Patent GB-964922-A (GB)
Title: Improvements in air travelling reaction propelled devices
IPC: F41A33/00
Filed: 1961-11-10
Abstract: 964,922. Practice and like rockets and launchers therefor. TEXACO EXPERIMENT Inc. Nov. 10, 1961 [Nov. 22, 1960], No. 40312/61. Headings F3A and F3C. [Also in Divisions E2 and F1] A rocket 12 launched by means of a structure 14 is provided with sealing means for the discharge nozzle 24, the sealing means 28 being held in position by a latching device co-operating with the tube from which the rocket is launched, means being provided to eject the rocket from the tube 38. The rocket 12 has a nose section 16 and an intermediate section 18 housing instruments or smoke-producing or like material together with recovery mechanism and behind these sections is a propellant storage section 20 and a tail section 22. The casing may be spun or cast aluminium, diecast metal or high impact strength plastics. Certain sections may be die-cast and the rest of spun or sheet aluminium, the sections being held together by conventional means and/or cement such as epoxy adhesive. Tail section 22, Fig. 4, which is preferably die-cast, carries at least one pair of bosses 64 cooperating with lugs 66 of latching levers 70 to hold the seal 28 in sealing position, the levers being held in the latching position by the launching tube. Seal 28 includes a plug 72 having locating lugs 82, which engage notches 84 in the nozzle rim. The plug 72 carries an insert 88, which extends into the nozzle 24 and may be used to fill the propellant chamber when provided with valve means 94. Collapsible fins 120 are pivoted on equi-spaced flanges 122 having milled surfaces 126 to co-operate with the curved surfaces 128 of the fins. Prior to insertion in the launcher, a resilient band 140 placed in notches 132 holds the fins in the collapsed position. On insertion in the launcher, band 140 is placed in notches 134 and together with a band 142 in notches 136 urges the fins to the deployed position after launching. Fig. 22 shows a modification in which the fins are pivoted on the rim of the nozzle, their free ends being received in brackets 402. Notches 410 in the fins engage a ring 411 carried by the plug, which is equipped with a felt gas check 409. The head 30 of the propellent chamber is preferably die-cast and provided with reinforcement ribs 122. Non-burning propellants are used, preferably liquefiable normally gaseous materials having a low boiling point or gases dissolved in liquid and maintained under pressure. Examples given are ammonia, "Freon" (Registered Trade Mark), sulphur dioxide, methyl chloride, propane, butane, carbon dioxide dissolved in water, dimethyl ether in water or difluoroethane in alcohol. The preferred propellant is carbon dioxide dissolved in acetone in a 50: 50 proportion by weight. A numerical example is given. Launcher.-The tube 38, Fig. 1, is preferably made in sections 40, 42, 43 having threaded connections 48, so that a rocket may be inserted from above in section 40, the lowermost section 40 being received in a sleeve 44 secured to a plate 140, which is carried above the launching platform 32 by uprights 142, 143. In plate 140 is an opening 144 to receive the valve means 94 of the rocket, the opening being made gas-tight by a cover 146. Launching fluid is led into the tube 38 through a conduit 46 when a valve 148 is opened by means of a lever 154, Figs. 1 and 11, the lever being biased to the open position by a spring 162, but held in the closed position by engagement of a pin 156 with a latch 166. The latch is pivoted in the launcher frame 172 and biased upwards by a spring 174 connected to a coupling 178, which also receives one end of a firing cable 180 the other end of which is taken to a remote point. Valve 148 is connected by a conduit 150 to a low-pressure reservoir 190 having a gauge 192 and connected to an intermediate pressure reservoir 194 equipped with a gauge 200, a reducing valve 198 being inserted in the connection. Reservoir 194 is connected to a source of gas or liquid under high pressure in a cylinder 202 by a manually actuated valve 204, conduit 206 and regulating valve 208. The rocket is charged by connecting a flexible hose 214 to the valve 94 and operating a valve 210. Before inserting the rocket in the launcher, the rocket is inverted and the plug 72 removed. Thereupon 1 1b. of acetone is poured into the chamber 20, the plug is replaced and the levers 70 are pushed to engage lugs 66 with the bosses 64. The fins being held in the folded position, the rocket is inserted in the tube 40 and sections 42, 43 placed in position prior to pressurizing chamber 20 to a pressure of about 50 p.s.i. by admission of 1 1b. of liquid carbon dioxide. Filling tube 214 is then disconnected and valve 148 closed. Reservoirs 194 and 190 are charged with carbon dioxide and valve 204 closed, the rocket then being ready for launching by a pull on cable 182. As the rocket leaves the tube, the plug 72 is unlatched and is pushed out by the propellant. Rocket recovery device.-Rocket recovery mechanism housed in section 18 includes a parachute 240, Fig. 13, attached by a lanyard to a rib 122 and section 18 has a removable panel 246 hinged at 254 and controlled by timing mechanism 250. The panel is secured by a latch pin 264 held in a keeper plate 260, Fig. 14, by a spring 266. The panel may be opened manually by inserting an implement in a hole 272 and pressing the latch pin downwardly. The timing mechanism 250 is set to release the latch pin 264 by inserting a key through an opening 290 to engage a shaft 286 carrying a gear 276 and connected to a spring motor 288. Gear 276 is in train with gears 278, 280, 282, 284, the gear 284 engaging an escapement 292 carrying opposed weights 294. When a bracket 296, which extends from a slidable plate 298, Fig. 16, engages a weight 294 the timing mechanism is immobilized. Plate 298 has a bracket arm 306 through which extends a rod 310 on which a weight 314 supported by a spring 316 is slidably mounted. When the spring motor is wound a pin 324 on the shaft 286 engages an arm 322 and urges the plate 298 upwards to stop operation of the gear mechanism. A slidable plate 328, having a bent end 340 in engagement with the latch pin 264, is forced downwardly by a cam 334 mounted on shaft 286, when the timing mechanism is actuated, and releases the pin 264. Door 246 is then forced open by the parachute, which then escapes. The door may be attached to the parachute for recovery purposes. When the rocket is launched, the acceleration causes the weight 314 to hit the arm 306 and force plate 298 downwardly, whereupon arm 296 moves away from weight 294 and frees the escapement. The timing mechanism then starts to operate. In a modification, the door panel is hinged to the rocket casing at top and bottom and a winding disc provided with setting indicia is accessible through an opening in the casing. The releasable doors may extend to the nose section 16, when it is necessary to expose sensing instruments for collecting meterological data or to allow passage of retractable means carrying instruments. Release of the door panel may release an antenna for transmitting radio signals.