JPH087280Y2 - Missile guidance device - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Object of the Invention] (Field of Industrial Application) This invention relates to a missile guidance device equipped with a proximity fuze and a homing device by an active radar device, respectively.

(Prior Art) Generally, a missile guidance device is equipped with a proximity fuze and a homing device by an active radar device, and during a period from launch to a hit, as shown in FIG. It can be divided into phases. In the first-middle guidance phase, the homing device guides the missile to a distance where it can lock on the target. When the lock-on possible distance is reached, the homing device starts transmission to start searching for a target. When the target is detected and the homing device locks on the target, the homing phase starts and homing to the target is started. When the distance between the target and the missile is approached to some extent, the target is locked off in relation to the transmission pulse of the homing device. From here, the missile becomes non-guided by entering the terminal phase, and when the missile is closest to the target by activating the close fuse, the warhead is detonated and the target is destroyed.

From the above, the homing device and the proximity fuze are independently mounted in the conventional missile guidance device.

(Problems to be Solved by the Invention) As described above, in the conventional missile guiding device, the proximity fuze and the homing device by the same active radar device are mounted separately from each other, so that the weight of the missile is increased.

The present invention has been made to solve the above-mentioned problem, and shares a common function part between the homing device and the proximity fuze, which results in a missile guidance device that has a small number of mounted items and can reduce weight and cost. The purpose is to provide.

[Structure of the Invention] (Means for Solving the Problems) In order to achieve the above object, the missile guiding device according to the present invention is a device equipped with a homing device and a proximity fuze, each of which is configured by an active radar system. hand,
The first antenna for the homing device, the second antenna for the proximity fuze, and the first antenna are selected in the initial state, and the second antenna is switched and selected by inputting a switching control signal. , A switching device for deriving a transmission / reception signal, a transmission / reception device for outputting a transmission signal to the selected antenna via this switching device, and a demodulation / detection signal for a reception signal from the antenna, and a detection output of this transmission / reception device for switching. And a switching control means for sending a switching control signal to the switching device by discriminating the timing.

(Operation) Since the homing device and the proximity fuze share the same function part in the missile guiding device having the above-described configuration, the number of mounted items can be reduced.

(Embodiment) An embodiment of the present invention will be described below with reference to FIG.

FIG. 1 shows its configuration, where 11 is a homing antenna and 12 is a close fuze antenna. Each antenna 1
The switches 1 and 12 are selectively connected to the transceiver 14 by the switch 13. The transceiver 14 inputs the received signal transmitted from the switch 13 to the circulator 141 and the receiver 142. The receiver 142 frequency-converts the received signal by a high frequency (RF) amplifier A and an intermediate frequency (IF) amplifier B, and then a signal processing circuit C extracts homing data or terminal data and detects a phase state. The switching device 13 is switched and controlled by the homing / terminal switching signal Sc output from the signal processing circuit C. Further, the transmission output of the transmitter 143 is selectively led to each of the antennas 11 and 12 via the circulator 141 and the switch 13.

That is, as described above, the homing device and the proximity fuze have a time lag because they are operated in the homing phase and the terminal phase, respectively. Further, since both the homing device and the close fuze are constituted by active radar devices, they have a common function. This device pays attention to this point and aims at sharing the transmitter and receiver.

That is, in the homing phase, the switching device 13 is switched to the homing antenna 11 side, and the antenna 11 and the transceiver 14 are switched.
And are connected to function as a homing device. Also,
In the terminal phase, the switch 13 is used as a near fuze antenna.
Switching to the 12 side, the antenna 12 and the transceiver 14 are connected to function as a proximity fuze. The switching of the antennas 11 and 12 may be performed when the distance between the target and the missile becomes sufficiently short, for example, when the relative distance between the target and the missile becomes 100 m or less. This can be easily calculated from the processing result of the signal processing circuit C.

Therefore, the missile guiding device having the above-described configuration shares the homing device and the transmitter / receiver of the proximity fuze, so that the number of missile-equipped products can be reduced, and the weight and cost can be reduced.

It should be noted that it is difficult to share the antenna part because the homing device and the proximity fuze have different coverage areas. However, if a conformal array antenna is realized in the future, it may be shared.

[Effects of the Invention] As described above, according to the present invention, the common function part of the homing device and the proximity fuze is shared, thereby providing a missile guiding device that has a small number of mounted items and can reduce weight and cost. be able to.

[Brief description of drawings]

FIG. 1 is a block diagram showing an embodiment of a missile guidance device according to the present invention, and FIG. 2 is a diagram showing a guidance sequence of a missile guidance device to which the present invention is applied. 11 …… Homing antenna, 12 …… Proximity fuze antenna, 13 …… Switcher, 14 …… Transceiver, 141 …… Circulator, 142 …… Receiver, 143 …… Transmitter, A …… RF amplifier, B: IF amplifier, C: signal processing circuit.

Claims (1)

[Scope of utility model registration request] 1. A missile guiding device equipped with a homing device and a proximity fuze, each of which is an active radar system, wherein a first antenna for the homing device, a second antenna for the proximity fuze, and an initial state are provided. The first antenna is selected, and the second antenna is switched and selected by inputting a switching control signal, and a switcher for deriving a transmission / reception signal and a transmission signal to the antenna selected via this switcher. And a switching control means for outputting a switching control signal to the switching device by discriminating the switching timing from the detection output of the transmitter / receiver and detecting and demodulating and detecting the received signal from the antenna. apparatus.