CN216815190U - Microminiature strap-down laser guidance control cabin - Google Patents
Microminiature strap-down laser guidance control cabin Download PDFInfo
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- CN216815190U CN216815190U CN202220662214.5U CN202220662214U CN216815190U CN 216815190 U CN216815190 U CN 216815190U CN 202220662214 U CN202220662214 U CN 202220662214U CN 216815190 U CN216815190 U CN 216815190U
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- control cabin
- missile
- microminiature
- steering engine
- electric steering
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Abstract
The utility model discloses a micro-miniature strapdown laser guidance control cabin which comprises a strapdown laser guide head, an electric steering engine, an on-missile computer, a control cabin shell and an inertia measurement unit, wherein the strapdown laser guide head is arranged on one end face of the control cabin shell and used for collecting the position relation between a target and a missile body, the electric steering engine is arranged in the control cabin shell and used for adjusting the posture of a missile by controlling a rudder piece on the electric steering engine to rotate, the on-missile computer is arranged in the control cabin shell and connected with the electric steering engine, the on-missile computer can send an instruction to the electric steering engine, and the inertia measurement unit is arranged in the control cabin shell and used for collecting the posture data of the missile body in the air and transmitting the data to the on-missile computer. The utility model provides a microminiature strapdown laser guidance control cabin which has the characteristics of simple structure, convenience in use, small occupied volume, high performance index and the like.
Description
Technical Field
The utility model belongs to the technical field of aviation, and particularly relates to a microminiature strapdown laser guidance control cabin.
Background
With the rapid development of unmanned aerial vehicle technology, the attack on small low-speed targets is gradually mature, and the load capacity of the unmanned aerial vehicle is limited, so that the micro ammunition becomes the first choice. The guidance control cabin is a core part for controlling the flight of the microminiature ammunition, and performance indexes of the guidance control cabin directly determine whether the missile can hit a target or not. Therefore, a guidance control cabin with simple structure, small occupied space and high performance index is needed.
SUMMERY OF THE UTILITY MODEL
In order to overcome the defects in the prior art, the utility model aims to provide a micro-miniature strapdown laser guidance control cabin which has the characteristics of simple structure, convenience in use, small occupied volume, high performance index and the like.
In order to achieve the above purpose, the utility model is realized by the following technical scheme:
a microminiature strapdown laser guidance control pod comprising: the missile-borne laser guidance system comprises a strapdown laser guidance head 1, an electric steering engine 2, a missile-borne computer 5, a control cabin shell 6 and an inertia measurement unit 8, wherein the strapdown laser guidance head 1 is arranged on one end face of the control cabin shell 6 and used for collecting the position relation between a target and a missile body, the electric steering engine 2 is arranged in the control cabin shell 6 and used for adjusting the posture of the missile by controlling the rotation of a rudder piece on the electric steering engine, the missile-borne computer 5 is arranged in the control cabin shell 6 and connected with the electric steering engine 2, the missile-borne computer 5 can send an instruction to the electric steering engine 2, and the inertia measurement unit 8 is arranged in the control cabin shell 6 and used for collecting the posture data of the missile body in the air and transmitting the data to the missile-borne computer 5.
Further, the microminiature strapdown laser guidance control cabin also comprises a wire cutter 3 and an umbilical cable 4 which is in communication connection with the outside.
Further, the missile-borne computer 5 can send instructions to the wire cutter 3, and the wire cutter 3 cuts off the umbilical cable 4 of the missile, which communicates with the outside.
Further, the microminiature strapdown laser guidance control cabin also comprises a thermal battery 7 which is used for supplying power to the strapdown laser guidance head 1, the electric steering engine 2, the pop-up computer 5 and the inertia measurement unit 8.
Further, the microminiature strapdown laser guidance control cabin is arranged on the missile body.
Drawings
Fig. 1 is a schematic structural diagram of a micro strapdown laser guidance control cabin.
Detailed Description
In order to make the technical solution of the present invention better understood by those skilled in the art, the following detailed description of the present invention will be made with reference to the accompanying drawings.
Referring to fig. 1, a micro strapdown laser guidance control cabin provided in an embodiment of the present invention includes: the missile-borne laser guidance system comprises a strapdown laser guidance head 1, an electric steering engine 2, a missile-borne computer 5, a control cabin shell 6 and an inertia measurement unit 8, wherein the strapdown laser guidance head 1 is arranged on one end face of the control cabin shell 6 and used for collecting the position relation between a target and a missile body, the electric steering engine 2 is arranged in the control cabin shell 6 and used for adjusting the posture of the missile by controlling a rudder piece on the electric steering engine to rotate, the missile-borne computer 5 is arranged in the control cabin shell 6 and connected with the electric steering engine 2, the missile-borne computer 5 can send an instruction to the electric steering engine 2, and the inertia measurement unit 8 is arranged in the control cabin shell 6 and used for collecting the posture data of the missile body in the air and transmitting the posture data to the missile-borne computer 5.
In the embodiment, the microminiature strapdown laser guidance control cabin further comprises a wire cutter 3 and an umbilical cable 4 which is in communication connection with the outside, the missile-mounted computer 5 can send instructions to the wire cutter 3, and the wire cutter 3 cuts off the umbilical cable 4 which is in communication with the outside of the missile.
In this embodiment, the micro-miniature strapdown laser guidance control cabin further comprises a thermal battery 7 for supplying power to the strapdown laser guidance head 1, the electric steering engine 2, the pop-up computer 5 and the inertia measurement unit 8. The microminiature strapdown laser guidance control cabin is arranged on the missile body.
The working principle of the microminiature strap-down laser guidance control cabin of the utility model is as follows: when the missile is normal in power-on self-test, the thermal battery 7 is activated after binding parameters are input, power is supplied to the strapdown laser seeker 1, the electric steering engine 2, the missile-mounted computer 5 and the inertia measuring unit 8, at the moment, the missile-mounted computer 5 gives an instruction to the wire cutter 3, the wire cutter 3 cuts off an umbilical cable 4 of the missile, which is communicated with the outside, and then the missile-mounted computer 5 gives an ignition instruction to the engine, and the missile is launched out of the barrel. During the initial flight process of the missile, the inertial measurement unit 8 collects the attitude data of the missile body in the air and transmits the attitude data to the missile-mounted computer 5, the missile-mounted computer 5 processes the attitude data and sends a command to the electric steering engine 2, and the electric steering engine 2 adjusts the attitude of the missile by controlling the rotation of the rudder piece. After the strapdown laser seeker 1 on the missile captures laser reflected by a target, the guidance of the missile is switched by the missile computer 5 from inertial guidance to the guidance of the strapdown laser seeker 1, the position relation between the target and the missile body collected by the strapdown laser seeker 1 is transmitted to the missile computer 5, the missile computer 5 processes the position relation and sends a command to the electric steering engine 2, and the electric steering engine 2 controls the rotation of the rudder piece to adjust the posture of the missile until the target is hit.
Through a multi-round target range test, the missiles all hit the target with the hit precision CEP less than or equal to 1.5 m.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (5)
1. A microminiature strapdown laser guidance control cabin comprises a strapdown laser seeker (1), an electric steering engine (2), an onboard computer (5), a control cabin shell (6) and an inertia measurement unit (8), wherein,
the strapdown laser seeker (1) is arranged on one end face of the control cabin shell (6) and used for collecting the position relation between a target and a projectile body;
the electric steering engine (2) is arranged in the control cabin shell (6) and adjusts the posture of the missile by controlling the rotation of a rudder piece on the electric steering engine;
the pop-up computer (5) is arranged in the control cabin shell (6) and is connected with the electric steering engine (2), and the pop-up computer (5) can send instructions to the electric steering engine (2);
the inertia measurement unit (8) is arranged in the control cabin shell (6) and used for collecting attitude data of the projectile body in the air and transmitting the attitude data to the projectile computer (5).
2. The microminiature strapdown laser guidance control pod of claim 1,
the microminiature strapdown laser guidance control cabin also comprises a wire cutter (3) and an umbilical cable (4) in communication connection with the outside.
3. The microminiature strapdown laser guidance control pod of claim 2,
the missile-mounted computer (5) can send an instruction to the thread cutter (3), and the thread cutter (3) cuts off an umbilical cable (4) for the missile to communicate with the outside.
4. The microminiature strapdown laser guidance control pod of claim 1 or 2,
the microminiature strapdown laser guidance control cabin further comprises a thermal battery (7) for supplying power to the strapdown laser seeker (1), the electric steering engine (2), the pop-up computer (5) and the inertia measurement unit (8).
5. The microminiature strapdown laser guidance control pod of claim 1 or 2,
the microminiature strapdown laser guidance control cabin is arranged on the missile body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220662214.5U CN216815190U (en) | 2022-03-25 | 2022-03-25 | Microminiature strap-down laser guidance control cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220662214.5U CN216815190U (en) | 2022-03-25 | 2022-03-25 | Microminiature strap-down laser guidance control cabin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216815190U true CN216815190U (en) | 2022-06-24 |
Family
ID=82046522
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220662214.5U Active CN216815190U (en) | 2022-03-25 | 2022-03-25 | Microminiature strap-down laser guidance control cabin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216815190U (en) |
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2022
- 2022-03-25 CN CN202220662214.5U patent/CN216815190U/en active Active
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