JPH02166399A - Flying body for test evaluation - Google Patents

Abstract

PURPOSE:To recover a flying body safely and prevent the leakage of secrrets and attempt to reuse the flying body by providing means to recover by the signal to detect distance in which shooting-down is not effective a flying body for test evaluation when the distance from a target to the flying body for test evaluation is over a specified distance after a fuse has generated a proximity initiation pulse or arrival initiation pulse. CONSTITUTION:A distance detection circuit 16 for distance between targets which outputs signal that detects the distance in which shooting-down is ineffective when, after an initiation pulse from the fuse has been generated, the distance between a target and a flying body for test evaluation is in excess of a specified distance is provided, and a recovery device 17 which operates when signal to detect the distance in which shooting-down is ineffective from the distance detection circuit for the distance between targets is inputted and recovers the flying body for test evaluation is provided. After a flying body N' for test evaluation which is constituted as described above is confirmed that it has traveled beyond the distance in which shooting-down in effective, the recovery device 17 operates, and it becomes possible to recover the flying body N' for test evaluation by the recovery device 17.

Description

[Detailed Description of the Invention] [Field of Industrial Application] This invention relates to a test and evaluation flying object that monitors the operational status during guided flight in real time and confirms the performance of two functions while flying.

In particular, after the test and evaluation is completed, the test and evaluation flying object can be safely recovered to prevent reuse of the device and leakage of secrets.

[Conventional technology]

A brief explanation will be given of the conventional test and evaluation projectile. In Figure 3, N is a test and evaluation projectile;
(1) is the target that the test and evaluation spacecraft N captures and tracks, and (2) is the transmitted wave that is irradiated to the target (1).

(3) is the reflected wave from target (1), (4) is the target (1)
Generates a transmission signal of the transmission wave (2) that irradiates the target, detects the target signal from the received reflected wave (3), and guides the flight path of the test and evaluation vehicle to the meeting point with the target (1). (5) is a guidance control device that outputs a steering command signal for steering in the direction and outputs a target signal to a signal conditioner; A steering device (6) is used to steer the flight route toward the meeting point with the target (1), and a signal conditioner (6) is used to level the output levels of various monitor signals output from the guidance control device (4) to predetermined levels.

(71, (81 is a modulator that modulates each leveled signal, (9) is a multiplexer that multiplexes various monitor signals modulated by the modulators (7) and (8),
α[ is a transmitter that amplifies high power in order to transmit a multiplexed signal, (11) is an antenna that transmits the amplified multiplexed signal to a receiving station (15), and (12) is a target (1
) A fuze that generates a proximity detonation pulse when it passes closest to the target (1), generates a single detonation pulse when it directly hits the target (1), and generates a detonation signal by the proximity detonation pulse or the landing detonation pulse, (131 is a power source 1 that supplies the necessary power to the components of the test and evaluation spacecraft N; and (14) is a propulsion device that provides thrust to the test and evaluation spacecraft N.

(15) is a receiving station that receives the multiplexed signal transmitted from the antenna (11).

[Problem to be solved by the invention]

The conventional test and evaluation spacecraft N is constructed in a stacked manner, and after completing the test and evaluation, the test and evaluation spacecraft N crashes into the ground or the sea, making it impossible to reuse, and also preventing leakage of secrets. The challenge was to connect.

This invention was made to solve the above problems,
The objective is to prevent the leakage of secrets and obtain a reusable test and evaluation spacecraft N' by making it possible to safely recover the test and evaluation spacecraft N using a recovery device after the test and evaluation are completed. do.

[Means to solve the problem]

The test and evaluation flying object N' according to the present invention is:

means for outputting a shot-down invalid distance detection signal when the distance between the target and the test and evaluation flying object N' exceeds a predetermined distance after the fuse generates a detonation signal of a proximity detonation pulse or an landing detonation pulse; , and means for recovering the test and evaluation aircraft N' based on the shot-down invalid distance detection signal.

[For production]

The test and evaluation flying object N' in this invention is:

Try it! After the evaluation, 1! Based on the fall invalid distance detection signal.

The test and evaluation spacecraft N' can be recovered by the recovery device.

〔Example〕

FIG. 1 is a diagram showing an embodiment of the present invention.

(1) to (15) are the same as in Figure 3, and (16) to
(17) is a new device added to FIG.

(16) is an inter-target distance detection circuit that outputs a shoot-down invalid distance detection signal when the distance between the target and the test and evaluation aircraft exceeds a predetermined distance after the fuse's detonation pulse is generated.

(17) has a recovery device which is activated when the shot-down invalid distance detection signal output from the inter-target distance detection circuit is input and recovers the test and evaluation aircraft N'.

This is a test and evaluation projectile N' that can be recovered by a second recovery device after the test and evaluation is completed.

After confirming that the test and evaluation aircraft N' configured as described above has passed the effective shooting distance and exceeded a predetermined distance, the second recovery device (17) is activated, and the test and evaluation aircraft N' is activated. It becomes possible to recover N' by the recovery device (17). Therefore, as shown in FIG. 4, the conventional test and evaluation spacecraft N crashes into the ground or the sea after the test and evaluation is completed, but the test and evaluation spacecraft N' of the present invention crashes.
As shown in Figure 2, two collection devices (17
) can be recovered.

〔Effect of the invention〕

This invention is configured as described above.

Since the test and evaluation spacecraft N' can be reused, the cost of test and evaluation can be reduced and leakage of secrets for recovery can be prevented.

[Brief explanation of the drawing]

FIG. 1 is a configuration block diagram showing an embodiment of the present invention, and FIG. 2 is an operational explanatory diagram showing the operation of the present invention. FIG. 3 is a block diagram showing the configuration of a conventional test and evaluation spacecraft, and FIG. 4 is an operation explanatory diagram showing the operation of the conventional test and evaluation spacecraft. In the figure, (1) is the target, (2) is the transmitted wave, (3) is the reflected wave, 14) is the guidance #pushing device, (5) is the steering device, (
6) is a signal conditioner, (7) and (8) are modulators, (9) is a multiplexer, (II is a transmitter, (
11) is the antenna, (12) is the fuse, (13) is the power source, (14) is the propulsion device, (15) is the receiving station, (
1B) is the distance detection circuit between targets, (17) is the recovery device,
N is a test and evaluation flying object. Note that in the two figures, the same reference numerals indicate the same or equivalent parts. (a an

Claims (1)

[Claims] A guidance control device that transmits a transmission wave to the target, detects the reflected wave that is reflected from the target, and outputs the necessary signals to each component, and a steering command signal output from the guidance control device. a steering device that steers the flight path of the body in the direction of the meeting point with the target; a signal conditioner that levels the output level of a plurality of monitor signals output from the guidance control device to a predetermined level; A modulator that modulates signals so that they can be multiplexed, a multiplexer that multiplexes various modulated monitor signals, a transmitter that amplifies the multiplexed signal with high power for transmission, and transmits the multiplexed signal to the receiving station. An antenna, a fuze that generates a proximity detonation pulse when passing closest to a target, generates a landing detonation pulse when it hits the target directly, and generates a detonation signal by the proximity detonation pulse or the landing detonation pulse, and components. In a test and evaluation spacecraft equipped with a power supply that supplies the necessary power and a propulsion device that provides thrust, the distance between the target and the test and evaluation spacecraft exceeds a predetermined distance after the fuse's detonation pulse is generated. and a recovery device that recovers the test and evaluation projectile when the inter-target distance detection circuit outputs a shoot-down invalid distance detection signal. A test and evaluation projectile featuring: