Home | Links | Contact Us | More About Intellectual Property | Bookmark
Search patents:
Home Telecommunications Shuttle-launch-system-for-model-rocket

 Ins alignment method using a doppler sensor and a GPS/HVINS
The following description of the preferred embodiments of the invention shown in the FIG. 1 and FIG...


 Method and device for displaying animated navigation information
The present invention satisfies the above described need and other needs by providing a GPS ...


 Bobbin transfer tail retainer
What is claimed is: 1. A yarn bobbin having a transfer tail retainer comprising a cylindrical tube ...


 Yarn carrier
An object of the present invention is to provide an improved yarn carrier. Another object of the ...


 Textile yarn carrier
This invention relates to tubular carriers of textile yarn packages particularly used with winding ...


 Spool for filament winder
It is therefore an object of the present invention to provide an improved spool for use in an ...


 Yarn tube with pickup groove accommodating left hand and right hand pickup
The present invention proposes a tube pickup groove specifically configured to both incorporate a ...


 Reusable winding tube
OF A PREFERRED EMBODIMENT Turning now to the drawings, and particularly to FIG. 1, there is ...


 Reusable high speed winding tube
OF PREFERRED EMBODIMENT Turning now to the drawings, and particularly to FIG. 1, there is ...


 Yarn winding apparatus and method
OF THE PREFERRED EMBODIMENTS The winding apparatuses, which are illustrated in FIGS. 1-4, 5, 6 and ...


 Shuttle launch system for model rocket

Details
Inventors: Karnish, Eugene;
Assignee:
Primary Examiner: Barefoot; Galen L.
Assistant Examiner:
Attorney, Agent or Firm: Law Offices of John A. Beehner

A shuttle launch system for a model rocket which includes a model rocket engine having a propellant charge for propelling the model rocket in a first direction and an ejection charge for ejecting matter in a second direction generally opposite the first direction consists of a booster rocket having a longitudinally extended tube with a peripheral sidewall, an inner chamber and top and bottom ends and an engine-receiving chamber adjacent the bottom end of the tube. A shuttle glider support structure is mounted on the booster rocket for releasably supporting a shuttle glider thereon. A fluid passage extends between the inner chamber of the booster rocket and the shuttle glider support structure such that a portion of gas within the inner chamber is redirected from the inner chamber through the fluid passage and out of the shuttle glider support structure. The shuttle launch system further includes a shuttle glider having a fuselage and at least one wing, the shuttle glider removably mounted on the shuttle glider support structure on the booster rocket. Finally, the shuttle glider is separated from the booster rocket upon ejection of matter from the ejection charge of a model rocket engine held within the engine receiving chamber, the ejected matter compressing gas within the inner chamber, a portion of that gas being redirected from the inner chamber through the fluid passage and outward from the shuttle glider support structure thereby propelling the shuttle glider outward from the booster rocket.

DETAILED DESCRIPTION The present invention provides a shuttle launch system for a model rocket which includes a model rocket engine having a propellant charge for propelling the model rocket in a first direction and an ejection charge for ejecting matter in a second direction generally opposite the first direction.
The system includes a booster rocket having a longitudinally extended tube with a peripheral side wall, an inner chamber and top and bottom ends and an engine receiving chamber adjacent the bottom end of the tube.
A shuttle glider support structure is mounted on the booster rocket, the support structure operative to releasably support a shuttle glider thereon.
A fluid passage extends between the inner chamber of the booster rocket and the shuttle glider support structure such that a portion of gas compressed by the ejection charge of the model rocket is redirected from the inner chamber through the fluid passage and out of the shuttle glider support structure.
The shuttle launch system further includes a shuttle glider having a fuselage and at least one wing.
The shuttle glider is removably mounted on the shuttle glider support structure on the booster rocket.
The shuttle glider is then separated from the booster rocket upon ejection of matter from the ejection charge of the model rocket engine held within the engine receiving chamber, the ejected matter compressing fluid within the inner chamber, a portion of compressed fluid being redirected from the inner chamber through the fluid passage and outward from the shuttle glider support structure thereby propelling the shuttle glider outward from the booster rocket.
The present invention also provides a method of launching a shuttle glider from a model rocket which includes providing the booster rocket, model rocket engine, shuttle glider support structure, fluid passage and shuttle glider described above and removably mounting the shuttle glider on the shuttle glider support structure.
The propellant of the model rocket engine is ignited thus launching the booster rocket and shuttle glider into the atmosphere



Related patents
  Control propulsion unit, especially for exerting transverse forces on a missile
An object of the present invention is to provide a control propulsion unit of the type discussed having a simple design, which will enable the thrust of the propulsion ...
  Venting apparatus for controlling missile underwater trajectory
Accordingly, the present invention relates to apparatus for actively controlling the venting of gas from the interior of a missile in such a manner as to influence the ...
  Discrete impulse spinning-body hard-kill (disk)
DISK is a munition system for intercepting a target wherein the system comprises a base platform dispenser, a right circular cylinder having a circular periphery, ...
  System for steering a missile by means of lateral gas jets
The object of the present invention is to provide a system of the above mentioned type having both valving means with low inertia and valving control without ...
  Forebody nozzle for aircraft directional control
Theoretical considerations and an experimental study of the control of forebody vortex flow fields using forebody pneumatic jets are described in the article by C...
  Device for guiding a missile
The above object is achieved according to the present invention by a device for guiding a missile having a missile tip and a cylindrical section adjoining the tip of the ...
  Vehicle guidance system for guided missiles having adaptive trajectory bias
What is claimed is: 1. In a guided missile system of the type including a seeker for providing pitch and yaw rate control signals in response to a sensed relative target ...
  Static vent units
According in one aspect this invention provides a static vent unit for use on a vehicle and which in operation is subjected to airflow from any direction within a wide ...
  Differential GPS ground station system
An object of the present invention is to provide a differential GPS ground station having enhanced continuity, availability of function, and integrity. In the present ...
  Communication system employing space-based and terrestrial telecommunications equipment
To meet the above and other objectives, the present invention provides for a communications system employing a terrestrial telestation that includes an advanced ...

0.024

Archive: All patents - Links

Copyright (c)2006 Eipa-patents.org - All rights reserved