JPH01159600A - Freezing preventive device for missile launcher front cover - Google Patents

Abstract

PURPOSE: To enable the anti-icing of a front cap to smoothly launch an airframe at a cold district by mounting a heater near a front cap mount of the airframe. CONSTITUTION: When the open air temp. is below the icing point, a heater 5 is energized to heat the joint face of a flange 4 to a front cap 1 enough to avoid icing the front cap 1 to the flange 4 and launcher body 2 wherein the heat quantity of the heater 5 is so controlled as to increase with the lowering of the open air temp., thereby avoiding icing the front cap 1. When the open air temp. rises over the icing point, the heater 5 is deenergized. By voiding icing the front cap 1, the launch of the airframe at a cold district can be smoothly made, without icing the front cap 1, the same as at a warm district.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a front lid icing prevention device for a launcher for launching a projectile.

[Conventional technology]

In order to prevent and reduce icing on the front lid of a projectile launcher, conventional methods include covering the entire front lid attachment part of the launch tube with a heat insulating material such as cloth, or applying waterproof coating. has been adopted.

[Problem that the invention seeks to solve]

As mentioned above, in the past, active measures to prevent the front lid from freezing in cold regions have not been implemented, and the only way to reduce freezing was to insulate the front lid with a heat insulating material such as cloth or apply waterproof coating.

In such conditions, when the weather is cold, ice forms between the launch tube body and the front cover, and a large force is required to open the front cover when launching a projectile. Therefore, when opening the front cover by pushing out the radome at the tip of the flying body, the opening force may be insufficient and the missile cannot be fired, or even if the front cover can be opened, a strong impact may be applied to the radome at the tip. This may adversely affect the radio wave characteristics inside the projectile.

Further, in the conventional method of covering with a cloth or the like to prevent icing, it is difficult to attach and remove the cloth, making it impractical.

The present invention aims to solve the above-mentioned problems caused by freezing.

[Means for solving problems]

In the present invention, in an air vehicle launcher including a launcher and a front cover attached to the front end of the launcher, a heater is attached near the front cover mounting portion of the launcher.

[For production]

In the present invention, since the heater is installed near the front lid attachment part of the firing tube, when the outside temperature drops below the freezing temperature, the front lid attachment part is heated by the heater, and the front lid is fired. It can prevent ice from forming on the cylinder.

When heating with the above heater, a temperature sensor that detects the outside air temperature and a temperature controller are used to turn on electricity to the heater when the outside air temperature falls below the freezing temperature, and conversely turn on the electricity when the outside air temperature becomes above the freezing temperature. By cutting off the ice, it is possible to automatically prevent freezing.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 to 4. Figure 1 shows the launcher 2 containing the projectile mounted on a mount 3.
The figure shows the state in which it is installed.

Further, FIGS. 2 and 3 show the detailed structure of the launch tube front cover anti-icing device shown in FIG. 1. As shown in these drawings, a 5-shaped 7-lunge 4 is attached to the outer periphery of the front end of the cylindrical launch barrel body 2 for tightly fixing the circular front cover 1. . The 7 langes 4 and the front lid 1 are closely fixed by a pair of hangers 6.6 and a hanger pin 12 that attaches the hangers to the front lid 1 on diametrically opposite sides. 7 more lunges 4
An anti-icing heater 5 is attached to the flange surface on the back side of the surface where the and front lid 1 are joined.

As shown in FIG.
0, it has a waterproof sealed structure consisting of an electrical insulator 11 covering the nichrome wire, and a lath cloth 9 covering the electrical insulator 11, and as shown in FIG. It has a mat-like shape having a short cylindrical shape with a slightly larger inner diameter, and is attached to the flange 4 near the attachment part of the front cover 1 with attachment bolts 7.

Further, the heater 5 is controlled to be energized by a temperature regulator (not shown) that receives a signal from an outside temperature sensor.

Since the present embodiment is configured as described above, when the outside air temperature falls below the freezing temperature, the heater 5 is energized and generates heat to heat the joint surface between the flange 4 and the front cover 1, and the front cover 1 is 7
Freezing on the lunge 4 and the launch tube body 2 is prevented.

In this case, the amount of heat generated by the heater 50 is controlled by the temperature regulator so as to increase as the outside temperature decreases, thereby preventing the front lid 1 from freezing.

Moreover, if the outside air temperature rises to a freezing temperature or higher, the power supply to the heater 5 is cut off.

As described above, in this implementation i, by preventing the front cover 1 from freezing, the launch of two flying objects in cold regions can be carried out smoothly without the front cover 1 freezing, as in warm regions. Can be done.

In the above embodiment, the heater is attached to the flange provided on the outer periphery of the front end of the firing tube body, but the attachment position of the heater in the present invention is not limited to this. It can be appropriately selected in the vicinity of the section. Furthermore, it goes without saying that the heater is not limited to that shown in FIGS. 4 and 5.

〔Effect of the invention〕

The present invention makes it possible to prevent the front lid from freezing in cold regions with a simpler mechanism, and prevents the tip of the projectile from impacting the dome due to the excessive opening force of the front lid due to freezing. Projectiles can be launched smoothly.

[Brief explanation of the drawing]

Fig. 1 is an overall view of one embodiment of the present invention, Fig. 2 is a cross-sectional view taken along line A-A in Fig. 1, Fig. 3 is a cross-sectional view taken along line BB' in Fig. 1, and Fig. 4 is a cross-sectional view taken along line BB' in Fig. 1. A plan view of the heater used in the example, and FIG. 5 is a cross-sectional view taken along line c-c' in FIG.
Frame 4...7 Lange 5...Heater
6...Hanger 9...Glass cloth 10
... Nichrome wire 11 ... Electrical insulator Figure 1 Figure 2 Figure 3

Claims (1)

[Scope of Claims] A projectile launcher comprising a launch tube and a front cover attached to the front end thereof, characterized in that a heater is attached near the front cover attachment part of the launch tube. Anti-icing device for the front lid of the launcher.