JPH04188000A - Flying object for evaluating test - Google Patents

Abstract

PURPOSE:To facilitate recovery of a flying object for evaluating a test by a method where a control signal is outputted when an intertarget distance detecting circuit outputs a shoot-down ineffective distance detecting signal, when a speed detecting circuit outputs a fly ineffective speed detecting signal, or when a meeting time detecting circuit outputs an ineffective meeting time signal. CONSTITUTION:A flying object for evaluating a test confirms that it flies through a given distance after the passage of it through a shoot-down effective distance, that the flying speed of the flying object for evaluating a test is reduced to a value lower than a given speed, that a time in which the flying object for evaluating a test meets a target is decreased to a value lower than a given time, or that the flying object for evaluating a test flies out of a preset flying prediction route range. In which case, a fall to a ground and an impossibility for the flying object to be re-utilized owing to direct hit rupture are prevented from occurring in a way that through operation of a parachute 21, the flying object for evaluating a test is lowered as it is floated by means of the parachute 21.

Description

[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a test and evaluation flying object that flies while monitoring the operational status of an inductive root system in real time and checking the performance of nine functions. In particular, after the test and evaluation is completed, the test and evaluation flying object can be safely recovered and the equipment can be reused.

and to prevent the leakage of secrets.

[Prior Art 1] This type of conventional test and evaluation flying object will be briefly explained. In Figure 3, N is a test and evaluation projectile;
(1) is the target captured and tracked by the test and evaluation spacecraft N, (2) is the transmitted wave irradiated to the target fl), (3) is the reflected wave from the target (1), and (4) is the target ) Generates the transmitted signal of (2) and receives reflected wave (3)
Guidance control that detects a target signal from the vehicle, outputs a steering command signal to steer the flight path of the test and evaluation flying object in the direction of the meeting point with the target (1), and applies the target signal to the signal conditioner. device, (5) is guidance control device (4)
(6) is a steering device that uses the output steering command signal to steer the flight path of the test and evaluation flying object N in the direction of the meeting point with the target (target); (6) is the guidance control device (4) outputs various monitor signals; A signal conditioner that levels the level to a predetermined level, (7) and +8+ are modulators that modulate the leveled signals, and (9) is a modulator (
A multiplexer that multiplexes various monitor signals modulated by 7) and +8).

(10) is a transmitter that amplifies high power in order to transmit a multiplexed signal, and fil) is a transmitter that amplifies the amplified multiplexed signal.
The antenna (12) that transmits to the receiving station (15) generates a proximity detonation pulse when it passes closest to the target (1),
In addition, the fuse, +13), which generates a landing detonation pulse when it directly hits the target (1) and generates a detonation signal by a proximity detonation pulse or a landing detonation pulse, is necessary for the components of the test and evaluation air vehicle N. +14
1 is a propulsion device that provides thrust to the test and evaluation flying object N;
(15) is a receiving station that receives the multiplexed signal transmitted from the antenna (11).

[Problems to be Solved by the Invention] The conventional test and evaluation spacecraft N is configured as described above, and after the test and evaluation is completed, the test and evaluation spacecraft N is placed on the ground or on the ground as shown in FIG. The problem was that it crashed into the ocean, making it impossible to reuse it and potentially leaking secrets.

This invention was made to solve the above problems,
7 After the test and evaluation is completed, the test and evaluation spacecraft N is prevented from falling to the ground, hitting directly, and being destroyed and becoming unusable, and at the same time being made easy to recover, thereby preventing the leakage of secrets. The purpose is to obtain a reusable test and evaluation flying object N.

[Means for Solving the Problems] The test and evaluation aircraft according to the present invention includes means for outputting a shot-down invalid distance detection signal when the distance between the target and the test and evaluation aircraft exceeds a predetermined distance. means for outputting an invalid flight speed detection signal when the speed of the test and evaluation projectile falls below a predetermined speed; and means for outputting an invalid meeting time signal when the meeting time with the target falls within a predetermined time. and a means for detecting whether or not the test and evaluation projectile is within a preset predicted flight path range, and outputting a signal outside the predicted path range if the test evaluation projectile falls outside the range. , whether the inter-target distance detection circuit outputs an invalid shot-down distance detection signal, whether the speed detection circuit outputs an invalid speed detection signal, whether the meeting time detection circuit outputs an invalid meeting time signal, or whether the target distance detection circuit outputs an invalid shooting range detection signal. A means for outputting a control signal when the internal/external detection circuit outputs a predicted route out-of-range signal, and a control signal that prevents the test and evaluation aircraft from crashing, hitting the ground, or being destroyed so that it cannot be reused. The present invention is equipped with a means for preventing such occurrence and at the same time facilitating collection.

[Function] After the test and evaluation are completed, the test and evaluation flying object of the present invention lowers the test and evaluation flying object N while floating in response to the shot-down invalid distance detection signal to facilitate rotation.

[Example 1 The first section is a diagram showing an embodiment of the present invention.

fl) to (15) are the same as in Figure 3, +16+,
+171°f18], +19), (20)
, +21+ is a new device added to Fig. 3.

(16) is an inter-target distance detection circuit that outputs a shot-down invalid distance detection signal when the distance between the target and the test and evaluation body exceeds a predetermined distance; (171 is the flight speed of the test and evaluation body); [18] is a speed detection circuit that detects the speed and outputs a flight invalid speed detection signal when the speed falls below a predetermined speed. , a meeting time detection circuit which outputs an invalid meeting time; +20+ is a target distance detection circuit (16
) or outputs a shot-down invalid distance detection signal, or speed detection circuit (17) outputs a shot-down invalid speed detection signal,
OR that outputs a control signal when the meeting time detection circuit (18) outputs an invalid meeting time signal or when the flight prediction range inside/outside detection circuit (19) outputs a predicted route outside range signal.
The circuit +21+ is a parachute attached to the inside of the test and evaluation scale body so that it can be deployed, and this parachute is deployed in the external space of the test and evaluation scale body by the control signal of the OR circuit (20), and the parachute is allowed to fly. It acts to make the body float while descending.

The test and evaluation body constructed as described above passes through the effective shooting distance and exceeds a predetermined distance, or when the flight speed of the test and evaluation body falls below the predetermined speed. Confirm that the meeting time of the test and evaluation elongated body with the target is within the predetermined time, or that the test and evaluation elongated object N is out of the preset predicted flight path range. After that, parachute (
21) is activated and the parachute for testing and evaluation is suspended and lowered using the parachute (21), making it possible to prevent it from falling to the ground or being directly damaged and unable to be reused, and at the same time, it is possible to recover the specimen. . Therefore, as shown in FIG. 4, in the conventional test and evaluation scale body, after the test and evaluation are completed.

However, as shown in Figure 2, with the test and evaluation scale body of the present invention, after the test and evaluation are completed, the parachute +21) prevents the device from falling into the ground or the sea and being destroyed. Since it can be prevented, it can be reused.

[Effect of the invention] This invention is configured as described above.

Since the scale body N° for test and evaluation can be reused, the cost of test and evaluation can be reduced, and since it can be recovered, leakage of secrets can be prevented.

In the above embodiment, a parachute is used to make the flying object N° reusable, but the present invention is not limited to a parachute, and can also be applied to, for example, a balloon.

[Brief explanation of the drawing]

FIG. 1 is a configuration block diagram showing an embodiment of the present invention, FIG. 2 is an operation explanatory diagram showing the operation of this invention, FIG. 3 is a configuration block diagram showing a conventional test and evaluation scale body, and FIG. The figure is an operation explanatory diagram showing the operation of a conventional test and evaluation measuring body. In the figure, (I) is the target, (2) is the signal wave, (3) is the reflected wave, (4) is the guidance control device, (5) is the steering device, (
6) is a signal conditioner, +7), +8+
is a modulator, (9) is a multiplexer, (10) is a transmitter, (11) is an antenna, (12) is a fuze,
+13) is the power supply, (14) is the propulsion device, +
15+ is the receiving station, +161 is the target distance detection circuit,
(17) is a speed detection circuit. (18) is a meeting time detection circuit, 119) is a flight prediction range inside/outside detection circuit, (20) is an OR circuit,
+21+ is a parachute, and N is a rod for testing and evaluation. Note that in the two figures, the same reference numerals indicate the same or equivalent parts. Figure 2 N' Figure 4 (b)

Claims (1)

[Claims] A guidance control device that transmits a transmission wave to the target, detects the reflected wave reflected from the target, and outputs the necessary signals to each component, and a steering command signal output from the guidance control device to create a flight for test evaluation. a steering device that steers the flight path of the body toward a meeting point with a 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 multiplexed signals leveled by the above modulator, a multiplexer that multiplexes the various monitor signals modulated by the modulator, and a transmitter that amplifies the multiplexed signal with high power for transmission. and an antenna that transmits the multiplexed signal to the receiving station, which generates a proximity detonation pulse when it passes closest to the target, and which generates an arrival detonation pulse when it hits the target directly, and which uses the proximity detonation pulse or the arrival detonation pulse to , a test and evaluation spacecraft equipped with a fuse that generates a detonation signal, a power source that supplies the necessary power to the components, and a propulsion device that provides thrust, with a predetermined distance between the target and the test and evaluation spacecraft. An inter-target distance detection circuit that outputs an invalid shot-down distance detection signal when the distance exceeds the distance of A speed detection circuit that outputs a speed detection circuit, a meeting time detection circuit that outputs an invalid meeting time signal when the meeting time with the target exceeds a predetermined time, and a test against a preset predicted flying route range. A flight prediction range in/out detection circuit detects whether or not the evaluation missile is within the range and outputs a predicted route out-of-range signal if it misses, and the target distance detection circuit outputs a shoot-down invalid distance detection signal. or the speed detection circuit outputs an invalid speed detection signal, the meeting time detection circuit outputs an invalid meeting time signal, or the in/out predicted range detection circuit outputs a signal outside the predicted route range. When,
An OR circuit that outputs a control signal is installed so that it can be deployed inside the test and evaluation spacecraft, and is deployed in the external space of the test and evaluation spacecraft in response to the control signal from the OR circuit.
A test and evaluation spacecraft characterized by comprising means for lowering the test and evaluation spacecraft while floating it.