专利检索_ ..伞投照明弹专利检索_ ..伞投照明弹专利检索查询

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
1	Infrared decoy flare missile	JP35709699	1999-12-16	JP2001174196A	2001-06-29	KOYAMA IKUO; SUZUKI YOSHIMASA
PROBLEM TO BE SOLVED: To provide a decoy for enabling an armored vehicle and the like to avid an infrared foaming missile launched from an aircraft such as a helicopter and the like. SOLUTION: The decoy includes an infrared radiation cloth having a floatable shape in the air, a heat source equipped with firing and heating agents, and discharging means equipped with a propellant, delaying and ejecting agents for propelling the missile as high as a predetermined height and ejecting the infrared radiation cloth, respectively, so that the infrared radiation cloth discharged by the ejecting means after the missile reaches the predetermined height comes down while radiating infrared rays by continuously rotammg burning flame of the heating agent for a period of time. COPYRIGHT: (C)2001,JPO
2	照明組成物、当該照明組成物を含む照明弾および関連する方法	JP2015054336	2015-03-18	JP2015178450A	2015-10-08	ダニエル・ビー・ニールソン; ロイス・シー・デューク; カーティス・ダブリュー・フィールディング
【課題】従来の近赤外線(NIR)放射照明組成物を用いる場合に遭遇する望ましくない性質(例えば、低いNIRの発生、過剰な可視光の発生、低い燃焼速度、不均一な燃焼など)のうちの少なくとも一つを軽減し、その際に、そのような照明組成物の他の望ましくない性質のうちの少なくとも一つのものを著しく低下させることのない照明組成物の提供。【解決手段】少なくとも一つの酸化剤、燃料と結合剤のうちの少なくとも一つ、及び少なくとも一つの燃焼速度調節剤を含む照明組成物。少なくとも一つの酸化剤はカリウム含有酸化剤とルビジウム含有酸化剤から選択され、少なくとも一つの酸化剤は照明組成物の中に約50〜約70wt%までの量で存在し、そしてそれぞれが独立して約25〜約325μmまでの範囲内の大きさを有する粒子を含む。追加の照明組成物、照明弾、及び標的を照らす方法。【選択図】なし
3	Infrared Dekoifurea flying object	JP35709699	1999-12-16	JP4276348B2	2009-06-10	郁雄小山; 慶正鈴木

4	Device for pyrotechnical explosive, descending speed thereof is decreased	JP977987	1987-01-19	JPS62194199A	1987-08-26	KUROODO MORE

5	JPS523520B1 -	JP5759372	1972-06-09	JPS523520B1	1977-01-28

6	JPS5011200B1 -	JP3899071	1971-06-03	JPS5011200B1	1975-04-28

7	화재 위험으로부터 안전한 조명탄	KR2020150002989	2015-05-11	KR2020160002295U	2016-07-01	이한주
본발명은화재위험으로부터안전한조명탄에관한것으로서, 특히탄피와, 조명체와, 신관및 낙하산을포함하는조명탄에있어서, 상기낙하산은투명방염재질로저면에입구가형성된유선형으로형성되어상기조명체에서발생되는열기에의해상기조명체를일정고도로유지시키도록풍등형낙하산이다. 상기와같은본 발명에따르면풍등형낙하산을조명탄에설치하여조명체에서발생하는열기에의해풍등형낙하산이일정고도를유지하도록함으로써화재위험을미연에방지할수 있다.
8	무지향성 폭발형 고섬광 발생장치	KR1020120041348	2012-04-20	KR1020130118471A	2013-10-30	김동우; 권미라; 방기복; 김성식; 함왕식
PURPOSE: A non-directional explosion type bright flash device is provided to damage electronic devices of enemies by irradiating strong flash of a visible ray area, an infrared light area, and a ultra-violet area through an air bag of a light penetration type. CONSTITUTION: A non-directional explosion type bright flash device comprises an air bag (10), front and rear gunpowder holder fixing plates (13,14), an initiating pipe (15), a gas tank (17), a gunpowder stopper (18), and a control unit (20). The gas tank is installed on the outer side of the front gunpowder holder fixing plate and supplies inert gas through an inlet port with the air bag. The gas tank includes an opening and closing valve (17'). The gunpowder stopper prevents gunpowder from being shaken in a gunpowder holder (12). The control unit controls the opening and closing valve of the gas tank and the initiating pipe.
9	RETENTION CLIPS FOR SAFETY MECHANISMS OF ILLUMINATION FLARES, SAFETY MECHANISMS AND ILLUMINATION FLARES SO EQUIPPED, AND RELATED METHODS	US14857207	2015-09-17	US20170082408A1	2017-03-23	Mark A. Thompson; Steven M. Robbins; Michael Geslin
Retention clips for safety mechanisms of illumination flares include an abutment surface configured for abutment of an end of a rigid sleeve coupled to an igniter initiation cable and one or more protrusions configured to extend at least partially over a lateral side surface of the rigid sleeve when the rigid sleeve is retained by the clip. Safety mechanisms, illumination flares, and methods for igniting illumination flares involve such retention clips.
10	Method of generating and displaying a flare drift vector symbol	US14497621	2014-09-26	US09569973B2	2017-02-14	Douglas J. Eaton, Jr.; Scott T. Dubeck
The present disclosure is generally directed to a method of generating and displaying a parachute flare drift vector symbol on a navigation display of the aircraft capable of deploying a flare relative to a real-time navigation map. The flare drift vector symbol includes a flare ignition forward/aft distance relative to the aircraft deploying the flare, a flare ignition left/right distance relative to the aircraft deploying the flare, a flare burn vector distance, and a flare burn vector direction. The flare drift vector symbol is generating based on the flare parameters, the wind parameters, the flare drift distance, the flare drift direction and the aircraft parameters.
11	Method of Generating and Displaying A Flare Drift Vector Symbol	US14497621	2014-09-26	US20160117930A1	2016-04-28	Douglas J. Eaton, JR.; Scott T. Dubeck
The present disclosure is generally directed to a method of generating and displaying a parachute flare drift vector symbol on a navigation display of the aircraft capable of deploying a flare relative to a real-time navigation map. The flare drift vector symbol includes a flare ignition forward/aft distance relative to the aircraft deploying the flare, a flare ignition left/right distance relative to the aircraft deploying the flare, a flare burn vector distance, and a flare burn vector direction. The flare drift vector symbol is generating based on the flare parameters, the wind parameters, the flare drift distance, the flare drift direction and the aircraft parameters.
12	IGNITER SAFE AND ARM, IGNITER ASSEMBLY AND FLARE SO EQUIPPED AND METHOD OF PROVIDING A SAFETY FOR AN IGNITER ASSEMBLY	US11559867	2006-11-14	US20080110364A1	2008-05-15	Kevin W. Richards; Kendall Dye; Robert G. Jones
A parachute flare igniter assembly includes a novel safety for arresting the motion of a slider when subjected to external forces, but allows slider motion when subjected to intended cable actuation forces. The igniter safety includes a housing, a slider, a cable and a sleeve. The slider, connected to the cable, is slidably received within the housing. The cable moves the slider by applying a cable force conventionally obtained by actuation of a parachute associated with the flare and connected to an end of the cable opposite an end connected to the slider. The sleeve is connected to the cable and is disposed between the housing and the slider, so that the sleeve will arrest the slider with respect to the housing when the cable force is not present. A flare and a method of providing a safety in an igniter assembly is also provided.
13	Steerable parachute control system and method	US10315466	2002-12-09	US06889942B2	2005-05-10	Daniel Preston
An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. A predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the system's impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute. If the system reaches a position substantially above target area prior to the parachute transition altitude the flight computer controls the system into a spiral dive or other rapid altitude dropping maneuver until the transition altitude is reached. Once transitioned to the landing parachute the system descends for a brief period unguided under the landing parachute until touchdown.
14	Steerable parachute control system and method	US10315466	2002-12-09	US20030197095A1	2003-10-23	Daniel Preston
An autonomous guided parachute system for cargo drops that divides the requirements of guidance and soft landing into separate parachutes. Said invention includes a high wing-loaded ram air parachute for guidance, a larger round parachute for soft landing, a harness/container system, flight computer, position sensors and actuation system. The system is dropped from an airplane. a predetermined period of drogue fall ensures a stable position prior to deploying the guidance parachute. The flight controller determines a heading to intersect with an area substantially above the desired target and controls the guidance parachute via pneumatic actuators connected to the parachutes steering lines to fly on that heading. At a minimum altitude prior to the systems impact with the ground the flight computer transitions the system from the fast high performance guidance parachute to a larger landing parachute by releasing the guidance parachute to static line extract and deploy the landing parachute. If the system reaches a position substantially above target area prior to the parachute transition altitude the flight computer controls the system into a spiral dive or other rapid altitude dropping maneuver until the transition altitude is reached. Once transitioned to the landing parachute the system descends for a brief period unguided under the landing parachute until touchdown.
15	Directional flare	US727735	1976-09-29	US4082041A	1978-04-04	John S. Wilson
A directional flare system is disclosed. A flare is used which emits light generally isotropically when actuated. An opaque shield is located to one side of the flare to prevent the transmission of light from the flare throughout a preselected sector about a vertical axis passing through the flare. Means are provided for maintaining the opaque shield in a preferred angular orientation about the vertical axis.
16	Devisible pyrotechnic device	US3791299D	1972-07-31	US3791299A	1974-02-12	SIMMONS B
An illuminating body which is attachable to a parachute is divided into a number of partial flares which slant outward from the axis of the body at given angles by virtue of the fact that an elongated body of pyrotechnic material is divided into a number of axial sections which fan out from a common connection at one end.
17	Aircraft parachute flare having tapered core candle	US3747528D	1972-02-25	US3747528A	1973-07-24	HARKNESS B; HUMERICKHOUSE B; MATHEIS N; NORRIS A
An aircraft parachute flare having an outer case of consumable material filled with a candle of pyrotechnic material. The pyrotechnic candle is provided with a tapered core that provides a chamber for storing a parachute. An environmental fuze is provided for initiating parachute deployment and deployment of the parachute initiates an igniter which, in turn ignites the pyrotechnic candle.
18	Target marking device	US3745324D	1971-06-04	US3745324A	1973-07-10	SHEFLER S; DUFF H
A target marking device comprising a parachute or panel soaked in a chemiluminescent agent sealed inside a canister which upon rupture releases the canopy which falls to the target location where the agent reacts with oxygen in the air forming a glow visible from all quadrants, particularly at night.
19	Aerial flare with drogue parachute	US3719146D	1971-06-11	US3719146A	1973-03-06	THURSTON J
D R A W I N G A SPECIALLY DESIGNED DROGUE PARACHUTE IS ATTACHED TO THE HOUSING OF AN AERIAL FLARE TO INHIBIT SPINNING, WHICH OTHERWISEIMPAIRS FUNCTIONING OF TIMING MECHANISMS WHEN SUCH FLARES ARE DEPLOYED WITH EXTENSIVE FREE FALLS, AS FROM HIGH ALTITUDES. THE OPEN END OF THE SACK-LIKE PARACHUTE HAS A REINFORCING RING THAT ALSO FUNCTIONS ASA SPRING TO OPEN THE PARACHUTE WHENN IT IS DEPLOYED.
20	Castable illuminant flare composition and method for making flare body therewith	US3605624D	1969-02-10	US3605624A	1971-09-20	DINSDALE VERN THOMAS; REED RUSSELL JR; MEYER ROBERT E
A FLARE BODY FOR A PARACHUTE TYPE FLARE PROVIDING SUPERIOR BRILLIANCE AND SUSTAINED OUTPUT OF ILLUMINATION EVER AFTER 14 DAYS OF 24-HOUR TEMPERATURE CYCLING BETWEEN -65 AND 165*F. IS OBTAINED BY MEANS OF A NOVEL, CASTABLE ILLUMINANT FLARE COMPOSITION COMPRISING AN UNCURED, HIGH OXYGEN CONTENT LIQUID POLYMERIC BINDER MATERIAL, PARTICULARLY A LIQUID SATURATED POLYESTER POLYMER/ LIQUID EPOXY RESIN SYSTEM, WHICH IS LOADED INTO A FLARE BODY CASING LINED ON ITS INNER BOTTOM AND SIDE SURFACES WITH AT LEAST PARTIALLY CURED LINER MATERIAL COMPRISING THE BINDER MATERIAL AND FURTHER COMPRISING AN ANCHOR SHEET MATERIAL BONDED COMPLETELY ON ITS INNER SURFACE TO THE OUTER SURFACE OF THE LINER AND ON ITS OUTER SURFACE TO THE INNER CASING WALL ESSENTIALLY ONLY BY A RELATIVELY NARROW ANCHOR STRIP OF MATERIAL RUNNING FROM THE TOP TO THE BOTTOM OF THE CASING. THE LOADED CASING AND ITS CONTENTS THEN ARE HEATED TO CURE THE POLYMERIC BINDER MATERIAL IN THE COMPOSITION, LINER AND ANCHOR STRIP.

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