US2161081A - Automatic bomb releasing device - Google Patents

Description

June 6, 1939.

A. OVTSCHlNNlKOFF AUTOMATIC BOMB RELEASING DEVICE Filed April 1, 195e` 2 sheets-sheet 1 my?, @SX i, CV srv `Hume 6, 1939. A. ovTscHlNNlKoFF n AUTOMATIC BOMB RELEASING DEVICE Filed April l, 1936 2 Sheets-Sheet 2 Patented June 6, 1939 TES UN ETE ST r our-sica 4,

Application 7 Claims.

My invention relates to means for releasing bombs suspended from aircraft and more especially to an automatically operated device for releasing the bomb at the moment when the craft passes over a point on the ground so spaced from the point to be hit that, taking into consideration the speed and altitude at which the craft is travelling, the bomb, when released, Awill drop on the predetermined place. y

The invention relates quite particularly to a device of the kind aforesaid whichis released automatically in dependency upon .the turning. 'about a horizontal axisof a telescope used as a sighting device.

With these and other objects in view my invention will now .be described with reference to the drawings alxed to this specification and forming part thereof, which illustrate, in a purely diagrammatic manner and by way of example a bomb releasing device embodying my invention.

In the drawings: v

Fig. l is a diagram serving to explain the principle according to which the new device operates.

Figs. 2 and 3 are a side and end elevation.,` respectively, of the device as a whole and Figs. 4, 5 and 6 are sections on the line IV-IV in Fig'. 3 illustrating the device in three consecutive positions.

Fig- 7 is the wiring diagram.

Referring to the drawings and rst to Fig. 1, which is intended to explain the effects of the displacement of an aircraft travelling at a predetermined distance above ground relative to the object to be hit, S represents the ground, A the automatically active switching device serving to actuate the releasing device proper and 2 is the sighting telescope xed to the switching device and arranged to be turned together with same about a horizontal pivotal axis .0. Assuming the telescope to be directedonto the point N, which marks the place or object to be hit, N1 and N2 are the end points of two possible curves described by a bomb when dropped at the point occupied, in the drawings, by the' pivotal axi's O, according to the speed of ight of the craft. While the craft is displaced in the direction of the arrow relative to the ground, the trajectories, which depend solely on the altitude and the speed of iiight, remain the same and there is a moment when the point of intersection between these trajectories and the ground, after having passed through the positions indicated at N1, Na and Na. will reach the point N aimed at.I 1f the altitude,

at which the craft is flyingl should change, the

April 1, 1936, Serial No. 72,134 In France July 9, 1935 v (CL. Sil- 1.5)

ground need only be shifted graphically into a position such as S' shown in the drawings. At the moment when the point of intersection between the trajectory and the ground reaches the point N, which is the moment at which the bomb must be released, the sighting line T and the vertical V extending through O enclose between themy a predetermined angle a at which the switching device must automatically establish the contact for the release of the bomb. In order that the automatic establishingI` of this contact takes place in time, the switching device is arranged to close, by means of a mercury switch M, a first circuit to cause a chronometer 3 to start running, the moment, when this circuit is closed, being determined by a sighting angle which is much larger than theangle a and in fact largerthan any angles a corresponding to all possible speeds and altitudes of the craft. This chronometer 3 is adapted to produce, a predetermined, and variable, time after the passage of the telescope through a given xed angular position, a modication in the flow of the mass of mercury of a mercury switch pivoted together with said telescope and adapted to close the circuit of the bomb release device.

The sighting and switching device as illusktrated in detail' in Figs. 2 to 6, comprises 'abody of mercury M filling about one half of the length of the annular conduit'Ainto which extend two contacts I3 and 22 which are spaced angularly and the rst of which is connected in the circuit of an electromagnet I4, the armature I5 of which governs a rock lever I6 serving to act `on a pin Il, which is arranged to set the chronometer 3 going. The contact 22 is connectedin the elctric circuit of the bomb release device proper.

The chronometei` 3 is also fixed to the switching device A. 6 is a ring arranged to be turned about the chronometer and held in place by the leaf spring I8. 5 is a stop formed on the ring 6 and serving to cooperate with the pointer 4 of the chronometer to cause the pointer, when the stop '5 has been set to a predetermined angular position, to be read on the scale 1 (Fig. 2) to close, across the spring I8 a circuit enclosing the electromagnet I9 which governs the quantity of mercury utilized to close the releasing circuit. The two electromagnets are connected in parallel in a circuit including the wire i (Fig. 3) of the cable 8 and also the wire 1c leading to the body of mercury. Both thesewires are connected outside of the annular conduit, for the sake oi' simplicity.

The annular conduit A is subdivided, in its left hand half, into two concentric segments I0 and II by an annular partition 30. 'I'he conduit II is comparatively narrow; the conduit I0 is larger, but is constricted at 23. The conduit II is in permanent open communication with the right hand part of the annular conduit A. Communication between this right hand part of conduit A and the conduit I0 is governed by the valve I2 Acontrolled by the armature 20 of the eletromagnet I9 vacting on the valve rod 2I. In the right hand side of the annular conduit A there is provided a spiral-shaped element 9 which serves to reduce the rate of the now of the mercury therethrough.

The releasing circuit, which is closed by the contact'22, comprises the wire l of the lcable .8, the return wire lc connected to the main body of mercury, the battery B and the igniting or other actuating device (not shown) of the releasing device proper. Y

'I'he operation of the device above described is governed by the telescope 2 directedtowards the point or object sighted and gradually inclined in correspondence with the reduction of the distance between this point and the craft. In the positionfshown in Fig. 2 the telescope A is assumed to be directed onto a point beyondthe angle in Fig. 1. In this position of the telescope the chronometer is at rest and the two contacts I3. and 22 are positioned above the mercury. In thefpo'sition of the telescope shown in Fig. 4 the mercury level has reached the plane a-b right above the throttled portion 23 and corresponds to the angle enclosed between the telescope and the vertical. In this position the contact I3 just touches the mercury so as to close the circuit oi the electromagnet I5 which thereupon attracts the lever I6 to set the chronometer 3 moving, the pointer 4 of which now starts on its course. In the position shown in Fig. 5 the mercury level has reached the plane c-d extending through the constricted portion 23 of the annular conduit I0 and through a point between the contacts I3 and 22. At the same time the pointer 4 has reached the stop 5, which had previously 'been adjusted to the position coriesponding to 13 sec-v onds calculated by the operator as corresponding to the altitude at which the craft is travelling. Exactly 13 seconds after the telescope has entered the angle the circuit of the electromagnet I9 is closed, and this electromagnet in itsv turn closes the valve I2, thereby closing up that part of the body of mercury which is enclosed in the section IIJ of the annular conduit.

' As the telescope continues to be'turned more or to the plane e-f (Fig. 6) which passes through the contact 22, while the mercury level in the section ID of the conduit remains in the plane g-h. The period of time required by the mobile body' of mercury to reach e-f and to close the switching circuit will obviously diier from that which the entire body of mercury enclosed in the device would require.

The period of time, within which the mercury travels from the plane a-b including the contact I3 to the plane e-f including the contact 22, and which corresponds to the rotation of the telescope between the sighting lines enclosing the angles and a and ending in NB and N2, is the sum of a variableperiod dened by the position of the stop 5 of the chronometer and the period required by the mercury to travel between the constricted portion of the annular section IIl and the plane e-l, this latter period of time depending upon the speed of flight on which depends the speed of rotating the tele-l scope, and the altitude of flight, which acts on the position of the plane c-d. By calculation considering the altitude of flight the stop S can beso adjusted that the surn total of the two periods of time above dened causes the bomb to be released for the correct sighting angie which corresponds to the passage of the sighting point from N1 to N2.

I wish it to be understood that I do not desire to be limited to the exact details of construction shown and described for obvious irvaiflcations will occur yto a person skilled in the art.

I claim: Y Y n n 1. A control apparatus for use on an aircraft in connection with an electrically operated bomb 'release device, which comprises, in combination.

a frame adapted to be fixed on said aircraft, a sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed towarda target on the ground, an electric contactor carried by said frame including an insulating conduit with atleast one contact, and a conducting liquid normally apart from said contact, means,

operative by said sighting element, for production, and an electric circuit for controlling said.

bomb release device including in series said contact and said liquid.

Q2. A control apparatus for use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination, a frame adapted to be xed on said aircraft, a sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed toward a target on the ground, an electric contactor carried by saidframe including an insulating conduit with at least one contact, and a of a conducting liquid in said conduit normally apart from saidy contact, means operative by said sighting element for pivoting said conduit so as to produce a displacement of said mass of liquid toward said contact synchronous with the movement of said sighting member when the latter is pivoted downwardly so as to be kept pointedto-l ward the target, means for modifying the conditions of flow of said liquid in said conduit an adjustable time after said sighting element has passed through a given angular position, and an electric circuit for4 controlling said bomb release device including in series said contact and said mass of liquid.

3. A control apparatus for use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination, a frame adapted to be fixed on said aircraft, a sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed toward a target on the ground, an electric contactor carried by said frame including an insulating annular conduit rigid with said pivoting sighting element coaxially therewith, a contact in said conduit, and a mass of a conducting liquid in said conduit, normally apart from. said contact and adapted to move toward said contact when said sighting element is pivoted downwardly so as to be kept pointed toward the target, means for modifying the section of the passage for said liquid in said conduit an adjustable time after said sighting element has passed through a given angular position, and an electric circuit for controlling said bomb release device including in series said contact and said liquid.

4. A control apparatus f or use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination,

a frame adapted to be xed on said aircraft, a`

sighting element pivotally carried by said frame about a horizontal axis so as to permit of keeping said element continuously pointed toward a target on the ground, an electric contactor carried by said frame including an insulaing annular conduit rigid with sald pivoting sighting element coaxially therewith, a contact in said conduit, and a mass of a conducting liquid, normally apart from said contact and arranged to move in said conduit toward said contact, when said sighting element is pivoted downwardly so as to be kept pointed toward said target, an annular partition dividing said conduit longitudinally into two chambers, extending to a distance from said contact, means for closing one of said chambers an' adjustable time after said sighting element has passed through a given angular position, and an electric circuit for controlling said bomb release device including in series said contact and said mass of liquid.

5. A control apparatus for use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination, a frame adapted to be xed onsaidaircraft; a sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed toward a target on the ground, an electric-contactor carried by said frame including an insulating annular conduit rigid with said pivoting sighting element coaxially therewith, a contact in said conduit and a mass of a conducting liquid in said conduit normally apart from said contact and adapted to move toward said contact when said sighting element is pivoted downwardly so as to be kept pointed toward said target, liquid control means for modifying the conditions of iiow of said liquid in said conduit, a chronometer having a pointer. an adjustable contact on said chronometer adapted to cooperate with said pointer for a given angular position thereof, means operative by the mass of liquid in said conduit for starting said chronometer when said sighting element passes through a predetermined angular position, an electric circuit for operating said liquid control means, including said adjustable contact and said 6. A controll apparatus for use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination,

a frame adapted to be xed on said aircraft, a-

sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed toward a target on the ground, an electric contactor carried by said frame including an insulating annular conduit rigid with said pivoting sighting element coaxially therewith, a contact in said conduit and a mass of a conducting liquid, normally apart from said contact and arranged to move in said conduit toward said contact when said sighting element is being pivoted downwardly y so as to be kept pointed toward the target, an annular partition dividing said conduit longitudinally into two chambers, extending to a distance from said contact, means for closing one of said chambers, a chronometer having a pointer, an adjustable contact on said chronometer adapted to cooperate with. said pointer for a given angular position thereof, means operative by the mass of liquid in said conduit for starting said chronometer when said sighting element passes through a predetermined angular position, an electric circuit for operating said closing means, including said adjustable contact and said pointer, and an electric circuit for controlling said bomb release device including in series said rst mentioned contact and said mass oi' liquid.

` 7. A control apparatus for use on an aircraft in connection with an electrically operated bomb release device, which comprises, in combination, a frame adapted to be ixed on said aircraft, a sighting element pivotally carried by said frame about a horizontal axis, so as to permit of keeping said element continuously pointed toward a target on the ground, an electric contactor carried by said frame including an insulating annular conduit rigid with said pivoting sighting element coaxially therewith,two contacts in said conduit, and a mass of a conducting liquid, normally apart from said contacts and arranged to move in said conduit toward said contacts, when said sighting element is beingpivoted downwardly so as to be kept pointed toward said target, an annular partaining in series said mass of liquid and the first oi said two contacts, for starting said chronometer when said mass of liquid reaches said ilrst contact, which corresponds to said sighting element passing through a predetermined fixed angular pcsition,an electric circuit for operating said valve, including said adjustable abutment 'and said pointer, and an electric circuit for controllingsaid bomb release device including in series the.

second of said contacts and said mass of liquid.

ALEXANDRE OVTSCHDINIKOFF.

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