FUNCTION

A. It has the function of capturing, locking and tracking the target before/after launch;
B. It can output the target line of sight angular velocity signal;
C. It can output the seeker frame angle signal;
D. It has a memory function and can track the target again after the target is temporarily lost;
E. It can isolate the optical axis movement of the seeker from the movement of the missile body;
F. It can adapt to the requirements of two working modes: the working mode of locking the target for off-axis launch before launch and the working mode of searching, capturing and tracking the target after launch;
G. It has a self-test function;
H. It has a telemetry output function, which can output parameters reflecting the working status of the seeker for analysis and judgment by the equipment on the missile;
I. It has the ability to recapture the target lost due to short-term occlusion.

PERFORMANCE INDICATORS

1) Weight: 2.3kg±0.2kg;
2) Length: ≤200mm (excluding interface section);
3) Diameter: Φ;
4) Head curve: spherical radius 65mm, the shape and docking diagram of the seeker are shown in Figure 3;
5) Working wavelength: 1.064μm;
6) Frequency: default 20Hz (50000us), the period range can be set to 40000us～65000us;
7) Accurate frequency gate width: can be set, ±2us~±10us;
8) Output signal format: RS-422 interface, baud rate 614.4kbps, communication cycle when not captured 50ms, the capture communication cycle is based on the laser cycle;
9) Definition of frame angle output polarity: Looking from the back to the front along the missile axis, the pitch direction is positive when the target is on the top, negative when the target is on the bottom, positive when the target is on the left in the heading direction, and negative when the target is on the right;
10) Definition of line of sight angular velocity output polarity: Looking from the back to the front along the missile axis, the pitch direction is positive when the target moves upward, negative when the target moves downward, positive when the target moves to the left in the heading direction, and negative when the target moves to the right;
11) Action range: Under the following conditions, the target capture distance is not less than 8km (non-linear zone), and the
capture probability is not less than 98%
1. Laser irradiator energy: 80mJ
2. Aerial irradiation distance: ≤8km
3. Laser pulse width: 10ns～20ns
4. Laser beam divergence: 0.2mrad
5. Target diffuse reflection coefficient: 0.25～0.35
6. Atmospheric visibility: 15km
12) Stable platform isolation: ≤2% (3Hz, 2°), ≤2.5% (1Hz, 5°);
13) Tracking delay: ≤100ms (0.5Hz, 2°);
14) Tracking range: Heading: not less than +30°～－30°, pitch: not less than +10°～－50°;
15) Instantaneous field of view: -6°～+6°;
16) Maximum tracking angular velocity: heading 12°/s, pitch 12°/s;
17) Line of sight angular velocity error (heading, pitch, mean): [-2, 2] °/s interval: ≯ 0.1°/s [-12, -2] °/s and [2, 12] °/s interval: ≯ 5% of the actual value;
18) Line of sight angular velocity noise (heading, pitch, indoor equivalent 4km energy, 2σ): [-2, 2] °/s interval: ≯ 0.2°/s [-12, -2] °/s and [2, 12] °/s interval: ≯ 0.4°/s;
19) Frame angle prediction accuracy: absolute value ≤0.2°;
20) Blind area: <50m;
21) Startup time: ≤30s;
22) Maximum continuous working time: 30min;
23) Memory time: 0.5s ± 0.1s;
24) Power consumption: 24~32V DC power supply, startup current ≤5A, working current ≤ 3A. 25) The program can be upgraded online through the RS-422 communication interface;
26) The gyro of the guidance head has a self-calibration function and a storage memory function;

MECHANICAL DIMENSION(mm)