# US 4,397,215 A · System for controlling the temperature of the upper end of a missile

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- Number: US 4,397,215 A
- Document ID: US4397215A
- Status: Granted
- Kind: A
- Application number: 06/232,288
- Filed: 1981-02-06
- Granted: 1983-08-09
- Earliest claimed: 1981-02-06
- Assignees: Westinghouse Electric Corp.
- Inventors: Vernon Stroud
- Web page: https://patentgrep.com/patent/US4397215A

## CPC

- F41F 3/04: for rockets
- F41F: APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS (smallarms F41C); LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS (functional features or details common to both smallarms and ordnance, mountings therefor F41A; projecting missiles without use of explosive or combustible propellant charge F41B)

## Abstract

A diaphragm is disposed in the upper end of the launch tube to ensure circulation of air to control the temperature of the nose of a missile disposed in the launch tube.

## Claims

### Claim 1

A system for controlling the temperature of the upper end of a missile disposed in a launch tube having its upper end closed by a hatch, the system comprising:
a port in the launch tube disposed below the hatch;
means for supplying and removing fluid from said launch tube disposed in fluid communication with the port;
a heat exchanger disposed in fluid communication with the fluid supply and removing means;
a diaphragm disposed below the hatch;
a peripheral seal at the junction of the diaphragm and the launch tube whereby fluid is passed over the upper end of the missile to control its temperature as fluid is alternately supplied and removed from the launch tube.

### Claim 2 (depends on 1)

A system as set forth in claim 1 wherein the heat exchanger can supply or remove heat.

### Claim 3 (depends on 1)

A system as set forth in claim 1 wherein the diaphragm is larger than the cross-sectional area of the launch tube.

### Claim 4 (depends on 1)

A system as set forth in claim 1 wherein the diaphragm has a substantial amount of sag.

### Claim 5 (depends on 1)

A system as set forth in claim 1 wherein the diaphragm contacts the missile when fluid is removed from the launch tube and is spaced from the missile when fluid is supplied to the launch tube.

### Claim 6 (depends on 1)

A system as set forth in claim 1 wherein the heat exchanger is disposed within the launch tube below the hatch.

### Claim 7 (depends on 1)

The system as set forth in claim 1 wherein the heat exchanger is disposed outside of the launch tube.

### Claim 8 (depends on 1)

The system as set forth in claim 1 wherein a heat exchanger is disposed within the launch tube and an additional heat exchanger is disposed externally of the launch tube.