公开(公告)号：US20150241185A1

公开(公告)日：2015-08-27

申请号：US13929313

申请日：2013-06-27

Applicant: Exquadrum, Inc.

Inventor： Robert L. GEISLER ,  Kevin E. MAHAFFY

IPC: F42B12/44

CPC classification number: F42B12/44 ,  F42B12/52 ,  F42B12/58

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

Abstract translation: 提供了一种动力火球燃烧弹药，具有外壳或炸弹外壳，其中包括一个或多个燃烧弹药，因此也提供点火器。 每个子弹药包括燃烧部分，至少一个将目标体积内的子弹药推进的火箭发动机，以及用于燃烧部分和火箭发动机的氧化剂。 子弹药释放足够的热量以在目标结构内产生升高的温度，以使其内容物热化，而不产生显着的超压或爆炸效应。

公开(公告)号：US20160054108A1

公开(公告)日：2016-02-25

申请号：US14828918

申请日：2015-08-18

Applicant: Exquadrum, Inc.

Inventor： Robert L. GEISLER ,  Kevin E. MAHAFFY

IPC: F42B12/44

CPC classification number: F42B12/44 ,  F42B12/52 ,  F42B12/58

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

公开(公告)号：US20160032867A1

公开(公告)日：2016-02-04

申请号：US14212974

申请日：2014-03-14

Applicant: Exquadrum, Inc.

Inventor： Kevin E. MAHAFFY ,  Byron HENNING ,  Korey Robert KLINE ,  Philip PELFREY ,  Eric Schmidt ,  Elias Wilson

IPC: F02K9/24 ,  F02K9/97 ,  F02K9/52 ,  F02K9/34

CPC classification number: F02K9/52 ,  F02K9/34 ,  F02K9/72 ,  F02K9/97

Abstract: A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.

Abstract translation: 描述了一种混合火箭发动机，其通过具有富燃料气体发生器气体的核心流动来实现稳定，高效的混合燃烧，其中气流被环形注入的氧化剂包围。 富含燃料的气体用于蒸发和分解氧化剂，例如一氧化二氮，并将其制备用于有效，稳定的燃烧。 在一个实施例中，这在燃烧室的前端进行。 然后可以通过喷嘴将燃烧产物膨胀以产生推力。 发动机可以是上级发动机，其可以包括模块化推力室和集成的空气喷嘴。 推力室可以排列成环状空气喷嘴的顶部的阵列。