted to the rocket by the rocket-ground communication module so as to control the electric control system of the rocket; the rocket is isolated from the ground command terminal by the wireless control mode, so that the system stability is ensured, and the geographical limitation of the ground test, launch and control system is reduced.
Description
Technical Field
The present disclosure relates generally to the field of rocket launching technology, and more particularly to a multifunctional wireless ground control system for a rocket.
Background
The launching of the small and medium-sized rockets generally adopts a launcher, and before launching, a ground control system is needed to control the electrification of the rockets, the self-checking of each system and the like through bus communication, electrification control signals and other modes.
The ground control system used by the existing rocket generally adopts a wired and direct connection mode, and the control function comprises rocket-ground communication and control functions. Other devices are needed to be used for detecting the transmitting field environment, the levelness of the transmitting frame and the like, and certain observation complexity exists. Therefore, a multifunctional wireless ground control system for rockets is provided to solve the problems that the position limitation caused by wire connection is poor, the system universality is poor, and the functional requirements of rockets of different models cannot be met.
Disclosure of Invention
In view of the above-mentioned defects or shortcomings in the prior art, it is desirable to provide a multifunctional wireless ground control system for rocket, which reduces the geographical location limitation, has multiple communication, control, acquisition and detection functions, and is strong in universality, small in size, light in weight and convenient to carry.
In a first aspect, the present application provides a multifunctional wireless ground control system for a rocket, comprising: the ground control unit is arranged in the controller shell;
the top of the controller shell is provided with a folding type handle;
the ground control unit is communicated with the ground command terminal and the rocket; the ground control unit includes: the wireless communication module, the signal conversion module, the central processing unit module and the rocket-ground communication module are in communication connection;
the wireless communication module is used for receiving a wireless control signal transmitted by the ground command terminal;
the signal conversion module is used for converting the wireless control signal into a control instruction;
the central processing unit module is used for processing the control instruction and restoring the control instruction;
the rocket-ground communication module is used for transmitting the restored control instruction to the rocket.
According to the technical scheme provided by the embodiment of the application, a levelness signal acquisition module and a temperature signal acquisition module are arranged between the central processing unit module and the rocket;
the levelness signal acquisition module is used for acquiring levelness data of rocket installation;
and the temperature signal acquisition module is used for acquiring actual temperature data of the rocket in a launching site.
According to the technical scheme provided by the embodiment of the application, a signal detection module and a discrete magnitude signal acquisition module are further arranged between the central processing unit module and the rocket.
According to the technical scheme provided by the embodiment of the application, the method further comprises the following steps: the power supply module is connected with the central processor module;
and the power supply module is used for supplying power to the ground control unit.
According to the technical scheme provided by the embodiment of the application, a power connector and a controller connector are arranged on the controller shell, and the power connector is close to the bottom of the controller shell relative to the controller connector;
one end of the power connector is connected with the power module, and the other end of the power connector is connected with a charging power supply; one end of the controller connector is connected with the rocket ground communication module, and the other end of the controller connector is connected with the rocket through a wire.
According to the technical scheme provided by the embodiment of the application, at least two symmetrically arranged mounting holes are formed in the bottom of the controller shell; the heat dissipation plate is arranged in the mounting hole and forms an accommodating groove with the side wall of the mounting hole; a supporting part is hinged to one side wall of the accommodating groove; the supporting part can be arranged in the accommodating groove; the supporting part is used for supporting the controller shell when being unfolded; the accommodating groove side wall is provided with an elastic clamping part used for clamping the supporting part.
According to the technical scheme provided by the embodiment of the application, the supporting part is further provided with a handle.
In summary, the present technical solution specifically discloses a specific process of a multifunctional wireless ground control system for a rocket. The ground control system is characterized in that a controller shell is specifically designed, a ground control unit is installed in the controller shell, and a folding type lifting handle is designed at the top of the controller shell, so that the ground control system is convenient to carry and carry; furthermore, a ground control unit is formed by the wireless communication module, the signal conversion module, the central processor module and the rocket-ground communication module and serves as bridging equipment between the ground command end and an electric control system of the rocket, the ground control unit is connected with the ground command end through wireless communication and is connected with the rocket through a cable, the wireless communication module receives a control instruction sent by the ground command end, and the control instruction is transmitted to the electric control system of the rocket through the rocket-ground communication module after being processed by the central processor module so as to control the electric control system of the rocket; the rocket is isolated from the ground command terminal by the wireless control mode, so that the stability of the system is ensured, and the geographical limitation of the ground test, launch and control system is reduced.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the following detailed description of non-limiting embodiments thereof, made with reference to the accompanying drawings in which:
fig. 1 is a schematic flow chart of a multifunctional wireless ground control system for rockets.
Fig. 2 is a schematic structural diagram of the controller housing.
FIG. 3 is a circuit diagram of the X axis of levelness of the rocket.
FIG. 4 is a circuit diagram of the acquisition rocket's levelness Y-axis.
FIG. 5 is a circuit diagram of the acquisition rocket's levelness Z-axis.
FIG. 6 is a circuit diagram for collecting rocket temperature data.
FIG. 7 is a circuit diagram for collecting rocket temperature data.
Fig. 8 is a structural schematic diagram of the bottom of the controller housing when the support portion is in an operating state.
Fig. 9 is a structural diagram of the bottom of the controller housing when the support part is in a non-working state.
FIG. 10 is a schematic view of a structure of the accommodating groove.
Reference numbers in the figures: 1. a ground command terminal; 2. a rocket; 3. a ground control unit; 4. a wireless communication module; 5. a signal conversion module; 6. a central processor module; 7. a rocket-ground communication module; 8. a levelness signal acquisition module; 9. a temperature signal acquisition module; 10. a signal detection module; 11. a discrete magnitude signal acquisition module; 12. a power supply module; 13. a controller housing; 14. A power supply connector; 15. a folding handle; 16. a controller connector; 17. a heat dissipation plate; 18. A support portion; 19. an elastic clamping part; 20. a handle.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant invention and not restrictive of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Example one
Please refer to fig. 1, which is a schematic structural diagram of a first embodiment of a multifunctional wireless ground control system for rockets according to the present application, comprising: a controller housing 13 and a ground control unit 3 provided inside the controller housing 13;
a folding type handle 15 is arranged at the top of the controller shell 13;
the ground control unit 3 is communicated with the ground command terminal 1 and the rocket 2; the ground control unit 3 includes: the wireless communication module 4, the signal conversion module 5, the central processor module 6 and the rocket-ground communication module 7 are in communication connection;
the wireless communication module 4 is used for receiving a wireless control signal transmitted by the ground command terminal 1;
the signal conversion module 5 is configured to convert the wireless control signal into a control instruction;
the central processor module 6 is used for processing the control instruction and restoring the control instruction;
the rocket-ground communication module 7 is used for transmitting the restored control instruction to the rocket 2.
In the present embodiment, as shown in fig. 2, the controller case 13, as an installation body, is used for installing the floor control unit 3;
the folding type handle 15 is arranged at the top of the controller shell 13, so that the controller shell 13 is convenient for workers to move and is convenient to carry, and the occupied space can be saved under the condition that the position of the controller shell 13 is not changed due to the fact that the handle has a folding function.
As shown in fig. 1, the ground control unit 3, as a bridging device between the ground command terminal 1 and the electrical control system of the rocket 2, is connected to the ground command terminal 1 through wireless communication and is connected to the rocket 2 by a cable, the ground control unit 3 receives a control instruction sent by the ground command terminal 1, and transmits the control instruction to the electrical control system of the rocket 2 to control the electrical control system; the rocket 2 is isolated from the ground command terminal 1 in the wireless control mode, so that the stability of the system is ensured, and the geographical limitation of a ground test, launch and control system is reduced;
the wireless communication module 4 is used for receiving a wireless control signal transmitted by the ground command terminal 1; here, the type of the wireless communication module 4 is, for example, a radio frequency antenna;
the signal conversion module 5 is used for converting the wireless control signal into a control instruction and transmitting the control instruction to the central processor module 6;
the central processing unit module 6 is used for processing the control instruction and restoring the control content represented by the control instruction; here, the model of the central processor module 6 is, for example, AMD Ryzen 75800X;
and the rocket-ground communication module 7 is used for transmitting the restored control instruction to the rocket 2 so as to control the electric control system of the rocket 2.
In any preferred embodiment, a levelness signal acquisition module 8 and a temperature signal acquisition module 9 are arranged between the central processor module 6 and the rocket 2;
the levelness signal acquisition module 8 is used for acquiring levelness data installed on the rocket 2;
and the temperature signal acquisition module 9 is used for acquiring actual temperature data of the rocket 2 in a launching site.
In the present embodiment, as shown in fig. 3, 4 and 5, the levelness signal acquisition module 8 is configured to acquire levelness data of rocket 2 installation; furthermore, the collected levelness data is processed by the central processor module 6, sent out by the wireless communication module 4 and fed back to the ground command terminal 1;
as shown in fig. 6 and 7, the temperature signal collecting module 9 is used for collecting actual temperature data of the rocket 2 at a launching site; furthermore, the collected actual temperature data is processed by the central processor module 6, and then sent out by the wireless communication module 4 and fed back to the ground command terminal 1.
In any preferred embodiment, a signal detection module 10 and a discrete quantity signal acquisition module 11 are further arranged between the central processor module 6 and the rocket 2.
In this embodiment, the signal detection module 10 is configured to detect other analog signals to achieve the universality of the ground control unit 3; here, the types of other analog quantity signals, such as voltage signals, and the detected voltage signals are processed by the central processor module 6, sent out by the wireless communication module 4, and fed back to the ground command terminal 1;
the discrete magnitude signal acquisition module 11 is used for acquiring discrete magnitude signals so as to detect some external time sequences or switch control information; here, the types of discrete quantity signals are, for example, a switching signal, active on-off and passive on-off; the switching signal of collection is handled the back by central processor module 6, is sent by wireless communication module 4, feeds back to ground command terminal 1 to according to the discrete magnitude information of difference, carry out different control processes.
In any preferred embodiment, further comprising: a power supply module 12 connected to the central processor module 6;
the power module 12 is configured to supply power to the ground control unit 3.
In this embodiment, the power module 12 is configured to supply power to the ground control unit 3; here, the type of the power module 12 is, for example, a secondary lithium battery.
In any preferred embodiment, the controller housing 13 is provided with a power connector 14 and a controller connector 16, and the power connector 14 is close to the bottom of the controller housing 13 relative to the controller connector 16;
one end of the power connector 14 is connected with the power module 12, and the other end thereof is connected with a charging power supply; one end of the controller connector 16 is connected with the rocket-ground communication module 7, and the other end thereof is connected with the rocket 2 through a wire.
In this embodiment, as shown in fig. 2, the power connector 14 is disposed on the controller housing 13, one end of the power connector is connected to the power module 12, and the other end of the power connector is connected to a charging power source, which is used as a charging interface of the power module 12, and can directly supply power to the ground control unit 3 through the connected charging power source, or can take off the power module 12 for independent charging;
a controller connector 16, which is arranged on the controller housing 13, one end of which is connected with the rocket-ground communication module 7, and the other end of which is connected with the rocket 2 through a wire, and which is used as an interface of the rocket-ground communication module 7 and is connected with the rocket 2 through a wire;
wherein the power connector 14 is located near the bottom of the controller housing 13 opposite the controller connector 16.
In any preferred embodiment, the bottom of the controller housing 13 is provided with at least two symmetrically arranged mounting holes; a heat dissipation plate 17 is arranged in the mounting hole, and an accommodating groove is formed between the heat dissipation plate and the side wall of the mounting hole; a supporting part 18 is hinged to one side wall of the accommodating groove; the supporting part 18 can be placed in the accommodating groove; the support portion 18 is used to support the controller case 13 when deployed; the side wall of the accommodating groove is provided with an elastic clamping part 19 for clamping the supporting part 18.
In the embodiment, the heat dissipation plate 17 is disposed in the mounting hole at the bottom of the controller housing 13, and is used for dissipating heat of the power module 12 when the power module is in operation;
and, the heat radiating plate 17 and the side wall of the mounting hole can form a receiving groove to receive the support part 18;
the supporting part 18 is hinged on one side wall of the accommodating groove and plays a role in supporting the controller shell 13;
as shown in fig. 8, when the ground control unit 3 works, the two supporting portions 18 are unfolded, the free ends of the two supporting portions are away from each other, the heat dissipation plate 17 can dissipate heat for the power module 12, and the surface of the supporting portion 18, which is relatively away from the adjacent heat dissipation plate 17, can abut against the edge of the accommodating groove, so that the two supporting portions 18 respectively form an included angle with the bottom of the controller housing 13, and a supporting effect is achieved on the controller housing 13;
as shown in fig. 10, an elastic catching portion 19 provided at a side wall of the receiving groove for catching the supporting portion 18;
when the ground control unit 3 is not in operation, the supporting part 18 is arranged in the accommodating groove, the two elastic clamping parts 19 clamp the supporting part 18 in the accommodating groove, the supporting part 18 is prevented from being separated from the accommodating groove when in an inoperative state, the supporting part 18 is damaged, and external dust is prevented from entering the controller shell 13 through the heat dissipation plate 17 and damaging internal devices.
In any preferred embodiment, the support portion 18 is further provided with a handle 20.
In this embodiment, as shown in fig. 9, a handle 20 is provided on the support portion 18 to facilitate the support portion 18 to be removed from the receiving groove to support the controller housing 13;
and, the handle 20 is located at one side of the supporting portion 18, and a groove capable of accommodating the handle 20 is opened at the bottom of the corresponding controller housing 13, so that the controller housing 13 can be stably placed when transporting the floor control system.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the above features may be replaced with (but not limited to) features having similar functions disclosed in the present application.
Claims (7)
1. A multifunctional wireless ground control system for a rocket, comprising: a controller housing (13) and a ground control unit (3) arranged inside the controller housing (13);
a folding type handle (15) is arranged at the top of the controller shell (13);
the ground control unit (3) is communicated with the ground command terminal (1) and the rocket (2); the ground control unit (3) comprises: the system comprises a wireless communication module (4), a signal conversion module (5), a central processor module (6) and an arrow-ground communication module (7) which are in communication connection;
the wireless communication module (4) is used for receiving a wireless control signal transmitted by the ground command terminal (1);
the signal conversion module (5) is used for converting the wireless control signal into a control instruction;
the central processor module (6) is used for processing the control instruction and restoring the control instruction;
the rocket ground communication module (7) is used for transmitting the restored control command to the rocket (2).
2. A multifunctional wireless ground control system for rocket according to claim 1, characterized in that a levelness signal acquisition module (8) and a temperature signal acquisition module (9) are arranged between the central processor module (6) and the rocket (2);
the levelness signal acquisition module (8) is used for acquiring levelness data installed on the rocket (2);
the temperature signal acquisition module (9) is used for acquiring actual temperature data of the rocket (2) at a launching site.
3. A multifunctional wireless ground control system for rocket according to claim 1, characterized in that a signal detection module (10) and a discrete quantity signal acquisition module (11) are further arranged between the central processor module (6) and the rocket (2).
4. A rocket-based multifunctional wireless ground control system according to claim 1, further comprising: a power supply module (12) connected with the central processor module (6);
the power supply module (12) is used for supplying power to the ground control unit (3).
5. A rocket-used multifunctional wireless ground control system according to claim 4, characterized in that said controller housing (13) is provided with a power connector (14) and a controller connector (16), and said power connector (14) is close to the bottom of said controller housing (13) relative to said controller connector (16);
one end of the power supply connector (14) is connected with the power supply module (12), and the other end of the power supply connector is connected with a charging power supply; one end of the controller connector (16) is connected with the rocket-ground communication module (7), and the other end of the controller connector is connected with the rocket (2) through a wire.
6. The multifunctional wireless ground control system for rockets according to claim 1, wherein the bottom of the controller housing (13) is provided with at least two symmetrically arranged mounting holes; a heat dissipation plate (17) is arranged in the mounting hole, and an accommodating groove is formed between the heat dissipation plate and the side wall of the mounting hole; a supporting part (18) is hinged to one side wall of the accommodating groove; the supporting part (18) can be arranged in the accommodating groove; the support part (18) is used for supporting the controller shell (13) when being unfolded; the side wall of the accommodating groove is provided with an elastic clamping part (19) used for clamping the supporting part (18).
7. A rocket multi-function wireless ground control system according to claim 6, characterized in that said supporting portion (18) is further provided with a handle (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120832045.0U CN215067790U (en) | 2021-04-22 | 2021-04-22 | Multifunctional wireless ground control system for rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120832045.0U CN215067790U (en) | 2021-04-22 | 2021-04-22 | Multifunctional wireless ground control system for rocket |
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| Publication Number | Publication Date |
|---|---|
| CN215067790U true CN215067790U (en) | 2021-12-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202120832045.0U Active CN215067790U (en) | 2021-04-22 | 2021-04-22 | Multifunctional wireless ground control system for rocket |
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| CN (1) | CN215067790U (en) |
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- 2021-04-22 CN CN202120832045.0U patent/CN215067790U/en active Active
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