Did You Know...
...that while attempting to develop a super strong glue, 3M employee Spencer Silver accidentally developed a glue that was so weak it would barely hold two pieces of paper together? However, his colleague Art Fry needed the glue. Fry sang with his church choir and marked the pages of his hymnal with small scraps of paper that often fell out. He used Silver's glue to hold the papers in place. Today we call this invention Post-it Notes.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 7257939 | Sliding-action magneto-mechanical injector throttling device Sliding-Action Magneto-Mechanical Injector Throttling Device (SLAMMIT) provides on-demand, yet accurate, throttling of the mass flow of the fuel and/or oxidizer into the combustion chamber of a vortex injector. At least two SLAMMIT sub-assemblies comprise the SLAMMI... | 08/21/2007 |
| 7124574 | Method and apparatus for a substantially coaxial injector element A system to provide a two piece robust fluid injector. According to various embodiments, the fluid injector is a fuel injector for a combustion engine. The injector includes two coaxially formed annuluses. One annulus is formed in a face plate and the second annulus... | 10/24/2006 |
| 7067732 | Apparatus for utilizing waste heat from weapon propulsion system to produce vapor explosion The apparatus of the present invention uses waste heat generated by a weapon propulsion system to melt and ultimately superheat metal. Upon termination of the weapon mission, the apparatus explodes thereby causing molten and superheated metal to be instantly introdu... | 06/27/2006 |
| 7051659 | Projectile structure A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compress... | 05/30/2006 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6530213 | Method and apparatus for ignition detection The present invention is directed to methods and apparatus of detecting engine ignition. The invention generally includes a camera assembly to detect electromagnetic spectra, and a control assembly operatively interconnected with the camera assembly to mo... | 03/11/2003 |
| 6370867 | Throttleable rocket injector assembly A throttleable rocket injector assembly is disclosed wherein the flow of oxidizer into each of the oxidizer injectors is simultaneously regulated by a mechanical assembly mounted entirely within the oxidizer chamber.... | 04/16/2002 |
| 6367243 | Atomic-based combined cycle propulsion system and method A method and system are provided for propelling an aerodynamic vehicle into space. The aerodynamic vehicle uses a nuclear-based thermal rocket (NTR) propulsion system capable of producing a hydrogen exhaust. A flow of air is introduced into the hydrogen e... | 04/09/2002 |
| 6205771 | Ducted fan gas turbine engine control system A control system for a ducted fan gas turbine engine (10) comprises a control unit (29) that receives input signals from a pressure transducer (27) located within the engine's fan duct (11) downstream of the fan (13) and a rotational speed transducer (32)... | 03/27/2001 |
| 5839272 | Dual concentric poppet valves for maintaining substantially constant the ratio of two fluid flows over an operating range of valve opening A dual concentric poppet valve assembly (44) includes an assembled body (45) having an opening (55) therethrough and having a sealing surface (56) surrounding the opening. A first member (46) is mounted in the body opening for axial movement relative to t... | 11/24/1998 |
| 5224343 | Constant fuel supply device for a thruster In a fuel supply system for a space missile or a spacecraft in which the thrusters are supplied with liquid or gaseous fuel from a fuel tank in which the tank pressure decreases continuously during the operational life of the system, the fuel throughput a... | 07/06/1993 |
| 5148674 | Method and apparatus for providing real-time control of a gaseous propellant rocket propulsion system In the representative embodiment of the new and improved methods and apparatus disclosed herein to provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants, real-time measurements representative of the engine per... | 09/22/1992 |
| 5063734 | Method for providing real-time control of a gaseous propellant rocket propulsion system In the representative embodiment of the new and improved methods and apparatus disclosed herein to provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants, real-time measurements representative of the engine per... | 11/12/1991 |
| 5054287 | Extended temperature range rocket injector A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connected to valves between these manifolds and p... | 10/08/1991 |
| 4928484 | Nonlinear multivariable control system There is disclosed an apparatus for and method of controlling a plant such as a turbojet engine wherein a model of the plant is created and plant performance request signals are applied to both the plant and the model of the plant. The performance of the ... | 05/29/1990 |
| 4777794 | Mass flow rate regulation of propellant fluid in the feed system of a bi-propellant, pressure-fed rocket engine A method and apparatus 10 for self-regulating the mass flow rate of a fluid comprises a housing 12 defining an upper chamber 14 and a lower chamber 16, a sealed and pressurized bellows 30 contained within the upper chamber 14, spring bias means 58 contain... | 10/18/1988 |
| 4744300 | Utilization of metal hydride and acidic reagent for the accelerating of masses and propulsion devices for applying such materials The utilization of metal hydride and an acidic reagent for the accelerating of masses, and propulsion devices for applying such materials. The materials are of a saline complex metal hydride and acidic reagent which is sprayed onto the metal hydride which... | 05/17/1988 |
| 4722183 | Method for controlling the utilization of fluid bipropellant in a spacecraft rocket engine A method is provided for controlling the utilization of a fluid bipropellant including two respective constituents separately in respective tanks aboard a spacecraft for consumption by a spacecraft rocket engine, comprising the steps of actuating the rock... | 02/02/1988 |
| 4697416 | Motor involving the control of the mixture ratio of fuel and oxidizer for a liquid fuel motor by measuring flows, and control systems for carrying out this process The process comprises the comparison of the flows of fuel and oxidizer measured at the outlet of the turbopumps with a set value corresponding to the optimum value of the mixture. The set value is periodically modified in dependence on the volumes of fuel... | 10/06/1987 |
| 4592508 | Translating jet engine nozzle plug A plug (24) has a fixed portion (26, 28) and a sliding portion (34). A tapered outer surface of portion (34) is adjacent to the throat (22) of a jet engine nozzle (20). Portion (34) includes two expansible chambers (36, 38) which are both defined by wall ... | 06/03/1986 |
| 4541238 | Process for the control of the mixture ratio of fuel and oxidizer for a liquid fuel motor by measuring flows, and control systems for carrying out this process The process comprises the comparison of the flows of fuel and oxidizer measured at the outlet of the turbopumps with a set value corresponding to the optimum value of the mixture. The set value is periodically modified in dependence on the volumes of fuel... | 09/17/1985 |
| 4409791 | Injection device for the combustion chamber of turbine engines A fuel intake tube passes radially through an engine casing. It is surrounded between the casing and an injector head by a second tube attached to the casing. Guidance means and a sealing element are provided between the fuel intake tube and the second tu... | 10/18/1983 |
| 4291533 | Supersonic ramjet missile 1. In a supersonic combustion ramjet missile, a body, an innerbody having a portion within the body and a portion projecting fordly therefrom, said innerbody being spaced from said body to define an inlet for compressing an air flow from a hypersonic flight M... | 09/29/1981 |
| 4184327 | Method and apparatus for rapid thrust increases in a turbofan engine Upon a landing approach, the normal compressor stator schedule of a fan speed controlled turbofan engine is temporarily varied to substantially close the stators to thereby increase the fuel flow and compressor speed in order to maintain fan speed and thr... | 01/22/1980 |
