CN116086241A

CN116086241A - Ballistic target based on electromagnetic ejection auxiliary driving primary gas gun

Info

Publication number: CN116086241A
Application number: CN202211716871.4A
Authority: CN
Inventors: 郭秉楠; 易翔宇; 屈振乐; 林键; 宫建; 纪锋; 朱浩; 姚大鹏; 陈勇富
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: 2023-05-09

Abstract

The invention provides a ballistic target based on electromagnetic ejection auxiliary driving primary gas cannon, which comprises a high-pressure gas propulsion section, an armature, a model, an electromagnetic ejection device, an expansion tank, a test cabin and a measurement and control system, wherein the armature is arranged on the high-pressure gas propulsion section; the electromagnetic ejection device comprises an electromagnetic emission tube, a multi-stage driving coil, an excitation power supply and a charger; the high-pressure gas propulsion section comprises a high-pressure air chamber and a high-pressure gas gun barrel; the high-pressure air chamber, the high-pressure air gun barrel, the electromagnetic emission pipe, the expansion tank and the test cabin are sequentially connected. The high-pressure air chamber releases high-pressure air to drive the armature and the model to move in the high-pressure air gun barrel; and then the armature drives the model to fly out of the electromagnetic emission pipe at high speed under the combined action of aerodynamic force and electromagnetic force provided by the electromagnetic ejection device, and the model enters the test cabin through the expansion tank. The invention adopts high-pressure gas and electromagnetic ejection composite primary driving, obviously enhances driving capability, can improve emission speed or equipment caliber and test model size, and can optimize and improve inner trajectory performance to realize soft emission.

Description

Ballistic target based on electromagnetic ejection auxiliary driving primary gas gun

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 primary gas 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 is used for carrying out aerodynamic/thermal, aerodynamic physical, ultra-high-speed collision and other test tests. Based on the scale effect of the model flight ground simulation test, under the same other conditions, the model size is closer to the prototype size of the aircraft, and the ground simulation data result is closer to reality. Under the same emission speed condition, the larger the caliber of the emission device is, the larger the model size is, and the better the simulation test effect is.

The ballistic target mainly comprises a model launching device, a test system and a measurement and control system. The power source of the ballistic target launching device is usually in the modes of gunpowder, compressed gas or hydrogen and oxygen detonation, and the ballistic target launching device mainly structurally comprises a first-stage gun, a second-stage light-gas gun, a third-stage light-gas gun and other configurations, and particularly the second-stage light-gas gun driven by gunpowder is most common. The secondary light air cannon can accelerate the projectile to 8km/s at maximum, but the diameter of the launching tube orifice is usually below 50mm (the maximum does not exceed 210 mm); three stages of light air cannons can accelerate the projectile up to about 11km/s, but the firing tube orifice diameter is typically below 20 mm. At present, two/three-level light air cannons cannot meet the requirements of large-size (caliber is more than 50 mm) model flight ground tests in an ultra-high speed (8 km/s and more) state.

Compared with a two/three-stage light gas gun, the primary muzzle diameter can reach more than 50mm, and better ground simulation test effect can be realized under the same firing speed condition. The methods of gunpowder, oxyhydrogen detonation and the like have the problems of poor safety, environmental pollution, policy control and the like, so that the application is limited; the high-pressure gas driving mode is safe and clean, but the initial gas injection pressure is limited by the capability of gas injection equipment, and the inherent problem that the bottom pressure of the projectile is rapidly reduced after the projectile is launched exists, so that higher average pressure cannot be provided for the projectile, the inner trajectory performance is poor, and the driving capability is weak. In short, the first-class gun firing speed is generally not more than 2km/s due to insufficient driving capability or safety of the traditional power source.

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 excellent and 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 secondary light gas gun adopting an electromagnetic gun for primary driving, which has higher safety than modes such as gunpowder driving, mixed gas detonation and the like, and has small occupied space and high emission speed compared with high-pressure nitrogen driving, but belongs to a secondary light gas gun structure, and the application has the defects that the caliber of a transmitting tube is smaller (for example, the diameter of the transmitting tube is only 14mm in an embodiment), the size and the quality of a test model are smaller, and the requirement of a large-size model ultra-high-speed flight simulation test cannot be met.

Disclosure of Invention

The invention provides a large-caliber ballistic target taking a high-pressure gas and electromagnetic ejection composite driving primary gun as a launching device, which aims to solve the problems of weak driving capability, small caliber, non-ideal inner ballistic performance and the like of the conventional ballistic target launching device, and to provide a safe, clean, efficient and controllable large-caliber test platform for aerodynamic/thermal, aerodynamic physical and ultra-high-speed collision and other tests.

In a first aspect, a ballistic target based on electromagnetic ejection auxiliary driving primary gas cannon is provided, and is used for performing flight measurement of a model, wherein the ballistic target comprises a high-pressure gas propulsion section, an armature, the model, an electromagnetic ejection device, an expansion tank, a test cabin and a measurement and control system; wherein,,

the high-pressure gas propulsion section comprises a high-pressure air chamber and a high-pressure gas gun barrel, wherein the armature and the model are arranged in the high-pressure gas gun barrel, and the armature is arranged behind the model;

the electromagnetic ejection device comprises an electromagnetic emission tube, a multi-stage driving coil wound on the electromagnetic emission tube, an excitation power supply for supplying power to the multi-stage driving coil and a charger for charging the excitation power supply, and the high-pressure air chamber, the high-pressure air gun tube, the electromagnetic emission tube, the expansion tank and the test cabin are sequentially connected;

The high-pressure air chamber releases gas, the armature and the model are driven to move forwards to fly out of the high-pressure gas gun barrel, and in the electromagnetic emission pipe, the armature pushes the model under the compound driving of gas thrust and electromagnetic force, and the model flies out of the emission pipe to 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 high-pressure gas chamber is air, nitrogen or helium, and the gas pressure is not more than 30MPa;

the high-pressure air chamber is connected with the high-pressure gas gun barrel through a flange structure or an opening sawtooth thread structure;

the total pressure P of the gas in the high-pressure gas chamber after the gas in the high-pressure 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 emission tube, V _1x (x) Gas volume for armature movement x distance;

the high-pressure air chamber comprises a release mechanism, and the release mechanism is a piston type release mechanism or a double-rupture-membrane release mechanism;

The ratio of the volume of the high-pressure gas gun barrel to the volume of the high-pressure gas chamber is more than or equal to 1.0;

the high-pressure gas gun barrel is made of gun steel materials.

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

the electromagnetic emission tube is made of resin matrix composite materials or ceramic materials, and the highest working temperature can reach 260 ℃;

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 emission tube 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 transmitting tube is 0.1-0.3;

the driving coil conductor of the electromagnetic ejection device is made of red copper material, and the outside of the driving coil conductor is coated with insulating material;

the outer whole of the multistage driving coil is covered by a metal layer.

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 more than or equal 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 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 high-pressure gas gun barrel and the electromagnetic emission pipe wall 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 the high-pressure gas gun barrel and the through holes in the wall of the electromagnetic emission 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,

the speed of the armature at the center line of the 1 st stage driving coil in the electromagnetic transmitting tube is v _za ，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 high-pressure air chamber releases air to drive the armature to push the model to move forwards;

step 2: let s=1, when the armature moves past the mth photoelectric probe behind the 1 st stage drive coil centerline, i=m, the following steps 2-1, 2-2 are cyclically performed 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 present 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 and passes through 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 n-th excitation power supply is turned onTime t of (2) _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: 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.

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 the speed of the time are respectively

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

the high-pressure gas gun tube and the electromagnetic emission tube are coaxial with each other and have the same inner diameter, and the inner diameter is not less than 50mm;

the high-pressure gas gun tube is connected with the electromagnetic emission tube through a flange structure;

the high-pressure gas gun tube or the electromagnetic emission tube is connected with each other by the same-specification tube sections, and 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;

the armature material is aluminum or aluminum alloy;

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 photographing 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 high-pressure air chamber, the high-pressure air gun barrel, the electromagnetic emission pipe, the expansion tank and the test cabin, and are arranged on the track system and can move along the track;

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

the high-pressure gas gun barrel, the electromagnetic emission pipe, the expansion tank and the test cabin in front of the model are filled with test gas which is air, and the air pressure is 10 Pa-0.2 MPa;

the armature has a velocity v at the centerline of the 1 st stage drive coil in the electromagnetic transmitting tube _za Satisfy 0 < v _za ≤150m/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 present loop and execute step 3;

if it is

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

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 using an armature speed measuring device, and performing signal processing by using a central controller to obtain the electricity at the moment and the positionPivot speed v _fi ；

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 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 5-3: let s=s+1.

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

(1) The launching device adopts a high-pressure gas and electromagnetic ejection composite driving mode, and compared with a primary gun driven by single high-pressure gas, the driving capability of the launching device is improved by more than several times. The electromagnetic driving device can solve the problem of high energy supply required by large-caliber equipment by using the characteristic of multistage energization of the electromagnetic driving device and increasing the number of stages of an excitation power supply and a driving coil.

(2) The electromagnetic catapulting device adopts a high-pressure gas and electromagnetic catapulting compound driving mode, an insulating transmitting tube is arranged between a driving coil (primary) and an armature (secondary) of the electromagnetic catapulting device, and related researches show that the larger the caliber is, the higher the electromagnetic coupling efficiency and the electromagnetic energy conversion efficiency are, and the coupling efficiency and the electromagnetic energy conversion efficiency of the caliber are reduced sharply below 50 mm. Compared with an electromagnetic driven secondary gun, the diameter of the launching tube is increased by a plurality of times on the premise of ensuring higher energy conversion efficiency, and the method is particularly suitable for large-size and large-mass model ballistic target tests.

(3) 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; when driven by electromagnetic ejection alone, the armature needs to accelerate from rest and accelerate slowly compared with the initial stage of high-pressure gas driving. The invention adopts a composite driving mode mainly comprising high-pressure gas and post electromagnetic ejection, combines the advantages of respective driving characteristics, drives an armature by the high-pressure gas to accelerate rapidly, gives a certain initial speed to the armature when the electromagnetic emission is started, and then utilizes the characteristics of axial distribution, multistage energization, single-stage independent regulation and control of an excitation power supply and a driving coil of an electromagnetic ejection device.

(4) The launching device adopts a high-pressure gas and electromagnetic ejection composite driving mode, has higher structural tightness and safety, and is a safer, cleaner and more efficient power source than gunpowder or oxyhydrogen detonation.

(5) With the breakthrough of the bottlenecks of high-energy density energy storage technology, high-voltage switch technology and high-strength new insulating material technology, the future multistage coil electromagnetic ejection device can realize modularization, miniaturization, light weight and intellectualization, and the electromagnetic driving force can be used as an independent power source of a ballistic target and has an increasingly larger advantage.

Drawings

FIG. 1 is a schematic diagram of a ballistic target structure based on electromagnetic ejection assisted driving of a primary gas cannon;

FIG. 2 is a schematic diagram of an electromagnetic ejection device and a timing trigger 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 a high pressure plenum segment;

FIG. 5 is a schematic view of a half nut connection structure between sections of a high pressure gas gun barrel;

FIG. 6 is a schematic view of a flange connection structure of the high-pressure gas chamber and the high-pressure gas gun barrel;

FIG. 7 is a schematic view of a flange connection structure of a high-pressure gas gun barrel and an electromagnetic emission pipe;

FIG. 8 is a schematic diagram of flange connections between electromagnetic emitter tube segments;

FIG. 9 is a schematic top view of the expansion tank, test chamber and related measurement and control devices.

Reference numerals illustrate:

1-a high pressure gas propulsion section; 101-a high-pressure air chamber; 10101-high pressure plenum chamber; 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-high-pressure gas gun barrel; 10301-the kth section of the high-pressure gas gun barrel; 10302-the (k+1) th section of the high-pressure gas gun barrel; 10303-a half nut assembly; 2-an armature; 3-model; 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 emission tube; 50101-kth section of electromagnetic emission tube; 50102-the (k+1) th section of the electromagnetic emission tube; 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-an expansion tank; 601-the expansion tank interfaces with a vacuum system; 602-a side view window of the expansion tank; 603-expansion tank top viewing window; 7-a test cabin; 701-interface of the test chamber with a vacuum system; 702-a test chamber side view window; 703-a test cabin top view window; 8-a measurement and control system; 801-a central controller; an 802-pulse triggering circuit; 803-an armature speed measuring device in the transmitting tube; 80301-a photosensor body; 80302-an optoelectronic probe; 804-exciting a supply voltage measuring device; 805-a drive coil current measurement device; 806-an in-expansion tank model speed measuring device; 807-an expansion tank binocular vision measurement system; 808-testing the model speed measuring device in the cabin; 809—test cabin schlieren instrument; 810-a test chamber binocular vision measurement system; 811-a test chamber optical radiation measuring instrument; 9-a supporting mechanism; 10-track system.

Detailed Description

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 to scale unless specifically indicated.

As shown in fig. 1-2, the ballistic target based on electromagnetic ejection auxiliary driving primary gas cannon comprises a high-pressure gas propulsion section 1, an armature 2, a model 3, an electromagnetic ejection device 5, an expansion tank 6, a test cabin 7 and a measurement and control system 8.

The high pressure gas propulsion section 1 comprises a high pressure gas chamber 101 and a high pressure gas barrel 103. The electromagnetic ejection device 5 includes an electromagnetic emission tube 501, and a multistage driving coil 502 wound on the electromagnetic emission tube 501. The high-pressure air chamber 101, the high-pressure gas gun barrel 103, the electromagnetic emission pipe 501, the expansion tank 6 and the test chamber 7 are connected in sequence. The electromagnetic ejection device 5 may also include an excitation power source 505 that powers the multi-stage drive coil 502 and a charger 504 that charges the excitation power source. The charger 504 may employ an IGBT series resonant constant current charging power supply.

The high-pressure gas gun barrel 103 is internally provided with an armature 2 and a model 3, and the armature 2 is behind the model 3. The high-pressure gas chamber 101 is filled with high-pressure gas. The high-pressure gas gun barrel 103, the electromagnetic emission pipe 501, the expansion tank 6 and the test chamber 7 in front of the model 3 are filled with test gas. In a preferred embodiment, the high pressure gas in the high pressure gas chamber 101 is high pressure air or high pressure nitrogen or high pressure helium, and the gas pressure is not more than 30MPa; the high-pressure gas gun barrel 103, the electromagnetic emission pipe 501, the expansion tank 6 and the test chamber 7 in front of the model 3 are filled with test gas which is air with the pressure of 10 Pa-0.2 MPa.

The high pressure gas chamber 101 releases high pressure gas, driving the armature 2 and the pattern 3 to fly forward out of the high pressure gas barrel 103. In the electromagnetic emission tube 501, the armature 2 pushes the mold 3 to emit at a high speed under the combined drive of the high-pressure gas thrust and the electromagnetic force. The model 3 passes through the expansion tank 6 into the test chamber 7.

In one embodiment, after the gas in the high-pressure gas chamber is released, the armature and the piston are pushed to move in an isentropic expansion mode, and the total pressure P of the gas in the high-pressure gas chamber _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 emission tube 501, V _1x (x) For the high pressure gas volume at which the armature 2 moves x distance.

In one embodiment, the high pressure gas chamber 101 includes a release mechanism, either a piston release mechanism or a double rupture release mechanism, that acts to isolate the gas and to open quickly.

In one embodiment, the high pressure gas barrel 103 is made of a metallic material, preferably a steel material.

The electromagnetic emission tube 501 plays a role of guiding, and in one embodiment, the electromagnetic emission tube 501 is made of an insulating material, so as to ensure that the driving coil 502 and the armature 2 are not electrically conducted, and ensure that good electromagnetic induction is achieved between the driving coil 502 and the armature 2. The maximum operating temperature of the electromagnetic transmitting tube 501 may be up to 260 degrees celsius so that the temperature rise caused by the acceleration of the armature 2 is within the operating temperature range of the electromagnetic transmitting tube 501. The electromagnetic launch tube 501 is preferably a high strength resin matrix composite or a high strength ceramic material.

In one embodiment, the electromagnetic ejection device drive coil 502 is made of red copper material, and the exterior of the drive coil 502 is coated with an insulating material. The electromagnetic ejection device 5 may further include a metal layer 503, where the metal layer 503 may be wrapped around the multistage driving coil 502, and the metal layer 503 plays a role in electromagnetic shielding and plays a role in strengthening the structure of the electromagnetic emission tube 501 and the multistage driving coil 502.

In one embodiment, the armature 2 is configured as a solid cylinder or hollow cylinder type, and the armature 2 material is aluminum or aluminum alloy.

In one embodiment, the model 3 is a full caliber model without a spring holder or a combination model with a spring holder; when the model 3 is a full-caliber model without a spring holder, the model 3 enters a test cabin through an expansion tank after being transmitted; when the model 3 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 3 is transmitted, and the model body enters a test cabin.

In one embodiment, the number of stages of the multistage driving coils of the electromagnetic ejection device 1 is n, and n is more than or equal to 3. Under the set basic parameter conditions of the peak value speed, the average acceleration, the caliber of a pump pipe and the like of the model, 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 the limit parameter conditions, so that the efficient and safe acceleration of the armature 2 and the model 3 is conveniently 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 driving coil 502 to the inner diameter of the electromagnetic transmitting tube 501 of the electromagnetic ejection device 1 is 0.4-1.7, and the ratio of the distance between the opposite end surfaces of the driving coils 502 of adjacent stages to the inner diameter of the electromagnetic transmitting tube 501 is 0.1-0.3. 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, as shown in fig. 2, each stage of driving coil 502 of the electromagnetic ejection device is connected to an independent excitation power source 505, and the excitation power source 505 includes 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 8. The measurement and control system 8 monitors voltage information of the excitation power source 505, current information of the driving coil 502, pressure and temperature information of high-pressure gas and test gas, motion information of the high-pressure gas gun barrel 103, the electromagnetic emission pipe 501, the armature 2 and the model 3 in the expansion tank 6, motion information, aerodynamic/thermal information, aerodynamic physical information or high-speed collision information of the model 3 in the test chamber 7 through sensors.

The measurement and control system 8 comprises a central controller 801, a pulse trigger circuit 802 and an armature speed measuring device 803. The central controller 801 is preferably a digital signal processor DSP or a field programmable gate array FPGA. The armature speed measuring device 803 comprises a photoelectric sensor body 80301 and photoelectric probes 80302, and a plurality of photoelectric probes 80302 of the armature speed measuring device 803 are arranged on the walls of the high-pressure gas gun barrel 103 and the electromagnetic emission pipe 501 at intervals along the armature movement direction; the photoelectric sensor body 80301 and the photoelectric probe 80302 are connected by an optical fiber. The armature speed measuring device 803 photoelectric probe 80302 can send pulse optical signals with certain frequency to the armature 2 through holes on the walls of the high-pressure gas gun tube 103 and the electromagnetic transmitting tube 501, and receive optical signals reflected from the reflecting ring, and meanwhile, convert the optical signals into electric signals and transmit the electric signals to the central controller 801.

The central controller 801 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 model 3) passes through the photoelectric probe 80302, 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 802 by the central controller, and the pulse trigger circuit 802 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 For the velocity of the armature 2 (specifically, the area of the armature 2 at or near the rear face) at the centerline of the drive coil of stage 1 in the electromagnetic launch tube 501, h is the axial spacing of the centerlines of adjacent drive coils, t _m For the time interval when the drive coil discharge current rises from zero to a maximum value. In some embodiments, v _za Satisfy 0 < v _za Less than or equal to 1500m/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 mold 3 were pre-placed in place in the rear end of the high pressure gas barrel 103 near the outlet of the high pressure gas chamber 101. First, the exhaust valve 10110 of the high-pressure air chamber 101 is opened, and the armature tachometer 803 is controlled to emit an optical signal into the tube at a proper frequency. The high pressure gas chamber 101 releases high pressure gas to drive the armature 2, the armature 2 pushes the pattern 3 to move forward in the high pressure gas barrel 103, and the speed of the armature 2 and the pattern 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 velocity measuring device 803 performs measurement, and the central controller 801 performs signal processing to obtain the velocity v of the armature 2 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 velocity measuring device 803 performs measurement, and the central controller 801 performs signal processing to obtain the velocity v of the armature 2 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, measurement by armature tachometer 803, central controlThe signal processing is performed by the processor 801 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 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 _s+1 The armature 2 is expected to have a speed of

Taking this predicted speed as time t _s+1 The approximate value of the actual speed of the armature 2 can be calculated by the central controller at the same time to obtain the time t _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+ Time of day and speed of dayThe expected value 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 801, 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 semiconductor high voltage switch composed of thyristors.

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

As shown in fig. 2, the measurement and control system 8 may further comprise an excitation supply voltage measurement device 804 and a drive coil current measurement device 805. The excitation supply voltage measurement device 804 may be used to monitor the voltage of the storage pulse capacitor bank 50501. The drive coil current measurement device 805 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 high-pressure gas chamber 101 is connected to a high-pressure gas barrel 103 via a connection mechanism a 102. The high pressure 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 high pressure gas chamber 101. Simultaneously, the check valve 10105 is opened, high-pressure gas enters the high-pressure gas chamber cavity 10101 from the exhaust cavity 10102, and the air 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 high-pressure air chamber 101, high-pressure air in the inner cavity 10101 of the high-pressure air chamber immediately enters the high-pressure air gun barrel 103, and the armature 2 is driven to push the model 3 to move forwards in the high-pressure air gun barrel 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.

Due to the limitation of the manufacturing process, the length of the same-specification pipe is limited, and when the high-pressure gas gun tube 103 or the electromagnetic transmitting tube 501 is connected with each other by sections of the same-specification pipe, the sections are connected by adopting a flange structure, a half nut structure or a half clamp structure.

High pressure gas barrel 103 inter-segment connection mechanism embodiment:

as shown in fig. 5, the kth section 10301 of the high-pressure gas gun barrel is adjacent to the kth+1 section of the high-pressure gas gun barrel, the right end of the kth section 10301 of the high-pressure gas gun barrel is provided with a concave spigot, the left end of the kth+1 section 10302 of the high-pressure gas gun barrel 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 10303.

In one embodiment, the high pressure gas chamber 101 is connected to the high pressure gas barrel 103 by a connection means a 102; the connection mechanism a102 is a flange structure or an open sawtooth thread structure.

High pressure plenum 101 and high pressure gas barrel 103 flange connection embodiment:

as shown in fig. 6, the inlet straight pipe section of the high-pressure air chamber 101 is connected with the left end of the high-pressure air gun barrel 103 through a connecting mechanism a 102. The inlet straight pipe section of the high-pressure air chamber 101 is provided with a concave spigot, the left end of the high-pressure air gun barrel 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 orchid pipe Aa10201 and the steel making orchid pipe Ab10202 are respectively fixed with the outer surface of the inlet straight pipe section of the high-pressure gas chamber 101 and the outer surface of the left end of the high-pressure gas gun barrel 103 in a threaded or welded mode, and the steel making orchid pipe Aa10201 and the steel making orchid pipe Ab10202 are connected and fastened through a steel bolt assembly Ac10203.

In one embodiment, the ratio of the volume of the high pressure gas barrel 103 to the volume of the high pressure gas chamber 101 is greater than or equal to 1.0.

In one embodiment, the high-pressure gas gun barrel 103 and the electromagnetic emission pipe 501 are connected through a connecting mechanism B4, and the connecting mechanism B4 is in a flange structure.

High pressure gas barrel 103 and electromagnetic firing tube 501 connection mechanism B4 embodiment:

as shown in fig. 7, the inner diameter of the high-pressure gas gun barrel 103 is the same as that of the electromagnetic emission pipe 501, and generally the wall thickness of the high-pressure gas gun barrel 103 is larger, and the wall thickness of the electromagnetic emission pipe 501 is smaller. The high-pressure gas gun barrel 103 is connected with the electromagnetic emission pipe 501 through a connecting 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 high-pressure gas gun tube 103 in a threaded or welding mode, the insulating flange pipe fitting Bb is fixed with the outer surface of the left end of the electromagnetic emission tube 501 in an adhesive mode, and the steel flange pipe fitting Ba401 and the insulating flange pipe fitting Bb are connected and fastened through a bolt component Bc403.

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

Electromagnetic launch tube 501 inter-segment connection mechanism embodiment:

As shown in fig. 8, the kth segment 50101 of the electromagnetic emission tube and the kth+1th segment 50102 of the electromagnetic emission tube are adjacent to each other and connected to each other by an insulating flange connection mechanism C506. The insulating flanged pipe fitting Ca50601 with the concave spigot and the insulating flanged pipe fitting Cb50602 with the convex spigot are respectively adhered and fixed with the outer surface of the left end of the kth section 50601 of the electromagnetic emission pipe and the outer surface of the right end of the (k+1) th section of the electromagnetic emission pipe, and the insulating flanged pipe fitting Ca50601 with the concave spigot and the insulating flanged pipe fitting Cb50602 with the convex spigot are connected and fastened through an insulating bolt component Cc 50603.

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

as shown in FIG. 9, the expansion tank 6 and the test chamber 7 are filled with air having a pressure in the range of 10Pa to 0.2 MPa. The expansion tank 6 is provided with a vacuum system interface 601, a plurality of side optical windows 602 and a top optical window 603, a plurality of expansion tank internal model speed measuring devices 806 are arranged on the side parts, and a plurality of expansion tank binocular vision measuring systems 807 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 7 is provided with a vacuum system interface 701, a plurality of side optical windows 702 and a top optical window 703, a plurality of test chamber model speed measuring devices 808, a flow field display schlieren 809 and an optical radiation measuring system 711 for measuring optical radiation characteristics are arranged on the side, and binocular vision measuring systems 710 for measuring model flying attitudes are arranged on the side and the top.

In one embodiment, the expansion tank 6 and the test chamber 7 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.

In one embodiment, the ballistic target comprises a plurality of support mechanisms 9 and a rail system 10, the support mechanisms 9 are respectively positioned below the high-pressure gas chamber 101, the high-pressure gas gun barrel 103, the electromagnetic emission pipe 501, the expansion tank 5 and the test chamber 7, and the support mechanisms 9 are mounted on the rail system 10 and can move along the rail.

The working principle of the invention is as follows:

before the test, the armature 2 is placed in a proper position (such as in the rear end of the high-pressure gas gun barrel and near the outlet of the high-pressure gas chamber). In the test, the exhaust valve 10110 of the high-pressure air chamber 101 is firstly opened, and the armature speed measuring device 803 is controlled to emit an optical signal into the high-pressure air gun barrel 103 at a proper frequency. The high pressure gas chamber 101 releases high pressure gas to drive the armature 2 to push the model 3 to move forwards in the high pressure gas gun barrel 103, and the speed of the armature 2 and the model 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 803 is used for measuring, the central controller 801 is used for carrying out signal processing, the relevant steps of the time sequence trigger control method are circularly executed, and the 1 st stage predicted trigger time is obtained through calculation. At the predicted trigger time, the central controller 801 sends trigger control to the pulse trigger circuit 802 The pulse triggering circuit 802 outputs power pulse to conduct the primary exciting power switch 50502 of the 1 st stage, so that the energy storage pulse capacitor 50501 of the 1 st stage discharges through the driving coil 502 of the 1 st stage, after the energy storage pulse capacitor 50501 drops 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 vortex current and receive electromagnetic force. After the 1 st stage triggering, the armature 2 pushes the model 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 model to move forwards under the combined action of gas thrust and electromagnetic force of a plurality of stages of drive coils which are conducted and discharged. The armature 2 pushes the model 3 to fly out of the electromagnetic emission tube 501 at a high speed under the combined action of electromagnetic force and gas thrust at the rear end face and light gas resistance at the front end face. When the model 3 is a full-caliber model without a spring holder, the model enters a test cabin 7 through an expansion tank 6 after being launched; when the model 3 is a combined model with a spring holder, the spring holder and the model body are separated in the expansion tank 6, and the model body enters the test cabin 7./ >

The invention has been described in detail in connection with the specific embodiments and exemplary examples thereof, and no such description should be construed as limiting 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. The invention will now be described in further detail by way of the following examples, which are given by way of illustration only and not by way of limitation, and are not intended to limit the scope of the invention.

Claims

1. The ballistic target is characterized by being used for performing flight measurement of a model (3), and comprises a high-pressure gas propulsion section (1), an armature (2), the model (3), an electromagnetic ejection device (5), an expansion tank (6), a test cabin (7) and a measurement and control system (8); wherein,,

the high-pressure gas propulsion section (1) comprises a high-pressure air chamber (101) and a high-pressure gas gun tube (103), wherein the armature (2) and the model (3) are arranged in the high-pressure gas gun tube (103), and the armature (2) is arranged behind the model (3);

The electromagnetic ejection device (5) comprises an electromagnetic emission tube (501), a multi-stage driving coil (502) wound on the electromagnetic emission tube (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), wherein the high-pressure air chamber (101), the high-pressure gas gun tube (103), the electromagnetic emission tube (501), the expansion tank (6) and the test cabin (7) are sequentially connected;

the high-pressure air chamber (101) releases air, the armature (2) and the model (3) are driven to move forwards to fly out of the high-pressure air gun barrel (103), the armature (2) pushes the model (3) under the combined driving of air thrust and electromagnetic force in the electromagnetic emission pipe (501), and the model (3) flies out of the electromagnetic emission pipe (501) to enter the test cabin (7) through the expansion tank (6);

the measurement and control system (8) 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 high-pressure air chamber (101) is air, nitrogen or helium, and the gas pressure is not more than 30MPa;

The high-pressure air chamber (101) is connected with the high-pressure gas gun barrel (103) through a flange structure or an opening sawtooth thread structure;

the total pressure P of the gas in the high-pressure gas chamber (101) after the gas in the high-pressure gas 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 the electromagnetic emission tube (501), V _1x (x) A volume of gas when the armature (2) is moved x distance;

the high-pressure air chamber (101) comprises a release mechanism, wherein the release mechanism is a piston type release mechanism or a double-rupture type release mechanism;

the ratio of the volume of the high-pressure gas gun tube (103) to the volume of the high-pressure gas chamber (101) is more than or equal to 1.0;

the high-pressure gas gun barrel (103) is made of gun steel materials.

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

the electromagnetic emission tube (501) is made of resin matrix composite material or ceramic material, and the highest working temperature can reach 260 ℃;

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 emission tube (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 emission tube (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 outside of the multistage driving coil (502) is covered by a metal layer (503).

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 (8).

5. The ballistic target of claim 4, 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. The ballistic target according to claim 1, wherein the measurement and control system (8) comprises a central controller (801), a pulse trigger circuit (802) and an armature tachometer (803);

the armature speed measuring device (803) comprises a photoelectric sensor body (80301) and a plurality of photoelectric probes (80302), the photoelectric probes (80302) are arranged on the wall of the high-pressure gas gun barrel (103) and the electromagnetic emission tube (501) at intervals along the moving direction of the armature (2), and the photoelectric sensor body (80301) is connected with the photoelectric probes (80302) through optical fibers;

the photoelectric probe (80302) sends pulse optical signals to the armature (2) through the high-pressure gas gun barrel (103) and through holes on the wall of the electromagnetic emission pipe (501) and receives the reflected optical signals, and the photoelectric sensor body (80301) converts the optical signals into electric signals and transmits the electric signals to the central controller (801);

the central controller (801) processes the electric signals to obtain the time and the speed of the armature (2) passing through the photoelectric probe (80302), and calculates the predicted trigger time of the stage to be triggered according to a time sequence trigger control method;

And at the expected triggering moment, the central controller (801) sends a triggering control signal to the pulse triggering circuit (802), and the pulse triggering circuit (802) 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).

7. The ballistic target according to claim 6, wherein the photoelectric probe (80302) is used for detecting the rear end of the armature (2).

8. Ballistic target according to claim 6 or 7, characterized in that at least m photoelectric probes G are evenly arranged axially rearwards from the level 1 drive coil centre line _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,

the armature (2) has a velocity v at the centerline of the 1 st stage drive coil in the electromagnetic transmitting tube (501) _za ，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.

9. The ballistic target of claim 8 wherein the ballistic target is,

10. the ballistic target of claim 8, wherein t _m According to

11. The ballistic target of claim 8 wherein the time sequence trigger control method comprises:

step 1: the high-pressure air chamber (101) releases air to drive the armature (2) to push the model (3) to move forwards;

step 2: let s=1, when the armature (2) moves past the mth photoelectric probe behind the 1 st stage drive coil centerline, i=m, 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 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 velocity measuring device (803) performs measurement, and the central controller (801) performs signal processing to obtain the velocity v of the armature (2) at the moment and the position _fi ；

Step 2-2:

if it is

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;

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 and passes through 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 velocity measuring device (803) performs measurement, and the central controller (801) performs signal processing to obtain the velocity v of the armature (2) at the moment and the position _fi ；

Step 3-2:

if it is

Immediately triggering the s-th level excitation power supply to enables=s+1, let i=i-1;

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 (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 armature speed measuring device (803) is used for measuring, and the central controller (801) is used for signal processing to obtain t _s At the moment the armature (2) velocity v _s ；

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 a central controller (801) _s+1 The armature (2) is predicted to have a speed of

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

12. The ballistic target of claim 11, 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.

13. Ballistic target according to claim 11, 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 the speed of the time are respectively

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

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

the high-pressure gas gun tube (103) is connected with the electromagnetic emission tube (501) through a flange structure;

the high-pressure gas gun tube (103) or the electromagnetic emission tube (501) is connected with each other by the same-specification pipe sections, and the sections are connected by adopting a flange structure, a half nut structure or a half clamp structure;

the armature (2) is in a form of an integral solid cylinder or a hollow cylinder;

the armature (2) is made of aluminum or aluminum alloy;

the model (3) is a full-caliber model without a bullet holder or a combined model with a bullet holder, when the model (3) is a full-caliber model without a bullet holder, the model (3) enters the test cabin (7) through the expansion tank (6) after being transmitted, when the model (3) 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 (6) after the model (3) is transmitted, and the model body enters the test cabin (7);

The expansion tank (6) and the test cabin (7) are provided with a model speed measuring system, a photographic system for measuring the position and the posture of the model (3), a negative/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 a high-pressure air chamber (101), a high-pressure gas gun barrel (103), an electromagnetic emission pipe (501), an expansion tank (6) and a test cabin (7), and are arranged on the track system and can move along the track;

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

the high-pressure gas gun tube (103), the electromagnetic emission tube (501), the expansion tank (6) and the test cabin (7) in front of the model (3) are filled with test gas which is air, and the air pressure is 10 Pa-0.2 MPa;

the armature (2) has a velocity v at the centerline of the 1 st stage drive coil within the electromagnetic launch tube (501) _za Satisfy 0 < v _za ≤1500m/s。

15. A time sequential trigger control method, characterized in that the method is applied to a ballistic target according to any one of claims 8 to 13, the method comprising:

Step 2-2:

if it is