CN116202367A

CN116202367A - Ballistic target based on electromagnetic ejection auxiliary driving secondary light air cannon

Info

Publication number: CN116202367A
Application number: CN202211713589.0A
Authority: CN
Inventors: 林键; 胡梅晓; 宫建; 朱浩; 屈振乐; 易翔宇; 郭秉楠; 文帅; 孙日明
Original assignee: China Academy of Aerospace Aerodynamics CAAA
Current assignee: China Academy of Aerospace Aerodynamics CAAA
Priority date: 2022-12-29
Filing date: 2022-12-29
Publication date: 2023-06-02
Anticipated expiration: 2042-12-29
Also published as: CN116202367B

Abstract

A ballistic target based on electromagnetic ejection auxiliary driving secondary light gas cannon comprises a high-pressure gas propulsion section, an armature, a piston, an electromagnetic ejection device, a high-pressure pump pipe, a secondary connecting mechanism, a model, a launching pipe, an expansion tank, a test cabin and a measurement and control system; the high-pressure gas propulsion section primary air chamber, the gas pump pipe, the electromagnetic pump pipe of the electromagnetic ejection device, the high-pressure pump pipe, the secondary air chamber of the secondary connecting mechanism, the transmitting pipe, the expansion tank and the test cabin are connected in sequence; the first-stage air chamber releases high-pressure air to drive the armature and the piston to enter the electromagnetic pump pipe through the air pump pipe; the armature pushes the piston to enter the secondary air chamber through the electromagnetic pump pipe and the high-pressure pump pipe under the combined action of the air thrust and the electromagnetic force; the compressed light gas breaks through the secondary membrane, and the driving model enters the test cabin through the transmitting pipe and the expansion tank. The invention adopts high-pressure gas and electromagnetic ejection compound drive, and improves the driving capability of the gas by more than several times; can regulate and improve the inner ballistic characteristics and reduce the manufacturing cost under the same capability.

Description

Ballistic target based on electromagnetic ejection auxiliary driving secondary light air cannon

Technical Field

The application relates to the technical field of ultra-high-speed flight ground simulation tests, in particular to a ballistic target based on electromagnetic ejection auxiliary driving secondary light air cannon.

Background

The ballistic target is aerodynamic ground test equipment for realizing free flight of a pneumatic test model in static gas, can simulate real flight flow conditions, and can be used for carrying out aerodynamic force/heat, aerodynamic physics, ultra-high-speed collision and other test tests. From the perspective of improvement of the ballistic target testing capability and the trend of technology development, there is a need for ultra-high speed ballistic targets that provide larger size models and higher launch speed testing capability.

The traditional ballistic target generally uses a secondary light gas gun as a core launching device, uses gunpowder as a driving source, uses high-pressure gas after the combustion of the gunpowder to push a piston to move at high speed to a high-temperature and high-pressure state to compress light gas (hydrogen or helium) in a pump pipe, and uses the high-pressure light gas to drive a projectile (a model) to reach a required test speed so as to develop test tests such as aerodynamic force/heat, aerodynamic physics, ultra-high-speed collision and the like. Due to limitations in safety, uncertainty and drivability of gunpowder, current gunpowder-driven ballistic targets typically emit at speeds ranging from 2km/s to 6 km/s. In recent years, research is strengthened in the aspects of secondary light gas cannon power sources and the like in China, and secondary cannons driven by high-pressure gas as a first stage (see patent 201310279413.3 of Harbin university of industry), secondary light gas cannons driven by oxyhydrogen detonation as a first stage (see patent 201610989470.4 of Beijing university of technology) and the like are sequentially developed. For a secondary light gas gun driven by hydrogen and oxygen detonation as a first stage, the domestic requirements on flammable gas management are strict, and the technical safety and the test economy are poor; for a secondary light gas gun driven by high-pressure gas as the first stage, the safety is higher than that of gunpowder and oxyhydrogen detonation mode, but the driving capability is weaker. In summary, due to limitations of driving capability, safety and other factors, the diameter of the launching pipe of the traditional secondary light air cannon is smaller, usually below 50mm (the maximum diameter is not more than 210 mm), and the launching speed is difficult to reach or exceed the first cosmic speed (7.9 km/s). Meanwhile, the gas gun system driven by gunpowder gas and compressed gas has the inherent problems that after the projectile is launched, the bottom pressure of the projectile is rapidly reduced, and higher average pressure cannot be provided for the projectile, so that excellent inner ballistic performance cannot be ensured.

Therefore, a novel power source having a strong driving force, high safety and excellent inner ballistic performance is demanded for the ultra-high-speed ballistic target. The coil type electromagnetic ejection device has the characteristics of multistage axial distribution, graded modularized energization and single-stage independent and adjustable electromagnetic coils, and can realize better controllable inner ballistic performance. Chinese patent publication No. CN108759559a, publication date 2018, 11 month 6, the name of the invention is: the application discloses a first-stage drive adopts the second grade light gas gun of electromagnetism big gun, and the security is higher than modes such as gunpowder drive, mixed gas detonation, and is little than high-pressure nitrogen gas drive occupation of land space, firing rate is high, owing to belong to second grade light gas big gun structure, though can realize higher firing rate, its shortcoming is that initially the speed is slow, whole cost is higher (including the pulse power system of energy storage pulse capacitor bank in particular) for traditional drive mode, and the plastic piston is rebound easily near second air chamber when filling the parameter is not ideal and is led to the fact compression inadequately or equipment damage.

Disclosure of Invention

The invention aims to solve the problems of weak driving capability, non-ideal internal ballistic performance, low initial speed of electromagnetic gun driving and high overall manufacturing cost of the conventional ballistic target launching device, explores the potential of an electromagnetic ejection device driving mode, provides a super-high-speed ballistic target which adopts a high-pressure gas and electromagnetic ejection serial type compound driving two-stage light gas gun as a launching device for primary driving, ensures the driving capability to be improved under the super-high-speed launching condition, improves the internal ballistic performance, and provides a safe, clean, efficient and controllable large-caliber test platform for aerodynamic/thermal, pneumatic physical and super-high-speed collision and other tests.

The first aspect provides a ballistic target based on electromagnetic ejection auxiliary driving of a secondary light gas gun, which comprises a high-pressure gas propulsion section, an armature, a piston, an electromagnetic ejection device, a high-pressure pump pipe, a secondary connecting mechanism, a model, a transmitting pipe, an expansion tank, a test cabin and a measurement and control system; wherein,,

the high-pressure gas propulsion section comprises a first-stage gas chamber and a gas pump pipe;

the electromagnetic ejection device comprises an electromagnetic pump pipe, a multi-stage driving coil wound on the electromagnetic pump pipe, an excitation power supply for supplying power to the multi-stage driving coil and a charger for charging the excitation power supply;

the secondary connecting mechanism comprises a secondary air chamber and a secondary diaphragm, the primary air chamber, the air pump pipe, the electromagnetic pump pipe, the high-pressure pump pipe and the secondary air chamber are sequentially connected, the secondary air chamber is connected with the transmitting pipe, the secondary diaphragm is arranged between the secondary air chamber and the transmitting pipe, and the transmitting pipe is sequentially connected with the expansion tank and the test cabin;

an armature and a piston are arranged in the inlet section of the gas pump pipe, the armature is arranged behind the piston, a model is arranged in the inlet section of the transmitting pipe, and the model is arranged in front of the secondary diaphragm;

the primary air chamber releases air to drive the armature and the piston to move forwards to fly out of the air pump pipe and enter the electromagnetic pump pipe;

The exciting power supply is triggered step by step to enable the multistage driving coil to discharge step by step, the armature moves and pushes the piston under the combined action of gas thrust and electromagnetic force generated by the multistage driving coil, and the piston flies out of the electromagnetic pump pipe and enters the high-pressure pump pipe;

the electromagnetic pump pipe, the high-pressure pump pipe and the secondary air chamber in front of the piston are filled with light air, and the light air in the electromagnetic pump pipe, the high-pressure pump pipe and the secondary air chamber breaks the secondary diaphragm under the compression of the piston to push the model to emit out of the emission pipe and enter the test cabin through the expansion tank;

and the measurement and control system is used for determining the triggering moment of each stage of excitation power supply according to the moving speed and the position of the armature.

With reference to the first aspect, in certain implementations of the first aspect, the high pressure gas propulsion section satisfies at least one of:

the gas in the primary gas chamber is air, nitrogen or helium, and the gas pressure is not more than 30MPa;

the primary air chamber is connected with the air pump pipe through a flange structure or an opening sawtooth thread structure;

the total pressure P of the gas in the primary gas chamber after the gas in the primary gas chamber is released _1x And total temperature T _1x The expression of (2) is:

wherein, gamma ₁ P is the specific heat ratio of gas ₁₀ For the initial pressure of the gas, T ₁₀ For the initial temperature of the gas, V ₁₀ Is the initial volume of gas, x is the distance of armature movement, D is the inner diameter of electromagnetic pump tube, V _1x (x) Gas volume for armature movement x distance;

the first-level air chamber comprises a release mechanism, and the release mechanism is a piston type release mechanism or a double-rupture type release mechanism;

the ratio of the volume of the gas pump pipe to the volume of the primary air chamber is more than or equal to 1.0;

the gas pump tube is made of gun steel;

the roughness of the inner wall of the gas pump pipe is Ra less than or equal to 1.6.

With reference to the first aspect, in certain implementations of the first aspect, the electromagnetic ejection device meets at least one of:

the electromagnetic pump pipe is made of a high-strength resin matrix composite material or a high-strength ceramic material, and the maximum working temperature can reach 260 ℃;

the charger adopts an IGBT series resonance constant current charging power supply;

the number of stages of the multistage driving coils of the electromagnetic ejection device is n, and n is more than or equal to 3;

the structural parameters and electromagnetic parameters of the driving coils and the excitation power supply of each stage are the same;

the ratio of the length of each stage of driving coil to the inner diameter of the electromagnetic pump pipe is 0.4-1.7;

the ratio of the distance between the adjacent end surfaces of the adjacent driving coils to the inner diameter of the electromagnetic pump pipe is 0.1-0.3;

The driving coil conductor is made of red copper material, and the outside of the driving coil conductor is coated by an insulating material;

the outer part of the multistage driving coil is entirely covered by a metal layer;

the roughness of the inner wall of the electromagnetic pump pipe is Ra less than or equal to 1.6.

With reference to the first aspect, in certain implementations of the first aspect, the excitation power source includes a storage pulse capacitor bank, a main switch, a freewheel switch; the energy storage pulse capacitor bank is connected with the main switch in series and is connected with the flywheel switch in parallel at two ends of the driving coil, two ends of the energy storage pulse capacitor bank are also connected with two ends of the charger through the charging switch, and the connection and disconnection of the main switch and the charging switch are controlled by the measurement and control system.

With reference to the first aspect, in certain implementations of the first aspect, the excitation power supply satisfies at least one of:

the energy storage pulse capacitor group is formed by combining metallized film self-healing pulse capacitors, and the energy-volume ratio of the metallized film self-healing pulse capacitors is larger than or equal to that of the metallized film self-healing pulse capacitorsEqual to 0.5MJ/m ³ The service life is more than or equal to 1000 times;

the main switch is a spark gap switch or a high-voltage switch consisting of a semiconductor thyristor;

The follow current switch is formed by combining semiconductor high-voltage diodes.

With reference to the first aspect, in certain implementations of the first aspect, the high pressure pump tube meets at least one of:

the high-pressure pump pipe is made of gun steel;

the roughness of the inner wall of the high-pressure pump pipe is Ra less than or equal to 1.6;

the ratio of the mass of the piston to the cross-sectional area of the high-pressure pump pipe is more than 500kg/m ² 。

With reference to the first aspect, in certain implementations of the first aspect, the secondary air chamber satisfies at least one of:

total pressure P of light gas in secondary gas chamber before rupture of membrane of secondary membrane _2x And total temperature T _2x The expression of (2) is:

wherein, gamma ₂ Is the initial specific heat ratio of light gas, P ₂₀ Is the initial pressure of light gas, T ₂₀ The initial temperature of the light gas is that x is the movement distance of the piston, V ₂₀ The initial volume of the light gas is D is the inner diameter of an electromagnetic pump pipe, V _2x (x) The volume of the light gas is x distance of the piston;

the secondary air chamber comprises a large-diameter straight pipe section, a variable-diameter section and a small-diameter straight pipe section, wherein the ratio of the length of the large-diameter straight pipe section to the length of the variable-diameter section is 0.5-1.0, the ratio of the length of the small-diameter straight pipe section to the length of the variable-diameter section is 0.3-0.6, the variable-diameter section adopts a cone structure with a small cone angle, and the cone angle is 6-15 degrees;

The roughness of the inner wall of the secondary air chamber is Ra less than or equal to 0.8;

the second-stage sheet membrane adopts a flat plate structure, and is provided with a cross-shaped four-flap groove or a cross-shaped six-flap groove; the secondary diaphragm material is austenitic stainless steel with tensile strength of more than 500 MPa.

With reference to the first aspect, in certain implementations of the first aspect, the transmitting tube satisfies at least one of:

the launching tube is made of gun steel;

the ratio of the length to the inner diameter of the emitting tube is 240-480;

the roughness of the inner wall of the transmitting tube is Ra less than or equal to 0.8.

With reference to the first aspect, in certain implementations of the first aspect, the measurement and control system includes a central controller, a pulse trigger circuit, and an armature speed measurement device;

the armature speed measuring device comprises a photoelectric sensor body and a plurality of photoelectric probes, the photoelectric probes are arranged on the outer walls of the gas pump pipe, the electromagnetic pump pipe and the high-pressure pump pipe at intervals along the moving direction of the armature, and the photoelectric sensor body is connected with the photoelectric probes through optical fibers;

the photoelectric probe sends pulse optical signals to the armature through holes on the walls of the gas pump pipe, the electromagnetic pump pipe and the high-pressure pump pipe and receives the reflected optical signals, and the photoelectric sensor body converts the optical signals into electric signals and transmits the electric signals to the central controller;

The central controller processes the electric signals to obtain the moment and the speed of the armature passing through the photoelectric probe, and calculates the predicted trigger moment of the stage to be triggered according to a time sequence trigger control method;

and at the predicted triggering moment, the central controller sends a triggering control signal to the pulse triggering circuit, and the pulse triggering circuit outputs power pulse to trigger and conduct the excitation power source of the stage to be triggered, so that the energy storage pulse capacitor bank of the excitation power source of the stage to be triggered discharges through the driving coil.

With reference to the first aspect, in certain implementations of the first aspect, the photoelectric probe is used to detect a rear end of the armature.

With reference to the first aspect, in certain implementations of the first aspect, at least m photoelectric probes G are uniformly disposed axially rearward from a level 1 drive coil centerline _f1 、G _f2 、…、G _fi-1 、G _fi 、…、G _fm-1 、G _fm 1 st photoelectric probe G _f1 The axial distance between the photoelectric probe and the central line of the 1 st-stage driving coil is h/2, the axial distance between the photoelectric probes is h,

v _za for the speed of the armature at the center line of the 1 st stage driving coil in the electromagnetic pump tube, t _m A time interval when the discharge current for the drive coil rises from zero to a maximum value;

at least n photoelectric probes G are uniformly arranged along the axial forward direction from the center line of the 1 st-stage driving coil _z1 、G _z2 、…、G _zj 、G _zj+1 、、…、G _zn-1 、G _zn 1 st photoelectric probe G _z1 A 1 st photoelectric probe G positioned on the tube wall between the 1 st level driving coil and the 2 nd level driving coil _z1 Is spaced from the center line of the 1 st-stage driving coil and is the same as the 1 st photoelectric probe G _z1 The distance between the photoelectric probes and the center line of the 2 nd-stage driving coil is equal, and the axial intervals of the adjacent photoelectric probes are all h.

With reference to the first aspect, in certain implementations of the first aspect,

/>

with reference to the first aspect, in certain implementations of the first aspect, t _m According to

Determining L _d And C is the capacitance value of the energy storage capacitor bank for driving the sum of all self-inductance of the discharge loop before the coil discharge current freewheels through the diode.

With reference to the first aspect, in certain implementation manners of the first aspect, the timing trigger control method includes:

step 1: the primary air chamber releases air to drive the armature to push the piston to move forwards;

step 2: let s=1; i=m when the armature moves past the mth photoelectric probe behind the 1 st stage drive coil centerline; the following steps 2-1 and 2-2 are circularly executed until the 1 st stage excitation power source is triggered:

step 2-1: the armature is spaced from the centerline of the stage 1 drive coil by a distance l as the armature moves past the ith photoelectric probe behind the centerline of the stage 1 drive coil _fi1 = (i-1/2) h, performing measurement by an armature velometer, and performing signal processing by a central controller to obtain the armature speed v at the moment and the position _fi ；

Step 2-2:

if it is

Then at a delay time deltat ₁ Post-triggering the 1 st stage excitation power source, the delay time delta t ₁ The method meets the following conditions: />

Let s=s+1, let i=i-1, jump out of the loop and execute step 3.

If it is

Then no excitation power is ready to be triggered, let i=i-1;

step 3: the following steps 3-1 and 3-2 are circularly executed until the armature passes through the 1 st photoelectric probe behind the center line of the 1 st driving coil;

step 3-1: when the armature moves to the ith photoelectric probe behind the centerline of the 1 st stage driving coil, the distance between the armature and the centerline of the s-th stage driving coil is l _fis = (i+s-3/2) h, performing measurement by the armature velometer, and performing signal processing by the central controller to obtain armature speed v at the moment and the position _fi ；

Step 3-2:

if it is

Immediately triggering an s-th-stage excitation power supply, enabling s to be equal to s+1, and enabling i to be equal to i-1;

if it is

Then at a delay time deltat _s Post-triggering the s-stage excitation power supply, the delay time delta t _s The method meets the following conditions: />

Let s=s+1, let i=i-1;

if it is

Then no excitation power is ready to be triggered, let i=i-1;

step 4: when the armature passes through the center line of the 1 st-stage driving coil and moves to the 1 st photoelectric probe G in front of the center line of the 1 st-stage driving coil _z1 When the excitation power supply of the s-th stage is triggered to be turned on, the moment is t _s The central line distance between the armature and the 1 st stage driving coil is x _s =h/2; the armature speed measuring device is used for measuring, and the central controller is used for signal processing to obtain t _s Armature speed v at this point in time _s ；

Step 5: the following steps 5-1, 5-2 and 5-3 are circularly executed until the time t for turning on the nth stage excitation power supply is obtained _n ：

Step 5-1: at time t _s+1 Triggering and turning on the s+1st-stage excitation power supply at the time t _s+1 The method meets the following conditions:

v _s for time t _s Armature speed, a is armature moving average acceleration, h is center-to-center distance of adjacent two-stage driving coils, t _m A time interval from zero to a maximum value of the discharge current for the driving coil;

step 5-2: by central controlThe time t is calculated by the controller _s+1 The armature is predicted to have a speed of

Step 5-3: let s=s+1.

With reference to the first aspect, in certain implementations of the first aspect, the time t _s+1 The center line distance x between armature and 1 st stage driving coil _s+1 The method meets the following conditions: x is x _s+1 ＝x _s +h-at _m (t _s+1 -t _s )＜x _s +h，x _s For time t _s The armature is spaced from the centerline of the stage 1 drive coil.

With reference to the first aspect, in certain implementations of the first aspect, the armature passes through a jth photoelectric probe G in front of a centerline of the 1 st stage drive coil _zj J+1th photoelectric probe G _zj+1 The time and the speed of the time are respectively t _zj 、v _zj And t _zj+1 、v _zj+1 The armature passes through the j+1st photoelectric probe G in front of the center line of the 1 st driving coil _zj+1 The time and speed predicted value of the time is

With reference to the first aspect, in certain implementations of the first aspect, the ballistic target satisfies at least one of:

the gas pump pipe, the electromagnetic pump pipe and the high-pressure pump pipe are coaxial, have the same inner diameter and have the inner diameter not smaller than 50mm;

the light gas in the gas pump pipe, the electromagnetic pump pipe, the high-pressure pump pipe and the secondary gas chamber in front of the piston is hydrogen or helium, and the gas pressure is 0.01-1.0 MPa; the test gas in the emission tube, the expansion tank and the test cabin in front of the model is air, and the air pressure is 10 Pa-0.2 MPa;

the inlet end of the electromagnetic pump pipe is connected with the outlet end of the gas pump pipe through a flange structure;

the outlet end of the electromagnetic pump pipe is connected with the inlet end of the high-pressure pump pipe through a flange structure;

the ratio of the inner diameters of the gas pump pipe, the electromagnetic pump pipe and the high-pressure pump pipe to the inner diameter of the transmitting pipe is 3-5;

the large-diameter straight pipe section of the secondary air chamber is provided with a convex spigot, one end of the high-pressure pump pipe is provided with a concave spigot, and the concave spigot is matched with the convex spigot of the large-diameter straight pipe section of the secondary air chamber;

The small diameter straight pipe section of the secondary air chamber is provided with a convex spigot, one end of the transmitting pipe is sequentially provided with a concave spigot, a diaphragm groove and a conical groove along the central line, the concave spigot of the transmitting pipe is matched with the convex spigot of the small diameter straight pipe section of the secondary air chamber, the diameter of the concave spigot of the transmitting pipe is larger than that of the diaphragm groove, the secondary diaphragm is arranged in the diaphragm groove, the diameter of the conical groove is gradually reduced from one end of the diaphragm groove, the maximum diameter of the conical groove is smaller than that of the diaphragm groove, and the minimum diameter of the conical groove is equal to the inner diameter of the transmitting pipe;

the ratio of the lengths of the variable diameter sections of the high-pressure pump pipe and the secondary air chamber is 6-20;

when the gas pump pipe, the electromagnetic pump pipe, the high-pressure pump pipe or the transmitting pipe are required to be connected with each other by sections of pipes with the same specification, the sections are connected by adopting a flange structure, a half nut structure or a half clamp structure;

the armature structure is in a form of an integral solid cylinder or a hollow cylinder, and the armature material is aluminum or aluminum alloy.

The piston structure is of a whole cylinder shape or a piston head, a steel counterweight and a piston tail which are sequentially connected into a whole;

the piston material is preferably polyethylene or polytetrafluoroethylene.

The model is a full-caliber model without a bullet holder or a combined model with a bullet holder, when the model is a full-caliber model without a bullet holder, the model enters a test cabin through an expansion tank after being transmitted, and when the model is a combined model with a bullet holder, the combined model consists of a model body and a bullet holder, the bullet holder and the model body are separated in the expansion tank after the model is transmitted, and the model body enters the test cabin;

The expansion tank and the test cabin are provided with a model speed measuring system, a photographic system for measuring the position and the posture of the model, a shadow/schlieren instrument for displaying a flow field and a light radiation measuring system for measuring the light radiation characteristics.

The ballistic target comprises a plurality of supporting mechanisms and a track system, wherein the supporting mechanisms are respectively positioned below the primary air chamber, the air pump pipe, the electromagnetic pump pipe, the high-pressure pump pipe, the expansion tank and the test cabin, and are arranged on the track system and can move along the track;

the speed of the armature at the center line of the 1 st stage driving coil in the electromagnetic pump pipe is v _za At the outlet speed v of the electromagnetic pump pipe _zb ，0＜v _za ＜v _zb ≤1000m/s。

In a second aspect, there is provided a time-sequential trigger control method applied to a ballistic target as described in any one of the implementations of the first aspect above, the method comprising:

Step 2-2:

if it is

Let s=s+1, let i=i-1, jump out of the bookAnd (3) circularly executing the step 3.

If it is

Then no excitation power is ready to be triggered, let i=i-1;

Step 3-2:

if it is

if it is

Let s=s+1, let i=i-1;

if it is

Then no excitation power is ready to be triggered, let i=i-1;

step 4: when the armature passes through the center line of the 1 st-stage driving coil and moves to the 1 st photoelectric probe G in front of the center line of the 1 st-stage driving coil _z1 When the excitation power supply of the s-th stage is triggered to be turned on, the moment is t _s The central line distance between the armature and the 1 st stage driving coil is x _s =h/2; the armature speed measuring device is used for measuring,The central controller performs signal processing to obtain t _s Armature speed v at this point in time _s ；

step 5-2: the time t is calculated by the central controller _s+1 The armature is predicted to have a speed of

Step 5-3: let s=s+1.

Compared with the prior art, the scheme provided by the application at least comprises the following beneficial technical effects:

(1) According to the invention, the first stage of the transmitting device is driven by the electromagnetic catapulting device connected in series after the high-pressure gas, the electromagnetic driving capability is superposed on the basis of fully exerting the driving capability of the high-pressure gas, and the driving capability is improved by a method of increasing the number of stages of the exciting power supply and the driving coil by utilizing the characteristic of multistage energization of the electromagnetic driving device, so that the driving capability is improved by at least several times compared with the driving capability of the pure high-pressure gas. The primary compression pipeline and the secondary launching tube have a certain proportion relation in inner diameter, and the primary driving capability can be improved under the condition of ensuring the same launching speed, so that the caliber of the primary gun tube and the launching tube can be improved, and then the size and the quality of a projectile (model) can be synchronously improved, so that the ultra-high-speed simulation effect of the model is improved.

(2) The single high-pressure gas drive or the single multi-stage electromagnetic drive has the characteristic of the inner ballistic characteristic, the initial stage of projectile launching is fast in acceleration but the bottom pressure is fast reduced when the single high-pressure gas drive is carried out, the higher average pressure can not be provided for the projectile, the inner ballistic performance is poor, and the subsequent hypodynamia is; the initial acceleration is slow when driven by electromagnetic catapulting alone compared with the single high-pressure gas driving. The invention drives the electromagnetic catapulting device in series after the high-pressure gas, can combine the respective driving characteristic advantages of two modes, firstly drives the armature to accelerate rapidly by the high-pressure gas, gives a certain initial speed to the armature when the electromagnetic catapulting is started, and then uses the electromagnetic catapulting device to continuously and efficiently energize. Meanwhile, by utilizing the characteristics of axial distribution, multistage energization, single-stage independent regulation and control of an excitation power supply and a driving coil, and the like, the energy storage and energization scheme is optimized by regulating and controlling the structural parameters and electromagnetic parameters of each stage of circuit, so that the speed and acceleration of a model movement process are more stable and controllable while higher energy conversion efficiency is ensured, and the internal ballistic characteristic is improved by overall regulation and control.

(3) The first-stage driving of the invention adopts a serial structure of the high-pressure gas propulsion section and the electromagnetic ejection device, when the filling parameters are not ideal and the plastic piston rebounds near the second-stage air chamber, the reverse moving piston and the armature compress the gas in the first-stage air chamber, the gas pump pipe, the electromagnetic pump pipe of the electromagnetic ejection device and the high-pressure pump pipe of the high-pressure gas propulsion section in a reverse direction, and the damping effect for buffering the reverse movement of the piston can be achieved due to the air cushion effect of the space such as the first-stage air chamber, so that the piston and the armature gradually and reversely decelerate or oscillate and decelerate until the piston and the armature are stationary, and equipment and pipelines are prevented from being damaged.

(4) Because the cost of electrical equipment such as a pulse power supply system of the energy storage pulse capacitor bank is higher, under the condition of outputting the same kinetic energy, the construction cost of the single electromagnetic ejection driving equipment is higher than that of the single high-pressure gas driving equipment (particularly in a flight ground simulation research institution with complete compressed gas facilities). The invention adopts a serial connection compound mode of high-pressure gas and an electromagnetic ejection device for primary driving, fully exerts the driving capability of the two driving modes, and has lower construction cost than that of single electromagnetic ejection driving equipment under the same driving capability.

(5) The high-pressure gas pressure adopted by the primary driving and the electromagnetic force generated by the discharge induction of the multistage electromagnetic coil are safe, clean and efficient power sources, so that the device is effectively replaced by gunpowder or oxyhydrogen detonation driving, the damage to the device is small, the structural tightness and the safety are higher, no toxic gas is generated in the test, and the environment is not polluted.

(6) With the breakthrough of the bottlenecks of high-energy density energy storage technology, high-voltage switch technology and high-strength new insulating materials, the future synchronous electromagnetic coil propulsion device can realize modularization, miniaturization, light weight and intellectualization, and the electromagnetic thrust has greater and greater advantages as an independent power source or an important part of a power source of a light air gun and a ballistic target.

Drawings

FIG. 1 is a schematic diagram of a ballistic target structure based on electromagnetic ejection auxiliary driving of a secondary light air cannon;

FIG. 2 is a schematic diagram of an electromagnetic ejection device and a timing measurement and control system;

FIG. 3 is a schematic diagram of an armature speed measurement device arrangement and a timing trigger control method;

FIG. 4 is a schematic view of the structure of the high-pressure gas propulsion section;

FIG. 5 is a schematic diagram of the connection structure of the primary air chamber and the air pump pipe;

FIG. 6 is a schematic diagram of a half nut connection structure between sections of a gas pump pipe;

FIG. 7 is a schematic diagram of a connection structure of a gas pump pipe and an electromagnetic pump pipe;

FIG. 8 is a schematic diagram of a flange connection structure between sections of an electromagnetic pump pipe;

FIG. 9 is a schematic diagram of the connection structure of the electromagnetic pump pipe and the high-pressure pump pipe;

FIG. 10 is a schematic view of a flange connection between segments of a high pressure pump tube;

FIG. 11 is a schematic view of a high pressure connection and single membrane mechanism;

FIG. 12 is a schematic view of flange connections between sections of a launch tube;

FIG. 13 is a schematic top view of the expansion tank, test chamber and associated measurement and control device.

Reference numerals illustrate:

1-a high pressure gas propulsion section; 101-a first-level air chamber; 10101-first-order air chamber cavity; 10102-an exhaust chamber; 10103-compensating aperture; 10104-buffer chamber; 10105-one-way valve; 10106-damping chamber; 10107-a spring; 10108-valve body; 10109-intake valve; 10110-exhaust valve; 102-a connection mechanism a; 10201-steel making blue pipe Aa; 10202-steel flange pipe Ab; 10203-steel bolt assembly Ac; 103-a gas pump tube; 10301-gas pump line kth section; 10302-gas pump line kth+1th stage; 104-half nut assembly; 2-an armature; 3-piston; 4-a connecting mechanism B; 401-manufacturing a flange pipe Ba; 402-insulating flanged pipe Bb; 403-bolt assembly Bc; 5-an electromagnetic ejection device; 501-an electromagnetic pump tube; 50101-kth section of electromagnetic pump tube; 50102-the k+1th section of the electromagnetic pump pipe; 502-driving the coil; 503-a metal layer; 504-a charger; 50401-a charge switch; 505-excitation power supply; 50501-a storage pulse capacitor bank; 50502-main switch; 50503—freewheel switch; 506-insulating flange connection mechanism C; 50601-insulating flanged pipe fitting Ca; 50602-insulating flanged pipe Cb; 50603-insulating bolt assembly Cc; 6-a connection mechanism D; 601-insulating flanged pipe fitting Da; 602-manufacturing a flange pipe Db by steel; 603-bolt assembly Dc; 7-a high pressure pump tube; 701-the kth section of the high pressure pump tube; 702-high pressure pump tube section k+1; 703-steel flange connection means E; 70301-steel flange pipe Ea; 70302-steel flange pipe Eb; 70303-steel bolt assembly Ec; 8-a secondary connection mechanism; 801-a secondary air chamber; manufacturing flange pipe fitting Fa by 802-steel; 803-steel flange pipe Fb; 804-steel bolt assembly Fc; 805-a secondary diaphragm; 9-model; 10-emitting tube; 1001-the kth section of the transmitting tube; 1002-the k+1st section of the emission tube; 1003-steel flange connecting mechanism G; 100301-steel flange pipe Ga; 100302-steel flange pipe Gb; 100303-steel bolt assembly Gc; 11-an expansion tank; 1101-expansion tank interface with vacuum system; 1102-an expansion tank side view window; 1103-expansion tank top viewing window; 12-test cabin; 1201-interface of test pod with vacuum system; 1202-test chamber side view window; 1203—test cabin top view window; 13, a measurement and control system; 1301-a central controller; 1302-a pulse triggering circuit; 1303-armature speed measuring device; 130301—a photosensor body; 130302-an optoelectronic probe; 1304-exciting a supply voltage measuring device; 1305-driving a coil current measuring device; 1306-an expansion tank inner model speed measuring device; 1307-a binocular vision measurement system for the expansion tank; 1308-test in-cabin model speed measuring device; 1309-test cabin schlieren; 1310-a test chamber binocular vision measurement system; 1311—test chamber optical radiometer; 14-a supporting mechanism; 15-track system.

Detailed Description

The present application is described in further detail below with reference to the drawings and specific examples.

The present invention will now be described more fully hereinafter with reference to the accompanying drawings. Those of ordinary skill in the art will be able to implement the invention based on these descriptions.

The word "exemplary" is used herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are illustrated in the accompanying drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

As shown in fig. 1, 2 and 7, the ballistic target based on the electromagnetic ejection auxiliary driving secondary light air cannon comprises a high-pressure gas propulsion section 1, an armature 2, a piston 3, an electromagnetic ejection device 5, a high-pressure pump pipe 7, a secondary connecting mechanism 8, a model 9, a transmitting pipe 10, an expansion tank 11, a test cabin 12 and a measurement and control system 13.

The high pressure gas propulsion section 1 comprises a primary air chamber 101 and a gas pump tube 103. The electromagnetic ejection device 5 includes an electromagnetic pump tube 501, a multistage drive coil 502 wound around the electromagnetic pump tube, an excitation power source 505 that supplies power to the multistage drive coil, and a charger 504 that charges the excitation power source. In one embodiment, charger 504 employs an IGBT series resonant constant current charging power supply. The secondary connection 8 includes a secondary air chamber 801. The primary air chamber 101, the air pump pipe 103, the electromagnetic pump pipe 501, the high-pressure pump pipe 7 and the secondary air chamber 801 are connected in sequence. The secondary air chamber 801 is connected with the transmitting tube 10 and a secondary membrane 805 is arranged between the secondary air chamber 801 and the transmitting tube 10; the transmitting tube 10 is connected with the expansion tank 11 and the test cabin 12 in sequence.

The inlet section of the gas pump tube is internally provided with an armature 2 and a piston 3, and the armature 2 is behind the piston 3. The inlet section of the emitter tube 10 has a pattern 9 built in, the pattern 9 being in front of the secondary diaphragm 805. The primary air chamber 101 is filled with high-pressure air. The gas pump tube 103, the electromagnetic pump tube 501, the high-pressure pump tube 7 and the secondary air chamber 801 in front of the piston are filled with light gas. The launch tube 10, expansion tank 11 and test chamber 12 in front of the mold 9 are filled with test gas.

The primary air chamber 101 releases high pressure air, driving the armature 2 and piston 3 forward out of the air pump tube 103. In the electromagnetic pump pipe 501, the armature 2 pushes the piston 3 forward at a high speed under the combined action of the high-pressure gas thrust and the electromagnetic force. The piston 3 passes through the electromagnetic pump pipe 501 and the high-pressure pump pipe 7 to enter the secondary air chamber 801, and simultaneously compresses the light gas. The light gas breaks through the secondary membrane 805, pushing the model 9 to emit at high speed and fly out of the emission tube 10; the model 9 passes through the expansion tank 11 into the test chamber 12.

In one embodiment, the primary air chamber 101 includes a release mechanism, either a piston release mechanism or a dual rupture release mechanism, that acts to isolate the air and to open quickly.

In one embodiment, the ratio of the volume of the gas pump tube 103 to the volume of the primary gas chamber 101 is greater than or equal to 1.0.

In one embodiment, the gas pump pipe 103, the electromagnetic pump pipe 501 and the high-pressure pump pipe 7 are coaxial with each other and have the same inner diameter, and the inner diameter is not smaller than 50mm.

In one embodiment, the ratio of the inner diameters of the gas pump tube 103, the electromagnetic pump tube 501, the high-pressure pump tube 7 and the emitter tube 10 is 3 to 5.

In one embodiment, the air in the first-stage air chamber 101 is released to push the armature 2 and the piston 3 to move in an isentropic expansion mode, and the total air pressure P in the first-stage air chamber 101 _1x And total temperature T _1x The expression of (2) is:

wherein, gamma ₁ P is the specific heat ratio of high-pressure gas ₁₀ For the initial pressure of the high-pressure gas, T ₁₀ For the initial temperature of the high-pressure gas, V ₁₀ Is the initial volume of high-pressure gas, x is the distance of the armature 2, D is the inner diameter of the electromagnetic pump tube, V _1x (x) For the high pressure gas volume at which the armature 2 moves x distance.

In one embodiment, the ratio of the mass of the piston 3 to the cross-sectional area of the high-pressure pump tube 7 is greater than 500kg/m ² 。

In one embodiment, the gas pump tube 103, the high pressure pump tube 7, the firing tube 10 are made of a metallic material, preferably a gun steel material.

In one embodiment, the roughness of the inner walls of the gas pump pipe 103, the electromagnetic pump pipe 501 and the high-pressure pump pipe 7 is Ra.ltoreq.1.6.

In one embodiment, the electromagnetic pump tube 501 is made of an insulating material, preferably a high strength resin matrix composite or a high strength ceramic material, and has a maximum operating temperature of up to 260 ℃.

In one embodiment, the high pressure gas within the primary plenum 101 is high pressure air or high pressure nitrogen or high pressure helium, and the gas pressure is no greater than 30MPa; the gas pump pipe 103, the electromagnetic pump pipe 501, the high-pressure pump pipe 7 and the secondary air chamber 801 in front of the piston 2 adopt light gas which is close to an isentropic compression mode, the light gas can be hydrogen or helium, and the gas pressure is 0.01-1.0 MPa; the test gas in the transmitting tube 10, the expansion tank 11 and the test chamber 12 in front of the piston 3 is air, and the air pressure is 10 Pa-0.2 MPa.

In one embodiment, the total pressure P of the light gas in the secondary air chamber 801 before rupture of the membrane of the secondary diaphragm 805 _2x And total temperature T _2x The expression of (2) is:

/>

wherein, gamma ₂ Is the initial specific heat ratio of light gas, P ₂₀ Is the initial pressure of light gasForce T ₂₀ Is the initial temperature of light gas, x is the movement distance of the piston 3, V ₂₀ Is the initial volume of light gas, D is the inner diameter of the electromagnetic pump pipe 501, V _2x (x) Is the volume of light gas when the piston 3 moves x distance.

In one embodiment, the secondary membrane 805 adopts a flat plate structure, and is provided with a cross-shaped four-lobe groove or a cross-shaped six-lobe groove; the second-stage diaphragm material is austenitic stainless steel with tensile strength of more than 500 MPa.

In one embodiment, the ratio of the length of the emitter tube 10 to the inner diameter is 240 to 480.

In one embodiment, the roughness of the inner wall of the secondary air chamber 801 and the emitter tube 10 is Ra.ltoreq.0.8.

In one embodiment, the armature 2 is of unitary solid cylindrical or hollow cylindrical form, with the armature material being aluminum or an aluminum alloy.

In one embodiment, the piston 3 is in a whole cylinder or a piston head, a steel counterweight and a piston tail which are sequentially connected into a whole; the piston material is preferably polyethylene or polytetrafluoroethylene.

In one embodiment, the number of stages of the driving coil 502 of the electromagnetic ejection device 5 is n, and n is not less than 3. Under the set basic parameter conditions of peak piston speed, average acceleration, pump pipe caliber and the like, the acceleration length, the electric energy-kinetic energy conversion efficiency and the predicted total energy are reasonably estimated, and the reasonable number of stages of the driving coil 502 is determined by combining the limit parameter conditions (voltage resistance, current resistance, stress, temperature rise, equipment cost and the like) of the single-stage driving coil and the exciting power supply and comprehensively considering, so that the efficient and safe acceleration of the armature 2 and the piston 3 is realized. If the number of stages of the driving coil 502 is too small, the single-stage energy is too large, which affects the safety, technical difficulty and cost of the driving coil 502 and the excitation power source 505; if the number of the stages of the driving coil 502 is too large, the single-stage energy is too small, the acceleration length is too long, which is unfavorable for realizing the efficient and rapid acceleration of the armature 2, and the occupied area and the equipment cost of the equipment are greatly increased.

In one embodiment, the ratio of the length of each stage of drive coils 502 to the inside diameter of the electromagnetic pump tube 501 is 0.4 to 1.7, and the ratio of the distance between the facing end surfaces of adjacent stage of drive coils 502 to the inside diameter of the electromagnetic pump tube is 0.1 to 0.3. By reasonably setting the length of the drive coil 502, it is advantageous to bring the mutual inductance gradient and the overall driving capability of the drive coil 502 and the armature 2 within reasonable ranges.

In one embodiment, the drive coil 502 conductors are made of a red copper material, and the drive coil 502 conductors are coated with an insulating material.

In one embodiment, the multistage driver coil is entirely surrounded by a metal layer 503, the metal layer 503 functioning as an electromagnetic shield and as a structural reinforcement for the electromagnetic pump tube 501 and the multistage driver coil.

In one embodiment, as shown in fig. 2, each stage of drive coils 502 is connected to a separate excitation power source 505, the excitation power source 505 comprising a storage pulse capacitor bank 50501, a main switch 50502, and a freewheel switch 50503. The energy storage pulse capacitor bank 50501 may be connected in series with the main switch 50502 and in parallel with the freewheel switch 50503 across the drive coil 502. The two ends of the energy storage pulse capacitor bank 50501 are also connected to the two ends of the charger 504 through the charging switch 50401.

The charger 504 is connected with the energy storage pulse capacitor bank 50501 through a charging switch 50401; before the excitation power source 505 works, the charging switch 50401 is turned on, the charger 504 charges the energy storage pulse capacitor bank 50501, and when the energy storage pulse capacitor bank 50501 is charged to a preset voltage, the charging switch 50401 is turned off, and the charger 504 stops charging.

The excitation power supply 505 realizes the gradual discharge of the excitation power supply 505 by adopting a time sequence trigger control method through the measurement and control system 13. The measurement and control system 13 monitors the voltage information of the excitation power source 505, the current information of the driving coil 502, the pressure and temperature information of the high-pressure gas, the light-weight gas and the test gas through sensors, the movement information of the armature 2 and the piston 3 in the gas pump pipe 103, the electromagnetic pump pipe 501 and the high-pressure pump pipe 7, the movement information of the model in the transmitting pipe 10 and the expansion tank 11, and the movement information, aerodynamic/thermal information, aerodynamic physical information or high-speed collision information of the model in the test chamber 12.

The measurement and control system 13 comprises a central controller 1301, a pulse trigger circuit 1302 and an armature speed measuring device 1303. The central controller 1301 is preferably a digital signal processor DSP or a field programmable gate array FPGA. The armature speed measuring device 1303 comprises a photoelectric sensor body 130301 and photoelectric probes 130302, and a plurality of photoelectric probes 130302 of the armature speed measuring device 1303 are arranged on the walls of the gas pump pipe 103 and the electromagnetic pump pipe 501 at intervals along the armature movement direction; the photoelectric sensor body 130301 is connected with the photoelectric probe 130302 through an optical fiber. The photoelectric probe 130302 of the armature speed measuring device 1303 can send pulse optical signals with certain frequency to the armature through the through holes on the walls of the gas pump tube 103 and the electromagnetic pump tube 501, receive the optical signals reflected from the light reflecting ring, convert the optical signals into electric signals and transmit the electric signals to the central controller.

The central controller 1301 processes the electrical signal to obtain the time and speed at which the armature 2 (specifically, the area where the armature 2 is located at or near the rear end surface, and the rear direction refers to the direction in which the armature 2 is far away from the piston 3) passes through the photoelectric probe 130302, and calculates the predicted trigger time of the stage to be triggered by using the time sequence trigger control method, or queries a pre-stored data table to obtain the predicted trigger time of the stage to be triggered. At the expected trigger time, a trigger control signal is sent to the pulse trigger circuit 1302 by the central controller, and the pulse trigger circuit 1302 outputs a power pulse to conduct the next-stage excitation power source main switch 50502, so that the energy storage pulse capacitor bank 50501 discharges through the driving coil 502. When the energy storage pulse capacitor bank 50501 voltage drops to zero, the freewheel switch 50503 is turned on and the main switch 50502 is turned off, driving the coil 502 freewheel through the freewheel switch 50503 until the discharge current drops to zero. The excitation power supply of each stage works step by step in the same way.

As shown in FIG. 3, at least m photoelectric probes G are uniformly disposed axially rearward from the center line of the 1 st stage driving coil _f1 、G _f2 、…、G _fi-1 、G _fi 、…、G _fm-1 、G _fm . 1 st photoelectric probe G _f1 The axial distance between the photoelectric probe and the central line of the 1 st-stage driving coil is h/2, and the axial distance between the photoelectric probes is h.

v _za Level 1 actuation of armature 2 (in particular, the area of armature 2 at or near the rear face) within solenoid pump tube 501The speed at the center line of the moving coil 502 is h, the axial distance between the center lines of adjacent driving coils is t _m For the time interval when the drive coil discharge current rises from zero to a maximum value. In some embodiments, the exit velocity at solenoid pump line 501 is v _zb ，0＜v _za ＜v _zb Less than or equal to 1000m/s. Preferably->

In some embodiments, t _m Can be according to->

At least n photoelectric probes G are uniformly arranged along the axial forward direction from the center line of the 1 st-stage driving coil _z1 、G _z2 、…、G _zj 、G _zj+1 、…、G _zn-1 、G _zn 1 st photoelectric probe G _z1 A 1 st photoelectric probe G positioned on the tube wall between the 1 st level driving coil and the 2 nd level driving coil _z1 Is spaced from the center line of the 1 st-stage driving coil and is the same as the 1 st photoelectric probe G _z1 Equal to the center line spacing of the 2 nd stage driving coil. The axial intervals of the adjacent photoelectric probes are all h.

The timing trigger control method executed by the central controller may be specifically as follows.

Step 1: before the test, the armature 2 and the piston 3 are preset in the rear end of the gas pump tube 103 at a proper position near the outlet of the primary gas chamber 101. First, the first-stage air chamber 101 exhaust valve 10110 is opened, and the armature velometer 1303 is controlled to emit an optical signal into the tube at a proper frequency. The primary air chamber 101 releases high pressure air to drive the armature 2, the armature 2 pushes the piston 3 to move forward in the air pump tube 103, and the speed of the armature 2 and the piston 3 is continuously increased.

Step 2: to trigger the stage 1 excitation power source, s=1, i=m when the armature 2 moves past the mth photoelectric probe behind the stage 1 drive coil centerline. The following steps 2-1, 2-2 are cyclically performed until the 1 st stage excitation power source is triggered:

step 2-1: when the armature 2 moves past the ith photoelectric probe behind the centerline of the 1 st stage drive coil, the armature 2 is at a distance l from the centerline of the 1 st stage drive coil _fi1 = (i-1/2) h, the armature speed measuring device 1303 performs measurement, and the central controller 1301 performs signal processing to obtain the armature 2 speed v at this time and this position _fi ；

Step 2-2:

if it is

Then at a delay time deltat ₁ Post-triggering stage 1 excitation power supply, delay time delta t ₁ The method meets the following conditions: />

Let s=s+1, let i=i-1, jump out of the present loop and execute step 3;

if it is

Then no excitation power is ready to be triggered, let i=i-1;

until i=1 jumps out of the loop, let s=s+1, and step 3 is performed.

Step 3: the following steps 3-1, 3-2 are cyclically performed until the armature 2 passes the 1 st photo-electric probe behind the 1 st drive coil centerline and through the 1 st drive coil centerline.

Step 3-1: when the armature 2 moves to the ith photoelectric probe behind the centerline of the 1 st stage driving coil, the distance between the armature 2 and the centerline of the s-th stage driving coil is l _fis = (i+s-3/2) h, the armature speed measuring device 1303 performs measurement, and the central controller 1301 performs signal processing to obtain the armature 2 speed v at this time and this position _fi 。

Step 3-2:

if it is

if it is

Then at a delay time deltat _s Post-triggering the s-th stage excitation power supply, delay time delta t _s The method meets the following conditions: />

Let s=s+1, let i=i-1;

if it is

Then no excitation power supply is ready to be triggered, let i=i-1.

Step 4: when the armature 2 passes through the center line of the 1 st stage driving coil and moves to the 1 st photoelectric probe G in front of the center line of the 1 st stage driving coil _z1 When the excitation power supply of the s-th stage is triggered to be turned on, the moment is t _s The central line distance between the armature 2 and the 1 st stage driving coil is x _s =h/2, the measurement is performed by the armature velometer 1303, and the signal processing is performed by the central controller 1301, resulting in t _s At the moment the armature 2 velocity v _s 。

Step 5: the following steps 5-1, 5-2 and 5-3 are circularly executed until the time t for turning on the nth stage excitation power source is obtained _n ：

Step 5-1: at time t _s+1 Triggering and turning on s+1st-stage excitation power supply at time t _s+1 The method meets the following conditions:

v _s for time t _s Armature 2 speed, a is armature 2 moving average acceleration, h is adjacent two-stage driving coil center-to-center spacing, t _m A time interval from zero to a maximum value of the discharge current for the driving coil;

step 5-2: the time t is calculated by the central controller 1301 _s+1 The armature 2 is expected to have a speed of

Taking this predicted speed as time t _s+1 The approximation of the actual speed of the armature 2 can be calculated by the central control unit 1301 at the same time _s+1 The approximate value of the center line distance between the armature 2 and the level 1 driving coil is x _s+1 ＝x _s +h-at _m (t _s+1 -t _s )＜x _s +h；

Step 5-3: let s=s+1.

In some scenarios, the armature 2 passes through the jth photoelectric probe G in front of the centerline of the 1 st stage drive coil _zj J+1th photoelectric probe G _zj+1 The time and the speed of the time are respectively t _zj 、v _zj And t _zj+1 、v _zj+1 Wherein the armature 2 passes in front of the center line of the 1 st stage driving coil, 1 st photoelectric probe G _z1 The time and the speed of the time are respectively t _z1 ＝t _s 、v _z1 ＝v _s The method comprises the steps of carrying out a first treatment on the surface of the The j+1st photoelectric probe G in front of the center line of the 1 st driving coil passing through the armature 2 can be calculated by the central controller _zj+ The time and speed predicted value of the time is

Photoelectric probe G _z2 、…、G _zj 、G _zj+1 、…、G _zn-1 、G _zn The method can be used for measuring the moment and the speed of the armature 2 passing through the corresponding positions and comparing the moment and the speed predicted value calculated by the central controller 1301, so that the monitoring and analysis of the movement state of the armature 2 and the time sequence trigger control effect are facilitated, but the method does not participate in the dynamic control of the time sequence trigger.

Further, the energy storage pulse capacitor group 50501 is formed by combining metallized film self-healing pulse capacitors, and the energy-volume ratio of the metallized film self-healing pulse capacitors is more than or equal to 0.5MJ/m ³ The service life is more than or equal to 1000 times.

Further, the main switch 50502 is a spark gap switch or a high voltage switch composed of a semiconductor thyristor.

Further, the freewheel switch 50503 is formed by combining semiconductor high-voltage diodes.

As shown in fig. 2, the measurement and control system 13 may further include an excitation supply voltage measurement device 1304 and a drive coil current measurement device 1305. The excitation supply voltage measurement device 1304 may be used to monitor the voltage of the storage pulse capacitor bank 50501. The drive coil current measurement device 1305 may be used to monitor the current of the drive coil 502.

High pressure gas propulsion section 1 embodiment:

as shown in fig. 4, the primary air chamber 101 is connected to the air pump pipe 103 via the connection mechanism a 102. The primary air chamber 101 comprises a piston release mechanism, the principle of which is: the high pressure gas enters the exhaust chamber 10102 from the intake valve 10109, and the pressure in the exhaust chamber 10102 continuously rises, so that the valve body piston moves rightward to compress the spring 10107 and finally compress the valve body at the inlet of the first-stage air chamber 101. Simultaneously, the check valve 10105 is opened, high-pressure gas enters the first-stage gas chamber cavity 10101 from the gas exhaust cavity 10102, and the gas inlet valve 10109 is closed after the preset pressure is reached. When releasing is needed, the exhaust valve 10110 is opened, high-pressure gas in the exhaust cavity 10102 is rapidly exhausted, and meanwhile, the gas enters the damping cavity 10106 through the compensation hole 10103. The valve body piston drives the valve body 10108 to move leftwards rapidly under the action of the huge pressure difference at the left end and the right end and the elasticity of the spring 10107, the valve body 10108 leaves the inlet of the first-stage air chamber 101, high-pressure air in the inner cavity 10101 of the first-stage air chamber immediately enters the air pump pipe 103, and the armature 2 is driven to push the piston 3 to move forwards in the air pump pipe 103. When the left end of the valve body enters the buffer chamber 10104, the valve body 10108 is prevented from directly striking the release mechanism due to the compression of the gas in the buffer chamber 10104.

Embodiment of the connection mechanism a102 between the primary air chamber 101 and the air pump tube 103:

as shown in fig. 5, the inlet straight pipe section of the primary air chamber 101 is connected with the left end of the air pump pipe 103 through a connecting mechanism a 102. The straight pipe section of the inlet of the primary air chamber 101 is provided with a concave spigot, the left end of the air pump pipe 103 is provided with a convex spigot, and the connecting mechanism A102 comprises a steel flange pipe Aa10201, a steel flange pipe Ab10202 and a steel bolt component Ac10203. The steel making flanged pipe fitting Aa10201 and the steel making flanged pipe fitting Ab10202 are respectively fixed with the outer surface of the inlet straight pipe section of the primary air chamber 101 and the outer surface of the left end of the air pump pipe 103 by screw threads or welding, and the steel making flanged pipe fitting Aa10201 and the steel making flanged pipe fitting Ab10202 are connected and fastened by a steel bolt assembly Ac10203.

Embodiment of the gas pump tube 103 inter-segment connection mechanism 104:

as shown in fig. 6, the kth section 10301 of the gas pump pipe is adjacent to the kth+1th section of the gas pump pipe, the right end of the kth section 10301 of the gas pump pipe is provided with a concave spigot, the left end of the kth+1th section 10302 of the gas pump pipe is provided with a convex spigot, and the kth section 10301 and the kth section are connected and fastened through a steel half nut assembly 104.

Embodiment of the connection mechanism B4 between the gas pump tube 103 and the electromagnetic pump tube 501:

as shown in fig. 7, the gas pump tube 103 has the same inner diameter as the electromagnetic pump tube 501, and the gas pump tube 103 has a larger wall thickness and the electromagnetic pump tube 501 has a smaller wall thickness. The gas pump tube 103 is connected to the electromagnetic pump tube 501 via a connection mechanism B4. The connection mechanism B4 includes a steel flanged pipe Ba401, an insulating flanged pipe Bb402, and a bolt assembly Bc403. The steel flange pipe fitting Ba401 is fixed with the outer surface of the right end of the gas pump pipe 103 in a threaded or welded mode, the insulating flange pipe fitting Bb402 is fixed with the outer surface of the left end of the electromagnetic pump pipe 501 in an adhesive mode, and the steel flange pipe fitting Ba and the insulating flange pipe fitting Bb402 are connected and fastened through a bolt component Bc403.

Electromagnetic pump pipe 501 inter-segment connection mechanism C506 embodiment:

as shown in fig. 8, the kth segment 50101 of the electromagnetic pump pipe and the kth+1th segment 50102 of the electromagnetic pump pipe are adjacent to each other and connected to each other by an insulating flange connection mechanism C506. The insulating flange pipe fitting Ca 50601 with the concave spigot and the insulating flange pipe fitting Cb 50602 with the convex spigot are respectively adhered and fixed with the outer surface of the left end of the kth segment 50101 of the electromagnetic pump pipe and the outer surface of the right end of the (k+1) th segment 50102 of the electromagnetic pump pipe, and the insulating flange pipe fitting Ca 50601 with the concave spigot and the insulating flange pipe fitting Cb 50602 with the convex spigot are connected and fastened through an insulating bolt component Cc 50603.

Electromagnetic pump pipe 501 and high pressure pump pipe 7 connection mechanism D6 embodiment:

as shown in fig. 9, the electromagnetic pump pipe 501 has the same inner diameter as the high-pressure pump pipe 7, and the high-pressure pump pipe 7 has a large wall thickness, and the electromagnetic pump pipe 501 has a small wall thickness. The electromagnetic pump pipe 501 is connected to the high-pressure pump pipe 7 through a connection mechanism D6. The connection mechanism D6 includes an insulating flanged pipe member Da601, a steel flanged pipe member Db602, and a bolt assembly Dc603. The insulating flange pipe fitting Da601 is fixed with the outer surface of the right end of the electromagnetic pump pipe 501 in an adhesive mode, the steel flange pipe fitting Db602 is fixed with the outer surface of the left end of the high-pressure pump pipe 7 in a threaded or welding mode, and the insulating flange pipe fitting Da601 and the steel flange pipe fitting Db602 are connected and fastened through a bolt component Dc603.

High pressure pump pipe 7 inter-segment connection E703 embodiment:

as shown in fig. 10, the kth section 701 of the high-pressure pump pipe is adjacent to the kth+1st section 702 of the high-pressure pump pipe, and a female spigot arranged at the right end of the kth section 701 of the high-pressure pump pipe is matched with a male spigot arranged at the left end of the kth+1st section 702 of the high-pressure pump pipe; the steel flange pipe Ea70301 and the steel flange pipe Eb70302 are respectively fixed with the outer surface of the right end of the k section 701 of the high-pressure pump pipe and the outer surface of the left end of the k+1 section 702 of the high-pressure pump pipe in a threaded or welded mode, and are connected and fastened through a steel bolt component Ec 70303.

High pressure pump tube 7, two-stage connection 8, model 9, emitter tube 10 embodiment:

as shown in fig. 11, the transmitting tube 10 is provided with a concave spigot, a diaphragm groove and a conical groove in sequence along the central line from the left end to the right, the diameter of the concave spigot is larger than that of the diaphragm groove, and the secondary diaphragm 805 is arranged in the diaphragm groove; the diameter of the conical groove is gradually reduced from one end of the diaphragm groove, the maximum diameter of the conical groove is smaller than the diameter of the diaphragm groove, and the minimum diameter of the conical groove is equal to the inner diameter of the transmitting tube 10; the concave spigot arranged at the left end of the transmitting tube 10 is matched with the convex spigot of the small-diameter straight tube section of the secondary air chamber 801; the convex spigot of the large-diameter straight pipe section of the secondary air chamber 801 is matched with the concave spigot arranged at the right end of the high-pressure pump pipe 7.

The secondary air chamber 801 of the secondary connecting mechanism 8 comprises a large-diameter straight pipe section, a reducing section and a small-diameter straight pipe section, wherein the large-diameter straight pipe section and the small-diameter straight pipe section are respectively provided with a convex spigot; the diameter-variable section adopts a cone structure with a small cone angle, and the cone angle is 6-15 degrees.

In some embodiments, the ratio of the large diameter straight pipe section to the variable diameter section length is 0.5 to 1.0.

In some embodiments, the ratio of the small diameter straight tube section to the variable diameter section length is 0.3 to 0.6.

In one embodiment, the ratio of the length of the variable diameter section of the high-pressure pump pipe 7 to the length of the secondary air chamber 801 is 6 to 20.

Embodiment of the coupling mechanism between segments of the launch tube 10:

as shown in fig. 12, the kth section 1001 of the transmitting tube is adjacent to the kth+1th section 1002 of the transmitting tube, and a female spigot provided at the right end of the kth section 1001 of the transmitting tube is adapted to a male spigot provided at the left end of the kth+1th section 1002 of the transmitting tube; the steel flange pipe Ga100301 and the steel flange pipe Gb100302 are respectively fixed with the outer surface of the right end of the k 1001 of the transmitting pipe and the outer surface of the left end of the k+1th 1002 of the transmitting pipe in a threaded or welded mode, and are connected and fastened through a steel bolt component Gc 100303.

Expansion tank, test cabin and related measurement and control device embodiments:

as shown in FIG. 13, the expansion tank 11 and the test chamber 12 are filled with air having a pressure in the range of 10Pa to 0.2 MPa. The expansion tank 11 is provided with a vacuum system interface 1101, a plurality of side optical windows 1102 and a top optical window 1103, a plurality of expansion tank internal model speed measuring devices 1306 are arranged on the side parts, and a plurality of expansion tank binocular vision measuring systems 1307 for measuring the separation dynamic process of the combined model bullet holder and the model body are arranged on the side parts and the top parts; the test chamber 12 is provided with a vacuum system interface 1201, a plurality of side optical windows 1202 and a top optical window 1203, a plurality of test chamber model speed measuring devices 1308 are arranged on the side, a flow field display schlieren 1309 and an optical radiation measuring system 1311 for measuring optical radiation characteristics are arranged on the side, and a binocular vision measuring system 1310 for measuring model flying postures is arranged on the side and the top.

In one embodiment, the ballistic target comprises a plurality of support mechanisms 14 and a rail system 15, the support mechanisms 14 are respectively positioned below the primary air chamber 101, the air pump tube 103, the electromagnetic pump tube 501, the high pressure pump tube 7, the launch tube 10, the expansion tank 11 and the test chamber 12, and the support mechanisms 14 are mounted on the rail system 15 and can move along the rails.

In one embodiment, the model 9 is a full caliber model without a spring holder or a combination model with a spring holder; when the model 9 is a full-caliber model without a spring holder, the model 9 enters a test cabin through an expansion tank after being transmitted; when the model is a combined model with a bullet holder, the combined model is composed of a model body and a bullet holder, the bullet holder and the model body are separated in an expansion tank after the model 9 is launched, and the model body enters a test cabin.

In one embodiment, the expansion tank 11 and the test chamber 12 are equipped with a model speed measuring system, a camera system for measuring the position of the model and its posture, a shadow/schlieren for flow field display, and an optical radiation measuring system for measuring optical radiation characteristics.

The working principle of the invention is as follows:

before the test, the armature 2 and the piston 3 were placed in the left end of the gas pump tube 103 in a proper position near the outlet of the primary gas chamber 101. The first-stage air chamber 101 is pre-filled with high-pressure air or high-pressure nitrogen or high-pressure helium with pressure not more than 30MPa, and the gas pump pipe 103, the electromagnetic pump pipe 501, the high-pressure pump pipe 7 and the second-stage air chamber 801 in front of the piston 2 are pre-filled with hydrogen or helium with pressure of 0.01-1.0 MPa, and the emission pipe 10, the expansion tank 11 and the test cabin 12 in front of the piston 3 are pre-filled with air with pressure of 10 Pa-0.2 MPa.

In the test, the first-stage air chamber 101 exhaust valve 10110 is first opened, and the armature velometer 1303 is controlled to emit an optical signal into the air pump tube 103 at a proper frequency. The primary air chamber 101 releases high pressure air to drive the armature 2 to push the piston 3 to move forwards in the air pump tube 103, and the speed of the armature 2 and the piston 3 is continuously increased. The armature 2 has a certain initial velocity as the armature 2 moves past the mth photoelectric probe behind the centerline of the stage 1 drive coil. The armature speed measuring device 1303 performs measurement, the central controller 1301 performs signal processing, and the relevant steps of the time sequence trigger control method are circularly executed, so that the 1 st stage predicted trigger time is obtained through calculation. At the stage 1 predicted trigger time, a trigger control signal is sent to the pulse trigger circuit 1302 by the central controller 1301, the stage 1 excitation power source main switch 50502 is conducted by the output power pulse of the pulse trigger circuit 1302, the stage 1 energy storage pulse capacitor group 50501 is discharged through the stage 1 driving coil 502, after the energy storage pulse capacitor group 50501 is reduced to zero, the driving coil 502 freewheels through the freewheel switch 50503, and the pulse current excites the pulse magnetic field to enable the armature 2 to generate vortexCurrent and electromagnetic force are applied. After the 1 st stage is triggered, the armature 2 pushes the piston 3 to move forwards under the combined action of the gas thrust and the electromagnetic force of the 1 st stage driving coil. And continuously executing relevant steps of the time sequence trigger control method, triggering a plurality of stages of excitation power supplies, and enabling the armature 2 to move under the combined action of gas thrust and electromagnetic force of a plurality of stages of conducted and discharged driving coils, passing through a 1 st photoelectric probe behind the center line of the 1 st driving coil and passing through the center line of the 1 st driving coil. At time t _s The armature 2 moves to the 1 st photoelectric probe in front of the center line of the 1 st driving coil, the s-th excitation power supply is triggered and conducted, and the speed v of the armature 2 at the moment is obtained through speed measurement _s . Time t _s Thereafter, the armature 2 is subjected to a uniform acceleration movement substantially according to a substantially constant acceleration, at the moment

Triggering and switching on the s+1th stage excitation power supply, and circularly executing relevant steps of the time sequence triggering control method until the nth stage excitation power supply is switched on. In the process of uniform acceleration movement, the armature 2 pushes the piston 3 to move forwards under the combined action of electromagnetic force and gas thrust of the rear end face and light gas resistance of the front end face, and the armature flies out of the electromagnetic pump pipe 501 at a high speed and enters the high-pressure pump pipe 7. The piston 3 enters the secondary air chamber 801 through the high-pressure pump pipe 7, and simultaneously compresses the light gas to a high-temperature and high-pressure state; the light gas high pressure breaks the secondary membrane 805, pushing the mold 9 to launch out of the launch tube 10 at high speed. When the model 9 is a full-caliber model without a spring holder, the model enters a test cabin 12 through an expansion tank 11 after being launched; when the model 9 is a combined model with a spring holder, the spring holder and the model body are separated in the expansion tank 11, and the model body enters the test cabin 12.

The invention has been described in detail in connection with the specific embodiments and exemplary examples thereof, which are intended to be illustrative and not limiting, and are not to be construed as limiting the scope of the invention. It will be understood by those skilled in the art that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, and these fall within the scope of the present invention. The scope of the invention is defined by the appended claims. What is not described in detail in the present specification is a well known technology to those skilled in the art.

Claims

1. The ballistic target based on the electromagnetic ejection auxiliary driving secondary light air cannon is characterized by comprising a high-pressure gas propulsion section (1), an armature (2), a piston (3), an electromagnetic ejection device (5), a high-pressure pump pipe (7), a secondary connecting mechanism (8), a model (9), a transmitting pipe (10), an expansion tank (11), a test cabin (12) and a measurement and control system (13); wherein,,

the high-pressure gas propulsion section (1) comprises a primary air chamber (101) and a gas pump pipe (103);

the electromagnetic ejection device (5) comprises an electromagnetic pump pipe (501), a multi-stage driving coil (502) wound on the electromagnetic pump pipe (501), an excitation power supply (505) for supplying power to the multi-stage driving coil (502) and a charger (504) for charging the excitation power supply (505);

the secondary connecting mechanism (8) comprises a secondary air chamber (801) and a secondary membrane (805), wherein the primary air chamber (101), the air pump pipe (103), the electromagnetic pump pipe (501), the high-pressure pump pipe (7) and the secondary air chamber (801) are sequentially connected, the secondary air chamber (801) is connected with the transmitting pipe (10), the secondary membrane (805) is arranged between the transmitting pipe and the transmitting pipe, and the transmitting pipe (10) is sequentially connected with the expansion tank (11) and the test cabin (12);

an armature (2) and a piston (3) are arranged in the inlet section of the gas pump pipe (103), the armature (2) is arranged behind the piston (3), a model (9) is arranged in the inlet section of the emission pipe (10), and the model (9) is arranged in front of the secondary membrane (805);

The primary air chamber (101) releases the air driving armature (2) and the piston (3) to move forwards to fly out of the air pump pipe (103) and enter the electromagnetic pump pipe (501);

the exciting power supply (505) is triggered step by step to enable the multistage driving coil (502) to discharge step by step, the armature (2) moves and pushes the piston (3) under the combined action of gas thrust and electromagnetic force generated by the multistage driving coil (502), and the piston (3) flies out of the electromagnetic pump pipe (501) and enters the high-pressure pump pipe (7);

the electromagnetic pump pipe (501), the high-pressure pump pipe (7) and the secondary air chamber (801) in front of the piston (3) are filled with light gas, and the light gas in the electromagnetic pump pipe (501), the high-pressure pump pipe (7) and the secondary air chamber (801) breaks through the secondary diaphragm (805) under the compression of the piston (3) to push the model (9) to emit and fly out of the emission pipe (10) and enter the test cabin (12) through the expansion tank (11);

the measurement and control system (13) is used for determining the triggering moment of each stage of excitation power supply (505) according to the moving speed and the moving position of the armature (2).

2. Ballistic target according to claim 1, wherein the high pressure gas propulsion section (1) fulfils at least one of the following:

The gas in the primary air chamber (101) is air, nitrogen or helium, and the gas pressure is not more than 30MPa;

the primary air chamber (101) is connected with the air pump pipe (103) through a flange structure or an opening sawtooth thread structure;

the total pressure P of the gas in the primary air chamber (101) after the gas in the primary air chamber (101) is released _1x And total temperature T _1x The expression of (2) is:

wherein, gamma ₁ P is the specific heat ratio of gas ₁₀ For the initial pressure of the gas, T ₁₀ For the initial temperature of the gas, V ₁₀ Is the initial volume of gas, x is the distance of the armature (2) to move, D is the inner diameter of an electromagnetic pump pipe (501), V _1x (x) A volume of gas when the armature (2) is moved x distance;

the primary air chamber (101) comprises a release mechanism, and the release mechanism is a piston type release mechanism or a double-rupture type release mechanism;

the ratio of the volume of the gas pump pipe (103) to the volume of the primary air chamber (101) is more than or equal to 1.0;

the gas pump tube (103) is made of gun steel;

the roughness of the inner wall of the gas pump pipe (103) is Ra less than or equal to 1.6.

3. Ballistic target according to claim 1, wherein the electromagnetic ejection device (5) fulfils at least one of the following:

the electromagnetic pump pipe (501) is made of a high-strength resin matrix composite material or a high-strength ceramic material, and the highest working temperature can reach 260 ℃;

The charger (504) adopts an IGBT series resonance constant current charging power supply;

the number of stages of the multistage driving coils (502) of the electromagnetic ejection device (5) is n, and n is more than or equal to 3;

the structural parameters and electromagnetic parameters of the driving coils (502) and the excitation power supply (505) of each stage are the same;

the ratio of the length of each stage of driving coil (502) to the inner diameter of the electromagnetic pump pipe (501) is 0.4-1.7;

the ratio of the distance between the adjacent end surfaces of the adjacent driving coils (502) to the inner diameter of the electromagnetic pump pipe (501) is 0.1-0.3;

the conductor of the driving coil (502) is made of red copper material, and the outside of the conductor of the driving coil (502) is coated by insulating material;

the whole exterior of the multistage driving coil (502) is covered by a metal layer;

the roughness of the inner wall of the electromagnetic pump pipe (501) is Ra less than or equal to 1.6.

4. The ballistic target of claim 1, wherein the excitation power source (505) comprises a storage pulse capacitor bank (50501), a main switch (50502), a freewheel switch (50503); the energy storage pulse capacitor bank (50501) is connected with the main switch (50502) in series and is connected with the follow current switch (50503) in parallel at two ends of the driving coil (502), two ends of the energy storage pulse capacitor bank (50501) are further connected with two ends of the charger (504) through the charging switch (50401), and the connection and disconnection of the main switch (50502) and the charging switch (50401) are controlled through the measurement and control system (13).

5. The ballistic target of claim 1, wherein the excitation power source (505) satisfies at least one of:

the energy storage pulse capacitor group (50501) is formed by combining metallized film self-healing pulse capacitors, and the energy volume ratio of the metallized film self-healing pulse capacitors is more than or equal to 0.5MJ/m ³ The service life is more than or equal to 1000 times;

the main switch (50502) is a spark gap switch or a high voltage switch consisting of a semiconductor thyristor;

the freewheel switch (50503) is formed by combining semiconductor high-voltage diodes.

6. Ballistic target according to claim 1, wherein the high pressure pump tube (7) fulfils at least one of the following:

the high-pressure pump pipe (7) is made of gun steel;

the roughness of the inner wall of the high-pressure pump pipe (7) is Ra less than or equal to 1.6;

the ratio of the mass of the piston (3) to the cross-sectional area of the high-pressure pump pipe (7) is greater than 500kg/m ² 。

7. The ballistic target according to claim 1, wherein the secondary air chamber (801) fulfils at least one of the following:

the total pressure P of light gas in the secondary air chamber (801) before membrane rupture of the secondary membrane (805) _2x And total temperature T _2x The expression of (2) is:

/>

wherein, gamma ₂ Is the initial specific heat ratio of light gas, P ₂₀ Is the initial pressure of light gas, T ₂₀ Is light in weightThe initial temperature of the gas, x is the movement distance of the piston (3), V ₂₀ Is the initial volume of light gas, -D is the inner diameter of an electromagnetic pump pipe (501), V _2x (x) A light gas volume when the piston (3) moves x distance;

the secondary air chamber (801) comprises a large-diameter straight pipe section, a variable-diameter section and a small-diameter straight pipe section, the ratio of the length of the large-diameter straight pipe section to the length of the variable-diameter section is 0.5-1.0, the ratio of the length of the small-diameter straight pipe section to the length of the variable-diameter section is 0.3-0.6, the variable-diameter section adopts a cone structure with a small cone angle, and the cone angle is 6-15 degrees;

the roughness of the inner wall of the secondary air chamber (801) is Ra less than or equal to 0.8;

the secondary membrane (805) adopts a flat plate structure, and is provided with a cross-shaped four-lobe groove or a cross-shaped six-lobe groove; the material of the secondary membrane (805) is austenitic stainless steel with tensile strength of more than 500 MPa.

8. Ballistic target according to claim 1, wherein the launch tube (10) fulfils at least one of the following:

the launching tube (10) is made of gun steel material;

the ratio of the length to the inner diameter of the emitting tube (10) is 240-480;

the roughness of the inner wall of the transmitting tube (10) is Ra less than or equal to 0.8.

9. The ballistic target according to claim 1, wherein the measurement and control system (13) comprises a central controller (1301), a pulse trigger circuit (1302) and an armature tachometer (1303);

The armature speed measuring device (1303) comprises a photoelectric sensor body (130301) and a plurality of photoelectric probes (130302), the photoelectric probes (130302) are arranged on the outer walls of the gas pump pipe (103), the electromagnetic pump pipe (501) and the high-pressure pump pipe (7) at intervals along the moving direction of the armature (2), and the photoelectric sensor body (130301) is connected with the photoelectric probes (130302) through optical fibers;

the photoelectric probe (130302) sends pulse optical signals to the armature (2) through holes on the pipe walls of the gas pump pipe (103), the electromagnetic pump pipe (501) and the high-pressure pump pipe (7) and receives reflected optical signals, and the photoelectric sensor body (130301) converts the optical signals into electric signals and transmits the electric signals to the central controller (1301);

the central controller (1301) processes the electric signals to obtain the time and the speed of the armature (2) passing through the photoelectric probe (130302), and obtains the predicted triggering time of the stage to be triggered by resolving according to a time sequence triggering control method;

and at the expected triggering moment, the central controller (1301) sends a triggering control signal to the pulse triggering circuit (1302), and the pulse triggering circuit (1302) outputs power pulses to trigger and conduct the to-be-triggered stage excitation power supply (505) so that the energy storage pulse capacitor bank (50501) of the to-be-triggered stage excitation power supply (505) discharges through the driving coil (502).

10. Ballistic target according to claim 9, wherein the optoelectronic probe (130302) is used for detecting the rear end of the armature (2).

11. Ballistic target according to claim 9 or 10, characterized in that at least m photoelectric probes G are evenly arranged axially rearwards from the centre line of the level 1 drive coil (502) _f1 、G _f2 、…、G _fi-1 、G _fi 、…、G _fm-1 、G _fm 1 st photoelectric probe G _f1 The axial distance between the photoelectric probe and the central line of the 1 st-stage driving coil is h/2, the axial distance between the photoelectric probes is h,

v _za for the velocity, t, of the armature (2) at the centerline of the stage 1 drive coil within the solenoid pump tube (501) _m A time interval when the discharge current for the drive coil rises from zero to a maximum value; />

At least n photoelectric probes G are uniformly arranged along the axial forward direction from the center line of the 1 st-stage driving coil _z1 、G _z2 、…、G _zj 、G _zj+1 、…、G _zn-1 、G _zn 1 st photoelectric probe G _z1 At level 1 drive coilOn the tube wall between the 2 nd-stage driving coils, the 1 st photoelectric probe G _z1 Is spaced from the center line of the 1 st-stage driving coil and is the same as the 1 st photoelectric probe G _z1 The distance between the photoelectric probes and the center line of the 2 nd-stage driving coil is equal, and the axial intervals of the adjacent photoelectric probes are all h.

12. The ballistic target of claim 11 wherein the ballistic target is a high-density ballistic target,

13. the ballistic target of claim 11, wherein t _m According to

14. The ballistic target of claim 11 wherein the time sequence trigger control method comprises:

step 1: the primary air chamber (101) releases air to drive the armature (2) to push the piston (3) to move forwards;

step 2: let s=1; i=m when the armature (2) moves past the mth photoelectric probe behind the 1 st stage drive coil centerline; the following steps 2-1 and 2-2 are circularly executed until the 1 st stage excitation power source (505) is triggered:

step 2-1: when the armature (2) moves past the ith photoelectric probe behind the centerline of the 1 st stage driving coil, the armature (2) is separated from the centerline of the 1 st stage driving coil by a distance l _fi1 = (i-1/2) h, the armature speed measuring device (1303) performs measurement, and the central controller (1301) performs signal processing to obtain the armature (2) speed v at the moment and the position _fi ；

Step 2-2:

if it is

Then at a delay time deltat ₁ Post-triggering a stage 1 excitation power source (505), the delay time Deltat ₁ The method meets the following conditions: />

Let s=s+1, let i=i-1, jump out of the present loop and execute step 3;

if it is

Then no excitation power supply is ready to be triggered (505), let i=i-1;

Step 3: the following steps 3-1 and 3-2 are circularly executed until the armature (2) passes through the 1 st photoelectric probe behind the center line of the 1 st driving coil;

step 3-1: when the armature (2) moves to the ith photoelectric probe behind the centerline of the 1 st stage driving coil, the distance between the armature (2) and the centerline of the s-th stage driving coil is l _fis = (i+s-3/2) h, the armature speed measuring device (1303) performs measurement, and the central controller (1301) performs signal processing to obtain the speed v of the armature (2) at the moment and the position _fi ；

Step 3-2:

if it is

Immediately triggering an s-th stage excitation power supply (505), enabling s to be s+1 and enabling i to be i-1;

if it is

Then at a delay time deltat _s Post-triggering the s-th stage excitation power source (505), the delay time delta t _s The method meets the following conditions: />

Let s=s+1, let i=i-1;

if it is

Then no excitation power supply is ready to be triggered (505), let i=i-1; />

Step 4: when the armature (2) passes through the center line of the 1 st stage driving coil and moves to the 1 st photoelectric probe G in front of the center line of the 1 st stage driving coil _z1 When the s-th excitation power supply (505) is triggered to be turned on, the time is t _s The central line distance between the armature (2) and the 1 st stage driving coil is x _s =h/2; the armature speed measuring device (1303) is used for measuring, and the central controller (1301) is used for signal processing to obtain t _s At the moment the armature (2) velocity v _s ；

Step 5: the following steps 5-1, 5-2 and 5-3 are circularly executed until the time t for turning on the nth stage excitation power source (505) is obtained _n ：

Step 5-1: at time t _s+1 Triggering and turning on an s+1st-stage excitation power supply (505), wherein the time t is _s+1 The method meets the following conditions:

v _s for time t _s The speed of the armature (2), a is the moving average acceleration of the armature (2), h is the center-to-center distance of two adjacent driving coils, and t _m A time interval from zero to a maximum value of the discharge current for the driving coil;

step 5-2: the time t is calculated by the central controller (1301) _s+1 The armature (2) is predicted to have a speed of

Step 5-3: let s=s+1.

15. The ballistic target of claim 14, wherein the time t _s+1 The central line distance x between the armature (2) and the 1 st stage driving coil _s+1 The method meets the following conditions: x is x _s+1 ＝x _s +h-at _m (t _s+1 -t _s )＜x _s +h，x _s For time t _s The armature (2) is spaced from the centerline of the stage 1 drive coil.

16. Ballistic target according to claim 14, wherein the armature (2) passes through a jth photoelectric probe G in front of the centerline of the level 1 drive coil _zj J+1th photoelectric probe G _zj+1 The time and the speed of the time are respectively t _zj 、v _zj And t _zj+1 、v _zj+1 The armature (2) passes through the j+1st photoelectric probe G in front of the center line of the 1 st driving coil _zj+1 The time and speed predicted value of the time is

17. The ballistic target of claim 1, wherein the ballistic target meets at least one of the following:

the gas pump pipe (103), the electromagnetic pump pipe (501) and the high-pressure pump pipe (7) are coaxial with each other, have the same inner diameter, and have the inner diameter not smaller than 50mm;

the light gas in the front of the piston (3) is hydrogen or helium, and the gas pressure is 0.01-1.0 MPa, wherein the light gas in the gas pump pipe (103), the electromagnetic pump pipe (501), the high-pressure pump pipe (7) and the secondary air chamber (801); the test gas in the transmitting tube (10), the expansion tank (11) and the test cabin (12) in front of the model (9) is air, and the air pressure is 10 Pa-0.2 MPa;

the inlet end of the electromagnetic pump pipe (501) is connected with the outlet end of the gas pump pipe (103) through a flange structure;

the outlet end of the electromagnetic pump pipe (501) is connected with the inlet end of the high-pressure pump pipe (7) through a flange structure;

the ratio of the inner diameter of the gas pump pipe (103), the electromagnetic pump pipe (501) and the high-pressure pump pipe (7) to the inner diameter of the emission pipe (10) is 3-5;

the large-diameter straight pipe section of the secondary air chamber (801) is provided with a convex spigot, one end of the high-pressure pump pipe (7) is provided with a concave spigot, and the concave spigot is matched with the convex spigot of the large-diameter straight pipe section of the secondary air chamber (801);

the small diameter straight pipe section of the secondary air chamber (801) is provided with a convex spigot, one end of the transmitting pipe (10) is sequentially provided with a concave spigot, a diaphragm groove and a conical groove along the central line, the concave spigot of the transmitting pipe (10) is matched with the convex spigot of the small diameter straight pipe section of the secondary air chamber (801), the diameter of the concave spigot of the transmitting pipe (10) is larger than that of the diaphragm groove, the secondary diaphragm (805) is arranged in the diaphragm groove, the diameter of the conical groove is gradually reduced from one end of the diaphragm groove, the maximum diameter of the conical groove is smaller than that of the diaphragm groove, and the minimum diameter of the conical groove is equal to the inner diameter of the transmitting pipe (10);

The ratio of the length of the variable-diameter section of the high-pressure pump pipe (7) to the length of the variable-diameter section of the secondary air chamber (801) is 6-20;

when the gas pump pipe (103), the electromagnetic pump pipe (501), the high-pressure pump pipe (7) or the transmitting pipe (10) are connected with each other by sections of pipes with the same specification, the sections are connected by adopting a flange structure, a half nut structure or a half clamp structure;

the armature (2) is in a solid cylinder or hollow cylinder type, and the armature (2) is made of aluminum or aluminum alloy;

the piston (3) is of an integral cylinder type or is formed by sequentially connecting a head of the piston (3), a steel counterweight and a tail of the piston (3) into a whole;

the piston (3) material is preferably polyethylene or polytetrafluoroethylene;

the model (9) is a full-caliber model without a bullet holder or a combined model with a bullet holder, when the model (9) is a full-caliber model without a bullet holder, the model (9) enters the test cabin (12) through the expansion tank (11) after being transmitted, and when the model (9) is a combined model with a bullet holder, the combined model consists of a model (9) body and a bullet holder, the bullet holder and the model body are separated in the expansion tank (11) after the model (9) is transmitted, and the model body enters the test cabin (12);

the expansion tank (11) and the test cabin (12) are provided with a speed measuring system of the model (9), a photographic system for measuring the position and the posture of the model (9), a shadow/schlieren instrument for displaying a flow field and a light radiation measuring system for measuring the light radiation characteristics;

The ballistic target comprises a plurality of supporting mechanisms and a track system, wherein the supporting mechanisms are respectively positioned below the primary air chamber (101), the air pump pipe (103), the electromagnetic pump pipe (501), the high-pressure pump pipe (7), the expansion tank (11) and the test cabin (12), and the supporting mechanisms are arranged on the track system and can move along the track;

the armature (2) has a velocity v at the centerline of the 1 st stage drive coil (502) in the electromagnetic pump tube (501) _za At the outlet speed v of the electromagnetic pump pipe (501) _zb ，0＜v _za ＜v _zb ≤1000m/s。

18. A time sequential trigger control method applied to the ballistic target of any one of claims 11 to 16, the method comprising:

step 2: i=m when the armature moves past the mth photoelectric probe behind the 1 st stage drive coil centerline; the following steps 2-1 and 2-2 are circularly executed until the 1 st stage excitation power source is triggered:

Step 2-2:

if it is