US3307451A

US3307451A - Pressure control device

Info

Publication number: US3307451A
Application number: US400745A
Authority: US
Inventors: Bucklisch Ludwig; Volpert Ludger
Original assignee: Dynamit Nobel AG
Current assignee: Dynamit Nobel AG
Priority date: 1963-10-02
Filing date: 1964-10-01
Publication date: 1967-03-07
Anticipated expiration: 1984-03-07
Also published as: BE653646A; GB1093171A; DE1428630A1

Description

*March 7, 1967 Y L. BUCKLISCH ETAL PRESSURE CONTROL DEVICE Filed Oct. 1, 1964 INVENTORS LUDWIG BUCKLISCH LUDGER .VOLPERT ATTORNEYS United States Patent Ofiflce Claims. in. 39-1101 The present invention relates to a mechanism for influencing the pressure of propellent charges for a shell or projectile to be fired from a barrel.

The starting velocity of a shell or projectile which is fired out of a barrel depends, as known, on the pressure which develops during the burning of the propellent charge powder. This pressure, in turn, depends on the prevailing temperature of the propellent charge powder which is the reason why shells or projectiles of one and the same type with different firing temperatures of the propellent but otherwise under completely identical conditions have a different starting velocity resulting in very considerable differences as regards firing accuracy, penetrating force and flight distance of the shell or projectile in addition to strongly varying loads of the gun barrel.

In order to avoid these disadvantages one seeks to achieve over the range of all firing temperatures of the propellent charge powder that possibly occur in practice, a constant starting velocity of the shells or projectiles. A known measure to influence the starting velocity of a projectile in this sense resides in the use of partial charges of differently rapidly burning propellent charge powders. With recoilless guns there has been used with good success for propellent powder charges of predetermined size also a change in the inertia mass corresponding to the temperature differences. Both prior art measures have, however, the considerable disadvantage that they require a supiply maintenance and experimentation of additional charge or inertia elements which represent a considerable inconvenience and burden for a field-type deployment or for combat action of the troops.

According to the present invention there is proposed a mechanism for influencing the pressure of propellent charges for projectiles to be fired from a barrel which can be manipulated in simple manner similar to a range finder adjustable to a desired distance. The mechanism according to the present invention is characterised in that the pressure space for the propellent charge is connected for the purpose of discharge or release of a variably quantity of propellent charge gases through one or several apertures, bores or the like arranged in the wall of the gun barrel, with recoilless guns possibly also in the body of an inertia means, with an additional pressure space closed oflf against the outside or also connected with the atmosphere by further apertures, bores or the like or also directly with the atmosphere.

By means of the device of the present invention, one can readily control and always accurately adjust, by simple discharge or outflow of a corresponding quantity of the gases developing during burning of the propellent charge powder out of the pressure space for the propellent charge, the pressure of the propellent gases within the pressure space corresponding to the prevailing firing temperature of the propellent charge powder to such a value that the projectile always has the same starting velocity. If, for example, one intends to let the excess quantity of propellent gas flow out or escape directly into the atmosphere, then only the apertures, bores or the like connected with the pressure space have to be constructed with adjustable outflow cross section and the prevailing free outflow cross section has to be adjusted correspondingly, which can take place, for example, in such a manner that a threaded ring is arranged on the gun barrel which,

3,307,451 Patented Mar. 7, 1967 depending on the adjustment in the one or the other direction, frees or opens up a greater or smaller number of correspondingly arranged apertures of the gun barrel. With recoilless guns, axial bores may also be provided within the body of an inert mass whose inside cross section are more or less opened up, for example, by means of a disk rotatably secured at the inertia mass so that the corresponding excess propellent gas quantity can flow out of the opened-up bores.

In the interest of as little as possible an impairment of the rigidity of the gun barrel and also in the interest of as little as possible an endangering of the operating personnel by the high pressure of the outflowing or released propellent gases, it may, however, also be advisable not to let the excess quantity of propellent charge escape into the atmosphere or at least to let the same flow out into the atmosphere only indirectly by way of an auxiliary pressure space connected with the main pressure space. In that case, use may be made of various measures. For example, the pressure space may be connected with an auxiliary pressure space which is closed, completely tight with respect to the outside atmosphere and of constant volume, though of suflicient volume for all possible applications, in that the excessive propellent gas quantity is then let ofl or released by way of bores of adjustable flow cross section. In lieu thereof, however, the volume of the auxiliary pressure space may be made adjustable and the flow cross section of the apertures, bores or the like can then, instead, be kept constant. Finally it is also possible to render adjustable both the volume of the auxiliary pressure space as well as also the flow cross section of the bores.

An excessively high load of the auxiliary pressure space by the propellent gas quantity let out of the pressure space can be avoided in that at least a part of this excess propellent gas quantity is permitted to flow out of the auxiliary pressure space into the atmosphere. In that connection the present invention proposes to construct the bores or the like provided in the walls of the auxiliary pressure space with adjustable flow cross section and according to a further feature of the present invention to couple the change of the flow cross section with the change in volume of the auxiliary pressure space whereby not only an excessively high load is avoided but above all a constant loading is achieved.

In all cases the arrangement will appropriately be made in such a manner that the predetermined, non-adjustable volume of the pressure space corresponds to the desired starting velocity of the projectile at the lowest possible temperature of the propellent charge powder so that with a normal temperature always a portion of the propellent charge gases has to flow out in order to achieve the required starting velocity of the projectile or shell. This measure is necessary if an influencing of the pressure of the propellent charge gases is to be possible in the sense of a constant starting velocity of the projectile or shell both at higher as well as at lower temperatures than the normal temperature.

Accordingly, it is an object of the present invention to provide a pressure control mechanism adapted to control the pressure of the propellent for shells and projectiles in such a manner as to avoid by extremely simple and inexpensive means the shortcomings and drawbacks encountered with the prior art constructions.

It is another object of the present invention to provide a pressure control means for the propellent gases of shells and projectiles which is not only simple in construction but also operationally reliable as well as easy to handle and adjust.

A further object of the present invention resides in theprovision of a control mechanism operable to maintain constant the starting velocity of a projectile to be fired from a barrel regardless of prevailing temperature while simultaneously preventing any considerable changes in the loads and stresses to which the gun is subjected, particularly as regards the gun barrel.

A still further object of the present invention resides in the provision of a gun capable, by simple means, of compensating for temperature changes affecting the propellent thereby improving the firing accuracy, penetrating force and flight distance of the projectiles or shells thereof.

Another object of the present invention resides in the provision of a pressure control device for guns which requires no experimentation, testing or cumbersome storing facilities to assure at all times the same starting velocity for the shells or projectiles thereof.

Still another object of the present invention resides in the provision of a pressure control and adjusting device for guns adapted to maintain essentially constant the starting velocity of the projectile to be fired, which is simple in its adjustment as well as safe for the operating personnel.

These and other objects, features and advantages of the present invention will become more obvious from the following description when taken in connection with the accompanying drawing which shows, for purposes of illustration only, several embodiments in accordance with the present invention, and wherein FIGURE la is an axial longitudinal cross sectional view of a first embodiment of an adjusting mechanism in accordance with the present invention in which the influence of the pressure of the propellant gas takes place by means of an auxiliary pressure space surrounding the gun barrel in a ring shaped manner;

FIGURE 1b is a cross sectional view taken along line AA of FIGURE la;

FIGURE 2 is a transverse cross sectional view through a modified embodiment of a pressure control mechanism in accordance with the present invention having an auxiliary pressure space mounted over the gun barrel;

FIGURE 3a is a partial axial longitudinal cross sectional view through a recoilless gun provided with a control mechanism in accordance with the present invention, and

FIGURE 3b is a cross sectional view taken along line BB of FIGURE 3a.

Referring now to the drawing wherein like reference numerals are used throughout the various views to designate like parts, and more particularly to FIGURE 1, reference numeral 1 designates therein the gun barrel which is provided with radial bores 2; the bores 2 are arranged at the place of the highest starting pressure of the propellant powder gases developing during the burning of the propellant charge (not shown) and connect the inside of the barrel or the pressure space 7 with the auxiliary pressure space 3 formed by the barrel 1, the flange 5 provided on the barrel 1 as well as the annular housing 4 threadably mounted on the coarse thread 6 of the barrel 1. The volume of the auxiliary pressure space 3 is adjustable by rotating the annular housing 4 with respect to the barrel 1. The flange 5 is sealed with respect to the annular housing 4 by means of the annular seal 9. Under certain circumstances it may also be appropriate to provide an annular seal between the barrel 1 and the annular housing 4.

Upon a corresponding rotation of the annular housing 4 on the barrel 1 the auxiliary pressure space 3 decreases, whereby simultaneously the charge density is increased. Inversely the charge density decreases with an increase of the auxiliary pressure space 3 by an opposite rotation of the annular housing 4. The starting velocity of the projectile or shell may be influenced by means of this change in the charge density in the sense that it always has the same magnitude within the entire range of the normally occurring temperatures of the propellant charge powder, for example, from C. up to +40 C. The

volume of the auxiliary pressure space 3 corresponding to the respective temperature of the propellant charge powder can be adjusted by means of the temperature scale arranged at the rear end of the annular housing 4 (FIGURE 1b) in a most simple manner and to the correct magnitude whereby the indicator mark 10 secured at the flange 5 indicates always the condition under which the firing takes place.

In those cases in which a change of volume of the auxiliary pressure space 3 does not by itself sufiice to influence the effect of the propellant charge in the desired sense, the radial bores or apertures 11 may be providedas shown in dash and dot line in the lower half of FIGURE 1ain the walls of the annular housing 4. As may be readily seen from FIGURE 1a, the flange 5 upon rotation of the annular housing 4, that is, with a change of the volume of the auxiliary pressure space 3, frees or opens up a more or less large total cross section of the apertures 11 so that a more or less large portion of the propellant charge gases can escape into the atmosphere. It is recommended in practice to construct the apertures 11 with an approximately square or rectangular cross section and to stagger or offset the same in the circumferential direction with respect to one another in such a manner that the end of one aperture coincides accurately in the axial direction with the beginning of the aperture. In this manner a linear relationship is established between the change in volume of the auxiliary pressure space 3 and the change of the free cross section of the discharge apertures 11, whereby the pressure of the propellant charge gases can be changed continuously, that is, without pressure gaps. A disturbance of the predetermined relationship between powder temperature and charge density does not occur by reason of the arrangement of the discharge apertures 11 since the pressure decrease takes place linearly with partial discharge of the propellant gases.

The embodiment illustrated in FIGURE 2 of the mechanism according to the present invention is advantageous especially in those cases in which a considerable decrease of the charge density is not possible without endangering thereby the regular combustion process of the propellant powder. With this mechanism the auxiliary pressure space 3 is constituted by the threaded stud or connection 14 arranged on the barrel 1 at the place of the highest starting pressure, in this embodiment, for example, welded tnereonand by the cover 15 provided with discharge apertures 8 and threaded on the stud or connecting piece 14. The auxiliary pressure space 3 is in communication with the pressure space 7 on the inside of the gun barrel 1 by way of a bore 2 having a constant cross section. The volume of the auxiliary pres sure space 3 participating in determining the charge density is changed only slightly by rotating the cover 15 on the threaded stud or connection piece 14 whereby the end surface of the cover 15 and the oppositely disposed end surface of the threaded stud 14 form together an annular nozzle insofar as the cover 15 is not screwed-in up to the mutual abutment of the two end surfaces. This annular nozzle has its smallest cross section along the inner edge 16 of the threaded stud or connecting piece 14 whereby the respective size of the cross section is determined, in addition to being determined by the inner diameter of the threaded stud 14, also by the respective distance between the oppositely disposed end surfaces of the cover 15 and of the threaded stud 14. The distance between these end surfaces and therewith also the nozzle cross section can be changed within the given limits at will and continuously by rotating the cover 15. These limits are in practice a cross section of zero, that is, a closed nozzle for firing at the lowest powder temperature to be considered, and the nozzle cross section of such size that upon firing of the powder at the highest temperature to be taken into consideration, exactly so much of the propellant gas can escape that in both cases the same starting velocity of the projectile or shell is realized. In order to be able to adjust accurately the annular nozzle cross section in a simple manner, a temperature scale is again provided at the cover which indicates in connection with an indicator mark (not shown) and provided, for example, at the threaded stud 14 the prevailing conditions under which the firing takes place.

The annular nozzle constituted by the threaded stud 14- and the cover 15 is not subject to corrosion by the hot propellant gases since the heat is conducted away over a relatively large surface. At the outer circumference of the nozzle cross section, which increases in width with increasing diameter, the propellant gases are conducted into the atmosphere by way of apertures, bores or the like 8, arranged in a larger number in the cover 15, whereby the deflection eiTected by the shape of the cover 15 illustrated in the drawing of the propellant gases escaping or outfiowing in the direction of the arrows 13 neutralizes the momentum produced by these propellant gases.

The embodiment of FIGURE 3 shows the application of the control mechanism according to the present invention to a recoilless free gun. The influencing of the pressure of the propellant charge there-by takes place exclusive-1y with the aid of discharge apertures 18 of adjustable cross section arranged in the inertia mass 17 and constnlcted as bores parallel to the axis since with this type of gun the propellant charge is, as is well known, for the most part very sensitive to any change in the charge density. As shown in FIGURE 3b, the bores 18 parallel to the axis are arranged on a circle 28 concentric to the gun axis 19 and may be covered more or less by means of the rotatable disk 21 provided with a ring-shaped slot 22. A covering of all of the bores 18 corresponds to the conditions of a firing at the lowest powder temperature to 'be taken into consideration. Correspondingly with higher powder temperatures a more or less large portion of the entire cross section of the bores 18 is to be freed or opened up through rotation of the disk 21 by way of the slot 22. The rotation or adjustment of the disk 21 takes place prior to loading of the gun by means of the rotatable knob 23 which is rigidly connected with the disk 21 by means of the shaft 24. In order to enable a simple adjustment to the prevailing firing conditions, a temperature scale is appropriately arranged again at the end face 25 of the inertia mass 17 and an indicator mark (not shown) at the rotatable knob 23.

While we have shown and described several embodiments in accordance with the present invention, it is understood that the same is not limited thereto but is susceptible of numerous changes and modifications as known to a person skilled in the art and we therefore do not wish to be limited to the details shown and described herein, but intend to cover all such changes and modifications as are encompassed by the scope of the appended claims.

We claim:

1. A device for compensating variations of the firing temperature of propellant powder charges for projectiles to be fired from a recoilless rifle barrel having a projectile receiving axially extending bore partially defining a pressure chamber for the propellant powder charges, comprising: an inertia mass of substantially the same diameter as said bore to determine one axial wall of the pressure chamber; conduit means including at least one generally axially extending opening spaced radially inwardly from the outermost diameter of said inertia mass for extending through said inertia mass and connecting said pressure chamber for the propellant powder charge to the atmosphere for exhausting a predetermined fixed amount of the propellant powder charge gases from said pressure chamber to reduce the pressure within said pres sure chamber a corresponding predetermined fixed amount; adjustment means operable to adjust the effective cross sectional area 91 said conduit means to selectively change the fixed amount of gases exhausted in a direct correspondence with the temperature of the propellant powder charge to maintain substantially equal propellant charge gas pressures for producing substantially equal projectile starting velocities regardless of the temperature of the propellant powder charge; said adjustment means having a relatively fine adjustment only between two limits; said adjustment means at one limit of adjustment producing a substantially zero cross sec tional area of said conduit means to substantially prevent the exhausting of propellant gases from said pressure chamber operable to produce a standard gas pressure in said pressure chamber at the lowest firing temperature to be encountered; and said adjustment means at the other limit of adjustment producing the maximum cross sectional area of said conduit means to exhaust the maximum amount of propellant gases from said pressure chamber operable to produce the standard gas pressure in said pressure chamber at the highest firing temperature to be encountered.

2. The device of claim 1, wherein said adjustment means is manually adjustable.

3. The device of claim 1, wherein said adjustment means includes a scale to indicate the adjustment of said conduit means that corresponds to a specific firing temperature.

4. The device of claim 1, wherein said one limit of adjustment corresponds to a temperature of minus 20 degrees centigrade and said other limit of adjustment corresponds to a temperature of plus 40 degrees centigrade.

5. The device of claim 4, wherein said adjustment means is manually adjustable and includes a scale to in dicate the adjustment of said conduit means that corresponds to a specific firing temperature.

6. The device of claim 1, wherein said conduit means comprises a plurality of axially extending arcuately arranged discharge apertures extending the entire length of said inertia mass and said adjustment means is a disc having an arcuate slot and rotata-bly mounted with respect to and for alignment with said discharge apertures.

7. The device of claim 6, wherein said disc is mounted on the forward end of said inertia mass.

8. The device of claim 7, wherein said adjustment means includes a shaft axially extending through a central bearing bore in said inertia mass and having said disc rigidly secured to one end and a manually operable knob secured to the other end.

9. The device of claim 8, wherein said adjustment means includes a scale to indicate the adjustment of said conduit means that corresponds to a specific firing temperature.

15 The device of claim 9, wherein said one limit of adjustment corresponds to a temperature of minus 20 degrees centigrade and said other limit of adjustment corresponds to a temperature of plus 40 degrees centigrade.

References Cited by the Examiner UNITED STATES PATENTS 1,559,183 10/1925 Rimailho 89-1 1,864,374 6/1932 Romberg et al. 89l 2,383,053 8/1945 Fanger et al. 89-1 X 2,801,416 8/1957 Evans et al. 89-1 X 2,986,973 6/1961 Waxman 89-1.703 3,216,323 11/1965 Wengenroth et al. 891.701

FOREIGN PATENTS 308,510 8/1920 Germany. 126,336 5/1919 Great Britain.

OTHER REFERENCES Blacker, German application No. 1,107,129, pub. May 18, 1961.

SAMUEL FEINBERG, Primary Examiner.

SAMUEL W. ENGLE, BENJAMIN A. BORCHELT,

Examiners.

Claims

1. A DEVICE FOR COMPENSATING VARIATIONS OF THE FIRING TEMPERATURE OF PROPELLANT POWDER CHARGES FOR PROJECTILES TO BE FIRED FROM A RECOILLESS RIFLE BARREL HAVING A PROJECTILE RECEIVING AXIALLY EXTENDING BORE PARTIALLY DEFINING A PRESSURE CHAMBER FOR THE PROPELLANT POWDER CHARGES, COMPRISING: AN INERTIA MASS OF SUBSTANTIALLY THE SAME DIAMETER AS SAID BORE TO DETERMINE ONE AXIAL WALL OF THE PRESSURE CHAMBER; CONDUIT MEANS INCLUDING AT LEAST ONE GENERALLY AXIALLY EXTENDING OPENING SPACED RADIALLY INWARDLY FROM THE OUTERMOST DIAMETER OF SAID INERTIA MASS FOR EXTENDING THROUGH SAID INERTIA MASS AND CONNECTING SAID PRESSURE CHAMBER FOR THE PROPELLANT POWDER CHARGE TO THE ATMOSPHERE FOR EXHAUSTING A PREDETERMINED FIXED AMOUNT OF THE PROPELLANT POWDER CHARGE GASES FROM SAID PRESSURE CHAMBER TO REDUCE THE PRESSURE WITHIN SAID PRESSURE CHAMBER A CORRESPONDING PREDETERMINED FIXED AMOUNT; ADJUSTMENT MEANS OPERABLE TO ADJUST THE EFFECTIVE CROSS SECTIONAL AREA OF SAID CONDUIT MEANS TO SELECTIVELY CHANGE THE FIXED AMOUNT OF GASES EXHAUSTED IN A DIRECT CORRESPONDENCE WITH THE TEMPERATURE OF THE PROPELLANT POWDER CHARGE TO MAINTAIN SUBSTANTIALLY EQUAL PROPELLANT CHARGE GAS PRESSURES FOR PRODUCING SUBSTANTIALLY EQUAL PROJECTILE STARTING VELOCITIES REGARDLESS OF THE TEMPERATURE OF THE PROPELLANT POWDER CHARGE; SAID ADJUSTMENT MEANS HAVING A RELATIVELY FINE ADJUSTMENT ONLY BETWEEN TWO LIMITS; SAID ADJUSTMENT MEANS AT ONE LIMIT OF ADJUSTMENT PRODUCING A SUBSTANTIALLY ZERO CROSS SECTIONAL AREA OF SAID CONDUIT MEANS TO SUBSTANTIALLY PREVENT THE EXHAUSTING OF PROPELLANT GASES FROM SAID PRESSURE CHAMBER OPERABLE TO PRODUCE A STANDARD GAS PRESSURE IN SAID PRESSURE CHAMBER AT THE LOWEST FIRING TEMPERATURE TO BE ENCOUNTERED; AND SAID ADJUSTMENT MEANS AT THE OTHER LIMIT OF ADJUSTMENT PRODUCING THE MAXIMUM CROSS SECTIONAL AREA OF SAID CONDUIT MEANS TO EXHAUST THE MAXIMUM AMOUNT OF PROPELLANT GASES FROM SAID PRESSURE CHAMBER OPERABLE TO PRODUCE THE STANDARD GAS PRESSURE IN SAID PRESSURE CHAMBER AT THE HIGHEST FIRING TEMPERATURE TO BE ENCOUNTERED.