A new type of guided rocket projectile

Abstract

The utility model discloses a novel guided rocket belongs to guided weapon technical field, and guided rocket includes antenna cabin, electronic cabin, rudder cabin, fuse and combat unit that are connected in proper order, and the direction and stable flight are controlled through two fixed duck rudders on the outer wall of rudder cabin, and the wireless communication is carried out with satellite by utilizing antenna cabin, and the signal of antenna cabin is received through electronic cabin and sends the command to rudder cabin to control the pitch and yaw of guided rocket, and the thermocell combination of thermocell A and thermocell B provides power supply for electronic cabin and rudder cabin, the utility model provides guided rocket after launching thermocell A activates the power supply of electronic cabin by launching overload, and the pulse current generated after thermocell A activates reactivates thermocell B, can supply power to the rudder of rudder cabin, and the power supply problem of this low -speed rotating rocket is solved.

Description

Technical Field

[0001] This utility model belongs to the field of guided weapon technology, and specifically relates to a new type of guided rocket. Background Technology

[0002] There are numerous models and series of unguided rockets currently in existence, many of which are widely deployed both domestically and internationally. The large number of retired unguided rockets necessitates disposal, but direct destruction would inevitably result in significant waste. Currently, some other countries have a substantial demand for these retired unguided rockets, but require high precision strikes. Therefore, there is an urgent need to develop a new type of guided rocket that can be modified from retired rockets, achieving the goal of turning waste into treasure and reducing resource waste. Utility Model Content

[0003] To address the above problems, this invention provides a novel guided rocket.

[0004] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0005] A novel guided rocket, comprising an antenna compartment, an electronics compartment, a servo compartment, and a fuze for connection with a warhead, wherein the antenna compartment is disposed at the head of the guided rocket and the warhead is disposed at the tail of the guided rocket, and the antenna compartment, electronics compartment, servo compartment, fuze, and warhead are sequentially connected to form a guided rocket;

[0006] Two or more fixed canards are radially arranged on the outer wall of the servo compartment for controlling direction and stabilizing flight; the antenna compartment is used for wireless communication with satellites; the electronics compartment is used to receive signals from the antenna compartment and send commands to the servo compartment to control the pitch and yaw of the guided rocket; the inner cavity at the junction of the servo compartment and the fuze is equipped with a thermal battery assembly, which is connected to the fuze and can provide power to the electronics compartment and the servo compartment.

[0007] Furthermore, the fuze is connected to the servo compartment via a fuze adapter. The thermal battery assembly is disposed in the inner cavity of the fuze adapter. The thermal battery assembly includes thermal battery B and thermal battery A electrically connected to it. Both thermal battery B and thermal battery A are connected to the fuze. Thermal battery B provides power to the electronics compartment, and thermal battery A provides power to the servo compartment.

[0008] Furthermore, thermal battery A and thermal battery B are arranged side by side, and both thermal battery A and thermal battery B are threadedly connected to the end of the fuse.

[0009] Furthermore, the antenna compartment includes a dome and an antenna and an electromagnetic induction setting module inside it. The dome is conical in shape, and its large-diameter end is connected to the electronic compartment. The antenna is used to receive and transmit signals, and the electromagnetic induction setting module is used to detect and sense external environmental information. The antenna is wirelessly connected to a satellite to realize the navigation and positioning of the guided rocket. The electromagnetic induction setting module is connected to the electronic compartment.

[0010] Furthermore, the antenna is a GNSS antenna, which is glued to the inner wall of the middle part of the enclosure, and the electromagnetic induction setting module is glued to the inner wall of the large-diameter end of the enclosure.

[0011] Furthermore, the cover is made of polytetrafluoroethylene, and the large-diameter end of the cover is threadedly connected to the electronic compartment.

[0012] Furthermore, the servo compartment includes a housing and a servo motor inside it. A ground test interface is embedded in the side wall of the housing for testing and verifying the guided rocket before launch. The servo motor is a single-channel servo motor and is electrically connected to thermal battery A.

[0013] Furthermore, the electronic cabin includes a shell and an EU electronic component inside it. The EU electronic component is mounted on a bracket inside the shell. The EU electronic component is a PCB board integrating a satellite receiver, a CPU board, a power board, a rudder control power board, a rudder control board, and an overload switch. The satellite receiver, CPU board, and overload switch are all electrically connected to the power board. The power board is electrically connected to the thermal battery B. The servo motor is electrically connected to the rudder control board. The rudder control board is electrically connected to the rudder control power board. The rudder control power board is electrically connected to the thermal battery A.

[0014] The satellite receiver is used to measure the position and velocity information of the guided rocket; the CPU board is equipped with a geomagnetic roll measurement module, which is used to measure the roll angle of the guided rocket; the satellite receiver, power board, rudder control power board and electromagnetic induction setting module are all connected to the CPU on the CPU board.

[0015] Furthermore, the fixed canard is made of aluminum alloy and has an aerodynamic shape of a strake wing. The two fixed canards are symmetrically arranged on the outer wall of the servo compartment.

[0016] The technological advancements achieved by this invention compared to existing technologies are as follows:

[0017] This invention utilizes an antenna compartment, an electronics compartment, a servo compartment, a fuze, and a warhead connected in sequence. The guided rocket uses a fixed canard on the outer wall of the servo compartment to control its direction and stabilize its flight. The antenna compartment communicates wirelessly with a satellite. The electronics compartment receives signals from the antenna compartment and sends commands to the servo compartment to control the pitch and yaw of the guided rocket. A thermal battery assembly consisting of thermal battery A and thermal battery B provides power to the electronics compartment and the servo compartment.

[0018] After launch, thermal battery B is activated by launch overload to power the electronics compartment. The pulse current generated after thermal battery B is activated then activates thermal battery A, which can power the servo motors in the servo compartment, thus solving the power supply problem of this low-speed rotating rocket. Attached Figure Description

[0019] The accompanying drawings are provided to further understand the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention and do not constitute a limitation thereof.

[0020] In the attached diagram:

[0021] Figure 1 An external view of a novel guided rocket provided for an embodiment of this utility model;

[0022] Figure 2 for Figure 1 Left view of a guided rocket;

[0023] Figure 3 This is a schematic diagram of the internal structure of the guided rocket in an embodiment of this utility model.

[0024] In the picture:

[0025] 1-Antenna compartment; 2-Electronics compartment; 3-Servo compartment; 4-Fixed canard; 5-Ground test interface; 6-Fuse, 61-Fuse adapter; 7-Antenna; 8-Electromagnetic induction setting module; 9-EU electronic components; 10-Servo; 11-Thermocell A; 12-Thermocell B. Detailed Implementation

[0026] The following specific embodiments can be combined with each other, and the same or similar concepts or processes may not be described again in some embodiments. The embodiments of this utility model will be described below with reference to the accompanying drawings.

[0027] like Figure 1 , Figure 2As shown, a novel guided rocket includes an antenna compartment 1, an electronics compartment 2, a servo compartment 3, and a fuze 6 for connecting to a warhead (not shown). The antenna compartment 1 is located at the head of the guided rocket, and the warhead is located at the tail. The antenna compartment 1, electronics compartment 2, servo compartment 3, fuze 6, and warhead are sequentially connected to form the guided rocket. Two or more fixed canards 4 are radially arranged on the outer wall of the servo compartment 3 for controlling direction and stabilizing flight. The antenna compartment 1 is used for wireless communication with satellites. The electronics compartment 2 is used to receive signals from the antenna compartment 1 and send commands to the servo compartment 3 to control the pitch and yaw of the guided rocket. A thermal battery assembly is provided in the inner cavity at the junction of the servo compartment 3 and the fuze 6. The thermal battery assembly is connected to the fuze 6 and can provide power to the electronics compartment 2 and the servo compartment 3.

[0028] As a preferred structure, such as Figure 1 , 3 As shown, the fuze 6 is connected to the servo compartment 3 via a fuze adapter 61. One end of the fuze adapter 61 is threaded to the servo compartment, and the other end is connected to the fuze via a screw. The thermal battery assembly is disposed within the cavity of the fuze adapter 61. The thermal battery assembly includes a thermal battery B12 and a thermal battery A11 electrically connected to it. Both thermal batteries B12 and A11 are connected to the fuze 6. The thermal battery B12 provides power to the electronics compartment 2, and the thermal battery A11 provides power to the servo compartment 3. In specific assembly, the thermal batteries A11 and B12 are arranged side by side, and both are threaded to the end of the fuze 6. The thermal battery B12 is activated by the overload of the guided rocket launch, which is existing technology and will not be described in detail here. The pulse current after the thermal battery B12 is activated activates the thermal battery A11, which provides power to the servo compartment 3, and the thermal battery B12 provides power to the electronics compartment 2.

[0029] In specific embodiments of this utility model, such as Figure 3As shown, the antenna compartment 1 includes a dome and an antenna 7 and an electromagnetic induction setting module 8 inside it. The dome is conical in shape, and its large-diameter end is connected to the head of the electronic compartment 2. The antenna 7 is used to receive and transmit signals, and the electromagnetic induction setting module 8 is used to detect and sense external environmental information. The antenna 7 is wirelessly connected to a satellite for navigation and positioning of the guided rocket. The electromagnetic induction setting module 8 is connected to the electronic compartment 2. The electromagnetic induction setting module is existing technology and will not be described in detail here. Before launch, the electromagnetic induction setting module is held in place on the ground and fitted onto the mounting part inside the dome. The firing parameters are converted into induced voltage using the principles of electromagnetic and magnetoelectric induction and transmitted to the receiving coil of the wireless electromagnetic induction setting module. The receiving module demodulates the induced voltage to obtain the transmitted signal. The printed circuit boards inside the module are reinforced and locked, and 100% of the electronic components have undergone secondary screening, resulting in high reliability, small size, and light weight. The setting can be completed quickly without affecting the overall range and accuracy of the projectile.

[0030] During assembly, the large-diameter end of the cover is connected to the head of the electronic compartment 2 by a single row of 6 M3 radial countersunk screws with a sleeve interface length of 7mm. The tail of the electronic compartment 2 is connected to the servo compartment 3 by a single row of 6 M3 screws with a sleeve interface length of 7.5mm and an H8 / e8 fit tolerance. The servo compartment 3 is connected to the fuse adapter 61 and the fuse 6 by a single row of 6 M3 countersunk screws with a sleeve interface length of 8mm and an H8 / e8 fit tolerance.

[0031] In specific manufacturing, antenna 7 is a wall-mounted GNSS antenna, glued to the inner wall of the middle part of the radome. The electromagnetic induction setting module is glued to the inner wall of the large-diameter end of the radome, which is threadedly connected to the electronics compartment. Simultaneously, the radome is made of polytetrafluoroethylene (PTFE), which not only meets the wave transmission requirements of the GNSS antenna and electromagnetic induction setting module 8, but also meets the strength requirements of the guided rocket during high-speed flight.

[0032] In specific embodiments of this utility model, such as Figure 3 As shown, the servo compartment 3 includes a shell and a servo motor 10 inside. A ground test interface 5 is embedded in the side wall of the shell for testing the guided rocket before launch to verify its reliability. The servo motor 10 is a single-channel servo motor and is electrically connected to the thermal battery A11. The fixed canard rudders are a pair of control surfaces that provide the power required for the servo motor's rotation. Unlike other ordinary motors, to cope with the large deviation of the low-speed rotating projectile, this invention uses a high-frequency response single-channel electric servo motor to quickly respond to deviation correction within a single rotation cycle. Specifically, the fixed canard rudders 4 are made of aluminum alloy and have an aerodynamic shape of leading-edge extensions. Two fixed canard rudders 4 are symmetrically inserted into the outer wall of the servo compartment shell.

[0033] Further optimize the above solution, such as Figure 3 As shown, the electronic cabin 2 includes a shell and an EU electronic component 9 inside. The EU electronic component 9 is mounted on a bracket inside the shell. The EU electronic component is a PCB board integrating a satellite receiver, CPU board, power board, rudder control power board, rudder control board, and overload switch. The satellite receiver, CPU board, and overload switch are all electrically connected to the power board, which is electrically connected to the thermal battery B12. The servo motor 10 is electrically connected to the rudder control board, which is electrically connected to the rudder control power board, which is electrically connected to the thermal battery A11. The satellite receiver is used to measure the position and velocity information of the guided rocket. The CPU board is equipped with a geomagnetic roll measurement module for measuring the roll angle of the guided rocket. The satellite receiver, power board, rudder control power board, and electromagnetic induction setting module 8 are all connected to the CPU on the CPU board. The CPU can predict the impact point deviation in real time and use the rudder motor's control surfaces to perform lateral and longitudinal comprehensive corrections. These functions are existing technologies and will not be described in detail here.

[0034] The specific application process is as follows: After the guided rocket leaves the barrel, the projectile rotates at low speed. The thermal battery B is activated by the launch overload, and the EU electronic components are powered. At the same time, the thermal battery A is quickly activated, and the canard is locked to zero. The satellite receiver and geomagnetic module quickly measure the projectile's position, velocity and roll angle. The CPU calculates and predicts the impact point deviation, generates pitch and yaw control commands and transmits them to the servo control. After receiving the commands, the servo motor measures the projectile's attitude in real time, corrects the pitch deviation in the horizontal direction and the yaw deviation in the vertical direction until the target is hit.

[0035] During assembly, the GNSS antenna, electromagnetic induction setting module 8, EU electronic components 9, and fuse 6 are all electronically connected using aviation connectors. According to the set operating mode, the detonation energy is output in a timely manner to detonate the warhead and effectively kill the target. The aforementioned satellite receiver, electromagnetic induction setting module, single ballistic servo, and fuse are all mature products, small in size and low in cost, and can be purchased externally according to design requirements.

[0036] In summary, this invention boasts advantages such as compact structure and high integration. It utilizes the launch overload of the guided rocket to activate thermal battery B, which powers the electronics module. The pulse current generated by activated thermal battery B then activates thermal battery A, which in turn powers the servo motor, thus solving the power supply problem for this low-speed rotating guided rocket. Simultaneously, a high-dynamic satellite receiver measures the rocket's position and velocity, a high-precision geomagnetic roll measurement module measures the rocket's roll angle, the CPU predicts the impact point deviation in real time, and the servo motor performs comprehensive lateral and longitudinal corrections. This invention exhibits advantages such as strong anti-interference capability, high integration, and robust guidance logic. Furthermore, this invention utilizes decommissioned rockets for modification, enabling the recycling and reuse of spent rockets, reducing resource waste, and simultaneously generating foreign exchange for the country through exports.

[0037] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of the claims of this utility model.

Claims

1. A novel guided rocket, characterized in that: The guided rocket includes an antenna compartment, an electronics compartment, a servo compartment, and a fuze for connection with the warhead. The antenna compartment is located at the head of the guided rocket, and the warhead is located at the tail of the guided rocket. The antenna compartment, electronics compartment, servo compartment, fuze, and warhead are connected in sequence to form the guided rocket. Two or more fixed canards are radially arranged on the outer wall of the servo compartment for controlling direction and stabilizing flight; the antenna compartment is used for wireless communication with satellites; the electronics compartment is used to receive signals from the antenna compartment and send commands to the servo compartment to control the pitch and yaw of the guided rocket; the inner cavity at the junction of the servo compartment and the fuze is equipped with a thermal battery assembly, which is connected to the fuze and can provide power to the electronics compartment and the servo compartment.

2. The novel guided rocket according to claim 1, characterized in that: The fuze is connected to the servo compartment via a fuze adapter. The thermal battery assembly is located inside the fuze adapter. The thermal battery assembly includes thermal battery B and thermal battery A electrically connected to it. Both thermal battery B and thermal battery A are connected to the fuze. Thermal battery B provides power to the electronics compartment, and thermal battery A provides power to the servo compartment.

3. A novel guided rocket according to claim 2, characterized in that: The thermal battery A and thermal battery B are arranged side by side, and both thermal battery A and thermal battery B are threadedly connected to the end of the fuse.

4. A novel guided rocket according to claim 2, characterized in that: The antenna compartment includes a dome and an antenna and an electromagnetic induction setting module inside it. The dome is conical in shape, and its large-diameter end is connected to the electronic compartment. The antenna is used to receive and transmit signals, and the electromagnetic induction setting module is used to detect and sense external environmental information. The antenna is wirelessly connected to a satellite to realize the navigation and positioning of the guided rocket. The electromagnetic induction setting module is connected to the electronic compartment.

5. A novel guided rocket according to claim 4, characterized in that: The antenna is a GNSS antenna, which is glued to the inner wall of the middle part of the enclosure, and the electromagnetic induction setting module is glued to the inner wall of the large diameter end of the enclosure.

6. A novel guided rocket according to claim 4, characterized in that: The cover is made of polytetrafluoroethylene, and the large-diameter end of the cover is threadedly connected to the electronic compartment.

7. A novel guided rocket according to claim 4, characterized in that: The servo compartment includes a shell and a servo motor inside. A ground test interface is embedded in the side wall of the shell for testing and verifying the guided rocket before launch. The servo motor is a single-channel servo motor and is electrically connected to thermal battery A.

8. A novel guided rocket according to claim 7, characterized in that: The electronic cabin includes a shell and an EU electronic component inside. The EU electronic component is mounted on a bracket inside the shell. The EU electronic component is a PCB board integrating a satellite receiver, a CPU board, a power board, a rudder control power board, a rudder control board, and an overload switch. The satellite receiver, CPU board, and overload switch are all electrically connected to the power board. The power board is electrically connected to thermal battery B. The servo motor is electrically connected to the rudder control board. The rudder control board is electrically connected to the rudder control power board. The rudder control power board is electrically connected to thermal battery A. The satellite receiver is used to measure the position and velocity information of the guided rocket; the CPU board is equipped with a geomagnetic roll measurement module, which is used to measure the roll angle of the guided rocket; the satellite receiver, power board, rudder control power board and electromagnetic induction setting module are all connected to the CPU on the CPU board.

9. A novel guided rocket according to any one of claims 1-8, characterized in that: The fixed canard is made of aluminum alloy and has an aerodynamic shape of a strake wing. The two fixed canards are symmetrically arranged on the outer wall of the servo gear compartment.

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