CA1063401A - Apparatus for launching a missile - Google Patents
Apparatus for launching a missileInfo
- Publication number
- CA1063401A CA1063401A CA251,687A CA251687A CA1063401A CA 1063401 A CA1063401 A CA 1063401A CA 251687 A CA251687 A CA 251687A CA 1063401 A CA1063401 A CA 1063401A
- Authority
- CA
- Canada
- Prior art keywords
- projectile
- propellant
- braking
- assembly
- launch tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000003380 propellant Substances 0.000 claims abstract description 60
- 239000003721 gunpowder Substances 0.000 claims abstract description 30
- 239000000463 material Substances 0.000 claims abstract description 14
- 238000010304 firing Methods 0.000 claims abstract description 11
- 239000007789 gas Substances 0.000 claims description 16
- 230000001133 acceleration Effects 0.000 claims description 12
- 239000004576 sand Substances 0.000 claims description 4
- 238000007789 sealing Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 2
- 230000002093 peripheral effect Effects 0.000 claims 3
- 239000000779 smoke Substances 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 239000004429 Calibre Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
ABSTRACT OF THE DISCLOSURE
An assembly for launching a projectile comprises a launch tube having a smooth or rifled bore, a charge of gunpowder located in the tube for firing a projectile which is placed in the tube infront of the charge, a braking pro-pellant located in the tube behind the gunpowder charge and carrying a ballast material, and means ensuring that the gunpowder charge is ignited before the braking propellant.
The braking propellant may be connected to a projectile by means of a sleeve to form a rigid unit which is loadable in the launch tube, the sleeve containing the gunpowder charge.
An assembly for launching a projectile comprises a launch tube having a smooth or rifled bore, a charge of gunpowder located in the tube for firing a projectile which is placed in the tube infront of the charge, a braking pro-pellant located in the tube behind the gunpowder charge and carrying a ballast material, and means ensuring that the gunpowder charge is ignited before the braking propellant.
The braking propellant may be connected to a projectile by means of a sleeve to form a rigid unit which is loadable in the launch tube, the sleeve containing the gunpowder charge.
Description
The present invention relates to the launching of a projectile from a launch tube. In this event it is desirable that the reaction on the firing position is negligable;
that a high acceleration of the projectile is obtained; and 5. that a minimum amount of gas is discharged from the front of the tube, and to a lesser extent fr~m the rear of the tube, ln order to reduce the "signature'! of the launching, that is to say, the ease with which the point of launch may be spotted due to emission of smoke and gas, and to disturb -~ 10. the projectile and its guide-system, if any, as little as - possible.
It is already known from, for example, French Patent ; No.943319 to provide firing apparatus comprising a combustion chamber freely movable in a gun barrel which is open at both 15. ends, the combustion chamber having compartments which are completely separated from one.another and in which are arranged -. propellant charges. One of these charges, which is the first to be ignited and is arranged in the compartment open towards ` the rear of the barrel, is used to damp the recoil due to the ¦ 20. discharge of the shot, whilst the other propellant charge, . which is mounted in the compartment open towards the projectile ; and is ignited second, is used for propelling the projectile from the barrel. As mentioned, in an arrangement of this kind it is the rearward charge which is ignited first, and ; 25. one consequence is that accuracy of fire is not very good.
that a high acceleration of the projectile is obtained; and 5. that a minimum amount of gas is discharged from the front of the tube, and to a lesser extent fr~m the rear of the tube, ln order to reduce the "signature'! of the launching, that is to say, the ease with which the point of launch may be spotted due to emission of smoke and gas, and to disturb -~ 10. the projectile and its guide-system, if any, as little as - possible.
It is already known from, for example, French Patent ; No.943319 to provide firing apparatus comprising a combustion chamber freely movable in a gun barrel which is open at both 15. ends, the combustion chamber having compartments which are completely separated from one.another and in which are arranged -. propellant charges. One of these charges, which is the first to be ignited and is arranged in the compartment open towards ` the rear of the barrel, is used to damp the recoil due to the ¦ 20. discharge of the shot, whilst the other propellant charge, . which is mounted in the compartment open towards the projectile ; and is ignited second, is used for propelling the projectile from the barrel. As mentioned, in an arrangement of this kind it is the rearward charge which is ignited first, and ; 25. one consequence is that accuracy of fire is not very good.
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According to the invention, a projectile launching assembly includes a launch tube, a charge of gunpowder located in said launch tube for communication therewith upon ignition and for firing from said tube a projectile which is placed in said tube in front of said gunpowder charge, means permitting, upon firing, the applica-tion of pressure of gases from said gunpowder charge against the rear of the projectile and the inner wall of the launch tube, a braking propellant slidably located in said launch tube behind said gunpowder charge, a ballast material carried by said braking propellant, and means for sequential ignition of said gunpowder charge followed by ignition of said braking propellant to cause the projectile to leave the front end of the launch tube and the braking propellant to leave the rear end of the tube.
The ballast material is preferably in powdery or liquid form, which will cause the ballast to be braked rapidly in air. Particularly suitable for ballast material are grains of sand.
Preferably, the charge of gunpowder i9 contained in a cylindrical sleeve which also serves to connect a projectile to the braking propellant so that a rigid unit is formed which comprises the projectile, the gunpowder, and the braking propel-lant, and which is loadable as a unit into the launch tube. Such a unit is itself novel and forms an important aspect of the present invention. A sealing diaphragm, which may form part of the unit, may be provided behind the braking propellant, this diaphragm serving to retain the ballast before ignition of the braking pro-pellant and being designed to break and release the ballast material when this material undergoes a negative acceleration following ignition of the propellant.
Preferably the arrangement of the launching assembly ~9 .
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is such that the braking propellant leaves the rear end of , the launch tube before the projectile leaves the front end, thereby reducing the pressure of the gases acting on the base of the projectile and consequently the amount which 5. issues from the front end of the tube after the projectile.
An example of a launching assembly in accordance with the invention will now be described with reference to the accom-panying drawings, in which:- ~
Figure 1 is an elevation of a rigid unit which forms 10. part of the launching assembly and which consists of the projectile connected to the braking propellant; and Figure 2 is a 3ongitudinal section through the launching assembly, showing the unit of Figure 1 loaded in a launch tube.
15. ' 'Figure 2 shows a conventional launching tube 10, which-' ' may have a smooth or rifled bore,'and in which is placed a projectile 12-to be launched. A charge of gunpowder~l4 ' ' is located behind the projectile l2, and behind this pow~der_is arranged a braking propellant 16. The braking propellant 20. 16 contains blocks of powder, which are not shown, and ; carries''a ballast'mat~Jr'iaI. ~In th~s example,' ! ~ ~
the br~king propellant 16 carries ballast 18 formed by grain~s of sand retained in an envelope 20. These grains of sand' will~exhibit the characteristic of being braked rapidly in 25. ' air whilst having a terminal veloclty of fall, given by , . , : , .
106340~
- Stokes' formula, greaterthan the particles contained in the smoke emitted during the discharge of the projectile.
They are therefore less visible and for a shorter time than this smoke.
.- 5. As shown in.. Figure 1 the braking propellant 16 is ; connected to the projectile 12 by a slee~e 22, the gunpowder 14 provided for propelling the projectile being contained within the sleeve 22. The assembly represented in Figure 1 consisting of the projectile 12, the gunpowder 14, and the 10. braking propellant 16 w1th its. bal-las~.:
18, constitutes a rlgid loadable unit.
The cylindrical sleeve 22 which connects the braking propellant 16 and the projectile 12 contains a series of - apertures 36, which may be drilled, and which are opened . 15. -progressivély as the braking propellant leaves the tube, thus enabling the expansion of the gases from the gunpowder to be spaced slightly.
.~ .
Behind the braking propellant 16 a sealing diaphragm 26 is provided, which at the same time serves to retain the 20. . ballast be~ore ignition of the braking propellant~
In this example an electrical ignition system 30 for : the gunpowder 14 is shown passing through the nozzle of the braking propellant 16, and operation of the launching assembly . is. as follows: At the instant.of firing, the gunpowder 14 is 25. ignited by the firing system 30, and the pressure of the .. . . ... ., . , .. ~ .. , ~ ,.. -,; .... . . .
-10634~1 resulting gases unlocks the projectile from the sleeve 22 of the propellant 16.
The projectile of mass Ml acquires a velocity Vl at a given instant, and the ballasted propellant of total mass 5. M2 acquires a velocity V2. Neglecting for a first approximation the thrust of the braking propellant, which is going to be ignited by the gases from the gunpowder passing through a gauged orifice 24 provided for this purpose, one can write:
Ml Vl = M2 V2 10. The centre of gravity of the two masses remains fixed.
-I-f, for example, M2 = 2Ml~ one has at every instant:
V2 = V
and the distances covered are in the same ratio.
If the projectile 12 carries a cruising propellant 15. it may be ignited by letting the gases from the ignited gunpowde~ penetrate through the nozzle of the propellant, via a gauged orifice limiting the pressure. It has been -mentioned above that the braking propellant is intended to ~ be ignited in a similar way~ the dimensions-of the gauged~
20. hole 24, ~r holes9 provided for this purpose being a function of the v~lume to be filled and of the delay required for the ignition.
Ignition of the braking propellant 16 provides a braking thrust P, which may be taken into account in analysing -r 25~ t~e motions, by writing that the centre-of gra~ity of (Ml-+ M2) ,: , ~ 106~4(~1 undergoes an acceleration of:
.~ _P
.- Ml + M2 This acceleration will, in general, be negligible compared - with that obtained by the gun effect.
The length of the launch tube 10, and the masses and arrangement in the tube of the projectile 12, the gunpowder 14, the braking propellant 16 and ballast 18, is such that the tube is open first towards the rear, that is to say, the braking propellant 16 leaves the tube before the projectile. In this case, the larger amount of gas is dis-charged from the rear of the tube, It is desirable that the ~` projectile 12 leaves the tube 10 only when the expansion wave has reached it, in order to limit the pressure of the gas on the base of the projectile and hence reduce to a minimum the amount of gas discharged from the front of the tube after the projectile.
It can be shown that the thrust P from the braking propellant 16 may be such that it is braked over a distance of the order of 2 to 4 metres.
The total amount of powder consumed and hence the smoke and flame produced are most certainly a little greater with a launching assembly in accordance with the invention than those produced by a gun giving the same velocity to the ~; projectile, but are much less than those brought into play using a conventional acceleration propellant or recoilless gun.
~j'l .
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' ~, - . . . . -., ' , ,, '.' . -- ' ~, ' -' -~0~4(;~1 In this prefered embodiment of the invention the connec-tion between the projectile and the sleeve 22 of the braking propellant is provided with means which causes an angular acceleration dtW to be given to the projectile when the 5. projectile is fired. It goes without saying that after separàtion of the projectile from the launching system shown - in Figure 2:
Ilwl + I2w2 = O
Il, I2, wl, w2 being the moments of inertia and the angular 10. velocities of the projectile and the launching system.
In the embodiment shown, the sleeve 22 has for this purpose one or more grooves 32, which e~tend obliquely with - respect to the axis of the tube 10, and in which engage one or more studs 34 provided at the rear of the projectile. When 15. the projectile is fired, the displacement of the studs-in the grooves as the projectile separates from the sleeve sets the projectile 12 in rotation.
It should remain clearly understood that this invention is not restricted to the embodiment just described and illu-~- 20. strated, but that it encompasses many variations~within the : scope of the claims. For example, while the presence of a sleeve 22 connecting the projectile to the braking propellant 16 is a feature of one advantageous embodiment of the invention, it may not be present in another embodiment. In this case, 25. the projectile 12, and if necessary the braking propellant 16 . .
: . - .: . . . ~
.. .. . - . : . .. -- . - .
~06340~
may be furnished with at least one groove in the outer wall extending obliquely with respect to the longitudinal axis.
These grooves are arranged to receive lugs or studs integral with the inner wall of the launching tube 10. Such an 5. arrangement enables the projectile 12 and the braking propellant 16 to be set in rotation with opposite angular velocities (the slope of the grooves on the projectile and .
on the braking propellant with respect to the longitudinal axis being in opposite directions for each of these elements) 10. whilst minimizing the reactions upon the tube 10. This is particularly advantageous for launch tubes of small calibre.
:" .
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- - . - - - ... .. ..... . . . . . ..
.. . -.. . . .. .
.
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According to the invention, a projectile launching assembly includes a launch tube, a charge of gunpowder located in said launch tube for communication therewith upon ignition and for firing from said tube a projectile which is placed in said tube in front of said gunpowder charge, means permitting, upon firing, the applica-tion of pressure of gases from said gunpowder charge against the rear of the projectile and the inner wall of the launch tube, a braking propellant slidably located in said launch tube behind said gunpowder charge, a ballast material carried by said braking propellant, and means for sequential ignition of said gunpowder charge followed by ignition of said braking propellant to cause the projectile to leave the front end of the launch tube and the braking propellant to leave the rear end of the tube.
The ballast material is preferably in powdery or liquid form, which will cause the ballast to be braked rapidly in air. Particularly suitable for ballast material are grains of sand.
Preferably, the charge of gunpowder i9 contained in a cylindrical sleeve which also serves to connect a projectile to the braking propellant so that a rigid unit is formed which comprises the projectile, the gunpowder, and the braking propel-lant, and which is loadable as a unit into the launch tube. Such a unit is itself novel and forms an important aspect of the present invention. A sealing diaphragm, which may form part of the unit, may be provided behind the braking propellant, this diaphragm serving to retain the ballast before ignition of the braking pro-pellant and being designed to break and release the ballast material when this material undergoes a negative acceleration following ignition of the propellant.
Preferably the arrangement of the launching assembly ~9 .
.,, ~ , . ..
- ~ -, . , ,.. ;., :. ~ ~ . . . . :
~063~0~
is such that the braking propellant leaves the rear end of , the launch tube before the projectile leaves the front end, thereby reducing the pressure of the gases acting on the base of the projectile and consequently the amount which 5. issues from the front end of the tube after the projectile.
An example of a launching assembly in accordance with the invention will now be described with reference to the accom-panying drawings, in which:- ~
Figure 1 is an elevation of a rigid unit which forms 10. part of the launching assembly and which consists of the projectile connected to the braking propellant; and Figure 2 is a 3ongitudinal section through the launching assembly, showing the unit of Figure 1 loaded in a launch tube.
15. ' 'Figure 2 shows a conventional launching tube 10, which-' ' may have a smooth or rifled bore,'and in which is placed a projectile 12-to be launched. A charge of gunpowder~l4 ' ' is located behind the projectile l2, and behind this pow~der_is arranged a braking propellant 16. The braking propellant 20. 16 contains blocks of powder, which are not shown, and ; carries''a ballast'mat~Jr'iaI. ~In th~s example,' ! ~ ~
the br~king propellant 16 carries ballast 18 formed by grain~s of sand retained in an envelope 20. These grains of sand' will~exhibit the characteristic of being braked rapidly in 25. ' air whilst having a terminal veloclty of fall, given by , . , : , .
106340~
- Stokes' formula, greaterthan the particles contained in the smoke emitted during the discharge of the projectile.
They are therefore less visible and for a shorter time than this smoke.
.- 5. As shown in.. Figure 1 the braking propellant 16 is ; connected to the projectile 12 by a slee~e 22, the gunpowder 14 provided for propelling the projectile being contained within the sleeve 22. The assembly represented in Figure 1 consisting of the projectile 12, the gunpowder 14, and the 10. braking propellant 16 w1th its. bal-las~.:
18, constitutes a rlgid loadable unit.
The cylindrical sleeve 22 which connects the braking propellant 16 and the projectile 12 contains a series of - apertures 36, which may be drilled, and which are opened . 15. -progressivély as the braking propellant leaves the tube, thus enabling the expansion of the gases from the gunpowder to be spaced slightly.
.~ .
Behind the braking propellant 16 a sealing diaphragm 26 is provided, which at the same time serves to retain the 20. . ballast be~ore ignition of the braking propellant~
In this example an electrical ignition system 30 for : the gunpowder 14 is shown passing through the nozzle of the braking propellant 16, and operation of the launching assembly . is. as follows: At the instant.of firing, the gunpowder 14 is 25. ignited by the firing system 30, and the pressure of the .. . . ... ., . , .. ~ .. , ~ ,.. -,; .... . . .
-10634~1 resulting gases unlocks the projectile from the sleeve 22 of the propellant 16.
The projectile of mass Ml acquires a velocity Vl at a given instant, and the ballasted propellant of total mass 5. M2 acquires a velocity V2. Neglecting for a first approximation the thrust of the braking propellant, which is going to be ignited by the gases from the gunpowder passing through a gauged orifice 24 provided for this purpose, one can write:
Ml Vl = M2 V2 10. The centre of gravity of the two masses remains fixed.
-I-f, for example, M2 = 2Ml~ one has at every instant:
V2 = V
and the distances covered are in the same ratio.
If the projectile 12 carries a cruising propellant 15. it may be ignited by letting the gases from the ignited gunpowde~ penetrate through the nozzle of the propellant, via a gauged orifice limiting the pressure. It has been -mentioned above that the braking propellant is intended to ~ be ignited in a similar way~ the dimensions-of the gauged~
20. hole 24, ~r holes9 provided for this purpose being a function of the v~lume to be filled and of the delay required for the ignition.
Ignition of the braking propellant 16 provides a braking thrust P, which may be taken into account in analysing -r 25~ t~e motions, by writing that the centre-of gra~ity of (Ml-+ M2) ,: , ~ 106~4(~1 undergoes an acceleration of:
.~ _P
.- Ml + M2 This acceleration will, in general, be negligible compared - with that obtained by the gun effect.
The length of the launch tube 10, and the masses and arrangement in the tube of the projectile 12, the gunpowder 14, the braking propellant 16 and ballast 18, is such that the tube is open first towards the rear, that is to say, the braking propellant 16 leaves the tube before the projectile. In this case, the larger amount of gas is dis-charged from the rear of the tube, It is desirable that the ~` projectile 12 leaves the tube 10 only when the expansion wave has reached it, in order to limit the pressure of the gas on the base of the projectile and hence reduce to a minimum the amount of gas discharged from the front of the tube after the projectile.
It can be shown that the thrust P from the braking propellant 16 may be such that it is braked over a distance of the order of 2 to 4 metres.
The total amount of powder consumed and hence the smoke and flame produced are most certainly a little greater with a launching assembly in accordance with the invention than those produced by a gun giving the same velocity to the ~; projectile, but are much less than those brought into play using a conventional acceleration propellant or recoilless gun.
~j'l .
Z ~
~-"~
' ~, - . . . . -., ' , ,, '.' . -- ' ~, ' -' -~0~4(;~1 In this prefered embodiment of the invention the connec-tion between the projectile and the sleeve 22 of the braking propellant is provided with means which causes an angular acceleration dtW to be given to the projectile when the 5. projectile is fired. It goes without saying that after separàtion of the projectile from the launching system shown - in Figure 2:
Ilwl + I2w2 = O
Il, I2, wl, w2 being the moments of inertia and the angular 10. velocities of the projectile and the launching system.
In the embodiment shown, the sleeve 22 has for this purpose one or more grooves 32, which e~tend obliquely with - respect to the axis of the tube 10, and in which engage one or more studs 34 provided at the rear of the projectile. When 15. the projectile is fired, the displacement of the studs-in the grooves as the projectile separates from the sleeve sets the projectile 12 in rotation.
It should remain clearly understood that this invention is not restricted to the embodiment just described and illu-~- 20. strated, but that it encompasses many variations~within the : scope of the claims. For example, while the presence of a sleeve 22 connecting the projectile to the braking propellant 16 is a feature of one advantageous embodiment of the invention, it may not be present in another embodiment. In this case, 25. the projectile 12, and if necessary the braking propellant 16 . .
: . - .: . . . ~
.. .. . - . : . .. -- . - .
~06340~
may be furnished with at least one groove in the outer wall extending obliquely with respect to the longitudinal axis.
These grooves are arranged to receive lugs or studs integral with the inner wall of the launching tube 10. Such an 5. arrangement enables the projectile 12 and the braking propellant 16 to be set in rotation with opposite angular velocities (the slope of the grooves on the projectile and .
on the braking propellant with respect to the longitudinal axis being in opposite directions for each of these elements) 10. whilst minimizing the reactions upon the tube 10. This is particularly advantageous for launch tubes of small calibre.
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- - . - - - ... .. ..... . . . . . ..
.. . -.. . . .. .
.
.
.
Claims (18)
1. A projectile launching assembly including a launch tube, a charge of gunpowder located in said launch tube for communication therewith upon ignition and for firing from said tube a projectile which is placed in said tube in front of said gunpowder charge, means permitting, upon firing, the application of pressure of gases from said gunpowder charge against the rear of the projectile and the inner wall of the launch tube, a braking propellant slidably loca-ted in said launch tube behind said gunpowder charge, a ballast material carried by said braking propellant, and means for sequential ignition of said gunpowder charge followed by ignition of said brak-ing propellant to cause the projectile to leave the front end of the launch tube and the braking propellant to leave the rear end of the tube.
2. An assembly as claimed in claim 1, wherein said launch tube has a smooth bore.
3. An assembly as claimed in claim 1, wherein said launch tube has a rifled bore.
4. An assembly as claimed in claim 1, wherein said ballast material is in powdery form whereby said material is braked rapidly in air.
5. An assembly as claimed in claim 4, wherein said ballast material is sand.
6. An assembly as claimed in claim 1, wherein said ballast material is in liquid form whereby said material is braked rapidly in air.
7. An assembly as claimed in claim 1, further including means separating said gunpowder charge from said braking propellant and defining at least one gauged hole whereby, in operation, said braking propellant is ignited by gases from the ignited gunpowder charge.
8. An assembly as claimed in claim 1, for launching a projectile provided with a cruising propellant, said assembly including means defining a gauged orifice through which ignition of said cruising propellant is effected by gases from the ignited gunpowder charge.
9. An assembly as claimed in claim 1, wherein the length of said launch tube and the locations of said projectile, said gunpowder charge, and said braking propellant in said launch tube are such that, after firing said braking propellant leaves the rear end of said launch tube before said projectile leaves the front end of said tube, thereby causing the pressure of gases acting on the base of said projectile to be limited.
10. An assembly as claimed in claim 1, further including said projectile and a cylindrical sleeve connecting said braking propellant to said projectile to form a rigid unit which is loadable as a unit into said launch tube, said gunpowder charge being contained within said cylindrical sleeve.
11. An assembly as claimed in claim 10, further including a sealing diaphragm behind said braking propellant, said sealing diaphragm being designed to break and release said ballast material when said ballast material undergoes a negative acceleration following ignition of said braking propellant.
12. An assembly as claimed in claim 10, wherein said cylindrical sleeve connecting said projectile and said braking propellant is provided with means defining a series of apertures whereby, after firing, said apertures are cleared progressively as said braking propellant leaves said launch tube, thereby enabling the expansion of the gases from said gunpowder charge to be spread out.
13. An assembly as claimed in claim 10, wherein said cylind-rical sleeve and said projectile are provided with co-operating means for causing an angular acceleration to be given to said projectile when said projectile is fired.
14. An assembly as claimed in claim 13, wherein said co-operating means comprises means defining at least one groove in said cylindrical sleeve extending obliquely with respect to the axis of said launch tube, and a stud on said projectile which engages in said groove.
15. An assembly as claimed in claim 1, wherein the bore of said launch tube is provided with means for causing a pro-jectile to be given an angular acceleration when said pro-jectile is fired.
16. An assembly as claimed in claim 15, wherein said means for causing angular acceleration of said projectile comprises at least one stud integral with said bore and projecting inwards for engagement in a peripheral groove in said pro-jectile which extends obliquely to the axis of said projectile.
17. An assembly as claimed in claim 15, including means for causing said braking propellant to be given an angular acceleration of opposite sense to said projectile when said projectile is fired.
18. An assembly as claim 17, wherein said means for causing angular acceleration of said braking propellant comprises at least one stud integral with said bore of said launch tube, and means defining a peripheral groove in said braking propellant extending obliquely to the axis of said launch tube, said stud engaging in said peripheral groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA251,687A CA1063401A (en) | 1976-05-03 | 1976-05-03 | Apparatus for launching a missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CA251,687A CA1063401A (en) | 1976-05-03 | 1976-05-03 | Apparatus for launching a missile |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1063401A true CA1063401A (en) | 1979-10-02 |
Family
ID=4105855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA251,687A Expired CA1063401A (en) | 1976-05-03 | 1976-05-03 | Apparatus for launching a missile |
Country Status (1)
| Country | Link |
|---|---|
| CA (1) | CA1063401A (en) |
-
1976
- 1976-05-03 CA CA251,687A patent/CA1063401A/en not_active Expired
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