A multi-power flow controllable phase change booster launcher

Abstract

The invention discloses a multi-power flow controllable phase change booster launcher, comprising a solenoid valve, a barrel, and a ball sleeve as part of a Laval nozzle; the ball sleeve is connected to the front end of the barrel; the Laval nozzle contraction section, the solenoid valve, and the Laval nozzle expansion section are sequentially connected to form a Laval nozzle; the Laval nozzle contraction section is connected to the rear end of the barrel; the barrel is provided with multiple high-pressure chambers, which are filled with liquid carbon dioxide; the high-pressure chambers are provided with a heating device; the barrel serves as a low-pressure chamber; the high-pressure chambers are provided with a diaphragm assembly; both the high-pressure and low-pressure chambers are provided with temperature sensors and pressure sensors to control the start-up time of the heating devices on different high-pressure chambers, realize sequential heating of the high-pressure chambers, and increase the pressure of the low-pressure chambers by controlling the timed heating of the remaining high-pressure chambers. This solves the problem of large overload and impact damage to drones caused by high-pressure gas.

Description

Technical Field

[0001] The present invention belongs to the field of UAV launch test, in particular to a multi-power flow controllable phase change booster launcher. Background Art

[0002] Rocket-assisted drone launch is a zero-length launch method. With the help of a booster rocket, the drone can quickly achieve takeoff speed and a certain altitude. The rocket then detaches, and the drone continues its flight under the power of its engine. This launch method offers excellent maneuverability and low investment costs. It does not require a track and is not restricted by airport conditions. It can also be launched from the ground or from ships, expanding the range of drone applications. Therefore, it is a commonly used drone launch method.

[0003] Rocket boosting usually uses a Laval nozzle to control the thrust, but it cannot adjust the thrust during the boosting process, which is not conducive to the subsequent processing of the propellant grain. The boosting process produces high-temperature and high-pressure gas, which has a great impact and damage on the UAV, and the boosting device structure is complex.

[0004] The dynamic parameters in the interior ballistic model are the most important part of the interior ballistics, affecting the performance and efficiency of the entire propulsion process. Therefore, optimizing the interior ballistic model is an essential step in establishing the interior ballistic model. There are many factors that affect the parameters of the interior ballistic process, which can be optimized by improving the interior ballistic process method.

[0005] When using gas as a working fluid for thrust, as the working fluid in the high-pressure chamber gradually enters the low-pressure chamber, the pressure in the high-pressure chamber will gradually decrease, causing the difference between the pressure in the high-pressure chamber and the pressure in the low-pressure chamber to gradually decrease. The pressure in the low-pressure chamber cannot continue to increase, resulting in insufficient pressure and failure to meet the thrust requirements. Summary of the Invention

[0006] The purpose of the present invention is to provide a multi-power flow controllable phase change booster launcher, which solves the problems of traditional boosters such as short working time, difficulty in achieving multiple starts, and unadjustable Laval nozzle surface-to-throat ratio during the boosting process.

[0007] The technical solutions for achieving the purpose of the present invention are:

[0008] A multi-power flow controllable phase change booster launcher includes a barrel, a ball head cover and a solenoid valve as a part of a Laval nozzle;

[0009] The ball head cover is connected to the front end of the barrel;

[0010] The Laval nozzle convergence section, the solenoid valve, and the Laval nozzle expansion section are sequentially connected to form a Laval nozzle as a whole; the Laval nozzle convergence section is connected to the rear end of the barrel; the solenoid valve is used to control the surface-to-throat ratio of the Laval nozzle and control the gas flow;

[0011] The barrel is provided with a plurality of high-pressure chambers filled with liquid carbon dioxide; the plurality of high-pressure chambers are arranged in a direction parallel to the axial direction of the barrel, and the axial direction of the high-pressure chambers is perpendicular to the axial direction of the barrel;

[0012] The high-pressure chamber is provided with a heating device for heating the liquid carbon dioxide in the high-pressure chamber to complete the transformation of the liquid carbon dioxide from liquid to gas;

[0013] The barrel serves as a low-pressure chamber, and a temperature sensor and a pressure sensor are provided on its front end. A diaphragm assembly is provided on the high-pressure chamber. When the phase change pressure of the liquid carbon dioxide in the high-pressure chamber reaches a set value, the gas breaks through the diaphragm assembly and the high-pressure chamber is injected into the low-pressure chamber.

[0014] The high-pressure chamber is provided with a temperature sensor and a pressure sensor, which serve as both a measuring device for controlling the filling of liquid carbon dioxide and an output device for the pressure and temperature changes of the high-pressure chamber, so as to control the start-up time of the heating devices on different high-pressure chambers and realize the sequential heating of the high-pressure chambers. One of the high-pressure chambers provides an auxiliary driving force. When the pressure of the low-pressure chamber drops to the set value, the timed heating is completed by controlling one or more of the remaining high-pressure chambers to increase the pressure of the low-pressure chamber.

[0015] Compared with the prior art, the present invention has the following significant advantages:

[0016] (1) The present invention takes into account the problems of insufficient boosting force and timely heating boosting in the boosting process, and adopts multiple power units for boosting. First, one of the high-pressure chambers is heated to provide boosting force. When the sensor detects that the pressure of the low-pressure chamber begins to drop, the remaining high-pressure chambers are heated again, thereby further increasing the pressure of the low-pressure chamber until all the high-pressure chambers are heated to meet the boosting task. Through multi-power boosting, the pressure is avoided from being concentrated in the same high-pressure chamber, and the pressure of the low-pressure chamber is increased multiple times, which continuously provides power for the boosting process, meets the final speed requirement under the condition of reducing the maximum value of the overload coefficient, and solves the problem of large overload and impact damage to the UAV caused by high-pressure gas.

[0017] (2) The present invention takes into account the universality of the propulsion indicators of different UAVs, designs the high-pressure chamber, the Laval nozzle contraction section and the Laval nozzle contraction section into modular parts, and replaces the throat of the Laval nozzle with the solenoid valve control to adjust and control the gas mass flow rate. By changing the volume of the high-pressure chamber, the throat area of ​​the nozzle and the surface-to-throat ratio of the Laval nozzle to the solenoid valve channel, the adjustment of UAVs of different masses, different exit velocities and different maximum overload coefficients can be achieved.

[0018] (3) The present invention takes into account the problem that the membrane of the high-pressure chamber cannot be broken after heating. The pressure relief valve interface at the tail of the high-pressure chamber is connected to the pressure relief solenoid valve. The solenoid valve is normally closed and opens after power is turned on to realize pressure relief of the high-pressure chamber.

[0019] (4) The present invention uses liquid carbon dioxide as the actuating fluid and uses a heating device to provide phase change conditions for supercritical carbon dioxide, which will not cause ablation of the booster device and reduce the mass of the total working fluid. At the same time, carbon dioxide can reduce pollution as a clean energy source. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of a multi-power flow controllable phase change booster launcher of the present invention.

[0021] Figure 2 It is a partial diagram of a multi-power flow controllable phase change booster launcher of the present invention.

[0022] Figure 3 It is a schematic diagram of the internal structure of a multi-power flow controllable phase change booster launcher of the present invention.

[0023] Figure 4 This is a schematic diagram of a high-voltage chamber in which electric heating is selected as the heating method.

[0024] Figure 5 This is a schematic diagram of a high-pressure chamber in which gunpowder heating is selected as the heating method.

[0025] Figure 6 This is a schematic diagram of a high-pressure chamber using thermite heating as the heating method.

[0026] Figure 7 It is a schematic diagram of the internal structure of the solenoid valve.

[0027] 1- Laval nozzle expansion section, 2- solenoid valve, 3- Laval nozzle contraction section, 4- barrel, 5- ball head sleeve, 6- charging interface, 7- aviation plug-in, 8- pressure relief valve interface, 9- sensor interface, 10- high-pressure chamber, 11- diaphragm end cover, 12- diaphragm, 13- bolt, 14- electric heating rod, 15- gunpowder heating rod, 16- thermite heating rod, 17- sleeve. DETAILED DESCRIPTION

[0028] The present invention will be further described below with reference to the accompanying drawings and specific embodiments.

[0029] Combine Figure 1-Figure 7The present invention provides a multi-power flow controllable phase change booster launcher, comprising a barrel 4, a ball head cover 5, a heating device, a diaphragm assembly, and a solenoid valve 2 as part of a Laval nozzle; the Laval nozzle comprises a Laval nozzle contraction section 3, the solenoid valve 2, and a Laval nozzle expansion section 1;

[0030] The Laval nozzle contraction section 3 is connected to the rear end of the barrel 4, and the air inlet and outlet ends of the solenoid valve 2 are respectively threadedly connected to the Laval nozzle contraction section 3 and the Laval nozzle expansion section 1, and the three are combined to form a Laval nozzle as a whole; the front end surface of the barrel 4 is provided with the sensor interface 9 for external temperature and pressure sensors, which accurately transmits high-frequency pressure and temperature signals, and can test the changes in low-pressure chamber pressure and temperature during the entire movement of the booster drone during the test.

[0031] The top of the solenoid valve 2 is threadedly connected to the aviation plug-in 7, and the aviation plug-in is externally connected to a power supply. When the solenoid valve is powered off, the valve channel is opened and the airflow passes normally. When the solenoid valve is powered on, the valve channel is closed to prevent the airflow from passing. The movement of the plunger in the solenoid valve is controlled by an external relay, thereby controlling the size of the valve channel, thereby controlling the surface-to-throat ratio of the Laval nozzle, so that the speed of the airflow changes with the change of the spray cross-sectional area, and different assisting forces are obtained.

[0032] The ball head sleeve 5 is welded to the front end of the barrel to enhance the stability of the thrust and control the direction of the thrust. The barrel 4 is provided with multiple high-pressure chambers 10 for filling with liquid carbon dioxide. The arrangement direction of the multiple high-pressure chambers 10 is parallel to the axial direction of the barrel 4, and the axial direction of the high-pressure chamber 10 is perpendicular to the axial direction of the barrel 4; the high-pressure chamber 10 contains four threaded holes, three of which serve as the filling interface 6, the pressure relief valve interface 8 and the sensor interface 9 respectively, and the other threaded hole is connected to the aviation plug-in 7; the filling interface 6 is used to fill liquid carbon dioxide; the pressure relief valve interface 8 is externally connected to the pressure relief valve to control the pressure of the high-pressure chamber. The solenoid valve is normally closed. When powered on, the solenoid valve opens to realize the pressure relief of the high-pressure chamber; the sensor interface 9 is externally connected to the temperature and pressure sensor to test the pressure and temperature of the high-pressure chamber.

[0033] like Figure 4-7 As shown, the heating device includes three types: a thermite heating rod 16, an electric heating rod 11, and a gunpowder heating rod 15. One of these can be selected based on actual needs. The aviation plug-in 7 is threadedly connected to the heating device. When using electric heating, the aviation plug-in is connected to an external power source to heat the electric heating rod. When using gunpowder heating, gunpowder and propellant are pre-loaded inside the heating rod. The aviation plug-in is then connected to an external relay and igniter to ignite the gunpowder and heat it. When using thermite heating, the aviation plug-in 7 is connected to a sleeve 17, which is pre-loaded with aluminum powder. The sleeve 17 is threadedly connected to the thermite heating rod 16, and the nickel-chromium alloy wire inside generates sparks, igniting the aluminum powder and heating it.

[0034] The diaphragm assembly includes a diaphragm end cover 11 and a diaphragm 12. The tail of the high-pressure chamber 10 is connected to the diaphragm assembly via the bolt 13. The upper end of the barrel is threadedly connected to multiple high-pressure chambers 10. The outer end of each high-pressure chamber is provided with a throat, and the throat port is provided with a diaphragm assembly. The diaphragm 12 is press-fitted onto the high-pressure chamber 10 via the annular diaphragm end cover 11. On the one hand, the external sensor of the high-pressure chamber sensor interface 9, as a static pressure measuring device, is mainly used to control the filling of liquid carbon dioxide. During filling, the filling interface fills the liquid carbon dioxide into the high-pressure chamber, observes the sensor signal, and closes the filling interface 6 when the filling pressure is reached, and the filling is completed; on the other hand, it can be used to output the pressure and temperature changes of the high-pressure chamber.

[0035] A remote control controls the heating device to heat the interior of the high-pressure chamber 10. First, one of the high-pressure chambers 10 is heated to provide a boost. When a sensor connected to the barrel detects a drop in the low-pressure chamber (barrel) pressure (reaching a set value), the remaining high-pressure chambers 10 are heated again (by controlling the heating device activation time), further increasing the low-pressure chamber pressure until all high-pressure chambers 10 are heated. After heating, the liquid carbon dioxide undergoes a phase change, and the pressure in the high-pressure chamber 10 continues to rise. When the predetermined rupture pressure is reached, the diaphragm 12 breaks, and high-pressure gas rushes into the low-pressure chamber, reaching the convergent section of the Laval nozzle. Here, the nozzle's cross-sectional area gradually decreases, increasing the gas velocity. The solenoid valve 2 controls the high-pressure gas mass flow rate, propelling the drone to the desired boost speed. Next, the gas enters the divergent section 1 of the Laval nozzle, where its cross-sectional area gradually increases and its velocity decreases. If the diaphragm fails to rupture properly, the high-pressure chamber gas can be released through a pressure relief valve.

[0036] After the experimental device of the present invention is built, the barrel and high-pressure chamber are unscrewed, and the diaphragm with the required rupture pressure is installed on the end face of the high-pressure chamber using bolts; then, the barrel and the high-pressure chamber are screwed back; the barrel and the Laval nozzle contraction section are threaded together, and the solenoid valve is threaded together with the Laval nozzle expansion section and the Laval nozzle contraction section respectively, and the booster is installed in the specified position; the filling interface is opened, and liquid carbon dioxide is filled. The filling pressure is observed by the signal of the high-pressure chamber sensor. When the specified pressure is reached, the filling interface is closed, and the heating device is controlled by a remote switch to increase the temperature inside the high-pressure chamber; the liquid carbon dioxide undergoes a phase change, and the pressure in the high-pressure chamber continues to increase. When the predetermined rupture pressure is reached, the diaphragm is destroyed, and the high-pressure gas rushes into the low-pressure chamber and reaches the Laval nozzle contraction section. In this section, the cross-sectional area of ​​the nozzle gradually decreases, and the gas velocity increases. The solenoid valve controls the mass flow of the high-pressure gas, pushing the drone to take off and reach the required boost speed. Next, the gas enters the Laval nozzle expansion section, where the cross-sectional area of ​​the nozzle gradually increases and the gas velocity decreases.

Claims

1. A multi-power flow controllable phase change booster launcher, characterized in that: Includes the barrel, ball sleeve, and solenoid valve as part of the Laval nozzle; The ball head cover is connected to the front end of the barrel; The Laval nozzle convergence section, the solenoid valve, and the Laval nozzle expansion section are sequentially connected to form a Laval nozzle as a whole; the Laval nozzle convergence section is connected to the rear end of the barrel; the solenoid valve is used to control the surface-to-throat ratio of the Laval nozzle and control the gas flow; The barrel is provided with a plurality of high-pressure chambers filled with liquid carbon dioxide; the plurality of high-pressure chambers are arranged in a direction parallel to the axial direction of the barrel, and the axial direction of the high-pressure chambers is perpendicular to the axial direction of the barrel; The high-pressure chamber is provided with a heating device for heating the liquid carbon dioxide in the high-pressure chamber to complete the transformation of the liquid carbon dioxide from liquid to gas; The barrel serves as a low-pressure chamber, and its front end is equipped with a temperature sensor and a pressure sensor for testing the pressure and temperature changes in the low-pressure chamber. The high-pressure chamber is provided with a diaphragm assembly. When the phase change pressure of the liquid carbon dioxide in the high-pressure chamber reaches a set value, the gas breaks through the diaphragm assembly and completes the injection of the high-pressure chamber into the low-pressure chamber. The high-pressure chamber is provided with a temperature sensor and a pressure sensor, which serve as both a measuring device for controlling the filling of liquid carbon dioxide and an output device for the pressure and temperature changes of the high-pressure chamber, so as to control the start-up time of the heating devices on different high-pressure chambers and realize the sequential heating of the high-pressure chambers. One of the high-pressure chambers provides an auxiliary driving force. When the pressure of the low-pressure chamber drops to the set value, the timed heating is completed by controlling one or more of the remaining high-pressure chambers to increase the pressure of the low-pressure chamber.

2. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The diaphragm assembly comprises a diaphragm end cover and a diaphragm; the diaphragm is press-fitted on the high-pressure chamber through the annular diaphragm end cover.

3. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The high-pressure chamber is provided with a filling interface, an aviation plug-in, and a pressure relief valve interface; the filling interface is used to fill liquid carbon dioxide; the aviation plug-in is used for a heating device; the pressure relief valve interface is used to connect an external pressure relief valve to control the pressure of the high-pressure chamber, and when the diaphragm cannot rupture normally, the gas in the high-pressure chamber is released through the pressure relief valve.

4. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The heating device includes a thermite heating rod.

5. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The heating device comprises an electric heating rod.

6. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The heating device includes a powder heating rod.

7. The multi-power flow controllable phase change booster launcher according to claim 1, characterized in that: The outer end of the high-pressure chamber is provided with a throat, and the diaphragm assembly is arranged at the throat port.

Images