EP0413670A1 - Method for separating warheads - Google Patents
Method for separating warheads Download PDFInfo
- Publication number
- EP0413670A1 EP0413670A1 EP90850280A EP90850280A EP0413670A1 EP 0413670 A1 EP0413670 A1 EP 0413670A1 EP 90850280 A EP90850280 A EP 90850280A EP 90850280 A EP90850280 A EP 90850280A EP 0413670 A1 EP0413670 A1 EP 0413670A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- missile
- actuation part
- actuation
- separating
- remaining
- 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.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000000926 separation method Methods 0.000 claims abstract description 14
- 238000005096 rolling process Methods 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
Definitions
- the present invention relates to a method and arrangement for separating an actuation part from a non-spin-stabilized missile, for example a winged shell or the like.
- the actuation part When an actuation part is to be separated from a non-spin-stabilized missile, for example a winged shell, the actuation part will be positioned to the side of the trajectory of the missile so as not to collide with other missile parts.
- This separation can be carried out in several ways.
- one known method involves the actuation part being positioned to the side of the trajectory by means of a band being secured via a receiving element on the front part and pulled round behind the actuation part and attached to the front edge of the rear part of the missile.
- the actuation part is lifted by the steel band out of the rear part and, in the final stage when the band is stretched, acquires a velocity perpendicular to the direction of flight.
- the disadvantage of this method is that the actuation part is not positioned to the side of the missile trajectory in a controlled manner.
- Another known method for smoke shells is to have the actuation part and the rear part of the missile constitute one unit. Following an impulse from a rocket motor, which turns the missile, the front body is separated from the rear part of the missile, after which a parachute is released from the separation section of the rear part and lands the actuation part at a suitable, low velocity.
- the disadvantage of the above method is that it requires a special rocket motor for turning the missile, and the construction is difficult to apply to illuminating shells.
- the aim of the present invention is to provide a separation method and arrangement for an actuation part in non-spin-stabilized missiles which in a simple manner positions the actuation part to the side of the trajectory of the missile.
- Figure 1 shows a missile 1 commencing a separation procedure in the top right-hand corner of the figure.
- the missile can be, for example, a winged shell which has been fired from a shell thrower in a conventional manner in a stable ballistic trajectory, that is to say the centre of gravity of the missile lies with an adequate margin in front of the common point of impact of the air forces, the centre of pressure, so that the shell seeks to fly with its longitudinal axis in the direction of the trajectory tangent.
- the actuation part can be a lighting unit for illuminating the target area.
- the separation procedure begins when the front part 2 of the missile is caused to separate from the rest of the missile, consisting of the actuation part 3 and the rear part 4 of the missile, for example by means of an internal overpressure from a pyrotechnic charge.
- the actuation part and the rear part of the missile become unstable and roll round. If the centre of gravity of the actuation part lies in front of the centre of rotation, the actuation part 3 is slung off from the rear part 4 of the missile by the centrifugal force and ends up to the side of the missile trajectory.
- a body If a body is exposed to an impinging medium, in this case air, it is subject to external forces.
- the rolling of the actuation part and of the rear part of the missile can be achieved or reinforced by means of a special design of the actuation part.
- the asymmetrical front ends of the actuation part as described also acquire an impulse, cooperating with the air forces, from the internal gas pressure separating the missile, if such is used.
- the impulse arises at the moment when the separation of the front body is completed and it is emptied of the separating gases.
- a pyrotechnic charge or rocket motor 7 can also be used, which gives an impulse directed transverse to the trajectory, see Figure 4.
- the above description of the invention is based on the assumption that the front part of the missile is first removed and the actuation part thereafter separates from the rear part of the missile during rolling.
- the separation method is equally applicable when the rear part of the missile is the first part to be separated.
- the arrangements above can also be designed so that they are adapted to this case.
- the advantages of the invention are its simple construction and its use of the impinging of the air and, if appropriate, the impulse from the gases separating the missile, or a simple pyrotechnic charge, for tipping the actuation part and rear body and thereby initiating a separation by means of the effect of the centrifugal forces.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Automatic Assembly (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE8902755 | 1989-08-17 | ||
SE8902755A SE468367B (sv) | 1989-08-17 | 1989-08-17 | Separeringssaett foer verkansdelar |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0413670A1 true EP0413670A1 (en) | 1991-02-20 |
Family
ID=20376681
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP90850280A Withdrawn EP0413670A1 (en) | 1989-08-17 | 1990-08-15 | Method for separating warheads |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0413670A1 (sv) |
SE (1) | SE468367B (sv) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19518312C1 (de) * | 1995-05-18 | 1996-10-24 | Daimler Benz Aerospace Ag | Antriebsloser Flugkörper |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2654320A (en) * | 1949-03-07 | 1953-10-06 | Roy J Schmid | Severable aircraft |
LU56243A1 (sv) * | 1967-06-13 | 1968-09-23 | ||
US3534686A (en) * | 1968-10-04 | 1970-10-20 | Nasa | Payload/burned-out motor case separation system |
FR2189703A1 (sv) * | 1972-06-22 | 1974-01-25 | State Of Israel Ministry Defen |
-
1989
- 1989-08-17 SE SE8902755A patent/SE468367B/sv not_active IP Right Cessation
-
1990
- 1990-08-15 EP EP90850280A patent/EP0413670A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2654320A (en) * | 1949-03-07 | 1953-10-06 | Roy J Schmid | Severable aircraft |
LU56243A1 (sv) * | 1967-06-13 | 1968-09-23 | ||
US3534686A (en) * | 1968-10-04 | 1970-10-20 | Nasa | Payload/burned-out motor case separation system |
FR2189703A1 (sv) * | 1972-06-22 | 1974-01-25 | State Of Israel Ministry Defen |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19518312C1 (de) * | 1995-05-18 | 1996-10-24 | Daimler Benz Aerospace Ag | Antriebsloser Flugkörper |
Also Published As
Publication number | Publication date |
---|---|
SE8902755D0 (sv) | 1989-08-17 |
SE8902755L (sv) | 1991-02-18 |
SE468367B (sv) | 1992-12-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4674706A (en) | Projectile with an extendable boattail | |
EP0255214B1 (en) | Multiple flechette warhead | |
US6748871B2 (en) | Guided artillery missile with extremely long range | |
US2470120A (en) | Method of bombing from fast moving planes | |
US4565341A (en) | Inflatable decelerator | |
KR100796706B1 (ko) | 교환 가능한 페이로드를 포함하는 포 발사체 | |
US4384528A (en) | Duplex round | |
JPH05501448A (ja) | ミサイルの横方向スラスト集合体 | |
US5196650A (en) | Projectile and sabot assembly | |
EP0694156B1 (en) | A method and an apparatus for spreading warheads | |
US3635404A (en) | Spin stabilizing rocket nozzle | |
US4337911A (en) | Non-spinning projectile | |
EP0793798A1 (en) | Method and device for using warheads released from a launching vehicle to combat targets identified along the flight path of the launching vehicle | |
EP0413670A1 (en) | Method for separating warheads | |
US6657174B1 (en) | Method and design for increasing the firing range of artillery shells | |
US5159151A (en) | Missile nose fairing assembly | |
US2939395A (en) | Sabot for high velocity projectile | |
US3434417A (en) | Bomb braking system | |
JPS63172900A (ja) | スピン安定化した送弾子発射体 | |
DE3722038C2 (sv) | ||
US4283988A (en) | Tail carriage of stores | |
EP0228479B1 (en) | Inflatable decelerator | |
US4221230A (en) | Variable air inlet for a ramjet powered missile | |
CA1231861A (en) | Inflatable decelerator | |
JPH0694400A (ja) | 防御弾 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT DE FR GB |
|
17P | Request for examination filed |
Effective date: 19910710 |
|
17Q | First examination report despatched |
Effective date: 19911009 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN |
|
18W | Application withdrawn |
Withdrawal date: 19930814 |