US3721155A

US3721155A - Safety device for locking a missile on its launcher or in its container in either the transport or the launching position

Info

Publication number: US3721155A
Application number: US00116959A
Authority: US
Inventors: E Stauff; M Maree; J Roze
Original assignee: IND AEROSPATIALLE SOC NAT
Current assignee: IND AEROSPATIALLE SOC NAT; SOC NAT IND AEROSPATIALLE FR
Priority date: 1970-02-23
Filing date: 1971-02-19
Publication date: 1973-03-20
Anticipated expiration: 1990-03-20
Also published as: DE2104609C3; DE2104609A1; FR2080080A5; DE2104609B2

Abstract

A safety device for locking a missile either in the transport position in its container, or in the firing position on its launcher, in which means maintains electric circuit for energizing the missile propellant igniters short-circuited as long as the missile is not in a condition to be fired, and actuating means with movable restraining means permitting to fetch the missile from an initial locking position to a final retracted position and latching said movable means in their final retracted position.

Description

United States Patent [191 Stauff et al.

[ lMarch 20, 1973 [54] SAFETY DEVICE FOR LOCKING A MISSILE ON ITS LAUNCHER OR IN ITS CONTAINER IN EITHER THE TRANSPORT OR THE LAUNCHING POSITION [75] Inventors: Emile Stauff, Versailles; Michel Mare'e, Chilly-Mazarin; Jacques Roze des Ordons, Paris, all of France [73] Assignee: Societe Nationale Industrielle Aerospatialle, Paris, France 22 Filed: Feb. 19,1971

[21] Appl.No.: 116,959

[30] Foreign Application Priority Data Feb. 23, 1970 France ..70064ll [52] US. Cl ..89/1.807, 89/l.814 [51] Int. Cl. ..F41f 3/04 [58] Field of Search ..89/l.806, l R, 1 B, 1.807, 89/l.814

[56] References Cited UNITED STATES PATENTS 2,751,818 6/1956 Bonnett ..89/1 .807 2,788,712 4/1957 Kuller et a1 .....89/l.807 3,331,278 7/1967 Brown ..89/l R Primary Examiner-Samuel W Engle Attorney-Karl W. Flocks [5 7] ABSTRACT A safety device for locking a missile either in the transport position in its container, or in the firing position on its launcher, in which means maintains electric circuit for energizing the missile propellant igniters short-circuited as long as the missile is not in a condition to be fired, and actuating means with movable restraining means permitting to fetch the missile from an initial locking position to a final retracted position and latching said movable means in their final retracted position.

7 Claims, 6 Drawing Figures J PATENTEDMARZOIQYS. 3.721.155

SHEET 10F 2 9 5 2 e; SP L FIGS INVENTORS EMILE STAUFF MICHEL MAREE JACQUES ROZE DES ORDONS BY W A TTORNE) SAFETY DEVICE FOR LOCKING A MISSILE ON ITS LAUNCHER OR IN ITS CONTAINER IN EITHER THE TRANSPORT OR THE LAUNCHING POSITION The present invention relates to a safety device for looking a missile on its launcher or in its container, irrespective of whether the missile is in the transport or launching position.

It is well-known that any missile, be it inside its container or on its launcher, must be effectively and reliably restrained in order to fully safeguard its opera tors.

In particular, therefore, the locking system used to that end rnust rigorously interdict accidental igniting of the propulsion systems, and this not only until the firing command has been given but also until the restraining mechanism has completely retracted and been latched in its retracted position.

Accordingly, any locking system designed to provide the above safeguards must have the following features:

Its mechanism must have faultless efficacy and reliability.

It must be capable of short-circuiting the igniters used for the missile propellants, in order notably to protect the same against magnetic effects due to environmental phenomena.

It must be capable of opening or short-circuiting the firing circuits through the agency of the missile restraining element for as long as the latter is maintained in the locking position.

It must be capable of re-making the circuits to the igniters used for the propellants by setting the missile restraining element in the released position, and must do so directly without recourse to an intermediate element.

It must be capable of causing the firing circuits to be closed solely by virtue of the fact that the missile restraining element is in its released position and held therein.

It is the object of the present invention to provide a locking device which possesses the above-mentioned features, that is to say which provides, when in its locking position, safe latching of the missile on its launcher or in its container irrespective of whether the missile is in the transport or launching position, and, when latched in its retracted position, all the electrical contacts required for satisfactory firing of the missile.

Essentially, a safety latching device according to this invention is characterized by the fact that it includes a mechanical restraining mechanism capable of occupying: either an initial locking position wherein it restrains the missile, breaks the electric circuit for energizing the missile propellant igniters, which circuit is additionally short-circuited; or, responsively to an actuating mechanism, a final retracted position wherein it is completely clear of the path of the missile, cancels the short circuit and closes the igniter energizing circuit, means being provided for latching the restraining mechanism in both its initial and final positions, the means for latching the restraining mechanism in its final retracted position being so devised as to allow the current for igniting the missile propulsion system to pass only if said restraining mechanism is effectively in its unlatched position, whereby safe operation is ensured, on the one hand by the fact that accidental firing due to an environmental magnetic field or unwanted energization of the igniters is prevented and, on the other, by the fact that the restraining mechanism is retracted and latched in that position throughout the missile blast-off phase.

Further particularities and advantages of the present invention will emerge from the description which follows of a possible embodiment of a safety locking device according to the invention, given with reference to the accompanying non-limitative exemplary drawings, in which:

FIG. 1 is a cross-sectional side elevation view of a locking device according to the invention, the component parts of its mechanism being depicted in the initial locking position; '7 V V 7' FIG. 2 is a cross-sectional side elevation view corresponding to FIG. 1 but in which the component parts of the mechanism are depicted in the final retracted position;

FIG. 3 is a detail plan view of the end of the printed circuit providing the electrical circuitry, in the position it occupies when the mechanism is in its initial locking configuration;

FIG. 4 is a detail view corresponding to that of FIG. 3 but in which the end of the printed circuit is shown in the position it occupies when the mechanism is in its final retracted configuration; and

FIGS. 5 and 6 are explanatory electrical diagrams showing the electrical connections which are made when the mechanism is in its locking and retracted positions respectively.

The locking device illustrated in the accompanying drawings basically includes a restraining mechanism which in the exemplary embodiment shown is formed by a cylindrical locking pin 1 made of high tensile steel and capable of sliding along its longitudinal axis xx through a housing generally designated by reference numeral 2 which is secured by any convenient means to a boss 3,, with which the missile container or launcher 3 is provided to that end. The boss 3,, is formed with a bore 4 through which the locking pin 1 extends in such manner that the head 1,, thereof be capable, when the pin is in its upper locking position shown in FIG. 1, of engaging into a lodging 5 provided for the purpose in missile 6. The missile is accordingly restrained along two mutually perpendicular axes which are horizontal in the case of FIG. 1, and the missile is further restrained along the third axis, namely along the locking-pin axis xx by an additional thrust exerted on the missile and schematically portrayed on the drawing by the arrows F Housing 2 is formed in its middle part with an annular flange 7 which bounds two separate compartments, to wit an upper compartment 2; containing electrical contacts to which more detailed reference will be made hereinafter, and a lower compartment 2 through which locking pin 1 is guided and which is accordingly formed with a cylindrical abutment 8 capable of sliding within compartment 2, after the fashion of a piston through a cylinder, as will be explained in greater detail hereinafter.

Further, locking pin 1 is provided over its middle portion with a sleeve 9 made of insulating material which is an exact fit through annular flange 7, and abutment 8 is provided with a seal 8,,. A fluid-tight chamber is thus formed which communicates through an orifice 11 with a gas generator which is preferably a pyrotechnic system generally designated by reference numeral 12 and to which further reference will be made hereinbelow.

Pin 1 is restrained in the locking position of FIG. 1 by a shear-pin 13 which is inserted both through the wall of compartment 2, and into piston 8.

Provided in the upper housing compartment 2 on insulating member 14, are spring contacts 15 electrically connected to a flexible printed-circuit 16 which provides the overall electric circuitry and which shortcircuits the missile igniters for as long as the missile remains locked by pin 1, in the manner to be described in greater detail hereinbelow.

It should be noted, further, that when pin 1 is in the missile locking position, the moving portions of spring contacts 15 bear against the insulating sleeve 9, whereby the current supplies to printed circuit 16. as schematized by the arrow F are cut off.

Insulating sleeve 9 carries on its upper end contacts 17 which, as will be explained later, close the feed circuits when pin 1 descends into the retracted position.

As is clearly shown in FIG. 3, on which are shown the inputs e e and e, and the outputs s s and s the igniters are short-circuited by the end 16 A of flexible printed-circuit 16. This end 16,, is retained between the lower base of housing compartment 2, and a cover 18 secured by any convenient means. The cover 18 is formed with a central hole 19 for receiving the lower end of locking-pin 1 when the same is in its bottom position, and with a lodging 20 made of hard insulating material and forming, as will be explained in greater detail hereinafter, a stamping die which is caused to cut off the end 16,, of the printed circuit responsively to piston 8 (likewise made of insulating material) as the locking-pin l descends.

It will be appreciated that in the upper position shown in FIGS. 1, 3 and 5:

the pin 1 is in the locking position and restrains the missile 6 on its launcher or container 3 by virtue of the mechanical restraint exerted by its head 1,, in lodging 5;

the pin 1 is itself latched in the locking position by the mechanical restraint exerted by shear-pin 13;

the contacts 15 bear against insulating sleeve 9 of locking pin 1, whereby the igniter energizing circuit is open, thus providing an effective safeguard against accidental energization; and

the flexible printed-circuit 16 is itself effective in short-circuiting the circuit leading to the igniters, thereby providing an additional safeguard against accidental energization, and protection against electro-magnetic effects.

" It is important to note that, because the short-circuiting is done by the printed-circuit itself, all other connections such as welds, crimpings or other joining means offering imprecisely known and essentially variable contact resistance can be dispensed with. The short circuit is consequently highly dependable since its ohmic value depends solely on the geometric and electrical characteristics of the printed-circuit conductor.

To release the mechanism, all that is necessary is to ignite the gas generator 12.

Subsequent to such ignition, the pressure developed by the gas in chamber 10 is exerted against the piston 8 of locking-pin 1 and produces an axial force on locking-pin 1 which shears the pin 13 into two parts 13 13 and drives pin 1 downward. This movement of locking-pin 1 results (see FIGS. 2, 4 and 6) in mechanically releasing missile 6 through retraction from the flight path of all elements connected to the missile when the latter blasts off; in the end 16,, of the printed-circuit being out between the insulating portion of piston 8 and the stamping-die forming part 20 of cover 18; and in arresting the pin against the bottom of cover 18.

It may be seen that in this released position shown in FIG. 2:

the pin 1 is in the fully retracted position, whereby missile 6 is mechanically unrestrained;

the end 16,, of the printed circuit is cut in accordance with the diagram shown in FIG. 4, the effect of which is to eliminate the short-circuit protecting the propellant igniters; and

the moving contacts 15 bear against their counterparts 17 carried on the sleeve 9 of pin 1, whereby the circuit energizing the igniters is closed; in this configuration the electrical connections are as shown in FIG. 6.

It is important to note that pin 1 is restrained in the retracted position by the spring contacts 15 bearing against a shoulder 9,, formed on insulating sleeve 9 and projecting outwardly in relation to contacts 17.

This non-return device for pin 1, provided by the contacts themselves, can be further improved by damping any tendency of the pin to rebound when it is arrested, for example by means of a lead plate (not shown).

It will be appreciated from the foregoing that the overall system is completely safeguarded since in the event that the pin 1, after shearing its restraining pin 13 and the printed-circuit 16,,, were able to rebound into a position such that a portion thereof hindered launching of the missile, the firing command could not be transmitted to the igniters. This is because, in such position of the locking-pin, the contacts 15 for closing the energizing circuit would be unable to register with the counterpart contacts 17 carried by the firing-pin.

If this were to occur, the missile would be in the released configuration and would have to be handled with care, abandoned or destroyed, but in any event could not be launched under conditions representing a hazard for the operator.

It goes without saying that many changes and substitutions could be made in the preferred exemplary embodiment hereinbefore described, without departing from the-scope of the invention as set forth in the appended claims.

We claim: I

1. A safety device for locking a missile having an electrically ignited propulsion system, either in the transport position on' its container or in the firing position on its launcher, comprising, in combination:

an electric circuit for energizing the missile propellant igniters including short-circuiting means for maintaining said energizing circuit short-circuited for as long as the missile is not in a condition to be fired,

and switch means for making and breaking said enersaid short-circuiting means being a printed circuit gizing system; positioned by shearing by said movable means movable means for mechanically restraining the miswhen said movable means moves to its final sile n its pp capable of py ng either of retracted position to cancel the short-circuit t Stable POSIUOHS; 5 produced by said short-circuiting means. said movable means having an initial locking position 3 A safety ki d i as l i d i lai 2,

wherein said movable means restrains the missile f th characterized b and maintains said switch means in the circuit Said movable means having a piston portion hi h breaking position; passes through said short-circuiting means. and said movable means having a final retracted l0 A Safety locking device as Claimed in claim 3,

position wherein said movable means fully clears further characterized by the of th e.missil,e along its i f l said actuating means being pyrotechnic means to releases said energizing circuit short-circuitmg form a gas operating against said piston portion. means and moves said switch means into the make 5 A Safety locking device as claimed in claim 1 posluonl 1 further characterized by actuating means for moving said movable restraining said first latch means being a sheappin means from its initial position to its final position; 6 A Safet lockin device as claime'd in claim 5 first latch means to positively lock said movable y g further characterized by restraining means in its initial locking position for Said actuatin means bein rotechnic means as long as said actuating means has not operated; 2O 7 A Safety i g ig claimed in Claim 1 and f h h t db second latch means to positively lock said movable 6 mac enze y said second latch means being movable contacts 7 restraining means in its final retracted position i h 2. A safety locking device as claimed in claim 1, Much form Swtc further characterized by

Claims

1. A safety device for locking a missile having an electrically ignited propulsion system, either in the transport position on its container or in the firing position on its launcher, comprising, in combination: an electric circuit for energizing the missile propellant igniters including short-circuiting means for maintaining said energizing circuit short-circuited for as long as the missile is not in a condition to be fired, and switch means for making and breaking said energizing system; movable means for mechanically restraining the missile on its support, capable of occupying either of two stable positions; said movable means having an initial locking position wherein said movable means restrains the missile and maintains said switch means in the circuit breaking position; and said movable means having a final retracted position wherein said movable means fully clears the trajectory of the missile along its launcher, releases said energizing circuit shortcircuiting means and moves said switch means into the make position; actuating means for moving said movable restraining means from its initial position to its final position; first latch means to positively lock said movable restraining means in its initial locking position for as long as said actuating means has not operated; and second latch means to positively lock said movable restraining means in its final retracted position.

2. A safety locking device as claimed in claim 1, further characterized by said short-circuiting means being a printed circuit positioned by shearing by said movable means when said movable means moves to its final retracted position to cancel the short-circuit produced by said short-circuiting means.

3. A safety locking device as claimed in claim 2, further characterized by said movable means having a piston portion which passes through said short-circuiting means.

4. A safety locking device as claimed in claim 3, further characterized by said actuating means being pyrotechnic means to form a gas operating against said piston portion.

5. A safety locking device as claimed in claim 1, further characterized by said first latch means being a shear-pin.

6. A safety locking device as claimed in claim 5, further characterized by said actuating means being pyrotecHnic means.

7. A safety locking device as claimed in claim 1, further characterized by said second latch means being movable contacts which form said switch means.