A rocket projectile tracking compensator and system

Abstract

This invention relates to the field of rocket tracking technology, specifically a rocket tracking compensator and system, comprising: a rocket body, with a tracking compensator mounted on the front end of the rocket body; a launch platform, which is equipped with a launch device for fixing the rocket body, a human-machine interface for inputting target parameters, and a pre-launch programming interface for data communication with the tracking compensator; this invention utilizes the aerodynamic heat generated by the rocket's own supersonic flight after launch as a trigger source, and through the resistance change characteristics of the CTR thermistor sensor in the temperature range of 80℃ to 160℃, automatically activates the electromagnetic induction circuit without any external signal input, achieving passive end-point tracking; simultaneously, it combines infrared detection and over-temperature protection CTR thermistor material with magnetic detection technology used only in proximity fuses, so that the rocket is in a non-magnetic state in the first half of its flight due to the extremely high resistance of the sensor.

Description

Technical Field

[0001] This invention relates to the field of rocket tracking technology, specifically to a rocket tracking compensator and system. Background Technology

[0002] Traditional rockets rely primarily on pre-launch aiming systems for target locking, and their trajectories are fixed after launch, making it impossible to correct for target movement or launch errors, resulting in low hit rates. In terms of passive terminal sensing technology, vanadium oxide-based CTR thermistors have shown intrinsic characteristics of resistance values ​​undergoing abrupt changes of several orders of magnitude near critical temperatures. Internationally, doping with germanium, tungsten, and other materials can adjust the phase transition window from 68°C to a temperature range as high as 180°C. Meanwhile, magnetic fuze technology utilizes the magnetic field disturbance caused by the eddy current effect when the ammunition approaches a metallic target to achieve triggering, and has mature theoretical models and signal processing schemes for ferromagnetic target detection. However, current technologies have always used thermosensitive materials for infrared detection or conventional over-temperature protection, while magnetic detection is limited to the sensing and detonation closed loop in the field of proximity fuses. The combination of the two has never been truly constructed as a tracking and correction method for the terminal phase of rocket flight.

[0003] Therefore, we have made improvements to this and proposed a rocket tracking compensator and system. Summary of the Invention

[0004] The purpose of this invention is to provide a rocket tracking compensator and system to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: including: The rocket body, with a tracking compensator installed at the front end of the rocket body; The launch platform is equipped with a launch device for fixing the rocket body, a human-machine interface for inputting target parameters, and a pre-launch programming interface for data communication with the tracking compensator. The tracking compensator includes: a special battery pack with an output voltage ≥20V, a rated discharge current ≥50A, and an energy storage capacity that can be fully released within 1-3 seconds; The CTR thermistor sensor is made of vanadium oxide matrix material doped with germanium, nickel, and tungsten, and then sintered. Its resistance value ranges from ≥10 ohms in a temperature range of 60℃ to 180℃. 7 Ω drops sharply to ≤10 1 Ω has a negative temperature coefficient of resistance; The electromagnetic induction circuit is composed of the special battery pack, the CTR thermistor sensor, and a solenoid connected in series; the solenoid includes an iron core and a coil wound on the iron core. The iron core is made of soft magnetic material with an initial relative permeability ≥10. 5 The iron core is cylindrical, with an end cap connected to its front end and a concave surface at its rear end. The concave surface is fixed to the convex surface of the rocket body's head by an adhesive. The coil uses a conductive winding with 500 to 800 turns, wound in an annular groove on the iron core; The special battery pack is disposed inside the cavity of the iron core; The CTR thermistor sensor is fixed to the outer end face of the end cover, and its electrode leads pass through the wire channel inside the end cover and the iron core and are electrically connected to the special battery pack and the coil. The end cap is connected to the front end of the iron core via a detachable connection structure. The pre-launch programming interface is connected to the tracking compensator via contact and non-contact data links, and is used to write the target metal type threshold, trigger temperature window, and effective working time limit to the tracking compensator before launch. When the rocket body reaches a speed of 1 to 3 times the speed of sound after launch, aerodynamic heating causes the temperature of the CTR thermistor sensor to rise to 80°C to 160°C, and its resistance value drops sharply. The electromagnetic induction circuit is turned on, and the coil is energized to generate a magnetic field, causing the rocket's front end to generate a magnetic attraction force on the steel target.

[0006] As a preferred technical solution of this application, the launching platform is a portable launcher for individual soldiers, a vehicle-mounted launcher, an airborne launcher, and a shipborne launching device; the human-machine interface includes a touch screen, a rotary encoder, and a voice input module, used to input target distance, target speed, and target metal material; the pre-launch programming interface includes an electrical contact pin header, an infrared transceiver, and a radio frequency identification module. It also includes a handheld programmer, which is independent of the launch platform and has a built-in target parameter database. The database stores typical metal composition and thermal characteristic parameters of tanks, armored vehicles, ships, and armed helicopters, which are used to write the tracking compensator with one click.

[0007] As a preferred technical solution of this application, a flight status monitoring module is also included. This module is installed in the middle and tail of the rocket body and consists of a three-axis accelerometer, a three-axis gyroscope, a barometric altimeter, and a temperature sensor. The flight status monitoring module is connected to the tracking compensator via a single bus and wireless communication. When the flight speed of the rocket body reaches a preset Mach number threshold and the attitude angle deviation of the rocket body is less than ±5°, the flight status monitoring module sends a ready signal to the tracking compensator to reduce the risk of false triggering of the CTR thermistor sensor due to vibration and transient thermal shock.

[0008] As a preferred technical solution of this application, a multi-level trigger control circuit is also included. This multi-level trigger control circuit is connected in series between the CTR thermistor sensor and the electromagnetic induction circuit, and includes a first comparator, a second comparator, an AND gate circuit, and an electronic switch. The input terminal of the first comparator is connected to the voltage divider signal of the CTR thermistor sensor, and its reference voltage corresponds to a temperature threshold of 80°C. The input terminal of the second comparator is connected to the speed signal output by the flight status monitoring module, and its reference voltage corresponds to Mach 1.5. When both comparators output a high level simultaneously, the AND gate circuit drives the electronic switch to conduct, thereby connecting the electromagnetic induction circuit. The multi-level trigger control circuit is encapsulated in a metal shield and filled with thermally conductive potting compound.

[0009] As a preferred technical solution of this application, it also includes a terminal correction execution evaluation unit, which consists of a fluxgate magnetometer, a triaxial geomagnetic sensor and a microcontroller, and is installed inside the tracking compensator and at the tail of the rocket body; the fluxgate magnetometer is used to measure the magnetic field strength generated at the front end of the rocket in real time, and the triaxial geomagnetic sensor is used to measure the direction of the geomagnetic field; the microcontroller has a built-in ballistic correction algorithm, and when the detected magnetic field strength reaches ≥0.1T and lasts for ≥10ms, the microcontroller records the current timestamp and rocket attitude, and transmits the hit evaluation data back to the launch platform and command center through the telemetry launch module.

[0010] As a preferred technical solution of this application, it also includes a target feature database and an adaptive parameter preset module, which are integrated into the launch platform and the handheld programmer; the target feature database contains typical magnetic susceptibility, equivalent magnetic moment, and attack surface area of ​​ferromagnetic targets; the adaptive parameter preset module automatically calculates the trigger temperature window and effective working time according to the target type selected by the operator, and writes it into the tracking compensator through the pre-launch programming interface; the calculation formula for the trigger temperature window is: ; ; in The target velocity (m / s) For the target mass (tons), and This is an empirical coefficient.

[0011] As a preferred technical solution of this application, it also includes a ground and air multi-unit collaborative combat subsystem, which includes at least two launch platforms, a battlefield relay UAV, and a ground radar station; the battlefield relay UAV and the ground radar station are used to detect the position and trajectory of multiple metal targets, and send target allocation instructions to each launch platform through a data link; each launch platform automatically sets the trigger parameters of its onboard rocket tracking compensator according to the received target allocation instructions, so as to realize saturation attack of multiple rockets on the same target and distributed strike of multiple targets.

[0012] As a preferred technical solution of this application, a self-testing and status reporting module is also included. This module is integrated inside the tracking compensator and consists of a battery voltage detection circuit, a sensor resistance detection circuit, a coil connectivity detection circuit, and a status indicator light. When the rocket body is mounted on the launch platform and not launched, the self-testing and status reporting module reports the remaining battery power percentage, sensor room temperature resistance, and coil DC resistance to the launch platform through the pre-launch programming interface. When any parameter is detected to exceed the preset qualified range, the status indicator light emits a red flashing light and displays a fault code on the human-machine interface of the launch platform.

[0013] As a preferred technical solution of this application, a safety and insurance module is also included. This module is mechanically connected in series between the special battery pack and the electromagnetic induction circuit, and includes an inertial safety switch, an electronic safety switch, and a manual safety lever. The inertial safety switch automatically closes when the rocket body experiences a launch overload ≥100g. The electronic safety switch closes when the multi-level trigger control circuit outputs a conduction signal. The manual safety lever is located on the launch platform and is released by the operator before launch. The special battery pack can only supply power to the electromagnetic induction circuit when all three safety switches are closed simultaneously.

[0014] As a preferred technical solution of this application, it also includes a data recording and recovery analysis subsystem. This subsystem includes a black box module installed at the tail of the rocket body and a ground data recovery station. The black box module consists of an overload-resistant shell, a non-volatile memory, a temperature recorder, and a wireless beacon. It is used to record the time and temperature curves, time and current curves, time and magnetic field strength curves, and changes in the rocket's attitude angle during the entire flight process after launch. The wireless beacon emits positioning signals after the rocket hits the target and after landing to guide ground personnel to recover the black box. The data recovery station reads the data in the black box through wired and wireless interfaces and generates a flight report for subsequent parameter optimization and fault analysis.

[0015] Compared with the prior art, the beneficial effects of the present invention are: Utilizing the aerodynamic heat generated by the rocket's supersonic flight after launch as a trigger source, and leveraging the rapid resistance change characteristics of the CTR thermistor sensor within a temperature range of 80℃ to 160℃, the electromagnetic induction circuit is automatically activated without any external signal input, achieving passive terminal tracking. Simultaneously, by combining infrared detection and over-temperature protection CTR thermistor material with magnetic detection technology previously used only in proximity fuses, the rocket remains in a non-magnetic state during the first half of its flight due to the extremely high resistance of the sensor, avoiding interference from non-target metallic objects mid-flight. This significantly improves the tracking's anti-interference capability and terminal hit accuracy. Attached Figure Description

[0016] Figure 1 This is a block diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the rocket tracking compensator of the present invention; Figure 3 The temperature-resistance relationship diagram for a CIR thermistor sensor; Figure 4 It is an electromagnetic induction circuit. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] This invention provides a technical solution: such as Figure 1 The rocket tracking compensator and system shown include: The rocket body, with a tracking compensator installed at the front end of the rocket body; The launch platform is equipped with a launch device for fixing the rocket body, a human-machine interface for inputting target parameters, and a pre-launch programming interface for data communication with the tracking compensator. The tracking compensator includes: a special battery pack with an output voltage ≥20V, a rated discharge current ≥50A, and an energy storage capacity that can be fully released within 1-3 seconds; The CTR thermistor sensor is made of vanadium oxide matrix material doped with germanium, nickel, and tungsten, and then sintered. Its resistance value ranges from ≥10 ohms in a temperature range of 60℃ to 180℃. 7 Ω drops sharply to ≤10 1 Ω has a negative temperature coefficient of resistance; The electromagnetic induction circuit is composed of the special battery pack, the CTR thermistor sensor, and a solenoid connected in series; the solenoid includes an iron core and a coil wound on the iron core. The iron core is made of soft magnetic material with an initial relative permeability ≥10. 5 The iron core is cylindrical, with an end cap connected to its front end and a concave surface at its rear end. The concave surface is fixed to the convex surface of the rocket body's head by an adhesive. The coil uses a conductive winding with 500 to 800 turns, wound in an annular groove on the iron core; The special battery pack is disposed inside the cavity of the iron core; The CTR thermistor sensor is fixed to the outer end face of the end cover, and its electrode leads pass through the wire channel inside the end cover and the iron core and are electrically connected to the special battery pack and the coil. The end cap is connected to the front end of the iron core via a detachable connection structure. The pre-launch programming interface is connected to the tracking compensator via contact and non-contact data links, and is used to write the target metal type threshold, trigger temperature window, and effective working time limit to the tracking compensator before launch. When the rocket body reaches a speed of 1 to 3 times the speed of sound after launch, aerodynamic heating causes the temperature of the CTR thermistor sensor to rise to 80°C to 160°C, and its resistance value drops sharply. The electromagnetic induction circuit is turned on, and the coil is energized to generate a magnetic field, causing the rocket's front end to generate a magnetic attraction force on the steel target.

[0019] Furthermore, the launch platform can be a portable launcher for individual soldiers, a vehicle-mounted launcher, an airborne launcher, or a shipborne launch device; the human-machine interface includes a touch screen, a rotary encoder, and a voice input module for inputting target distance, target speed, and target metal material; the pre-launch programming interface includes an electrical contact header, an infrared transceiver, and a radio frequency identification module. It also includes a handheld programmer, which is independent of the launch platform and has a built-in target parameter database. The database stores typical metal composition and thermal characteristic parameters of tanks, armored vehicles, ships, and armed helicopters, which are used to write the tracking compensator with one click.

[0020] Furthermore, it also includes a flight status monitoring module, which is installed in the middle and tail of the rocket body and consists of a three-axis accelerometer, a three-axis gyroscope, a barometric altimeter, and a temperature sensor. The flight status monitoring module is connected to the tracking compensator via a single bus and wireless communication. When the flight speed of the rocket body reaches a preset Mach number threshold and the attitude angle deviation of the rocket body is less than ±5°, the flight status monitoring module sends a ready signal to the tracking compensator to reduce the risk of false triggering of the CTR thermistor sensor due to vibration and transient thermal shock.

[0021] Furthermore, it also includes a multi-level trigger control circuit, which is connected in series between the CTR thermistor sensor and the electromagnetic induction circuit. This circuit includes a first comparator, a second comparator, an AND gate circuit, and an electronic switch. The input of the first comparator is connected to the voltage divider signal of the CTR thermistor sensor, and its reference voltage corresponds to a temperature threshold of 80°C. The input of the second comparator is connected to the speed signal output by the flight status monitoring module, and its reference voltage corresponds to Mach 1.5. When both comparators output a high level simultaneously, the AND gate circuit drives the electronic switch to conduct, thus connecting the electromagnetic induction circuit. The multi-level trigger control circuit is encapsulated in a metal shield and filled with thermally conductive potting compound.

[0022] Furthermore, it also includes a terminal correction execution evaluation unit, which consists of a fluxgate magnetometer, a triaxial geomagnetic sensor, and a microcontroller, and is installed inside the tracking compensator and at the tail of the rocket body. The fluxgate magnetometer is used to measure the magnetic field strength generated at the front end of the rocket in real time, and the triaxial geomagnetic sensor is used to measure the direction of the geomagnetic field. The microcontroller has a built-in ballistic correction algorithm. When the detected magnetic field strength reaches ≥0.1T and lasts for ≥10ms, the microcontroller records the current timestamp and rocket attitude, and transmits the hit evaluation data back to the launch platform and command center through the telemetry launch module.

[0023] Furthermore, it also includes a target feature database and an adaptive parameter preset module, which are integrated into the launch platform and the handheld programmer. The target feature database contains typical magnetic susceptibility, equivalent magnetic moment, and attack surface area of ​​ferromagnetic targets. The adaptive parameter preset module automatically calculates the trigger temperature window and effective working time based on the target type selected by the operator, and writes this information into the tracking compensator through the pre-launch programming interface. The formula for calculating the trigger temperature window is: ; ; in The target velocity (m / s) For the target mass (tons), and This is an empirical coefficient.

[0024] Furthermore, it also includes a ground and air multi-unit collaborative combat subsystem, which includes at least two launch platforms, a battlefield relay UAV, and a ground radar station. The battlefield relay UAV and ground radar station are used to detect the position and trajectory of multiple metal targets and send target allocation instructions to each launch platform via data link. Each launch platform automatically sets the trigger parameters of its onboard rocket tracking compensator according to the received target allocation instructions, so as to achieve saturation attack of multiple rockets on the same target and distributed strike of multiple targets.

[0025] Furthermore, it also includes a self-test and status reporting module, which is integrated inside the tracking compensator and consists of a battery voltage detection circuit, a sensor resistance detection circuit, a coil connectivity detection circuit, and a status indicator light. When the rocket body is mounted on the launch platform and not launched, the self-test and status reporting module reports the remaining battery power percentage, sensor room temperature resistance, and coil DC resistance to the launch platform through the pre-launch programming interface. When any parameter is detected to exceed the preset qualified range, the status indicator light flashes red and displays a fault code on the human-machine interface of the launch platform.

[0026] Furthermore, a safety and insurance module is included, which is mechanically connected in series between the special battery pack and the electromagnetic induction circuit. This module includes an inertial safety switch, an electronic safety switch, and a manual safety lever. The inertial safety switch automatically closes when the rocket body experiences a launch overload ≥100g. The electronic safety switch closes when the multi-stage trigger control circuit outputs a conduction signal. The manual safety lever is located on the launch platform and is released by the operator before launch. The special battery pack can only supply power to the electromagnetic induction circuit when all three safety switches are closed simultaneously.

[0027] Furthermore, it also includes a data recording and recovery analysis subsystem, which comprises a black box module installed at the tail of the rocket body and a ground data recovery station. The black box module consists of an overload-resistant shell, a non-volatile memory, a temperature recorder, and a wireless beacon, used to record time and temperature curves, time and current curves, time and magnetic field strength curves, and changes in the rocket's attitude angle throughout the entire flight process after launch. The wireless beacon emits positioning signals after the rocket hits the target and after impact, guiding ground personnel to recover the black box. The data recovery station reads the data from the black box through wired and wireless interfaces and generates flight reports for subsequent parameter optimization and fault analysis.

[0028] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of protection of this application is limited to these examples; within the framework of this application, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of different aspects of one or more embodiments of this application as described above, which are not provided in detail for the sake of brevity.

[0029] One or more embodiments in this application are intended to cover all such substitutions, modifications, and variations that fall within the broad scope of this application. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of one or more embodiments in this application should be included within the protection scope of this application.

Claims

1. A rocket tracking compensator and system, characterized in that, include: The rocket body, with a tracking compensator installed at the front end of the rocket body; The launch platform is equipped with a launch device for fixing the rocket body, a human-machine interface for inputting target parameters, and a pre-launch programming interface for data communication with the tracking compensator. The tracking compensator includes: a special battery pack with an output voltage ≥20V, a rated discharge current ≥50A, and an energy storage capacity that can be fully released within 1-3 seconds; The CTR thermistor sensor is made of vanadium oxide matrix material doped with germanium, nickel, and tungsten, and then sintered. Its resistance value ranges from ≥10 ohms in a temperature range of 60℃ to 180℃. 7 Ω drops sharply to ≤10 1 Ω has a negative temperature coefficient of resistance; The electromagnetic induction circuit is composed of the special battery pack, the CTR thermistor sensor, and a solenoid connected in series; the solenoid includes an iron core and a coil wound on the iron core.

2. The rocket tracking compensator and system according to claim 1, characterized in that: The launch platform can be a portable launcher for individual soldiers, a vehicle-mounted launcher, an airborne launcher, or a shipborne launch device; the human-machine interface includes a touch screen, a rotary encoder, and a voice input module. The pre-transmission programming interface consists of an electrical contact header, an infrared transceiver, and a radio frequency identification module. It also includes a handheld programmer that is independent of the launch platform and has a built-in target parameter database.

3. The rocket tracking compensator and system according to claim 1, characterized in that: It also includes a flight status monitoring module, which is installed in the middle and tail of the rocket body and consists of a three-axis accelerometer, a three-axis gyroscope, a barometric altimeter and a temperature sensor; the flight status monitoring module is connected to the tracking compensator via a single bus and wireless communication.

4. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a multi-level trigger control circuit, which is connected in series between the CTR thermistor sensor and the electromagnetic induction circuit. The multi-level trigger control circuit includes a first comparator, a second comparator, an AND gate circuit, and an electronic switch. The input terminal of the first comparator is connected to the voltage divider signal of the CTR thermistor sensor, and its reference voltage corresponds to a temperature threshold of 80°C. The input terminal of the second comparator is connected to the speed signal output by the flight status monitoring module, and its reference voltage corresponds to Mach 1.

5.

5. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes an end-of-course correction evaluation unit, which consists of a fluxgate magnetometer, a triaxial geomagnetic sensor, and a microcontroller, and is installed inside the tracking compensator and at the tail of the rocket body; the fluxgate magnetometer is used to measure the magnetic field strength generated at the front end of the rocket in real time, the triaxial geomagnetic sensor is used to measure the direction of the geomagnetic field; the microcontroller has a built-in ballistic correction algorithm.

6. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a target feature database and an adaptive parameter preset module, which are integrated into the launch platform and the handheld programmer. The target feature database contains typical magnetic susceptibility, equivalent magnetic moment, and attack surface area of ​​ferromagnetic targets. The adaptive parameter preset module automatically calculates the trigger temperature window and effective working time based on the target type selected by the operator and writes them into the tracking compensator through the pre-launch programming interface. The calculation formula for the trigger temperature window is: ； ； in For the target speed, For target quality, and This is an empirical coefficient.

7. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a ground and air multi-unit collaborative combat subsystem, which includes at least two launch platforms, a battlefield relay UAV, and a ground radar station; the battlefield relay UAV and the ground radar station are used to detect the position and trajectory of multiple metal targets and send target allocation instructions to each launch platform via data link; Each launch platform automatically sets the trigger parameters of its onboard rocket tracking compensator based on the received target allocation instructions.

8. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a self-test and status reporting module, which is integrated inside the tracking compensator and consists of a battery voltage detection circuit, a sensor resistance detection circuit, a coil connectivity detection circuit, and a status indicator light. When the rocket body is mounted on the launch platform and not launched, the self-test and status reporting module reports the remaining battery power percentage, sensor room temperature resistance, and coil DC resistance to the launch platform through the pre-launch programming interface.

9. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a safety and insurance module, which is mechanically connected in series between the special battery pack and the electromagnetic induction circuit. This module includes an inertial safety switch, an electronic safety switch, and a manual safety lever. The inertial safety switch automatically closes when the rocket body experiences a launch overload ≥100g. The electronic safety switch closes when the multi-stage trigger control circuit outputs a conduction signal. The manual safety lever is located on the launch platform and is released by the operator before launch.

10. A rocket tracking compensator and system according to claim 1, characterized in that: It also includes a data recording and recovery analysis subsystem, which comprises a black box module installed at the tail of the rocket body and a ground data recovery station. The black box module consists of an overload-resistant shell, a non-volatile memory, a temperature recorder, and a wireless beacon, used to record time and temperature curves, time and current curves, time and magnetic field strength curves, and changes in the rocket's attitude angle throughout the entire flight process after launch. The wireless beacon emits positioning signals after the rocket hits the target and after impact, guiding ground personnel to recover the black box. The data recovery station reads the data from the black box through wired and wireless interfaces and generates flight reports for subsequent parameter optimization and fault analysis.

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