Patent
Jettisonable protective cover device
Reads0
Chats0
TLDR
An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettused in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles is presented in this paper.Abstract:
An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device. The pressure forces are sufficient to shear the retaining pins and accelerate the cover device sufficiently forward to clear the missile body at supersonic speeds. The missile angle of attack creates lateral aerodynamic forces on the cover deivce to clear it from the missile. The sensitive radome can then be used for high precision detection and tracking as required at intercept.read more
Citations
More filters
Patent
Thrusting separation system
TL;DR: In this article, a separating joint for use primarily in aerospace applications is provided having two operational components: the first component provides a very high force over a short stroke distance, using an explosively actuated expanding-tube, suitable for shearing connectors such as rivets.
Patent
Payload housing and assembly joint for a launch vehicle
Allan L. Chan,Robert M. Heath,Steven D. Mettler,Chau N. Pham,Douglas B. Pereyda,Robert J. MacDonald,Kenneth W. Epstein,David P. Kennon +7 more
TL;DR: In this article, a launch vehicle payload housing and assembly joint is described, consisting of a shroud having first and second shell sections, and a frusto-conical payload adapter mounted in the shroud.
Patent
Missile with multiple nosecones
TL;DR: In this paper, the separation of the outer nosecone from the payload assembly may cause backward movement of the center of pressure of the payload, bringing the center pressure closer to a center of gravity of the assembly.
Patent
Launch vehicle system
Ernest R. Bedegrew,Allan L. Chan,James J. Connors,Donald E. Damon,Kenneth W. Epstein,Daniel H. Hada,Robert M. Heath,Michael B. Prewitt,David L. Sutphin,Edward W. Szeto,Howard D. Trudeau,Michael J. Vogel,Michael Wong,Larry Y. Hsu,David P. Kennon,Robert J. MacDonald,Steven D. Mettler,Gene S. Ogden,Douglas B. Pereyda,Chau N. Pham +19 more
TL;DR: A launch vehicle system includes at least one primary solid fuel motor, a shroud for housing a payload and an attitude control system as discussed by the authors, which is connected intermediate the primary solid motor and the shroud.
Patent
Pyrotechnic removal of a radome cover
Andrew G. Laquer,Albert L. Bien +1 more
TL;DR: In this article, a radome cover is removed by scoring longitudinal recesses 50, preferably at least four, on the inner surface 26 of the cover 18, and a detonator 34 explodes all cords simultaneously.
References
More filters
Patent
Enabling device for a gas generator of a forced dispersion munitions dispenser
TL;DR: An enabling device for a gas generator (42) of a forced dispersion munitions dispenser (10) includes a housing (58) in which are formed a bore (60), an outlet lead (88) and a detonator opening (68), in which is positioned an electrically initiated detonator (70) as mentioned in this paper.
Patent
Method and system for ejecting fairing sections from a rocket vehicle
TL;DR: In this article, a method and system for deploying releasable clamshell fairing sections from a spinning rocket vehicle body, in which each fairing section is retained at its lower trailing edge portion, relative to the spin direction of the rocket, until it has been substantially despun and rotated outwardly from the rocket through a predetermined angle to thereby substantially eliminate the possibility of the fairing pieces striking the vehicle payload.