Accurate rocket two-stage electronic time delay ignition device
阅读说明：本技术 一种精确的火箭两级电子延时点火装置 (Accurate rocket two-stage electronic time delay ignition device ) 是由 赵汉青 王浩 刘晓 刘露露 杭佳 梁嘉琪 陈广凯 贾夏冬 梁甜 于 2020-05-13 设计创作，主要内容包括：本发明提供了一种精确的火箭两级电子延时点火装置,包括电源模块、加速度检测模块、AD采集模块、主控模块Ⅰ、安全点火电路Ⅰ、超级电容模块、主控模块Ⅱ及安全点火电路Ⅱ；电源模块、加速度检测模块、AD采集模块、主控模块Ⅰ及安全点火电路Ⅰ构成第一级点火装置；所述超级电容模块、主控模块Ⅱ及安全点火电路Ⅱ构成第二级点火装置；电源模块用于给加速度检测模块、AD采集模块及主控模块Ⅰ供电,并在两级电路分离前给第二级点火装置的主控模块Ⅱ供电,给第二级点火装置的超级电容模块充电。本发明通过两级点火装置控制延时点火时间,不依赖火工品燃烧性能,精确度高。(The invention provides an accurate rocket two-stage electronic delay ignition device which comprises a power supply module, an acceleration detection module, an AD acquisition module, a main control module I, a safe ignition circuit I, a super capacitor module, a main control module II and a safe ignition circuit II, wherein the acceleration detection module is connected with the AD acquisition module; the power supply module, the acceleration detection module, the AD acquisition module, the main control module I and the safe ignition circuit I form a first-stage ignition device; the super capacitor module, the main control module II and the safe ignition circuit II form a second-stage ignition device; the power supply module is used for supplying power to the acceleration detection module, the AD acquisition module and the main control module I, supplying power to a main control module II of the second-stage ignition device before the two-stage circuit separation, and charging the super capacitor module of the second-stage ignition device. The invention controls the delay ignition time through the two-stage ignition device, does not depend on the combustion performance of initiating explosive devices, and has high accuracy.)
1. An accurate rocket two-stage electronic time delay ignition device is characterized by comprising a power supply module, an acceleration detection module, an AD acquisition module, a main control module I, a safe ignition circuit I, a super capacitor module, a main control module II and a safe ignition circuit II;
the power supply module, the acceleration detection module, the AD acquisition module, the main control module I and the safe ignition circuit I form a first-stage ignition device; the super capacitor module, the main control module II and the safe ignition circuit II form a second-stage ignition device;
the power supply module is used for supplying power to the acceleration detection module, the AD acquisition module and the main control module I, supplying power to a main control module II of the second-stage ignition device before the two-stage circuit is separated, and charging a super capacitor module of the second-stage ignition device;
after the power supply module supplies power, the main control module I drives the AD acquisition module to acquire the initiating explosive device resistance of the first-stage ignition device, the acceleration detection module detects the rocket acceleration, and the main control module I controls the initiating explosive device ignition delay time of the first-stage ignition device according to the rocket acceleration and the initiating explosive device resistance of the first-stage ignition device; in the ignition delay time of the initiating explosive device of the first-stage ignition device, the super capacitor module provides ignition energy for the initiating explosive device connected with the safety ignition circuit I to realize first-stage ignition; after the first-stage ignition is successful, the two-stage ignition devices are separated, the super capacitor module discharges to supply power to the main control module II, and ignition energy is provided for the initiating explosive device connected with the safety ignition circuit II according to the delay time set by the main control module II, so that the second-stage ignition is realized.
2. A precision rocket two stage electronic delay ignition device as recited in claim 1, wherein said acceleration detection module comprises an acceleration sensor and a vibration switch for detecting rocket acceleration in two ways.
3. The precise rocket two-stage electronic delay ignition device of claim 1, wherein the main control module I and the main control module II adopt high-speed crystal oscillators to control delay time.
4. The precise rocket two-stage electronic delay ignition device of claim 1, wherein when said AD acquisition module detects the resistance of the initiating explosive device, the current passing through the initiating explosive device is in the uA level; and after the detection is finished, the AD acquisition module is powered off.
Technical Field
The invention relates to the technical field of rocket ignition devices, in particular to an accurate rocket two-stage electronic delay ignition device.
Background
Rockets are widely used in civilian applications. When the civil rocket is launched, electric energy is generally provided to enable initiating explosive devices in the rocket projectile to be detonated at a specified delay time point to realize corresponding functions. The ignition delay time of the traditional civil rocket is related to the combustion performance of initiating explosive devices in the rocket projectile body, the accuracy of the delay time depends on the process of the initiating explosive devices, errors exist, and the function expansion of the civil rocket is restricted.
Disclosure of Invention
In view of the above, the invention provides an accurate rocket two-stage electronic delay ignition device, which controls delay ignition time through two stages of ignition devices, is independent of combustion performance of initiating explosive devices, and has high accuracy.
The technical scheme adopted by the invention is as follows:
an accurate rocket two-stage electronic delay ignition device comprises a power supply module, an acceleration detection module, an AD acquisition module, a main control module I, a safe ignition circuit I, a super capacitor module, a main control module II and a safe ignition circuit II;
the power supply module, the acceleration detection module, the AD acquisition module, the main control module I and the safe ignition circuit I form a first-stage ignition device; the super capacitor module, the main control module II and the safe ignition circuit II form a second-stage ignition device;
the power supply module is used for supplying power to the acceleration detection module, the AD acquisition module and the main control module I, supplying power to a main control module II of the second-stage ignition device before the two-stage circuit is separated, and charging a super capacitor module of the second-stage ignition device;
after the power supply module supplies power, the main control module I drives the AD acquisition module to acquire the initiating explosive device resistance of the first-stage ignition device, the acceleration detection module detects the rocket acceleration, and the main control module I controls the initiating explosive device ignition delay time of the first-stage ignition device according to the rocket acceleration and the initiating explosive device resistance of the first-stage ignition device; in the ignition delay time of the initiating explosive device of the first-stage ignition device, the super capacitor module provides ignition energy for the initiating explosive device connected with the safety ignition circuit I to realize first-stage ignition; after the first-stage ignition is successful, the two-stage ignition devices are separated, the super capacitor module discharges to supply power to the main control module II, and ignition energy is provided for the initiating explosive device connected with the safety ignition circuit II according to the delay time set by the main control module II, so that the second-stage ignition is realized.
Furthermore, the acceleration detection module comprises an acceleration sensor and a vibration switch, and the acceleration of the rocket is detected in a double-path mode.
Furthermore, the main control module I and the main control module II adopt high-speed crystal oscillators to control delay time.
Further, when the AD acquisition module detects the resistance of the initiating explosive device, the current passing through the initiating explosive device is in the uA level; and after the detection is finished, the AD acquisition module is powered off.
Has the advantages that:
1. the invention controls the delay ignition time through the two-stage ignition device, does not depend on the combustion performance of initiating explosive devices, and has high accuracy. Under the conditions that the first-stage ignition device is normally ignited and the power supply cannot supply power after the rocket structure is separated, the function of the second-stage ignition device for ignition at the accurate delay time point can be realized; secondly, the ignition device has low power consumption, a safe ignition circuit and safe and reliable ignition.
2. The acceleration detection module of the invention adopts the acceleration sensor and the vibration switch to detect the rocket acceleration in a double-way manner, thereby realizing redundant backup and improving the detection reliability.
3. According to the invention, the delay time is controlled by the high-speed crystal oscillators in the main control module I and the main control module II, so that the reliability of the delay ignition time is improved.
4. According to the invention, the current level of the initiating explosive device is small, and the AD acquisition module is rapidly powered off after the detection is finished, so that the safety of the initiating explosive device is ensured.
Drawings
FIG. 1 is a schematic block diagram of the present invention;
FIG. 2 is a schematic diagram of an acceleration detection module of the present invention;
FIG. 3 is a schematic diagram of a main control module I of the present invention;
FIG. 4 is a schematic diagram of an AD acquisition module of the present invention;
FIG. 5 is a schematic diagram of a safety ignition circuit I of the present invention;
FIG. 6 is a schematic diagram of a super capacitor module of the present invention;
FIG. 7 is a schematic diagram of a main control module II according to the present invention;
FIG. 8 is a schematic diagram of a safe ignition circuit II of the present invention;
wherein, A-vibration switch and B-acceleration sensor.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides an accurate rocket two-stage electronic delay ignition device, which comprises a power supply module, an acceleration detection module, an AD acquisition module, a main control module I, a safe ignition circuit I, a super capacitor module, a main control module II and a safe ignition circuit II, as shown in figure 1.
The power supply module, the acceleration detection module, the AD acquisition module, the main control module I and the safe ignition circuit I form a first-stage ignition device; and the super capacitor module, the main control module II and the safe ignition circuit II form a second-stage ignition device.
The power supply module is used for supplying power to the acceleration detection module, the main control module I and the AD acquisition module, supplying power to a main control module II of the second-stage ignition device before the two-stage ignition device is separated, and charging the super capacitor module of the second-stage ignition device.
The acceleration detection module is used for detecting rocket acceleration. The acceleration sensor B and the vibration switch A are matched, and the time when the acceleration meets a certain numerical value requirement is used as a timing zero point for starting delay ignition of the main control module I.
The AD acquisition module is used for detecting the initiating explosive device resistance of the first-stage ignition device; when the resistance of the initiating explosive device is detected, the AD acquisition module is rapidly powered off after the detection is finished at the uA level through the current of the initiating explosive device, so that the safety of the initiating explosive device is ensured.
The main control module I controls the initiating explosive device ignition delay time of the first-stage ignition device according to the rocket acceleration and the initiating explosive device resistance of the first-stage ignition device; and the delay time is controlled by adopting a high-speed crystal oscillator, so that whether the resistance value of the initiating explosive device of the first-stage ignition device is normal or not and whether the rocket acceleration meets the requirements or not are judged, and the charging process of the super-capacitor module and the discharging process of the super-capacitor module on the initiating explosive device of the first-stage ignition device are controlled when the requirements are met. If not, the ignition emission is not carried out.
The safety ignition circuit I is connected with the initiating explosive device of the first-stage ignition device and can be connected with more than one initiating explosive device for ensuring the safety of the first-stage ignition.
The super capacitor module is an energy storage element for ignition of initiating explosive devices of the first and second-stage ignition devices, and supplies power to a main control module II of the second-stage ignition device after the two-stage ignition devices are separated.
And the main control module II controls the delay time by adopting a high-speed crystal oscillator and is used for controlling the ignition delay time of the initiating explosive device of the second-stage ignition device.
And the safety ignition circuit II is connected with an initiating explosive device of the second-stage ignition device and is used for ensuring the safety of the second-stage ignition.
After the power supply module supplies power, the main control module I drives the AD acquisition module to acquire the initiating explosive device resistance of the first-stage ignition device, and the acceleration detection module detects the acceleration of the rocket; after the main control module I judges that the resistance value is normal and the rocket acceleration meets the requirement, the super capacitor module is charged, and the super capacitor module provides ignition energy for initiating explosive devices of a first-stage ignition device connected with the safety ignition circuit I through discharging according to the delay time set by the main control module I, so that first-stage ignition is realized; if the resistance value and the rocket acceleration do not meet the requirements, the ignition is not carried out; after the first-stage ignition is successful, the two stages of ignition devices are physically separated, the second-stage ignition device discharges electricity through the super capacitor module to supply power to the main control module II, ignition energy is provided for the initiating explosive device of the second-stage ignition device connected with the safety ignition circuit II according to the delay time set by the main control module II, and the second-stage ignition function is achieved.
As shown in fig. 2, VCC5 in the acceleration detection module is terminated at the output terminal of the power supply module, MISO is terminated at the MISO terminal in the main control module i, and the SCL and SDA terminals are connected to the SCL and SDA terminals in the main control module i, respectively.
As shown in fig. 3, VCC5 in the main control module i is connected to the output terminal of the power supply module, the SCL and SDA terminals are connected to the SCL and SDA terminals in the acceleration detection module, respectively, and the MISO terminal is connected to the MISO terminal in the acceleration detection module; the AD _ ON (NSS) end is connected with the AD _ ON (NSS) end in the AD acquisition module, and the AIN2(ref), AIN3 and AIN4 ends are respectively connected with the AIN2(ref), AIN3 and AIN4 ends in the AD acquisition module; the
As shown in fig. 4, VCC5 in the AD acquisition module is connected to the output terminal of the power supply module, AD _ on (nss) terminal is connected to AD _ on (nss) terminal in the main control module i, AIN2(ref), AIN3, AIN4 terminal are connected to AIN2(ref), AIN3, AIN4 terminal in the main control module i, FireOut1+ and FireOut2+ terminal are connected to the initiating explosive device.
As shown in fig. 5, the
As shown in fig. 6, PWR _ ON and RxAIN6 terminals in the super capacitor module are respectively connected with PWR _ ON and RxAIN6 terminals in the main control module i, VCC5Fire terminal is connected with VCC5Fire terminal in the safety ignition circuit i, and two
As shown in fig. 7, VCC5 and GND terminals in the main control module ii are respectively connected to two
As shown in fig. 8, VCC5 and GND terminals in the safety ignition circuit ii are respectively connected with two
After the first stage of ignition is successful, the two-stage ignition device is physically disconnected from the two
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
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