摘要:
An optical scanning apparatus embodied in a gyroscopic missile seeker to provide a rosette scan pattern of the field of view. A single driving motor (20) is employed with a traction drive assembly (38) to produce the necessary counter-rotation of scanned elements and thereby effect the rosette scan pattern.
摘要:
A technique for making a honeycomb structure includes bonding a less than totally cured composite skin (16) to a possibly contoured honeycomb core (8). The composite skin (16) comprises fibers and a resin chosen to maximize the strength and stiffness of the skin (16) when cured. Non- contiguous adhesive fillets (5) are prepositioned onto faying surfaces of the honeycomb core (8). The adhesive (5) is preselected, independently of the preselection of the resin, to maximize the strength of the bond between the skin (16) and the core (8). A thin, lightweight scrim cloth (14) is interposed between the starting skin (16) and the filleted core (8). The scrim cloth (14) prevents resin from flowing into the core (8) and allows a safe place for the intermingling of resin and adhesive (5). The assemblage is heated under pressure, cocuring the adhesive (5) and the resin. The fillets (5) are preferably prepositioned on surfaces (10) by means of applying an adhesive-coated fabric to the faying surface, heating the fabric-covered core (8) so that some of the adhesive (5) flows out of the fabric (1) and into the core (8) at a region near the faying surface, cooling the core (8) so that the only substance remaining adhered to the core edges (10) is the adhesive fillets (5).
摘要:
Ce système comporte une chambre de diffusion à extrémité ouverte (16) et une chambre de combustion adjacente (18) situées dans le nez (12) d'un projectile (10) pour recevoir de l'air sous pression dynamique qui enflamme un matériau combustible solide (20) à l'intérieur de la chambre de combustion (18). Deux orifices de commande latérale (22, 24) d'orientation opposée sont prévus à l'arrière de la chambre de combustion (18) et sont reliés à celle-ci par une vanne de déviation (28) que l'on peut commander pour dévier d'une manière sélective les gaz de combustion s'échappant de la chambre de combustion (18) vers un ou les deux orifices de commande (22, 24) afin de modifier ou de conserver la trajectoire du projectile (10) après sa mise à feu.
摘要:
O The invention proposes remote rotation sensing of a gyroscopically mounted rotor (40) by utilizing a single fiber optic (50) between a light reflector (35) on the rotor and a light sourcellight detector (64,68). The single fiber optic (50) provides transmission for both source light energy in a first direction and reflected light energy in the opposite direction. A second embodiment provides a discontinuity (51,53) in the fiber optic to allow for relative movement.
摘要:
A closed-loop system for precisely regulating the speed of an electrically driven rotating body. A tachometer rotor (53) mechanically linked to the rotating body is provided with p "teeth" (55) around its periphery. A sensor (57) produces a pulse signal upon passage of each of these teeth, to generate a cyclic tachometer signal having a frequency p times the frequency of rotation. A tachometer counter (5) counts this signal and produces a single output pulse after every n x p pulses from the sensor, such that the same one of the p teeth is responsible for triggering each of the successive output pulses, and variations in spacing between teeth do not cause variations in the period of the counter output. A high frequency clock (17) is counted by a second counter (14) which transfers its count to a storage register (23) and resets upon each pulse from the tachometer counter (5), such that the count held by the storage register is a continuously updated, highly accurate digital respresentation of the period of the rotating body. A period comparator (39) derives a speed control signal which is proportional to the inverse of the difference between the count and a digital speed command signal representative of the rotational period at the desired rotational speed.
摘要:
An opening (14) in the nose (12) of a missile allows entry of ram air during missile flight to a central chamber (18). Oppositely oriented steering jets (22),(24) are innerconnected with the aft end of the central chamber (18). A diverting mechanism (26) is located between the central chamber (18) and each of the steering jets (22),(24) to allow either one or none of the steering jets (22),(24) to provide correctional steering forces when desired. The rotatable diverting mechanism (26) is pneumatically driven by ram air communicated to an actuation chamber (44) located aft of the valve and controlled by electrically energized solenoids (60).
摘要:
A technique for making a honeycomb structure includes bonding a less than totally cured composite skin (16) to a possibly contoured honeycomb core (8). The composite skin (16) comprises fibers and a resin chosen to maximize the strength and stiffness of the skin (16) when cured. Non- contiguous adhesive fillets (5) are prepositioned onto faying surfaces of the honeycomb core (8). The adhesive (5) is preselected, independently of the preselection of the resin, to maximize the strength of the bond between the skin (16) and the core (8). A thin, lightweight scrim cloth (14) is interposed between the starting skin (16) and the filleted core (8). The scrim cloth (14) prevents resin from flowing into the core (8) and allows a safe place for the intermingling of resin and adhesive (5). The assemblage is heated under pressure, cocuring the adhesive (5) and the resin. The fillets (5) are preferably prepositioned on surfaces (10) by means of applying an adhesive-coated fabric to the faying surface, heating the fabric-covered core (8) so that some of the adhesive (5) flows out of the fabric (1) and into the core (8) at a region near the faying surface, cooling the core (8) so that the only substance remaining adhered to the core edges (10) is the adhesive fillets (5).