JPS6176898A - Thrust control rocket - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed Description of the Invention] [Technical Field of the Invention] This invention provides thrust control with the aim of receiving reflected waves from a target, capturing and tracking the target, and ultimately meeting the target. It's about rockets.

[Prior Art j Fig. 1 is a diagram simply showing a conventional thrust control rocket of this type. In the figure, 1M is a thrust control rocket), (1
1 is the target to be captured and tracked by the thrust control rocket M, (2)
is the reflected wave from the target (1), (3) is the thrust control rocket from the reflected wave (2). Thrust side - ○) When launching M, launch signal to thrust control rocket M and thrust control rocket M and target f1) at the time of launch.
The launcher (5) provides a distance signal between the launcher (4)
It is a rocket motor that generates thrust when the launch signal is human-powered.

Conventional thrust control rocket) M is configured as described above, and its purpose is to capture and track target il+, fly to the meeting point with target (1), and finally meet with target (1). It is said that

However, the conventional thrust control rocket M does not change the thrust force. In other words, in order to fly the required distance at a given flight altitude, as shown in Figure 2 for a given amount of propellant, the optimal thrust that can be generated to minimize the flight time until meeting the target is required. However, there was no device added to vary the thrust.

There was a drawback in that the performance of the rocket motor (5) was not maximized.

Note that FIG. 2 shows parameters in terms of reach distance.

[Summary of the invention]

This invention was made for the purpose of improving the above-mentioned drawbacks.
The thrust setting signal is output by the newly installed thrust setting selection section (7) based on the distance signal to the target (1) at the time of launch of the thrust control rocket M and the pressure altitude signal from the newly installed atmospheric pressure sensor (6). By controlling the thrust generated by the rocket motor (5) using a newly installed thrust control device (8), the performance of the rocket motor (5) is adjusted to minimize the time required to reach the target (1). At the same time, a newly installed pressure sensor (6) is used to maintain the external pressure of the thrust control rocket M' while the thrust control rocket M' is in flight.

In other words, if the altitude changes, it is detected and a thrust correction signal is output, and the thrust that generates the rocket motor (5) via the thrust control device (8) is adjusted to the external pressure of M/, that is, the altitude. You can correct the value accordingly,
This project proposes a thrust-controlled rocket that aims to meet target (1) as soon as possible.

In addition, early meeting of the thrust control rocket with the target if) increases the survival probability of the launcher (4), increases the probability of reaching the target (1) air defense destruction capability, target fl), and improves the ability to destroy the target (1). It is useful for

[Embodiments of the invention]

FIG. 3 is a diagram showing an embodiment of the present invention.

(1) to (5) are the same as in Figure 1, and (6) to (9)
This is a new device added to FIG. (6) is a barometric pressure sensor that outputs a pressure altitude signal and a thrust correction signal according to the altitude of the thrust control rocket M'; (7) is a launcher (
4) Distance signal from target (11) and barometric pressure sensor (6
) and select the optimal thrust setting according to the barometric altitude signal.

The set thrust selection section (8) outputs the thrust setting signal, and the thrust setting selection section (8) outputs the thrust setting signal from the set thrust selection section (7) and the barometric pressure sensor (
A thrust control device that controls the rocket motor (5) to generate a thrust according to a thrust correction signal from 6).

(9) is a delay circuit that delays the supply of the launch signal from the launcher (4) to the rocket motor (5) until the thrust selection unit (7) completes the thrust setting of the rocket motor (5). be.

In the thrust control rocket M' configured as described above, when the thrust control rocket M' is launched from the launcher (4), the distance signal at the target '1)-4+ from the second launcher (4) and Based on the pressure altitude signal from the pressure sensor (6), the set thrust selection unit (7) selects the thrust of the rocket motor (5) that can reach the target (1) in the shortest time and outputs a thrust setting signal. The rocket motor (5) is configured to generate thrust according to the thrust setting signal, and the thrust control device (8)
Controlled by Further, the thrust of the rocket motor (5) controlled as described above by the atmospheric pressure sensor (6) is applied to the thrust control rocket M' while the thrust control rocket M' is about to fly.
Detects changes in external pressure, that is, altitude, and outputs a thrust correction signal, and the thrust generated by the rocket motor (5) via the thrust control device (8) is controlled by the thrust control port (the thrust control port). This is because the value will be corrected according to the external pressure, that is, the altitude.

This means that the performance of the rocket motor (5) can be maximized.

〔Effect of the invention〕

With the configuration described above, this invention allows the rocket motor (5) to maximize its performance, shortens the time required to reach the target (1), improves the survival probability of the launcher (4), and (11) It has the effect of increasing the ability to break through air defense, increasing the ability to reach the target (+1), and improving the ability to destroy target (1).

[Brief explanation of drawings]

Fig. 1 is a block diagram showing a conventional thrust control rocket, Fig. 2 is a diagram showing the relationship between thrust, arrival time, and flight distance using the reaching distance as a parameter. Fig. 3 is a diagram showing an embodiment of the present invention. FIG. In the figure, (1) is the target, (2) is the reflected wave, (3) is the guidance control device, (4) is the launcher, (5) is the rocket motor, (6) is the barometric pressure sensor, and (7) is the setting. Thrust selection section, (
8) is a thrust control device, and (9) is a delay circuit. Note that the same reference numerals in each figure indicate the same or equivalent parts.

Claims (1)

[Claims] In a thrust control rocket equipped with a guidance control device that receives reflected waves from a target and steers the flight path toward a meeting point with the target, and a rocket motor that ignites and generates thrust based on a launch signal from the launcher. , a barometric sensor that detects the altitude of the thrust control rocket and generates a barometric altitude signal and a thrust correction signal, and when a launch signal is input from the launcher, a distance signal from the launcher to the target and a barometric altitude signal from the barometric sensor A setting thrust selection unit that selects the optimal thrust, a thrust control device that controls the rocket motor to generate the selected thrust, and a launch signal that supplies the rocket motor until the thrust setting of the rocket motor is completed. A thrust control rocket characterized in that it has a delay circuit.