KR850000014B1 - System for aircraft gunney - Google Patents

Abstract

The gunnery simulation system employs a sighting panel, such as a head-up display, for presenting a field of view including the target to the gun operator. Data describing the movement of the aircraft are generated and used to generate bullet indicia for display and the sighting panel in response to the simulated firing of the guns. The bullet indicia represent the actual paths which would have been taken by real bullets. The aircraft movement data includes roll rate, pitch and yaw rate, lift acceleration, air speed gun angle and relative air density.

Description

Shooting system

1 is a schematic diagram showing a view as viewed by a ballistic ballistic trajectory representing a simulated bullet fired from a target aircraft and by a pilot of the target aircraft and a pilot of the attacking aircraft.

2 is a comparison of accuracy of analytical vision distance method for analysis when radar automatic tracking is used.

3 is a schematic diagram showing the interrelationships between various components of a shooting system according to an embodiment of the present invention.

4 is a vector diagram useful for understanding the development of the mathematical theory underlying the operation and design of the shooting system.

5 is a schematic diagram showing in more detail the computer 30 shown in FIG.

6A and 6B are flowcharts of a program used to execute a shooting system and a shooting method with a computer (30).

7 is a memory location used by the computer in executing the shooting system and shooting method.

8 is a bullet display memory diagram used by the symbol generator 28 (FIG. 3) to control the display unit 30 (FIG. 3) to display a bullet-ballistic display pair representing a simulated bullet.

The present invention relates to a fire simulation system for use in simulated bombardment precision enhancement and bombardment training of an aircraft.

The most serious limitations in training for combat pilots' air-to-air firing skills were the lack of actual targets and the lack of equipment to score scoring targets when used.

Currently used targets are dart, beacon flags, pigads (Fiberlass aerial signs) and drones. The first target of these targets is towed and therefore its maneuverability is limited. They are also much smaller than conventional aircraft targets and are particularly difficult to practice over long ranges.

These limitations are largely overcome by the use of drones, but this method is extremely expensive due to the high cost of drone targets and ammunition for training of regular flight units. In addition, the use of ammunition and the generation of target debris create flight safety problems and constrain the space required for training due to the risk of falling debris. In addition, in the case of an unmanned aerial vehicle, an expensive control system is required and the unmanned aerial vehicle is used only once. When towing targets are used, the price is increased due to the need for towing aircraft and additional pilots for towing aircraft.

In addition to price and safety issues, the wrong way of measuring distance is not satisfactory when scoring actual shooting results. When using a target with a conventional whistle, only a circle of targets that are actually punctured can be reliably scored. It is also difficult to determine exactly what precise action actually produced by the pilot will result from the relative hits and misses recorded on the aiming video tape.

However, the most serious problem is the lack of realism of target mobility. Techniques developed for effective shooting against small, non-mobile targets may be inaccurate for the effective shooting of large, difficult-to-capture targets encountered in actual air combat.

In the prior art, the shooting of the simulated bullet on the actual manned aircraft target was attempted rather than the shooting of the simulated aircraft target. However, this real time system required the ability to estimate the target's automatic angle and range in order to calculate and display the number of hits per shot in the cockpit. Although such target tracking is desirable, there are many real air to air shooting situations where sufficient time is not available to achieve automatic tracking of angle trackers and range trackers, although this automatic tracking capability is useful for real or simulated aircraft.

It is therefore an object of the present invention to provide an improved aircraft shooting training and evaluation system in which an actual aircraft is used as a target.

In order to achieve the above object according to the present invention described and implemented hereinafter, an aircraft shooting simulation system for evaluating simulation and firing drills exhibits four seasons including a target for the gun operator. An aiming panel, a device for generating a data signal indicative of the operation of the aircraft, a display for displaying and displaying a simulated bullet, a device controlled by an operator to simulate the shooting of the aircraft at a target, Control the operation of the display device to display the simulated bullet in response to the simulated shooting and display the simulated trajectory of each simulated bullet displayed in response to the data signal so that the display of the trajectory of the simulated bullet is fired from an aircraft gun. It includes a device to represent the actual trajectory following the bullet.

The enclosed drawings, which are incorporated in and constitute a part of this specification, illustrate one embodiment of the invention together with a description to illustrate the principles of the invention.

Referring to FIG. 1, it can be seen that the present invention uses the principle of simulated bullet fired from a real target. This is accomplished by projections of "dots" or images used by the gunman (pilot) of the attacking aircraft to track the trajectory of bullets assumed on the head-up mark (HUD). This allows the pilot to observe the trajectory of the simulated bullet as it moves toward the target in essentially the same way as the tracer used for live bullets.

Alternately, the points are displayed only within the shooting camera system and are recorded for later use by estimating the pilot's capabilities. This can be done by superimposing the four-dot point marks of the gun camera 72 (FIG. 3), which may or may not be positioned to record the pilot's actual four seasons.

In this case, the marked "dots" do not directly represent the bullet itself, two more points are projected for each bullet and the bullet position (which does not actually need to be marked) is halfway between the two points. This principle is shown in FIG. 1, where points b ₁₁ and b ₁₂ are equidistant from the simulated ballistic trajectory of the first simulated pilot fired after the pilot pressed the trigger. The position of the circle itself is halfway between the points b ₁₁ , b ₁₂ . Points (b ₂₁ , b ₂₂ ), (b ₃₁ , b ₃₂ ) and (b ₄₁ , b ₄₂ ) are equidistant from the second, third and fourth simulated firings, respectively.

The target T is shown with respect to the pair of points and the distance between the pair of points is chosen to be equal to the known specification of the target, such as, for example, the wing length of the aircraft. The simulated home position of the points is marked as concentrated as it moves from its muzzle along its trajectory. When the source is a target range, the point is determined by observing the lateral separation between the pair of points representing the circle. When the distance between the points is equal to the selected target specification, the circle is in the plane of the target.

The use of dual points is used by the pilot or a person evaluating the pilot's ability through post-observation of the film or videotape generated by the camera 72 to determine the point at which the bullet penetrates through the target surface. At this point, the circle covering the target image is hit. Therefore, this simulated bullet display system provides a more accurate and useful pilot capability assessment than the conventional use of simulated target technology and tracking sources.

The accuracy of the target range that can be measured by this system is greatly limited by the video resolution of the videotape because the "hit" is determined visually by the match of the selected target specification and point space. For the best HUD operation these days, the camera film resolution is about 0.5 milli radians (mr) under normal brightness.

Figure 2 shows a set of diagrams A, B, and C for the assumed state as follows. The actual wind speed of the aircraft launch is about 450 knots (800 km / hr: 800 km / hr). "Target aircraft are F.4 fighters. The altitude between them is 3000 meters. The firing aircraft has an acceleration of 4.5 G, where G '= 980 cm / sec ² , acceleration due to Earth's gravity.

The horizontal side of Figure 2 shows the range, in meters, of the distance between the two aircraft. On the vertical side, the angle observed by the aircraft with the aircraft is expressed in milliradians (mr). Graph A is a range function that reflects the current angle by mr to the target aircraft at an angle of 30 °. Graph B shows the shot miss error (in mr) of the range function calculated by the normal aircraft radar calculation, which depends on inaccurate estimates for 2mr inaccurate 10m targets. Graph C represents the miss miss shot error calculated by the so-called "visual distance metric", which depends on the inaccuracy of 0.5mr due to the 0.5mr camera film resolution mentioned. It is clear that the sight distance metric is more precise than a conventional aircraft radar that calculates the target distance for a distance rising to 500 meters. Unexplained bullet impact errors are within normal target specifications outside the range of about 800m.

If radar autotracking is achieved, the point in time at which each simulated circle crosses the target range can be determined by the aircraft's operating characteristics and flight from known semi-mechanical parameters at launch time. This point can be marked in time and recorded directly on the pilot and videotape or other film. Thus, the visual acuity method can be used as a more accurate error evaluation method for short distances, that is, 500 m or less without radar automatic tracking, and as a long-distance backward evaluation method when the recorded data is analyzed.

Evaluation marks can be simply inspected by reducing the target wing length to zero, or by firing the real tracer under conditions that can be easily observed and photographed. Between the real and simulated members, the aircraft is maneuvered and must be matched one-on-one, while the circle is flying. Under normal operating conditions, this also provides the pilot with a valid way to check the aiming accuracy of the aircraft gun.

For example, there is no limitation that the exact target wing length of the simulated launch described above should be provided with the known actual target wing lengths and the values used. This complicates data reduction for precision but useful results can be obtained.

When the fire mark is included in the same HUD used by the pilot to aim the gun, the pilot has a sense of firing of the weapon that fires at the target during training exercises and provides a useful class of rapid return of the result. However, if the pilot's mind is distracted by the inclusion of an assessment mark with normal aiming, the simulator will be superimposed on the videotape generated by the aiming TV camera.

3 is a schematic diagram of an aiming system according to a preferred embodiment of the present invention. The pilot (gun gun operator) located in B is displayed in four seasons through the combined glass panel 22 arranged by the conventional HUD type. The four seasons of the pilot include a line of sight 11 to the target.

As practiced here, the display device for displaying and displaying a simulated bullet point or ballistic display includes a cathode ray tube (CRT) 26 and a collimating lens 27 and the pilot's quarterly image through the combined glass 22. It includes a view display unit 24 that operates to project the view mark. The aiming lens 27 is used to connect the display images so that they are radiated from the target area, for example, to the pilot. This aiming device is known in connection with the HUD system and is used to eliminate parallax problems and allows the pilot's head to move freely in the field of view without reducing the accuracy of the system.

As used herein, the display unit 24 protrudes the ballistic ball mark or points by a control signal received from the control device 25 including the symbol generator 28 and the digital computer 30. The latter device comprises a plurality of data input sources 34, 36 and 38 and an analog-to-digital (A / D) converter unit 32 from a device for generating a data signal depicting aircraft operation. Receive input via.

The wind speed data generator 34 has an A / D unit 32 with lines 52, 54 and 56 representing the actual wind speed V _a , attack gun angle α _g and relative air density ρ / ρ _o of the aircraft, respectively. To feed the signal. These signals are encoded by the A / D converter unit 32 and transferred to the computer 30 via the data bus 64.

The inertial data generator 36 outputs signals indicating landing acceleration Aw, roll rate p, pitch rate q, and shake rate r of the aircraft, respectively (58), (60), (62) and (64). To provide. These signals are also encoded by the A / D converter 32 and transferred to the computer 30 via the data bus 64.

As used herein, the device controlled by the operator to simulate the firing of an aircraft gun is a trigger subsystem that provides a signal T corresponding to the same type of target as the signal T representing the action of the gun port trigger by the pilot. (38). The signal T may be a single pulse representing the firing of a single bullet and more similarly may be a series of pulses corresponding to a series of bullets fired consecutively at the target. These signals are supplied to the A / D converter 32 and to the computer 30 via the data bus 64.

Suitable inertial and wind speed data detectors for digital computers, HUDs and modern fighters are sufficient for the mechanization of the display shown in FIG. Typical sensor requirements are as follows.

Actual wind speed 30 to 300m / sec ± 2%

Pitch Ratio -6 ° to + 30 ° / sec ± 0.05 ° / sec

Attack angle 0-20 ° ± 1 °

Flicker Ratio 20 ° / sec ± 0.05 ° / sec

Relative air density 0.2 to 1.1 ± 5%

Roll Rate 200 ° / sec ± 0.5 ° / sec

Normal acceleration -1 to + 7G '± 0.1G'

The videotape camera 72 is positioned to record its aim through the pilot's viewing panel 22. Thus, the ballistic ball or the target and approach stream of points can be recorded on the videotape for later analysis and evaluation.

It is necessary to calculate the trajectory of the simulated bullet to determine whether or not the simulated bullet is aimed correctly to hit the target aircraft. This calculation should take into account the bullet speed of the bullet, the impact of the bullet's gravity, the air velocity and direction of the air density and other factors when firing a simulated bullet.

및 사거리벡터

의 성분을 기하학적으로 도시한다. 발포항공기의 위치는 원래의 a/c 점에 관한 세공간규격을 측을 따른 유니트벡트를 나타내는 성분

,

및

및 원래 a/c 점에 의해 표시된다. 유니트벡터

는 항공기의 우측날개를 따르며, 유니트벡터

는 총구축을 따르며, 유니트벡터

는 관례에 의해 날개에 대한 정상방향내의 하방을 따른다. 유니트벡터

는 표적에 대한 조준선을 따른다. 벡터

는 총구속도 V_m의 스칼라 및 유니트 벡터

의 곱이다. 항공기의 실제충속은 벡터

에 의해 한정된다.Figure 4 is a bullet velocity vector describing the trajectory of a bullet at some point after firing.

And crossroad vector

The component of is shown geometrically. The position of the foamed air vehicle is a component representing the unit bet along the three-space specification relative to the original a / c point.

,

And

And the original a / c point. Unit vector

Follows the right wing of the aircraft, unit vector

Follows the total construction, unit vector

By convention follows downward in the normal direction to the wing. Unit vector

Follows the line of sight to the target. vector

Is a scalar and unit vector of the muzzle velocity V _m

Is the product of. The actual impact of the aircraft is vector

It is limited by.

및

을 산정하기 위한 방법은 많고 디지탈컴퓨터로 사용하기 적절한 특정한 것은 폐쇄루프집적이고 여기에서 총탄에 따른 작용력을 묘사하는 적분등식의 제1차적분은 다른 방법으로 초래되는 오차에 대한 약간의 교정을 포함하는데 의해 충분히 정확하게 이루어진다.vector

And

There are many methods for estimating, and one that is suitable for use as a digital computer is a closed loop aggregation, where the first integral of the integral equation, which describes the force acting on the bullet, includes some correction for errors caused by other methods. Is made sufficiently accurate.

The distance scalar moved by the bullet R _b from the airmass for a given time after firing is

From here

=0.36 rad/sec 이고 ρ/ρ_o는 상대적인 공 기밀도로서 0.2 내지 1.1이다.And k _o is the ballistic coefficient, approximately 0.00625

= 0.36 rad / sec and ρ / ρ _o are 0.2 to 1.1 as relative air tightness.

Except for the influence of gravity to be added later, the direction of R _b exactly follows the direction of the internal bullet velocity,

=

_a+

_m(2)

=

_a +

_m (2)

therefore

에서 통상적으로

는

를 의미하고 x는 벡터곱을 의미하며

이고, p, q 및 r은 각각 관성데이타발생기(제3도)에 의해 결정된 앞서 설명된 롤, 피치 및 흔들림비율이므로, Vb₍₀₎는 항공기 좌표시스템

,

,

내에서 관측될 필요가 있다.V _o is constant in the inertial system and the acceleration of the bullet at time t = 0

Normally in

Is

Means x product

And p, q and r are the roll, pitch and shake ratios described above determined by the inertial data generator (Fig. 3), respectively, so that Vb ₍₀₎ is the aircraft coordinate system.

,

,

It needs to be observed within.

therefore

α _o = 0 (fire time) attack angle of the gun

β _o is the side slip angle at 0

는

,

,

의 각도비율이다.

Is

,

,

The ratio of angular

therefore

,

,

에서 관측된 바와같이 총탄 내부속도성분은therefore

,

,

As observed in the bullet internal velocity component,

일 경우, 원에 대한 거리벡터는If the aircraft's position shift from the launch point

If, the distance vector for the circle is

a_b=

b-

a (10)

a _b =

b-

a (10)

to be.

가

좌표내에서 결정되는 것도 필수적이다.

end

It is also necessary to determine in coordinates.

The total gravity drop of the bullet including the air towing effect is easily shown for the 3/2 pressure towing to be formed.

Where g = G '= 980cm / sec ²

(18) the altitude and the turning component are respectively

Where θ is the aircraft posture and ψ is the aircraft roll attitude.

The altitude and pivot angle to be displayed for each pair of simulated bullets are

And where Z _p is a gun for aiming Time: 0≤Z ≤6m _p and w is the target wingspan.

These representations for λ _v , λ _W1 and λ _W2 can be simplified by replacing any term derived with a suitable approximation. In particular, the second and third terms on the right side of Eq. (15) can be ignored in terms of almost all air-to-air gun artillery situations. The maximum error resulting from this approximation is evaluated by estimating the ω _v R _aw term.

For _f ω _v = 0.25rad / sec, V _a = 270m / sec, T _f (gun bullet time) is 1 second and α = 0.2rad,

This is a negligible error of range.

Similar approximation of equation (7) is not appropriate. Because the corresponding range error is larger than that in (23).

이고 여기에서 통상적으로

이다. 특정한 비행시간에서의 전체고도 각 오차는However, a potentially important misorder can result from the finite ratio of incremental digital estimates. The measurement of this error can be obtained from the analysis of equations (8) and (9). The altitude angle error, ε, resulting from the digital integration for each mid-balance interval Δt is approximately

And here typically

to be. The overall altitude angle error at a particular flight time

이고 여기에서 n은 산정간격수이다.

Where n is the estimated interval.

Although this error is small, it cannot be ignored as a whole. However, since this is small, it is possible to correct by simply adding the measurement error 31 to the final calculation of the elevation angle. The turning error is measured in equation (8).

αω_u(34)를 가정하도록 오차분석에 대해 충분히 정확하다.V _bov = ω _u V _{bow -ω w} V _bou (33) This is the flying coordinate, ω _w

It is accurate enough for the error analysis to assume αω _u (34).

If the direction pedal is used at any significant angle to generate a side slip, the analysis of paragraph 2 (ω V _bou ) is handled exactly as performed in the development of (31). In this case ω _w is about 100 mr / sec, so the corresponding error due to the first order integration is about 1 mr (which can be ignored).

Typical maximums are ω _u = 2rad / sec, λ _v = -250mr, Δt = 0.0sec, ε ₂ = 5mr.

In particular, this is a horizontal error and is not ignored. Equation (42) is therefore a suitable correction to be added to the swing bullet angle. The angles of rotation 22 and 23 can be approximated with an arc tanfunction argument with sufficient precision.

···(43) 표 1은 x와 tan^-1x를 조사하여 제3차항(

)³을 생략하는데 기인하는 오차목록이다.tan ^-1 x = x-

(43) Table 1 shows the third order term by investigating x and tan ^-1 x.

) Error list due to omission of ³ .

TABLE 1

The third term is mandatory for altitude, but not for turning angles.

The above equation for deriving the angular coordinates λ _v , λ _w1 and λ _w2 for each pair of points corresponding to the simulated bullet can be summarized as follows.

1. Air Towing

2. Initial bullet velocity observed in aircraft (,,) coordinates

3. The firing range of the shooting point

R _au = τ V _bou R _bv = τV _bou R _bw = τ _bow

4. Aircraft range with respect to shooting point

5. Gravity drop

6. Total firing range for aircraft

R _abu = R _bu -R _au R _abv = R _bv -R _av R _abw = R _bw -R _aw

7. Aiming angle

Although the equations reviewed above operate gun fire and evaluation systems and methods to provide meaningful results in the performance of air guns, significant additional capabilities can be gained when the aircraft radar is used to validate range auto tracking. It is also possible to mark points or circles directly on the target range, even if the instant positions of the points are indicated.

The advantages of this method are as follows.

Direct display of bullet miss distance makes data reduction very simple.

2. The pilot can immediately see the result of the shooting efficiency in flight.

3. The missed distance can be measured more accurately over long distances.

4. The measurement margin of bullet miss distance provides additional precision or guarantee that some useful information will always be obtained.

u측 성분과 총탄위치의 u축을 비교하며 여기에서 R_T는 레이다로 부터의 표적사거리이고, λ_tv는 레이다 고도수평장치각도(ADL에 관한)이고, λ_tw는 레이다 선회수평장치각도이다. 총탄각도는 부등식(44)의 제1반복에서 대체된다.The angular position of the bullet at the target range is expressed in the form of 6mr circles (dispersion) at the time that the shot range is equal to the target range. A simple and sufficiently accurate method is to target the target area,

The u-axis of the u-side component and the bullet position is compared, where R _T is the target range from the radar, λ _tv is the radar elevation level angle (relative to ADL), and λ _tw is the radar turn level angle. The bullet angle is replaced in the first iteration of inequality (44).

Due to the high angular ratio characteristics of air-to-air guns, some intermediate term between computer iterations will generally be required.

For example, for an angle ratio of 200 mr / sec, the mentioned computer repetition time Δt of 0.02 sec results in 4 mr steps between successive gun angles. This is a small but negligible error.

If ΔR _bt = R _abu , (T _f ) -R _T (T _f ) (45) is the range u component from the target to the bullet of the first repetition after satisfaction of the inequality (44).

Therefore, proper correction of the total shot distance component before marking

여기에서 ΔR_abw(T_f)는 총탄이 표적을 관통하는 간격등안 R_abw(T_f)의 변화이고 ΔR_abu(T_f)는 총탄이 표적을 관통하는 간격동안 R_abu(T_f)의 변화이다.

This change in ΔR _abw (T _f) is changed and ΔR _abu (T _f) is R _abu (T _f) during the interval that the bullet passes through the target of not R _abw (T _f) at regular intervals to the bullet passes through the target in to be.

Due to the fairly low shake rate, the middle term for R _av is ignored.

Thus, the altitude and angle of rotation coordinates are calculated according to the equation summarized in equation (7) above.

5 shows the computer 30 of FIG. 3 in more detail. The computer 30 includes a central processing unit 102 interconnected with a timing circuit 104 and a memory 106. The central processing unit 102 receives outputs from the trigger subsystem 38 and the inertial data generator 36 via the air data generator 34 and the input / output control 108 and via the bus 64. Similarly, central processing unit 102 passes information from memory 106 to bus 66 and through symbol generator 28 through input / output control 108. This information includes the total ballistics indicator or the angular coordinates for a pair of points indicated by the aiming display unit 24 on the bonding glass 22. A suitable central processing unit is the MCP701A digital display processor built between General Electric.

In a preferred embodiment, the angular coordinates of the points are generated by the central processing unit 102 by the equations discussed above. In order to perform these calculations and generate angular coordinates, the central processing unit 102 is programmed to perform the necessary operations.

6A and 6B show a program for accomplishing this task.

7 shows a data table present in the memory 106 for storing data necessary to perform the calculation.

8 shows an indication table present in a memory for storing angular coordinates of points.

The following is a memory list of the amount of data used to calculate angular coordinates.

XC: C register of MCP701A computer

XA: A register of MCP701A computer

XB: B register of MCP701A computer

NBUT: The number of simulated bullets that can be displayed simultaneously to represent the bullet flow (max. 10).

KBUT: Initially same as NBUT used as pointer, decremented N times.

ITMAX: Constant + (total flight) / (repeat rate) equal to 1

TFF: Aviator for simulated bullet

PG35: Start address of page 3 scratchpad memory

DEND: Last position address used in display list

DRANG: Calculated range from launch aircraft to simulated bullet

DMIN: Constant set to check minimum range

BIPAS: If T (K) = 0, DRANG <DMIN or if the bullet is out of the four seasons of the HUD, the command to bypass the simulated bullet.

TRFLGI: Split asset equal to 1 when the trigger is tightened to fire a simulated bullet

BSC: counter used to indicate when a new bullet is launched

The table in FIG. 7 stores data describing the state of each simulated bullet. In this embodiment, each table has 10 entries and thus the system has the ability to simultaneously display 10 simulated bullets in the form of 10 pairs of bullet trajectories, ie 10 pairs of dots.

Information stored in the table includes the following:

T (K): Current flight time for simulated bullets

DRANG: Crossroad vector for simulated ammunition

DVBV: Different shot increment rate for V axis

DVBV1: DVBV from the previous iteration

DVBW: Total bullet increment along the W axis

RVDOT: V-Range Range of Bullet

RVDOT ₁ : RVDOT from previous iteration

RWDOT: W-Range Range of the Bullet

RWDOT ₁ : RWDOT from previous iteration

AB: the current acceleration of the bullet

VB: the current speed of the bullet

DVB: Total bullet speed minus aircraft speed

UBW: W-axis bullet speed

RVV: V-axis gun range

RVV ₁ : RVV from previous iteration

RWW: W-axis gun range

The RW, RVV ₁ and RWW quantities are all double precision, meaning that two storage words are provided for each of these quantities.

Referring to FIG. 6A, the operation of the launch evaluation and marking system is started by setting the A register and the B register to the PG35. K is set to 1 and KBUT is set to NBUT. The next step is to fetch T (K), which is T (1) in this case. This amount is checked for zero, and if it is zero then the entry of the bullet is not active and a new position of the bullet position is not required for that entry. In this case, the KBUT is decremented by 1 and checked if it is zero. If KBUT is 0, all entries in the bullet are processed and processed continuously to update any remaining display angle coordinates.

However, if the list of T (K) is non-zero, this entry in the bullet table indicates to reflect the bullet of the active parent, and both T (K) are set to both T (K) -1. The flight time is estimated as TFF = (ITMAX-T (K)) 0.02. The amount 0.02 is selected because the system is set on the bullets (1) to (10) simultaneously. The current 10 bullets have a minimum interruption time of 20 ms and therefore both ITMAX-T (K) represent the number of iterations executed, and the amount 0.02 corresponds to the time between iterations.

After calculating the flight time, the new bullet position TFF for bullet K is calculated by the above equation, and the result is stored in the Kth entry of the bullet table shown in FIG. Next, the pointer KBUT treated with the number of bullets is decremented by 1 and checked to see if it is zero. Otherwise, the A register is incremented by 1, the B register is incremented by 2, and K is incremented by 1. The next entry of the bullet is processed in the manner described above, and the same procedure is executed repeatedly until all entries of the bullet are called and a new bullet position is calculated and stored in each action entry.

Once this is accomplished, it is reset to A register and B register PG35, C register is set to DEND, K is reset to 1, and KBUT is set to NBUT. The process continuously updates the pair of bullet points stored in the bullet display list of FIG. 8 or the angular coordinates for each bullet ballistic display.

This is accomplished by first fetching the first entry of the bullet target T (K) (in this case K = 1). If T (K) is zero, the bullet entry of this bulletin ticket is not activated and no processing is required. Thus, the computer operation passes to BIPAS and is prepared to examine the next entry of the bullet. However, if the T (K) entry is not zero, the DRANG for that bullet entry in the bullet is checked against the minimum indicated range DMIN. If DRANG is less than DMIN, the processing for the bullet entry in the bullet is bypassed. Otherwise, the pair of points representing the simulated bullets, the X and Y positions for each point, are assigned to the maximum display variable to ensure that the computer 30 does not generate angular display coordinates outside the display range of the display unit 24. Are compared. If this is the case, other processing on the bullet entry of the bullet is bypassed. However, if the X and Y coordinates are within the marking limits, then the angular coordinates stored in the display list shown in FIG. 8 corresponding to this bullet position in the bullet bullet of FIG. 7 will be the newly calculated bullet position for that particular bullet entry. Change.

The display list in FIG. 8 uses six memory words for each bullet. These six memory words are POSX and POSY, which in turn correspond to λ _v and λ _w1 , respectively. The JM ₅ instruction means jumping the first five words and other JM ₅ instructions in the POSX and POSY processing corresponding to λ _v and λ _w1 , respectively.

The bullet display list shown in FIG. 8 reflects the working bullet position, that is, the bullet 1 and the non-acting bullet positions 3 to 10 of the bullets 2 and 8. In the inactive bullet position, the first memory is a JMP6 instruction that results in bypassing all processing for that entry in the bullet display list.

Once an entry in the bullet display list is updated with a new angular coordinate that reflects the newly determined bullet position, entry T (K) is checked to see if it is one. If so, that entry in the bullet is inactive by setting T (K) to zero. This is done because the flight time for the simulated bullet that corresponds to that entry in the bullet ticket is equal to the maximum flight time in the system so that the pairs of points for that particular bullet entry will not already be displayed.

As can be seen in Figure 6a, the operation follows. (1) BIPS Decision (2) The settings of Decision (3) T (K) with T (K) equal to 1 are all equally zero.

These operations include the increment of the A register by 1 and the B register by 2 and the increment of the C register by 6 and the K increment by 1 and the reduction of KBUT by 1. If the KBUT is not zero, the next entry in the bullet list is processed in the manner described above to update the corresponding entry in the bullet list.

If all entries of the bullet are processed, that is, KBUT is 0, the END routine is loaded into the display list and the symbol generator passes the angular coordinates of each point to the display unit for display on the aiming panel 22. Let's do it. The manner in which the display of points is achieved in response to angular display coordinates is known and need not be further explained.

The processing operation shown in FIG. 6B is performed in response to the firing of another simulated bullet by the gunman operator or the pilot. First, it is checked to show that the trigger marker TRFLG is 1. If not, a new simulated bullet is not fired and the process is reduced to a new routine of the illustrated bullet in FIG. 6A. If TRFLG is 1, other trigger markers TRFLG are also checked to show that this is 1. If so, the bullet counter BSC is decremented by 1 and checked to see if it is zero. If this is not 0, enough time is not passed because the previous bullet has not entered the system and is restored to the new bullet position routine in FIG.

However, if the BSC is zero, the BSC is reset. That is, in this case it is set to 6 and a new entry is placed in the bullet bullet shown in FIG.

The reason why the new bullet entry cannot be placed in the bullet table immediately upon the trigger press by the gun operator is that the system is set to adapt to a limited number of bullets, in this case 10, and is due to the processing speed by the central processing unit, Continuous pressurization of the trigger can very quickly drain the number of entries in the bullet. The system has been adjusted to display 10 bullets for the maximum cycle time per second, so slingshots enter the system every 10 seconds.

The system entry of the new simulated bullet is accomplished by examining the bullet table for entry 0 at the T (K) position. If zero entry is found, ITMAX is loaded into the T (K) storage location relative to the location of the bullet. In addition, the entry of certain variables is performed at this time, and the instantaneous values of the air data detector and the inertial data detector are stored in a form appropriate for the entry of the bullet. After these time steps are executed, the process is restored to the new bullet routine of FIG. 6A.

In operation, B (the pilot sitting in Figure 3 aims the target aircraft in his quarters 11. The pilot activates the trigger subsystem by triggering the aircraft's gun and the aircraft selector. Generates an aircraft selection pulse AS of the same type as the aircraft, and the trigger subsystem generates successive presses of the trigger or triggerers T for each pressurization These signals are provided to the analog-to-digital converter 32.

In the meantime, the air data generator 34 provides an instantaneous value for the speed V _a of the aircraft, the attack angle α _{g of the} gun and the relative air density p. These signals are similarly encoded by analog-to-digital converter 32. The inertial data generator 36 also supplies instantaneous values for the aircraft takeoff acceleration A _w and roll ratio P, pitch ratio q, and shake ratio r. Again, these signals are encoded by analog-to-digital converter 32 and supplied to the computer 30 as another input.

The computer 30 makes an entry of the bullet stored in its memory for each simulated bullet fired by the pilot. All necessary information for displaying and estimating the trajectory of the simulated bullet is stored in the corresponding entry of the bullet. From this data, the computer calculates the range and velocity vectors for each simulated bullet. The angular display coordinates are generated from a range vector and a velocity vector such that a pair of ballistics or a visual point can be displayed in a manner that represents the trajectory of a simulated bullet over a certain time length. Equations for calculating range and velocity vectors, as well as angular coordinates, have already been published.

The angle display coordinates for the points are stored in the bullet display list. Periodically, the computer transmits the contents of the bullet display list to the symbol generator 28 which controls the display unit 24 by projecting a ballistic ball mark or a point corresponding to each simulated bullet on the combined glass 22. . This superimposes the points on the pilot's four seasons so that the relative position of the target aircraft and points can be observed. Optionally, the camera 72 is coupled to the display unit 24 by the control line 74 so that the camera can record a superimposed image of the target and the point on the videotape as it is actually seen by the pilot.

The computer updates the trajectory for each pair of markers so that the points approach the target as if the actual bullet approached the target. This is achieved by reducing the distance between the points while the display position of the points is continuously updated. The tube composition between the points is calculated by the computer 30 by the target identical signal AS generated by the trigger subsystem. This separation is any standard function of the identified target, such as the wing length of an aircraft, for example. The concentration of the points is calculated to be clearly reduced to the selected specification of the target with increased distance.

The hit of the target aircraft by the simulated bullet occurs when the points are separated from each other and overlap the target at the same distance as the selected specification of the target. Again, as an example, if the selected specification is the wing length of the aircraft, the points overlap directly on the target. This corresponds to the plane intersection point of the target by the points representing the simulated bullet.

As an alternative embodiment, the radar unit 31 can be used to provide a true distance to the target R _t by radar auto tracking. Given this real range, the computer generates some form or pattern of dispersion of the visible signal indicating that the points reach the target range. If the points overlap directly on the target at the time of the visible signal, it can be assumed that the simulated bullet by the points hit the target aircraft. The video camera 72 records an image of the target and the visible signal generated continuously when the positions of the points and the points reach the target range.

It may be understood that the use of videotape in radar autotracking or the use of videotape without radar autotracking works to evaluate the pilot's firing technique and precision. This gears up to the pilot's shooting skills research, while using real aircraft as targets in simulated combat situations, eliminating the aforementioned drawbacks when using drones and towing targets.

It will be apparent to those skilled in the art that changes or modifications to the embodiments described herein may be made without departing from the spirit or scope of the invention. For example, in a system, ten or more bullets may be used to display simultaneously, and two or more points may be used to represent each simulated bullet.

Claims (1)

Aiming panel 22 containing the target and showing the four seasons to the gun operator, the aircraft's roll ratio P, pitch ratio q, shake ratio r, acceleration A _w , actual wind speed V _a , and attack gun angle α _g and relative air. A device (34, 36) for generating a data signal indicating a density ρ / ρ _o , a display device (24) for displaying and displaying a simulated trajectory by overlapping the four seasons on the aiming panel (22), and the target Displaying a simulated trajectory of the device 38 controlled by the operator to simulate the firing of an aircraft gun with respect to the simulated trajectory corresponding to the actual trajectory drawn by the live bullets fired from the aircraft gun at the target. Thereby displaying the simulated trajectory for each simulated trajectory displayed in the four seasons responsive to the data signal and operating the display device representing the simulated trajectory for the simulated firing of the aircraft gun. In the shooting simulation system, which is composed of a device 30 for firing and using an aircraft for evaluating the accuracy of shooting training and simulated shooting, each simulated trajectory is generated by the control device 30 and A controller configured to control the display device to display the pair of trajectories of trajectory including a pair of trajectories of interest and separated from each other by a distance representing the selected size of the target and equidistant from the simulated trajectories Featuring a shooting system.

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