CN1031891A - Aircraft laser air firing simulator - Google Patents
Aircraft laser air firing simulator Download PDFInfo
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- CN1031891A CN1031891A CN 87104966 CN87104966A CN1031891A CN 1031891 A CN1031891 A CN 1031891A CN 87104966 CN87104966 CN 87104966 CN 87104966 A CN87104966 A CN 87104966A CN 1031891 A CN1031891 A CN 1031891A
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Abstract
The present invention is a kind of aircraft laser air firing simulator, is applicable to be contained in air battle fistfight of simulating gun, boat arrow on the fighter plane or tactics, the technique drill of attacking on a surface target.This simulator is made up of laser, range only radar, button, ammunition reserve indicator, laser signal receptor and the attack effect demonstration etc. of vane of instrument, the shooting of simulated aircraft firepower.By with vane of instrument Fu gyro, control laser beam and boresight is synchronous, utilization opto-electronic conversion and signal conditioning are finished aiming, shooting and effect and are shown, implement air firing and simulate.This simulator biofidelity height can show attack effect, stable performance, reliable operation in real time.
Description
The present invention is a kind of aircraft laser air firing simulator, installs to be used as the simulated training system that aircraft is fought aboard, is specially adapted to the air battle fistfight of fighter plane boat arrow, gun or tactics, the technique drill of attacking on a surface target.
Traditional air reconnaissnce training adopts two kinds of methods usually.A kind of method is the target that fans the air, and target machine is a target in tow, and this kind method is a lot of to the flare maneuver restriction of attack plane, target machine, is only applicable to the part technique drill, and is inapplicable to superfighter.Second method is to take a picture to attack.Though this kind method is better than the target that fans the air as technique drill, with a low credibility and can not check attack effect in real time, take a picture and catch behind the target machine target machine and do not know that whether self is by hit in the attack plane.Therefore can not in time be withdrawn from acting by the aircraft of hit, need again the result who takes a picture to be carried out interpretation after the fistfight.A kind of laser cannon analog system that U.S. Pat 4273536 proposes, be applicable to the artillery shooting simulated training of aircraft, it includes the laser of simulated aircraft firepower shooting and relevant electronics package is formed, its simulation process is: utilize the fan-shaped laser pulse captured target of emission for the first time, laser pulse is run into target reflection, the attack plane receives target echo, handle, record target direction and distance, utilize the direction of beam deflector control laser beam, beam deflector adopts acousto-optic deflection device.According to the measurement laser pulse of emission for the first time provide apart from azimuth information, emission is " shell " laser pulse for the second time, if hit, target is a displayable signal, as sounding, be fuming, and notes.The attack plane also can utilize the echoed signal that receives to judge whether target hits.The analog system that U.S. Pat 4273536 proposes, the equipment of pilot operator and button are the task equipment and the buttons of this cannon analog system, not actual original equipment of aircraft and the button of doing the operation in wartime of aviator, be separated with existing equipment on the aircraft, and the deflection control equipment complexity of laser beam.
The purpose of this invention is to provide a kind ofly, can show attack effect in real time, the analog training device that can attack continuously empty or to biofidelity height in the ground assault training.
Second purpose of the present invention is after aircraft installs analog machine additional, and actual to do the operation in wartime in full accord to the operation of analog system and aircraft for the aviator, do not increase other operations because installing analog machine additional.
The 3rd purpose of the present invention is after aircraft installs analog machine additional, do not change the aerodynamic performance of aircraft, do not disturb other airborne equipment.
Aircraft laser air firing simulator of the present invention is that the attack plane utilizes the vane of instrument aiming, the pulse laser beam simulation artillery shooting of laser emission, utilize with vane of instrument Fu gyro control laser beam axis and boresight synchronous, the laser signal that the target machine utilization receives carries out opto-electronic conversion and signal conditioning, finish effect and show, implement aircraft air attack simulated training.
Accompanying drawing of the present invention
Fig. 1. the aircraft that firing simulator is housed is attacked the training scheme drawing
Fig. 2. the simulator functional block diagram
Fig. 3. the correction angle scheme drawing that vane of instrument constitutes
Fig. 4. the laser emitting light path system
Fig. 5. servo-actuated gyro control circuit
A. main coil control circuit
B. correction angle due to the force of gravity coil control circuit
C. angle of attack coil control circuit
D. angle of side slip coil control circuit
Fig. 6. apart from the comparator circuit functional block diagram
Fig. 7 .a. laser transmission circuit functional block diagram
B. the mode chart of Laser Modulation circuit
Fig. 8. laser signal receptor functional block diagram
Aircraft laser air firing simulator (see figure 2) mainly contains: the laser 4 that is used for the shooting of simulated aircraft firepower, range only radar 6, button 8, ammunition reserve indicator 9, be used to receive the laser signal receptor 11 of attack plane laser analog signal to attack, and be used to hit the smoking device 12 that effect shows, and PA-system 13 and recording device 14, the record of attack plane signal to attack is also carried out in recording device 14.Feature of the present invention also comprises the interior frame electromagnetism gyro of the three degree of freedom of two same model, one is the gyro of the airborne vane of instrument in attack plane 1, another is the servo-actuated gyro 2 that is used to control laser beam, the light path system 3 of laser beam outgoing, the synchronous servo-actuated gyro control circuit 5 of gyro that keeps servo-actuated gyro 2 and vane of instrument 1, be used for that radar ranging and optical ranging compare apart from comparator circuit 7, be subjected to shooting gate circuit 10 apart from comparator circuit 7, button 8, ammunition reserve indicator 9 controls.
Will consider the weapon trajectory parameter during air weapon emission, the influence of the factors such as aircraft state on target velocity and attack plane need be launched axis correction to weapon.Fig. 3 is the correction angle scheme drawing that vane of instrument constitutes.Wherein ψ is the shooting deviation that the revise goal motion causes, the angle that the relative downrange OM of weapon axis shifts to an earlier date, d is that corrected trajectory is bent downwardly the shooting deviation that causes, the angle that the relative downrange OM of weapon axis raises, β is for revising the shooting deviation that the attack plane state of kinematic motion causes, and inclined to one side correction angle of angle of attack band and sideslip that the relative downrange OM of weapon axis constitutes are with inclined to one side correction angle.φ
AlwaysPrediction angle for comprehensive above-mentioned each angle.Aerogun sights root problem to be solved will be set up prediction angle φ accurately exactly
Always
When utilizing the shooting of laser beam simulated weapons, because laser transmits with the light velocity, emission of lasering beam can the hit target when laser beam axis is consistent with boresight direction.Realizing the laser beam axis method consistent with boresight, is to make laser beam axis identical with the prediction angle that the angle of weapon axis keeps boresight and weapon axis to constitute, and promptly the correction angle that constitutes with laser beam is simulated the correction angle that vane of instrument constitutes.That is to say that above-mentioned two angles should be identical.Be total correction ψ that laser beam is constituted
AlwaysPrediction angle ψ with vane of instrument 1 formation
AlwaysIdentical.The embodiment of simulator of the present invention is the interior frame electromagnetism gyro of three degree of freedom that adopts two same model, one is the gyro of the original vane of instrument 1 of aircraft, another is the servo-actuated gyro 2 that is used to control the laser beam exit direction, servo-actuated gyro 2 is selected the gyro with vane of instrument 1 same model for use, and the servo-actuated precision realizes easily.By means of the gyro controlled mirror of servo-actuated gyro 2 control beam direction, make the laser-beam acquiring line locking.Claim this analog system to be: the gyro servo-actuated, Laser emission, the structure angle mould is intended.
Aircraft laser air firing simulator realization servo-actuated gyro 2 of the present invention is followed the synchronous method of gyro of vane of instrument 1, be from each coil of vane of instrument 1 gyro, to take out the correspondent voltage signal, control circuit 5 through servo-actuated gyro 2 is handled, and outputs current to each corresponding coil of servo-actuated gyro 2.
The control circuit of servo-actuated gyro 2 is referring to Fig. 5.Control circuit 5 makes laser beam constitute identical prediction angle ψ with the weapon axis respectively with vane of instrument in order to the motion of control servo-actuated gyro 2
Always, guarantee that the emitting laser axis overlaps with the boresight OM of vane of instrument 1.Each coil current of servo-actuated gyro should satisfy following requirement for this reason:
I
Main F=K
1I
Main(1)
I
Lift F=K
2I
Lift(2)
I
Meet F=K
2I
Meet(3)
I
Side F=K
2I
Side(4)
K in the formula
1, K
2Be coefficient; I
Main F, I
Lift F, I
Meet F, I
Side FBe respectively the main coil of servo-actuated gyro 2, correction angle due to the force of gravity coil, angle of attack coil, the electric current of angle of side slip coil; I
Main, I
Lift, I
Meet, I
SideBe respectively main coil, correction angle due to the force of gravity coil, the angle of attack coil of vane of instrument 1 gyro, the electric current of angle of side slip coil.The main coil control circuit is shown in Fig. 5 a.
u
208Be the signal voltage that vane of instrument 1 main coil takes out, its size is:
U
208=I
MainR
Main
R wherein
MainResistance can calculate from the main coil circuit.
YF
4Be the servo-actuated gyro 2 main coil control circuit first order, adopt op amp, its in-phase end incoming signal is u
208, the end of oppisite phase incoming signal is+15V voltage that output voltage is:
u
A=-(R
44)/(R
41+ R
45) * 15+ (R
43)/(R
42+ R
43) (1+ (R
44)/(R
41+ R
45)) u
208=-A
41* 15+A
42U
208CW
3For the servo-actuated gyro 2 main coil control circuit second stage, be integrated regulator, its maximum current output can reach 1.5 peaces.As input voltage u
BAOutput voltage u during=7-35 volt
CABe constantly equal to 5 volts, YF
4With CW
3Coupling, c point above earth potential is:
u
C＝u
CA+u
A＝5-A
41×15+A
42·u
208
Suitably choose YF
4Each resistance value, make CW
3Input voltage u
BAIn the regulation number range, and make output voltage u
CFor:
u
C＝A
42·u
208……（5）
Flow through servo-actuated gyro 2 main coil Q this moment
1FQ
2FElectric current be:
I
MainF=(A
42U
208)/(R
47+ R
QF)=(A
42R)/(R
47+ R
QF) I
Main(6)
R in the formula
QFBe Q
1F, Q
2FResistance value.
Suitably choose coefficient of amplification A
42, R
47Size, I then
Main FSatisfy the requirement of (1) formula.I
MainWith I
Main FBe linear relationship.R
45Be zero-regulator resistor, R
47Be adjustable resistance, in order to the difference of compensation gyro performance.
The correction angle due to the force of gravity coil control circuit is shown in Fig. 5 b.This circuit only adopts an op amp YF
1Incoming signal is u
301, u
316Take out from the correction angle due to the force of gravity coil two ends of vane of instrument 1 respectively, size satisfies following relation:
u
316-u
301=I
LiftR
Lift(7)
R in the formula
LiftBe the correction angle due to the force of gravity coil resistance.
Work as R
11=R
12R
14=R
13The time YF
1Output voltage be:
u
O=(R
14)/(R
12) (u
316-u
301)=A
1R
LiftI
Lift(8)
Flow through the correction angle due to the force of gravity coil Q of servo-actuated gyro 2
4FElectric current be:
I
Lift F=(u
0)/(R
15+ R
Lift F)=(A
1R
Lift)/(R
15+ R
Lift F) I
Lift(9)
Suitably choose magnification factor A
1Resistance R
15Size.I then
Lift FSatisfy the requirement of (2) formula.I
LiftWith I
Lift FBe linear relationship.R in the circuit
15Be adjustable resistance, in order to the difference of compensation gyro performance.
Shown in Fig. 5 C and 5d, its principle of work is identical with correction angle due to the force of gravity coil control circuit principle respectively for angle of attack coil and angle of side slip coil control circuit.
In order to prevent that the aviator is when using optical ranging, the ring of light is not wrapped target (promptly not surveying accurate distance) as yet, just launch laser, simulator of the present invention adopts optical ranging and radar ranging comparator circuit 7, make laser transmission circuit be subjected to control apart from comparator circuit 7, have only the transmission circuit that in the permissible value scope that the optical ranging of vane of instrument 1 and the radar ranging difference of range only radar 6 are being stipulated, could connect laser 4, otherwise the transmission circuit of laser 4 is disconnected.Shown in Figure 6 is functional block diagram apart from comparator circuit.It comprises distance measuring signal translation circuit 20, double-limit comparator 21, control relay circuit 22.The input u of signal conversion circuit
LDAnd u
GDBe respectively radar ranging voltage signal and optical ranging voltage signal.Distance measuring signal translation circuit 20 is output as the voltage Δ u relevant with optical ranging difference DELTA D with radar ranging
Δu＝A·（D
L-D
G）＝A·ΔD
A is the coefficient of amplification of distance measuring signal translation circuit 20 in the formula, D
LBe the distance of radar ranging, D
GBe anallatic distance, Δ D is the optical ranging error.
Double-limit comparator 21 is used to judge whether the Δ u signal of input is between two appointed threshold current potentials.When between two thresholding current potentials, be output as active potential, otherwise be output as high potential.The output of double-limit comparator 21 adds to the laser transmission circuit control relay, double-limit comparator 21 output active potential, and control relay is connected laser 4 transmission circuits, otherwise disconnects.
In addition, the Laser emission of analog machine of the present invention also is subjected to ammunition reserve indicator 9, the control of button 8.Therefore, having only could emission of lasering beam when satisfying simultaneously apart from comparator circuit 7, ammunition reserve indicator 9 and 8 three conditions of button.Above-mentioned three output signals are connected through shooting gate circuit 10 and laser transmission circuit.
Simulator of the present invention adopts semiconductor laser.For improving the power of received signal, need select for use the angle of divergence little, the large optical cavity laser that emissive power is big.Used laser power is 15-20 watt, and repeated freqnency is 5 kilocycles, and pulse width is 300 nanosecs.Threshold current 6-8 peace, operating wavelength 9100 dusts+30 dusts (during 300 ° of K of operating temperature).For realizing the maximum power output of laser 4, designed special-purpose exciting circuit.This circuit is made up of four parts and (is seen Fig. 7 a), include the mu balanced circuit 23 that the three-terminal voltage-stabilizing sheet is formed, the laser pulse modulation circuit 24 that integrated circuit is formed, the laser pulse that blocking oscillatot is formed forms circuit 25, high-power switch tube pulse power amplifier circuit 26.
Mu balanced circuit 23 provides 24 volts of stable vdcs for transmission circuit.Pulse modulated circuit 24 oscillation periods are 60 milliseconds, and work wave is shown in Fig. 7 b, at T
1Be positive pulse during this time, have high level, the blocking oscillatot that utilizes this high level to form circuit 25 for the next stage laser pulse adds positive bias, makes it have pulse output.At T
2Be low level during this time, close blocking oscillatot, make its not output, realize the purpose of modulation thus, in order to the situation of simulation gun or the emission of boat arrow.Every cycle of the firing rate of 30-1 gun is about 60 milliseconds.Plan takes 60 milliseconds to launch a laser pulse string, representative emission one bullet of firing.Because the laser pulse string of launching is subjected to the control of pulse modulated circuit 24, just at T
1Just there is the consecutive pulses laser beam to penetrate T during this time
2There is not pulse laser beam to penetrate during this time.
It is self-pushing blocking oscillators that laser pulse forms circuit 25, its output pulse frequency is 5000 hertz, and the blocking oscillatot dutycycle is big, and horsepower output is strong, can make output pulse width reach Millisecond, pulse power amplifier circuit 26 provides enough exciting currents for laser 4.
The simulator of present embodiment is installed in the aircraft cockpit, and the laser emitting light path system of simulator as shown in Figure 4.The dispersion shape laser of laser 4 emissions is converged to straight beam through collector 15, again through gyro controlled mirror 16 and center light deflector 17, passes the preceding light deflector 19 of light inlet window glass 18 directives, reflects canopy glass, from heading directive target machine.Gyro controlled mirror 16 is the moving elements in the optical system, is subjected to 2 controls of servo-actuated gyro, and when gyro controlled mirror 16 changed angle, the laser beam of ejaculation also changed in the angle in space thereupon.Present embodiment is according to 30-1 gun dispersion situation, and during in target machine distance D=1000 meter, fire dispersion face diameter is 5 meters, requires the spot diameter of laser beam on same distance also should be near 5 meters.For this reason, the focal distance f of collector 15 is selected 50 millimeters for use, and diameter of phi is selected 25 millimeters for use, and laser 4 places the focal position of collector 15, can receive the laser of 28 ° of spread angle range.In order to improve laser beam quality, the waste of power of minimizing in light path, it is 0.9 micron infrared laser high-reflecting film that each light deflector all plates wavelength, light inlet window glass plating anti-reflection film, make 0.9 micron infrared laser beam obtain high reflection, visible light can pass through again, thereby makes that aviator's aiming sight line is unaffected.
The laser signal receptor 11 of simulator of the present invention as shown in Figure 8.By filter 27, photoelectric commutator 28, amplifying circuit 29, the logical frequency filter circuit 30 of band, pulse width filter circuit 31, filter gate circuit 32 and step-by-step counting filter circuit 33 are formed.Output signal control PA-system 13, smoking device 12 and the recording device 14 of step-by-step counting filter circuit 33.
Laser signal enters photoelectric commutator 28 by filter 27, photoelectric commutator 28 adopts silicon photoelectric cell slice, the electric signal that obtains is through being with logical frequency filter circuit 30 and pulse width filter circuit 31, their output adds to filter gate circuit 32 simultaneously, filter gate circuit 32 output signals are again through pulse counting filter circuit 33 control smoking devices 12, PA-system 13, recording device 14.
The logical frequency filter circuit 30 of band is used for the filtering interfering signal different with the laser signal frequency, and the interfering signal that is greater than or less than the laser signal frequency is all filtered, and only allows the laser signal frequency to lead to frequency filter circuit 30 by band.The frequency of operation of simulator laser 4 of the present invention is 5000 hertz, and the central task frequency of the logical frequency filter circuit 30 of present embodiment band is 5000 hertz, and passband is ± 400 hertz, with adaptive circuit parameter drift and laser signal frequency error.Pulse width filter circuit 31 is used for the interfering signal of filtering pulse width greater than the basic pulse width.Step-by-step counting filter circuit 33 is used for the disturbing pulse string of filtering noncontinuity.Present embodiment is designed to only to reach the signal of 10 continuous laser train of impulses could be by step-by-step counting filter circuit 33.Simulator laser 4 of the present invention emitted laser pulse after modulating reaches tens continuously, so laser signal can be by step-by-step counting filter circuit 33.The interfering signal that every continuous impulse number out of reach is 10 is all filtered.In fact laser signal receptor 11 is by the logical frequency filter circuit 30 of band, pulse width filter circuit 31,33 3 filter circuits of step-by-step counting filter circuit are to interfering signal filtering in addition, make the ability of laser signal receptor 11 disturbance rejection signals improve greatly, guaranteed the reliable operation of laser signal receptor 11.
Simulator of the present invention is subjected to the control of vane of instrument 1 and transponder switch, in addition also has a nonshared control unit, in order to the break-make of control simulator, on the nonshared control unit and be provided with the Reset button and " writing down, fill bullet " button and ammunition reserve indicator 9.The power supply of simulator of the present invention is with the power supply on the aircraft, and present embodiment is used is 27 volts of direct currents and exchange 115 volts, 400 hertz of power supplys.
The aerial use of simulator of the present invention
When needs use simulator, only need the a/s simulator that connects in turn, the method for operating that uses in air battle by vane of instrument makes ring of light run-home implement to attack then, and simulator can normally play a role.
The connection order of simulator
Original total power switch on the connection machine before the engine starting, the switch of heating of vane of instrument 1, the operating switch of vane of instrument 1, the shooting switch that drops a bomb, the transponder switch, and the weapon selection switch of vane of instrument 1 is placed the position of institute's simulated weapons.
Connect the simulator source switch behind the engine starting, push the Reset button, the computing machine in the logger is restPosed, push " writing down, fill bullet " button.(when multimachine flew in the simulated strike of same spatial domain, the logger of each machine " writes down, fills bullet ", and button was pressed under commanding officer's unity of command.) logger " writes down, fills bullet " after button presses, logger is printed plane No., name, and enters recording status.
After taking off, the gyro lock handle of vane of instrument 1 is placed " starting " position, presses steady ring button, treat that the ring of light is stable after, simulator promptly is in normal working.Extinguish as the indicator lamp of finding ammunition reserve indicator 9 in the simulated strike, " writing down, the fill bullet " button on the push-button controller carries out once more " shooting " as required.
In the simulated strike training, the emission power of air weapon must be disconnected, in case launch true bullet.
The advantage of simulator of the present invention is mock battle fidelity height, the pilot is identical with operation under battle conditions to the operation with the simulator aircraft, there are not other additional operations, the training air combat that allows two-shipper or multimachine to attack against each other, the normal operation of electronic equipment on not impact of the simulator machine does not affect the aerodynamic quality of aircraft. Laser shoot imitator in air for airplane of the present invention provides reliable and effective means for the fighter-pilot's of air force combat training.
Claims (6)
1, a kind of gun that is applicable to, the boat arrow is to tactics empty or that attack on a surface target, the aircraft laser air firing simulator of technique drill, by vane of instrument 1, the laser 4 of simulated aircraft firepower shooting, range only radar 6, button 8, ammunition reserve indicator 9, laser signal receptor 11 and the smoking device 12 that is used to show attack effect, compositions such as PA-system 13 and recording device 14, feature of the present invention is to increase a servo-actuated gyro 2, by the gyro synchronous follow-up of servo-actuated gyro 2 with vane of instrument 1, it is total to make laser beam simulation boresight constitute prediction angle ψ, control laser beam and boresight are synchronous, in addition, also has servo-actuated gyro control circuit, laser light path system, the Laser emission control circuit, laser pick-off treatment circuit and apart from comparator circuit etc., to implement the air firing simulation.
2, firing simulator according to claim 1, it is characterized in that controlling servo-actuated gyro 2 employings of laser beam exit direction and the interior frame three degree of freedom electromagnetism gyro of the gyro same model of vane of instrument 1, the control circuit of servo-actuated gyro 2 adopts four computings device of giving out light, control main coil current, correction angle due to the force of gravity coil current, angle of attack coil current and angle of side slip coil current respectively, realize the motion of control servo-actuated gyro 2.
3, firing simulator according to claim 1 is characterized in that laser optical path is made up of gyro controlled mirror 16, center light deflector 17, light inlet window glass 18 and the preceding light deflector 19 etc. of the collector 15 of convergent laser bundle, control beam direction.
4, firing simulator according to claim 1, the quartz conductor large optical cavity laser that the angle of divergence is little, emissive power is bigger is selected in the emission that it is characterized in that laser for use, and its Laser emission control circuit is made up of four parts: the mu balanced circuit 23 that (1) is made up of the three-terminal voltage-stabilizing sheet; (2) pulse modulated circuit of forming by integrated package 24; (3) laser pulse of being made up of blocking oscillatot forms circuit 25; (4) pulse power amplifier circuit of forming by high-power switch tube 26.
5, firing simulator according to claim 1, it is characterized in that the laser pick-off treatment circuit leads to frequency filter circuit 30, pulse width filter circuit 31, filter gate circuit 32 and step-by-step counting filter circuit 33 by filter 27, photoelectric commutator 28, amplifying circuit 29, band and forms, output signal control smoking device 12, PA-system 13 and the recording device 14 of step-by-step counting filter circuit 33.
6, firing simulator according to claim 1 is characterized in that being made up of distance measuring signal translation circuit 20, double-limit comparator 21 and control relay circuit 22 etc. apart from comparator circuit, to finish the comparison of optical ranging signal and radar ranging signal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN87104966.XA CN1005871B (en) | 1987-07-25 | 1987-07-25 | Laser air shooting simulator for airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN87104966.XA CN1005871B (en) | 1987-07-25 | 1987-07-25 | Laser air shooting simulator for airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1031891A true CN1031891A (en) | 1989-03-22 |
| CN1005871B CN1005871B (en) | 1989-11-22 |
Family
ID=4815090
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN87104966.XA Expired CN1005871B (en) | 1987-07-25 | 1987-07-25 | Laser air shooting simulator for airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1005871B (en) |
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| CN101813947A (en) * | 2009-02-19 | 2010-08-25 | 北京航空航天大学 | Movement tracking method and device of flight emulation electric movement system |
| CN101893410A (en) * | 2010-05-11 | 2010-11-24 | 上海科斗电子科技有限公司 | Laser aiming system for rapid moving object |
| CN102135395A (en) * | 2010-01-27 | 2011-07-27 | 深圳华强智能技术有限公司 | Bullet stricken effect simulating device |
| CN104635240A (en) * | 2010-05-11 | 2015-05-20 | 上海聚然智能科技有限公司 | Mixedly-using target transmitting system for radio radar and laser radar |
| CN106448325A (en) * | 2016-11-16 | 2017-02-22 | 北京安达维尔航空设备有限公司 | Real soldier combating system for armed aircraft shooting training |
| CN107339908A (en) * | 2017-06-26 | 2017-11-10 | 北京盈想东方科技股份有限公司 | A kind of nachinegun fire dot laser simulator |
| CN110488633A (en) * | 2019-08-29 | 2019-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of avionics weapon attacking test macro |
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| CN113467516A (en) * | 2021-07-26 | 2021-10-01 | 深圳市北斗云信息技术有限公司 | Simulation control method, system and terminal based on unmanned aerial vehicle ground attack |
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1987
- 1987-07-25 CN CN87104966.XA patent/CN1005871B/en not_active Expired
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| CN101813947B (en) * | 2009-02-19 | 2014-07-23 | 北京航空航天大学 | Movement tracking method and device of flight emulation electric movement system |
| CN101813947A (en) * | 2009-02-19 | 2010-08-25 | 北京航空航天大学 | Movement tracking method and device of flight emulation electric movement system |
| CN102135395A (en) * | 2010-01-27 | 2011-07-27 | 深圳华强智能技术有限公司 | Bullet stricken effect simulating device |
| CN102135395B (en) * | 2010-01-27 | 2013-03-27 | 深圳华强智能技术有限公司 | Bullet stricken effect simulating device |
| CN104635240B (en) * | 2010-05-11 | 2017-05-10 | 上海聚然智能科技有限公司 | Mixedly-using target transmitting system for electromagnetic wave radar and laser radar |
| CN101893410B (en) * | 2010-05-11 | 2015-05-13 | 上海本星电子科技有限公司 | Laser aiming system for rapid moving object |
| CN104635240A (en) * | 2010-05-11 | 2015-05-20 | 上海聚然智能科技有限公司 | Mixedly-using target transmitting system for radio radar and laser radar |
| CN101893410A (en) * | 2010-05-11 | 2010-11-24 | 上海科斗电子科技有限公司 | Laser aiming system for rapid moving object |
| CN106448325A (en) * | 2016-11-16 | 2017-02-22 | 北京安达维尔航空设备有限公司 | Real soldier combating system for armed aircraft shooting training |
| CN106448325B (en) * | 2016-11-16 | 2019-03-22 | 北京安达维尔航空设备有限公司 | It is a kind of for equiping with arms the armed forces in real combat engagement system of aircraft gunnery training |
| CN107339908A (en) * | 2017-06-26 | 2017-11-10 | 北京盈想东方科技股份有限公司 | A kind of nachinegun fire dot laser simulator |
| CN110488633A (en) * | 2019-08-29 | 2019-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of avionics weapon attacking test macro |
| CN112464451A (en) * | 2020-11-16 | 2021-03-09 | 中国人民解放军海军工程大学 | Anti-aircraft missile weapon hit probability correction method based on combat simulation system |
| CN113467516A (en) * | 2021-07-26 | 2021-10-01 | 深圳市北斗云信息技术有限公司 | Simulation control method, system and terminal based on unmanned aerial vehicle ground attack |
| CN113467516B (en) * | 2021-07-26 | 2022-09-20 | 深圳市北斗云信息技术有限公司 | Simulation control method, system and terminal based on unmanned aerial vehicle ground attack |
| CN115164644A (en) * | 2022-08-30 | 2022-10-11 | 北京千禧卫通装备技术有限公司 | Method and system for accurately aiming and shooting cabin door machine gun in helicopter flying process |
| CN115164644B (en) * | 2022-08-30 | 2024-05-03 | 北京千禧卫通装备技术有限公司 | Accurate aiming shooting method and system for cabin door machine gun in helicopter flight process |
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