JPS6467600A - Guided missile - Google Patents

Guided missile

Info

Publication number
JPS6467600A
JPS6467600A JP22562687A JP22562687A JPS6467600A JP S6467600 A JPS6467600 A JP S6467600A JP 22562687 A JP22562687 A JP 22562687A JP 22562687 A JP22562687 A JP 22562687A JP S6467600 A JPS6467600 A JP S6467600A
Authority
JP
Japan
Prior art keywords
compound
fins
time
stabilizer
specified
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.)
Pending
Application number
JP22562687A
Other languages
Japanese (ja)
Inventor
Ichiji Nishimura
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Electric Corp
Original Assignee
Mitsubishi Electric Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Electric Corp filed Critical Mitsubishi Electric Corp
Priority to JP22562687A priority Critical patent/JPS6467600A/en
Publication of JPS6467600A publication Critical patent/JPS6467600A/en
Pending legal-status Critical Current

Links

Landscapes

  • Circuit Breakers (AREA)

Abstract

PURPOSE: To enhance motion performance and aerodynamic stability while preventing mechanical interference with a mother machine by incorporating stabilizer fins in the body of a guided projectile and developing the fins by resilient energy stored in a tensile spring with a specified time lag after launching through a locking unit comprising a powder of time prolonging compound and output compound and a gas cylinder. CONSTITUTION: Resilient energy stored in a tensile spring 8 acts to develop stabilizer fins 3 through an arm 10 and gears 12, 13 but it is blocked by a locking unit 7 and the fins 3 are retained in a contained state. When a body 1 is launched from an aircraft, an ignition plug 18 fires a time prolonging compound 19 based on an electric signal at the time of launching and the time prolonging compound 19 fires an output compound 20 upon elapsing a specified combustion time. A piston 15 enters into ascending motion at that moment by the pressure of a large quantity of combustion gas generated from the output compound 20 and it is drawn out by a hole 16 made in the stabilizer fin 3. Since the quantity of the time prolonging compound 19 is selected, the fins are developed with a specified time lag after a projectile is launched from a mother machine.
JP22562687A 1987-09-09 1987-09-09 Guided missile Pending JPS6467600A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP22562687A JPS6467600A (en) 1987-09-09 1987-09-09 Guided missile

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP22562687A JPS6467600A (en) 1987-09-09 1987-09-09 Guided missile

Publications (1)

Publication Number Publication Date
JPS6467600A true JPS6467600A (en) 1989-03-14

Family

ID=16832256

Family Applications (1)

Application Number Title Priority Date Filing Date
JP22562687A Pending JPS6467600A (en) 1987-09-09 1987-09-09 Guided missile

Country Status (1)

Country Link
JP (1) JPS6467600A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09159398A (en) * 1995-12-01 1997-06-20 Komatsu Ltd Wing unit for airframe

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09159398A (en) * 1995-12-01 1997-06-20 Komatsu Ltd Wing unit for airframe

Similar Documents

Publication Publication Date Title
GB1208669A (en) Improvements in or relating to rod penetrators for dispersal from missiles
ES297156Y (en) AMMUNITION, SUCH AS AN ARTILLERIA PROJECTILE, SUITABLE TO RECEIVE A DEVICE REDUCING ITS AERODYNAMIC RESISTANCE
GB1165802A (en) Improved Rifle Grenade
SE322442B (en)
US3750585A (en) Tracer projectiles
GB1465550A (en) Projectile launching device
JPS6467600A (en) Guided missile
JPS6467598A (en) Guided missile
US2263585A (en) Float light and smoke bomb
JPS6467599A (en) Guided missile
CN113494386B (en) Miniaturized multifunctional rocket engine
YU159889A (en) AMMUNITION WITH LAUNCH CUP AND ACTIVE BODY
GB929601A (en) Improvements in projectiles fitted with an electric detonator operated by a generator of the inertia type
GB520750A (en) Anti-aircraft projectile
GB927055A (en) Improvements in projectiles fitted with an electric generator of the inertia type
ATE8935T1 (en) PRACTICE AMMUNITION FOR HANDGUNS.
US2833216A (en) Jet-propelled missile
ES8705969A1 (en) Smoke-producing projectile.
JPS6457100A (en) Guided missile
GB940479A (en) Improvements relating to rocket devices
ES484133A1 (en) Rifle grenade
GB1108382A (en) Self-propelled projectile
RU16548U1 (en) ROCKET
JPS54100200A (en) Chaft bullet
FR2368686A1 (en) Smoke generating rifle grenade - has bullet trap formed by charge itself with hole slightly smaller than bullet