FN-6 Operation Manual

Operation manual of FN-6 ground-to-air missile weapon system

Operation Manual of FN-6

Ground-to-air Missile Weapon system


Contents

1. General description

1.1 System composition

1.2 Combat airspace

2. Combat procedures

2.1 Preparation procedure before combat

2.2 Launching procedure

2.3 Missile flight

3. Safety operation rule

3.1 General requirement

3.2 Warning

3.3 Safe notes during launching the missile

Appendix Launching zone and killing zone


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1. General description

FN-6 is a single-man-portable, shoulder-fired ground- to- air missile

weapon system (This manual only concerns combat equipment). Under

the visual condition, by head-on and tail-chase attack (mainly head-on),

the combat equipment can intercept the fighter, fighter-bomber, strike

aircraft and armed helicopter whose speed is no more than 300m/s,

maneuver overload is no more than 6 and the flight height is no more than

4000m. The combat equipment can also cooperate with other air defense

equipment to protect the marching troops and important places.

Featured by easy-operation (with manual and automatic launching),

flexible-launching (launched in standing or kneeling posture, refer to

Fig.1-1 and Fig.1-2) and “fire-and-forget” ability, FN-6 missile can be

launched not only from trench, wide-land, wetland and roof of buildings,

but also from ships and the armed vehicles driving in the flat road (the

speed is no more than 20km/h).

Fig.1-1 Standing launch Fig.1-2 Kneeling launch


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Combat

equipment

MIT

GPGSD

LM

OAD

Missile

Launching

tube

Guidance

section

Fuse/Warhead

section

Motor

section

Fig.1-3 Composition diagram of combat equipment

1.1 System composition

FN-6 weapon system consists of combat equipment, testing cabin

and training equipment. Combat equipment consists of HNT-6

missile-in-tube (MIT), ND-6 ground power/gas supply device (GPGSD),

SK-6 launching mechanism (LM) and MG-6 optical aiming device (OAD)

(Fig.1-3). The optical aiming device or mechanical aiming device can be

selected according to practical combat condition.

“Operation and maintenance manual of HNT-6 missile-in-tube” see

the Appendix 1.

“Operation and maintenance manual of ND-6 ground power/gas

supply device” see the Appendix 2.

“Operation and maintenance manual of SK-6 launching mechanism”

see the Appendix 3.

“Operation and maintenance manual of MG-6 optical aiming device”

see the Appendix 4.

Missile-in-tube, the basic part of weapon system, is composed of

missile and launching tube, etc. (see Fig.1-4) The missile is composed of

guidance section, fuse/warhead section, and motor section.


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Fig.1-4 Missile-in-tube

The guidance section consists of IR seeker and control section, see

Fig.1-5. The section fulfils all functions of missile guidance system. IR

seeker collects target’s IR radiating energy and measures moving features

of target to form a command signal. The control section circuit converts

the command signal to a control signal to form an actuator (control

surface)-deflecting signal to control the direction change of control

surface, and control the missile to fly towards the target by guidance law.

Fig.1-5 Guidance section

Fuse/warhead section (see Fig.1-6) consists of fuse and warhead.

The main function of fuse is to send an igniting signal to ignite warhead

at the moment when the missile hits a target directly. The target is killed,

blasted and ignited by fragment from warhead explosion, overpressure of

explosion shock wave and high-temperature metal burning material.


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Fig.1-6 Fuse/warhead section

Motor consists of launching motor, delay igniter and chief motor, see

Fig.1-7. The chief motor is a dual-thrust, single combustion chamber solid

rocket motor. Its basic operating process is as follows: first launch missile

from the launching tube by launching motor, so that the missile obtains

required speed and spinning rate to leave the tube. The delay igniter

ensures ignition of chief motor beyond a safe distance for protection of

the shooter. The missile is speeded to a predetermined cruise speed by the

first-stage thrust of chief motor, then the flight speed of the missile is

slowly increased by the second-stage thrust until the operation of chief

motor is terminated.

Fig.1-7 Motor

The launching mechanism is composed of structural components and

electronic circuitry. It serves the function of supplying power for onboard


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equipment, running and rotating gyro, unlocking, signal analysis and

implementation of launching procedure during launching preparation and

launching process. The missile will be launched by the operation of

shooter. Fig.1-8 is the launching mechanism.

Fig.1-8 Launching mechanism

Ground power/gas supply device will provide ±20V,＋5V power

for the onboard equipment, and the high-pressure pure argon which can

cool the indium antimonide detector quickly. It is expendable. Fig.1-9 is

the Ground power/gas supply device.

Fig.1-9 Ground power/gas supply device

Installed on the launching tube, the optical aiming device will

enlarge the distance of surveillance, track, and aiming to improve the


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operation ability of combat equipment. Fig.1-10 is the optical aiming

device.

Fig.1-10 Optical aiming device

The container provides a good environment for storage and

transportation of the combat equipment in order to guarantee its

performance and life. There are 5 kinds of containers: No.1 for two

missiles-in-tube and four ground power/gas supply devices; No.2 for one

launching mechanism with jacket and one protective eyeglasses; No.5 for

one optical aiming device; No.6 for spare parts and tools of

missile-in-tube; and No.7 for spare parts of launching mechanism.

The general picture of basic combat equipment of FN-6

ground-to-air missile weapon system refers to Fig.1-11.

1.2 Combat airspace

The combat airspace of FN-6 missile combat equipment is:

Max. interception altitude: 4000m

Min. interception altitude: 15m

Max. slant range: 5500m

Min. slant range: 800m (head-on attack), 500m (tail-chase attack)

Max. short-cut course: 2800m

In appendix, the diagram of theoretical combat zone (launching zone,

killing zone) is provided when the combat equipment intercepts the high

and low speed targets.


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Fig.1-11Combat equipment of FN-6 missile weapon system 1.Ground power/gas supply device; 2. Launching mechanism; 3. Optical aiming device;

4. Missile-in-tube.


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2. Combat procedures

The combat procedures include preparation procedure before combat,

launching procedure and missile flight.

2.1 Preparation procedure before combat

The preparation procedure before combat is composed of the

procedure converting from package status to marching status, and the

procedure converting from the marching status to combat status.

2.1.1 Converting from package status to marching status

The procedure of converting form package status to marching status

is as follows:

a. Remove the lead seal, open the No.1 container.

b. Rotate the document box cover on container, take out the packing

list and related paper, check if the document is complete, then make sure

if the products inside are complete as per packing list.

c. Take out one missile-in-tube and one ground power/gas supply

device, mount the latter on the former, and carry the missile-in-tube on

left shoulder by right-declined with the head downwards.

d. Remove the lead seal, open the No.2 container, take out one

launching mechanism with jacket and one protective eyeglass. Take out

one ground power/gas supply device from No.1 container and place it into

the jacket and carry them on the right shoulder by left-declined.

e. Take out the optical aiming device and sheath from No.5 container,

then put the optical aiming device into the jacket and carry it on the left

shoulder by right-declined.

Note:

1) The above procedure is for the case of using optional optical

aiming device.

2) Procedure “e” can be omitted in the case of no optional optical


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aiming device.

3) In marching status: The shooter carries the jacket containing

launching mechanism, protective eyeglasses and back-up ground

power/gas supply device on right shoulder by left-declined, and carries

the missile-in-tube (connected with the ground power/gas supply device)

on left shoulder by right-declined, with the head of missile-in-tube

downwards, refer to Fig.2-1.

Fig.2-1 Marching status

2.1.2 Converting from marching status to combat status

The procedure converting from marching status to combat status is

as follows:

a. The shooter kneels down by one leg or squats and moves the

missile-in-tube with ground power/gas supply device to the front of chest.

b. Take out the launching mechanism from jacket and connect it with

the missile-in-tube.

c. Remove the fore and aft covers.


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d. Take out the optical aiming device from its jacket, and connect it

with launching tube. Open the fore cover of optical aiming device, and

determine if the eye lens filter is needed according to background.

e. Carry the weapon on shoulder.

f. Aim at the targets through optical aiming device.

Note: 1) The above procedure is for the case of using optional optical

aiming device.

2) Procedure “d” can be omitted when the optical aiming device is

not adapted, and procedure “f” shall be altered to: Raise the fore and aft

aiming device and leading indicating pin on the launching tube, and aim

at targets through mechanical aiming device.

2.2 Launching procedure

The launching procedure is divided into manual launching and auto

launching procedure.

2.2.1 Manual launching procedure

a. Aim at the target through mechanical or optical aiming device

(note: keep away from sunlight during aiming).

b. Once the target is found, turn the impact trigger of ground

power/gas supply device according to the direction of arrow to activate

the device.

c. The stable light signal will be showed in the optical aiming device

after the seeker captures the target, and the stable light and sound signal

will appear on the launching tube.

d. Press the launching trigger to the first position when the target

enters the launching zone, then the seeker will be unlocked from

electric-locking status and track the target stably.

e. According to the type, speed, altitude, right/left course, short-cut

course and slant range of the target, set corresponding elevation/azimuth


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leading.

f. Press the launching trigger to the second position, and the missile

is launched.

g. After launching, the shooter can shift to shield place. In the case of

multi-batch enemy aircrafts, the shooter should prepare for the next

launching.

2.2.2 Automatic launching procedure

a. Same as the item “a” in clause 2.2.1.

b. Same as the item “b” in clause 2.2.1.

c. Same as the item “c” in clause 2.2.1.

d. When the target enters the launching zone, just press the trigger to

the second position.

e. If the seeker captures the target stably, it will be unlocked

automatically. Set the elevation/azimuth leading within one second. If

the angular velocity q = sqs /10/1 , the missile will be launched

automatically.

Tab.1

Target velocity and

shooting mode

Leading

Elevation Azimuth

Low-speed

target

Head-on

attack Not add Add 2.5º-5º along the target flight direction

Tail-chase

High-speed

target

Head-on

attack Add 10º

If the target entering angle is no less than 45º,

add 10º along the target flight direction; if the

target entering angle is less than 45º, add 5º

along the target flight direction. Tail-chase

Not add

Fixed target Not add Not add

2.2.3 Leading

In order to decrease the initial deviation of trajectory effectively and

shorten the correcting time, the leading is required to be set during


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launching. The hit probability will be improved (especially for the near

zone) if the leading is suitable.

2.2.3.1 Set of leading

The set of leading is relative to the flight characteristics (velocity,

course, altitude) of targets and the shooting mode (head-on

attack/tail-chase), etc.

Choose the leading according to the requirements in tab.1 during

launching. In the table, the “target-entering angle” is the acute angle

between target flight direction and line of sight during launching, refer to

the Fig.2-2.

Fig.2-2 The schematic diagram of target entering angle

2.2.3.2 Methods of setting leading

a. Add the leading by means of mechanical aiming device and

indicating pin

See the Fig.2-3, “A ” is the convex point of indicating pin, and “B”

is the end of pin. The distance between “O” and “A” indicates the

elevation leading of 20º; the distance between “O” and “C” indicates the

azimuth leading of 10º. “D”, “E” and “F” are the middle points of “BC”,

“CD” and “BD” respectively, and indicate the elevation leading of 5º, 10º

Flight direction of target

Sight-line direction In head-on attack launching

Launching site

Sight-line direction In tail-chase launching

Launching site

Flight direction of target Entering angle of target

Entering angle of target

Target entering angle during

head-on attack launching

Target entering angle during

tail-chase launching


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and 15º respectively. “G” is the middle point of “OC” and indicates the

azimuth leading of 5º. Based on the symmetry theory, “H” indicates the

azimuth leading of 5º, and “I” indicates the azimuth leading of 10º.

The example of setting leading is as follows:

When attacking a high-speed target in head-on mode from right

course, the initial aiming center is the mechanical aiming device center

“O”. Before launching, the azimuth and elevation leading are both

required adding by 10 (in Fig.2-3, the “D” is the leading point), so the

shooter aims at the target through “D” point.

Fig. 2-3 The leading diagram of mechanical aiming device and indicating pin

b. Adding the leading by graduation board of optical aiming device

The angle scale of elevation and azimuth is indicated in the

graduation board of optical aiming device. Fig.2-4 indicates the

graduation of leading in the board. Each grid of the board indicates 5,

and there are 4 grids in azimuth and 3 in elevation, so elevation leading

can be added up to 15, and the azimuth leading can be added by 10.

For example, if attacking the high-speed target entering from left

course in head-on mode, the cross center with circle is the initial aiming

center. The 10elevation leading and 5azimuth leading are needed(in


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Fig.2-4, “A” is the point of leading). The shooter aims the target through

“A” point (refer to Fig.2-4).

Fig.2-4 Adding leading via graduation board of optical aiming device

2.2.3.3 Notes of adding leading

a. Aim the target through leading point directly after adding the

elevation /azimuth leading simultaneously.

b. The shooter should track the target stably by leading point before

the missile leaves tube.

2.3 Missile flight

The missile-borne battery is activated after the launching mechanism

delivers the launching command. The ground power transfers to the

missile-borne power 0.6s later. The fuse is power on. The missile-borne

gas vessel is opened 0.15s later. The missile-block pin drops out 0.15s

later. The launching motor ignites, and the missile begins moving forward.

Meanwhile, the missile spins in the tube under the action of lateral

inclined component of the motor thrust.

When the motor thrust overload is more than or equal to 35 and lasts

more than 45ms, a reference signal of the fuse clock is generated. The

time circuit of the fuse begins to count time.

The missile moves in the tube for about 0.05～0.085s. The initial

velocity is about 30m/s and the spinning rate is about 20r/s while leaving.


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The snap-on tail fin sleeves on the missile when the missile lifts off. The

missile flies a safety distance for more than 8m by means of inertia before

the first stage of the chief motor operates.

The fuse releases the first stage safety when the chief motor operates.

And it releases the second stage safety when the missile flies for about

1.6s, and 0.03s later the initiation circuit charges. The detonator and

booster are aligned. The fuse is ready. When the missile encounters the

target, the fuse detonates the warhead. If the missile misses the target, the

fuse detonates the warhead for missile self-destruct when the missile flies

for about 16s.

The missile guidance and control function are implemented by the

guidance system. The four-element detector of the seeker receives the

infrared signal of the target and forms an output signal, whose amplitude

is direct proportional to the angular velocity of line-of-sight, and whose

phase is consistent with the target azimuth. This signal is delivered to the

autopilot to control the deflection of control surface and form control

force. The missile flies to the target by proportional guidance law.

While attacking the high speed target, a forward offset signal Uqy is

applied in the guidance loop before the missile hits the target to make the

hit point move forward to the critical part of the target..

The operation procedure of the combat equipment, refer to the

Fig.2-5: Launching preparation and procedure of combat equipment.


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Fig.2-5 Launching preparation and procedure of combat equipment

Discover and track the target

Activate the ground power

and gas supply device

Deliver gas to the detector and

power to the electronic combinat-

ion and missile-borne equipment

Start and stabilize the gyro rotation

Put the launching trigger to the

second position

Target captured?

Green lamp lighting, and the sound

producing continuously

Unlock the gyro of the seeker

Activate and transfer the

missile-borne power

Activate the missile-borne gas

Initiate electrical squib of the missile-block pin,

Drop missile-block pin out

Ignite launching motor

Missile lift off

Target captured?

Green lamp lighting,

and the sound

producing continuously

No sound

and light

signal No sound

and light

signal

Yes

No

No

Yes

Put the launch trigger

to the first position

Manual launch for

low velocity target

Green lamp blinking and

the sound producing

continuously

Green lamp not lighting,

and the sound producing

intermittently

Launch trigger returns

to zero

Green lamp lighting and

the sound producing

continuously

Put launching trigger to

the first position

Unlock gyro

Put launch trigger to the

second position

q analysis q ＞12(°)/s q ＜1(°)/s

Put the launch trigger

to the second position

Unlock gyro


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3. Safety operation rule

3.1 General requirement

a. The combat equipment should be kept well, ready for combat at

any moment.

b. The operation of the combat equipment should follow this rule

strictly.

c. Only specially trained and qualified personnel is allowed to

operate the combat equipment.

d. Drop out or collision is forbidden.

3.2 Warning

a. Forbid to take out the missile from tube.

b. Forbid to aim the missile-in-tube without the front cover at the

sun .

c. Forbid to turn the impact trigger of ground power/gas supply

device when not launching the missile.

d. Forbid to jump off vehicle or high position while carrying combat

equipment.

e. Forbid to lay the unpackaged combat equipment directly on the

floor of the vehicle carriage during moving.

3.3 Safety notes during launching the missile

a. To avoid the missile falling down to the earth, the elevation angle

of launching should not be less than15º; to avoid the plume of motor

endangering the shooter, the elevation angle of launching should not be

more than 60º when launching in standing posture ,and not more than 40º

when launching in kneeling posture.

b. Requirement of launching site.

Any person, ammunition or inflammable is forbidden to be close to

the shooter in 10m if there is blindage.


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Any person, ammunition or inflammable is forbidden to be in the

90 fan section of 18m diameter behind the shooter if there is gravel in

the launching site.

There should not be high constructions (wall, blindage wall or

claybank) within 0.5m behind the back end of launching tube.

c. Forbid to remove the launching mechanism when operating the

missile-in-tube.

d. Forbid to down-decline the head of launching tube before the

missile leaves the tube when the trigger of launching mechanism is

pressed to the second position.

e. Forbid to press the trigger of launching mechanism to the second

position in following situations:

· The included angle between line of sight to the target and sun is

15.

· The stable continuous light and sound signal for target acquisition

is not generated when manual launching.

· Any of flight parameters of target (velocity, altitude, short-cut

course, etc.) exceeds the permitted range.

f. Forbid to launch the missile when the aft cover is not removed.


A-1

Appendix Launching zone and killing zone

Theoretical launching zone (solid line) and killing zone (dotted line) against the low-speed target

0

1000

2000

3000

4000

-8000 -6000 -4000 -2000 0 2000 4000 6000 8000x(m)

y(m)


A-2

0

1000

2000

3000

4000

5000

-8000 -6000 -4000 -2000 0 2000 4000 6000x(m)

y(m)

Theoretical launching zone (solid line) and killing zone (dotted line) against high-speed targets

FN-6 Operation Manual

Documents

optical aiming

mechanical

green lamp

initial aiming

chief motor

theoretical

target entering

target flight