NO132561B - - Google Patents
Download PDFInfo
- Publication number
- NO132561B NO132561B NO80973A NO80973A NO132561B NO 132561 B NO132561 B NO 132561B NO 80973 A NO80973 A NO 80973A NO 80973 A NO80973 A NO 80973A NO 132561 B NO132561 B NO 132561B
- Authority
- NO
- Norway
- Prior art keywords
- ignition system
- pressure
- membrane
- circuit
- rocket
- Prior art date
Links
- 239000012528 membrane Substances 0.000 claims description 9
- 239000002360 explosive Substances 0.000 claims description 6
- 210000000056 organ Anatomy 0.000 claims description 3
- 230000000977 initiatory effect Effects 0.000 claims description 2
- 238000005474 detonation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000002775 capsule Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
- F42C15/40—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C11/00—Electric fuzes
- F42C11/02—Electric fuzes with piezo-crystal
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Measuring Fluid Pressure (AREA)
- Catching Or Destruction (AREA)
Description
Den foreliggende oppfinnelse angår en anordning ved rakett eller med rakettmotor forsynt prosjektil som bærer en sprengladning og har et elektrisk, fortrinnsvis piezoelektrisk tenningssystem. The present invention relates to a device for a rocket or a projectile equipped with a rocket engine which carries an explosive charge and has an electric, preferably piezoelectric, ignition system.
Ifølge oppfinnelsen er der i rakettmotoren anbragt et trykk-følende organ som er innrettet til ved et unormalt høyt gasstrykk å bevirke en slik omkobling av det elektriske tenningssystems strømkrets at initiering av sprengladningen forhindres. Det trykkfølende organ består hensiktsmessig av en membran som er innrettet til å kortslutte eller bryte det elektriske tenningssystems strømkrets. According to the invention, a pressure-sensing organ is placed in the rocket engine which is designed to cause, in the event of an abnormally high gas pressure, such a switching of the electric ignition system's circuit that initiation of the explosive charge is prevented. The pressure-sensing member conveniently consists of a membrane which is arranged to short-circuit or break the electric ignition system's current circuit.
Hensikten med anordningen ifølge oppfinnelsen er å skaffe The purpose of the device according to the invention is to provide
en banesikring for tilfellet av at der skjer en kraftig trykkstigning i rakettmotoren. En slik trykkstigning kan forårsake materialbrudd eller deformasjoner i rakettmotorkapselen eller i andre nærliggende komponenter. Disse brudd eller deformasjoner gir opphav til støtbølger som forplanter seg gjennom rakettens eller prosjektilets forskjellige deler med lydhastigheten i vedkommende materialer. Når disse støtbølger når frem til den piezoelektriske giver, kan denne frembringe en så høy elektrisk spenning at sprengladningen blir initiert. Dermed inntrer detonasjon i banen. Ved hjelp av anordningen ifølge oppfinnelsen elimineres risikoen for en slik detonasjon. a trajectory safeguard in the event of a strong increase in pressure in the rocket engine. Such an increase in pressure can cause material breakage or deformations in the rocket motor capsule or in other nearby components. These breaks or deformations give rise to shock waves that propagate through the various parts of the rocket or projectile at the speed of sound in the materials concerned. When these shock waves reach the piezoelectric sensor, this can produce such a high electrical voltage that the explosive charge is initiated. Thus, detonation occurs in the orbit. By means of the device according to the invention, the risk of such a detonation is eliminated.
Anordningen ifølge oppfinnelsen vil bli beskrevet nærmere The device according to the invention will be described in more detail
i det følgende under henvisning til tegningen, hvis figurer 1 hereinafter with reference to the drawing, whose figures 1
og 2 er koblingsskjemaer for hver sin utførelsesform for anordningen. and 2 are connection diagrams for each embodiment of the device.
På begge figurer betegner G en piezoelektrisk giver som er anbragt i spissen av raketten eller prosjektilet. Mellom ledningene fra giveren er der innkoblet en shuntmotstand R til av-ledning av støystrømmer. Mellom ledningene fra giveren er der på fig.. 1 innkoblet en elektrisk tenner T for sprengladningen i den ene stilling av en omkobler 0. I dennes annen stilling bevirker omkobleren kortslutning av ledningene. Omkobleren gjør således tjeneste som armeringsorgan. I rakettmotoren, nærmere bestemt hensiktsmessig i veggen av gasskanalen til dysen, er der anbragt et trykkfølende organ i form av en membran M. Membranen består i dette tilfelle av to sjikt, et ytre sjikt som vender mot gasstrykksiden og er utført av varmefast materiale, og et elektrisk ledende indre sjikt. Ved unormalt høyt trykk p i rakettmotoren. fås en blivende utbøyning av. den ettergivende membran til den. stiplet inntegnede stilling,, hvorved der inntrer kortslutning av ledningene. Kontakten K, som membranen kan bringes til anlegg mot, er hensiktsmessig belastet med en fjær. I utførelsen på fig. 2 er et kontaktorgan som påvirkes av membranen, koblét i serie mellom tenneren og omkobleren i dennes armeringsstilling. Ved utbøyning av membranen til den stiplet inntegnede stilling fås et brudd på strømkretsen gjennom tenneren. In both figures, G denotes a piezoelectric transducer which is placed at the tip of the rocket or projectile. A shunt resistor R is connected between the wires from the sensor to remove noise currents. Between the wires from the transmitter, in fig. 1, an electric igniter T for the explosive charge is connected in one position of a switch 0. In its other position, the switch short-circuits the wires. The switch thus serves as an arming device. In the rocket engine, more specifically appropriately in the wall of the gas channel to the nozzle, there is a pressure-sensing organ in the form of a membrane M. The membrane in this case consists of two layers, an outer layer that faces the gas pressure side and is made of heat-resistant material, and an electrically conductive inner layer. In case of abnormally high pressure p in the rocket engine. a permanent deflection of is obtained. the compliant membrane to it. dotted recorded position, whereby a short circuit of the wires occurs. The contact K, against which the membrane can be brought into contact, is suitably loaded with a spring. In the embodiment in fig. 2 is a contact member which is affected by the membrane, connected in series between the igniter and the switch in its arming position. When the membrane is deflected to the dashed position, a break in the current circuit through the igniter occurs.
Claims (3)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE270872A SE374198B (en) | 1972-03-03 | 1972-03-03 |
Publications (2)
Publication Number | Publication Date |
---|---|
NO132561B true NO132561B (en) | 1975-08-18 |
NO132561C NO132561C (en) | 1975-11-26 |
Family
ID=20260508
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
NO80973A NO132561C (en) | 1972-03-03 | 1973-02-28 |
Country Status (10)
Country | Link |
---|---|
JP (1) | JPS4912699A (en) |
BE (1) | BE796200A (en) |
CH (1) | CH569950A5 (en) |
DE (1) | DE2310549A1 (en) |
FR (1) | FR2174901B1 (en) |
GB (1) | GB1361168A (en) |
IT (1) | IT979701B (en) |
NL (1) | NL7303011A (en) |
NO (1) | NO132561C (en) |
SE (1) | SE374198B (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SE446860B (en) * | 1978-08-08 | 1986-10-13 | Nitro Nobel Ab | LAGENERGISTUBIN CONSISTS OF A PLASTIC HOSE WHICH HAVE BEEN COVERED WITH POWDER FORM |
US4290366A (en) * | 1979-07-16 | 1981-09-22 | Atlas Powder Company | Energy transmission device |
DE3345352A1 (en) * | 1983-12-15 | 1985-06-27 | Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt | Sensor of a safety arming device in missiles |
US9207054B2 (en) * | 2012-05-25 | 2015-12-08 | Bae Systems Land & Armaments L.P. | Solid state ignition safety device |
CN109654959A (en) * | 2018-11-13 | 2019-04-19 | 重庆长安工业(集团)有限责任公司 | Electronic security(ELSEC) insurance circuit for people's rain rocket projectile |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2721913A (en) * | 1950-07-17 | 1955-10-25 | Jr Raymond C Kent | Shock and static pressure discriminating switch |
US3198118A (en) * | 1960-12-06 | 1965-08-03 | Honeywell Inc | Arming circuit with pressure responsive discharge switch |
US3173252A (en) * | 1962-03-23 | 1965-03-16 | Lelan D Ziegenhagen | Restartable rocket motor |
US3136872A (en) * | 1962-07-23 | 1964-06-09 | Lloyd J Banaszak | Gas operated ignition switch for a multi-stage rocket propelled missile |
US3343489A (en) * | 1967-02-14 | 1967-09-26 | Howard G Whitehouse | Safety for pressure armed rocket fuze |
US3450046A (en) * | 1967-10-27 | 1969-06-17 | Us Army | Firing pressure activation system for fuzes and components |
DE2003466A1 (en) * | 1970-01-27 | 1971-08-05 | Diehl Fa | Release device and circuit arrangement for rocket detonators |
-
1972
- 1972-03-03 SE SE270872A patent/SE374198B/xx unknown
-
1973
- 1973-02-28 NO NO80973A patent/NO132561C/no unknown
- 1973-03-01 FR FR7307384A patent/FR2174901B1/fr not_active Expired
- 1973-03-01 CH CH298673A patent/CH569950A5/xx not_active IP Right Cessation
- 1973-03-02 IT IT4857073A patent/IT979701B/en active
- 1973-03-02 GB GB1025073A patent/GB1361168A/en not_active Expired
- 1973-03-02 BE BE128305A patent/BE796200A/en unknown
- 1973-03-02 DE DE19732310549 patent/DE2310549A1/en not_active Withdrawn
- 1973-03-02 NL NL7303011A patent/NL7303011A/xx not_active Application Discontinuation
- 1973-03-03 JP JP2560473A patent/JPS4912699A/ja active Pending
Also Published As
Publication number | Publication date |
---|---|
FR2174901B1 (en) | 1976-09-10 |
NL7303011A (en) | 1973-09-06 |
NO132561C (en) | 1975-11-26 |
GB1361168A (en) | 1974-07-24 |
SE374198B (en) | 1975-02-24 |
DE2310549A1 (en) | 1973-09-06 |
CH569950A5 (en) | 1975-11-28 |
JPS4912699A (en) | 1974-02-04 |
BE796200A (en) | 1973-07-02 |
IT979701B (en) | 1974-09-30 |
FR2174901A1 (en) | 1973-10-19 |
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