DEVICE FOR OVERCOMING THE PROBLEM OF CREW SAFETY DURING A SPACECRAFT LAUNCH AND INPROVE THE JOINTS CONNECTING THE SEGMENTS OF THE SOLID ROCKET BOOSTER

Abstract: Spacecraft, satellite, aeroplane and solid rocket booster are provided with similar locking device, comprise the housing (6-41), sleeve (9-42) and the screw clamps (11-15). The housing (6) is composite with thrust ring (7) and sleeve (9) with a number of sectors (10), which are provided with a module multiple thread. The screw clamps (11-15) are formed with a draw hook engageable with thrust ring (7) and provided with similar module multiple thread, so that to the sectors (10) screw in the screw with clamps (11-15) to joint the detachable sections. In addition to it, spacecraft, satellite, aeroplane are provided with a tripping mechanism which is disconnecting the joined sections. Explosive charges which may be fired by means of ejection gear mounted and disposed on a break line between sections and carry out detachment the sections from the remainder. The parachutes (4) in the pack are released one at a time or predetermined order and the crew capsule (2) or the compartment with people on board makes a safe, soft landing.

Description: Device for overcoming the problem of crew safety during a spacecraft launch and improve the joints connecting the segments of the Solid Rocket Booster I, Zinovi Levin, of 78, Kensington Gardens, Ilford, Essex, a oitizen of the United Kingdom and Colonies, do hereby declare the invention, for which I pray that a patent may be granted to me, and the method by which it is to be performed, to be particularly described in and by the following statement: - The present invention relates to a device for overcoming the problem of osβw safety during a spacecraft launch, improve the joints connecting the segments of the Solid Rocket Booster and salvage the Satelite during launch. This invention is original and Universal and can be applied in many instances. An object of the present invention is to provide spacecraft with devioe which becomes operable when the Spacecraft crew wish to abort the launoh when a dangerous situation arises. By operating a push button the orew capsule which is only a small part of the Spacecraft automatically detaches and separates itself from the remainder of the spacecraft and makes a safe, soft landin . Moreover ' known faulty design of the joints connecting the segmen s of the solid rocket booster, the O-ring seals on the Shuttle, - substituted design vtifch very much to improve construction of the joints connecting the segments of the solid rocket booster, means of original grips which constrict the solid rocket booster joints and compressed original metallic packing which is disposed between them with powerful force, thus to prevent buzsing fuel to escape in the most adverse weather conditions. disoover during a satelite launch that the satelite will deviate from its path. From the ground control put into effect button, in consequence of the satelite detaches and separates itself from launch vehicle and makes a safe, soft landing. An embodiment of the invention is more particularly described below by way of example, with reference to the accompanying drawings, Wherein;- Figure I is a front elevation view showing of the mounting spacecraft and constructed in accordance with the invention. Figure 2 is a top sectional view of the device of Figure I with crew capsule removed. Figure 3 is an enlarged fragmentary view illustrating the locking device used in the device of Figure I and 2. Figure 4 is a top view of Figure 3. Figure 5 is an enlarged view illustrating the Tripping mechanism in its neutral position used in the device of Figure I and Figure 2. Figure 6 is an enlarged view illustrating details of the disconnection the locking device means used in the Tripping mechanism and the arrangements for electrical connection with ejection gear of Figure 5. Figure 7 is an enlarged fragmentary view illustrating the ejection gear in its neutral position used in the device of Figure 1 and Figure 2. Figure 8 shows the arrangement for ejection the crew capsule of Figure 7. Figure 9 shows the separation the crew capsule from the spacecraft after catapulting of Figure 1, Figure 2 and Figure 8. Figure 10 is a fragmentary view showing details of the abutment oint in distribution lines. Flgure 12 is an enlarged fragmentary view illustrating details of the joints connecting the segments of the Solid Rocket booster which substituted 0-rlng seals at the present time on the shuttle. Figure 13 is a appearance the small civil aeroplane where is such device can be used and installation with spacing between wing aeroplane. Figure 1 is a view illustrating the means for screw up clamp by means of hook spanner. Referring particularly to Figure 1, Spacecraft is shown positioned is prepared for launch, generally designated Y comprises: The crew capsule 2, the body of spacecraft 3, a number of parachutes 4, which are disposed on surface crew capsule and on the adjacent side of crew capsule is located the sliding door 5. The crew capsule 2 is coupled with the housing 6 by welding or by means of a fixing screw. The housing 6 is composite with thrust ring 7, the bottom of the housing 6 provided with a ring groove in which is situated the gasket 8, the housing 6 is inserted freely into through hole of the sleeve 9. As shown particularly in Figure 1 and Figure 3, the sleeve is formed with a similar ring groove and incorporates with the housing 6 by gasket 8. By welding or by means of a fixling screw the sleeve 9 is connected with the body of spacecraft 3. As shown in Figure 1, Figure u and Figure 3, on surface of the sleeve 9 are fixed a number of sectors 10 therein, the sectors being disposed in a generally circular around the periphery of the Sleeve 9, each sector 10 is provided with a module multiple thread. It will be seen that to the sectors 10 screw in the screw clamps 11, 15 which is equal to the number ith a draw hook engageablβ with Thrust ring 7, which is formed of the housing 6. As shown particularly in Figure 1, Figure 2 and Figure 3, to make arrangements to operate with screw clamps 11, 15 to engage or disengage with sectors 10, initially in the operation simultaneously to put their in space ° its between at sectors 10 (slightly more than the size of sector L°) and by draw hook to hang up screw clamps 11, 15 on a thrust ring 7 and manually the turning to engage with sectors 10, a er that the screw clamps 11, 15 in succession to connect by a connectors 35 (see Figure 2 and Figure 3) and to secure by a locking nut. Therefrom by means of hook spanner 44 which in conjunction with each screw clamp (see Figure 14 " ), or some other manner, to give simultaneousl a screw clamps 11, 15 a good screw. The index movement is transferred to housing 6 and to sleeve 9, accordingly to the crew capsule 2 and to body of spacecraft 3, a sence of rotation the crew clamps 11, 15 accomplished by guides 12. It will be seen that by the method of thread joint, all mating members which is received powerful pressing force with at considerable dimensions embraces the following around the periphery of the sleeve and the thrust ring to form rigid connection. As shown in Figure 1, Figure a and Figure 5, on surface of the housing 6 mounted a plurality of rollers 13 as supporting and as guiding a guy rope 14, one end is tied with crew clamp 15 which is provided with the tightening ear, another end by means of provided into through hole in the housing 6 is fastened with a winding drum 16. The winding drum 16 is coupled with driven gear 17 are freely mounted on shaft. The driven gear 17 meshes with toothed sector 18 which is coupled with the rocking lever 19 are pivotally mounted on pin 20 which is fixed to housing 6. As shown in Figure 1, Figure 2 and Figure 5, it will be seen that the hydraulic ram 21 is pivotally mounted on pin 22 which is fixed to housing 6 and other end is pivotally mounted by a pin 23 with rocking lever 19, The hydraulic ram 21 is engaged with a hydraulic pump 24. As shown in Figure 1, Figure 2 and particularly in Figure 7, between junction of housing 6 and sleeve 9 are disposed a number of the ejection gear. Referring to the ejection gear comprises a number of permissible explosive 25 which are situated in the detonator housing. The detonator housing being disposed between housing 6 and sleeve 9. It will be seen that the detonator housing which is formed in the housing 6 is provided with an opening 26 and protected by the outer surface of safety catch 27 against the striker pin 28 which is actuated by a spring 29. The safety catch 27 is provided with an opening 30 in position aside from the striker pin 28 by means of restraining spring 31, As shown particularly in Figure 2 and Figure 7, the number of plungers electromagnet 32 which is equal to the number of safety catch 27 makes electrical communication to the power supply by • wire 33 (see Figure 2) which is connected with switch 34, The plunger electromagnet 32 have been arranged at a distance from safety catch 27 by technical requirements (see Figure 7). Referring first to the Spacecraft as illustrated in Figure 1, when prelaunch procedure is ready, the crew of spacecraft to place in the crew capsule 2, and to close the door 5. When during a launc a dangerous situation arises, by operating a push button 36, motor hydraulic pump 24 is ready for use. The plunger at the hydraulic ratii 21 co-operates with a rocking lever 19 which is fixed to the toothed sector 18 via the gear 17 which is fixed to the winding drum 16, thereby the winding drum 16 is driven by the hydraulic pump 24 and received rotary motion to coil up the guy rope 14 which is fastened with a winding drum 16, thus the guy < fope 14 is received constrained motion. This movement is transferred to clamp 15 (see Figure 2, Figure 5, Figure 6) and further to the clamps 11 which successively is connected with him by connectors 35. Thus the clamps 11, 15, simultaneously are moved out of engagement with sectors 10 to put their in the space LΪ at that time rib of the rocking lever 19 is received the switch 34 contact of the tip with the switch 34 being assured. The plungers of electromagnet 32 are received electromagnetic induction excitation (see figure 7 and Figure 8), Therewith the safety catch 27 will slip relative to eletromagnet 32 and is so arranged that opening 30 of the safety catch 27 (see Figureβ) will be disposed under the striker pin 28 which is activated by spring 29 and fall into opening 30 and 26 to impact permissible explosive 25 to acquire expulsive force. Thus the crew capsule 2 with the crew on board detaches and separates itself from the remainder of the spacecraft as illustrated in Figure 9. Then this occurs, immediately to put into operation the landing parachute 4 and the capsule 2 with the crew on board makes a safe, soft landing. Referring to the installation of the pipe-line, as illustrated in Figure 10 and Figure 11, it will be seen that, on a break line between the housing 6 and the sleeve 9, incorporates two adjustable similar elements 37 and 38, each is secured accordingly to housing and to sleeve 9 by means of hanger 39 each of which include number of clamp bolt 40. Thereby the two couple element 37 and 38 by clamp bolt 40 is received a tight coupling and as well allow easily detaches and separates one from other, when the crew capsule 2 separates itself from remainder. Referring is now to the satelite. The satelite is provided with similar safety device as described earlier, but the operation with the satelite is slightly dif erent from operation with a spacecraft. As a rule the satelite to accomplish a Task without of crew on board, therefore the handling of a satelite carrying out from the ground control. When the satelite will tend to deviate from a course, under the influence of ground control to the motor hydraulic pump 24 (see Figure 5 and Figure 6) (The interaction details of device described earSLier) , the satelite detaches and separates from rocket booster makes a safe, soft landing. It should be understood that the gear may be hydraulic drive or mechanical drive and.not Only hydraulic drive as indioated in the above embodiment. Should have indicated that a serious and potentially disastrous situation was developing on all solid rocket booster joints and is reasonable to conclude, to raise doubts about the safety of seals in the boosters, which .proved fatally .Blamed in the prevailing conditions.. The rubber ring become hard and slow at air temperatures close to freezing point, that it failed to prevent the escape of burning fuel. As shown particularly in Figure 12, it is primary object to provide improved design, which to substitute effectively known design faults in the solid rocket booster joints; The similar elements which are described earlier in Figure 1 and Figure 3, only that the housing 41 (see Figure 12) formed with an annular sawtood formation B° as its end against similar• formation carried by a sleeve 42. The housing 41 is connected with solid rocket booster and the sleeve 42 with booster attachment ring. Between housing and sleeve is disposed metallic packing (copper r or lead) 43 which have a similar ormation carried by housing and- sleeve. τ •The'-.method of thread therein lay its strength in which being formed rigid connection. As shown in Figure 13, such device as described earlier in Figure 1, Figure 2, Figure 5, Figure 6 and Figure 7, can be applied in the small civil aeroplane and are located between wing aeroplane as"D'J an interval between them free from passenger. Thereby being formed compartment which is apart one from other. Each compartment provided with the door, so as to work in conjunction with device. When a dangerous situation arises, by operating a push button which are located in several places at the compartment, the door automatically and securely locked in the closed position, the compartment detaches and separates P itself from the remainder and to put into operating the landing parachute 4 and the compartment with the passenger on board make s a safe, soft landing. The device illustrated in the drawings is used as follows: First, the device is applied to the overc oming the problem of crew safety during a spacecraft launch. Second, the device is applied of s alvage the satelite when the- satelite will-.-teiήd to deviate from a course . Third, the device is applied to improve the joints connecting the segments of the solid rocket booster. Fourth, the device is applied to the overcoming the problem of passenger safety during flight of the small civil aeroplane , to be locking device which abutment j oint the components of flying vehicle by screw j oint , sectors 10 with screw clamps 11, 15 and Thrust ring 7 , which becomes operable when the crew wish to abort the launch when a dangerous situation arises , by operating a push button 36 (Figure 1) to put into operation h draulic um 24 which drives lun er of the h d rocking lever 19, toothed sector 18, gear17 and the winding drum 16. The winding drum 16 Is received rotary motion to coil up the guy rope 14 (see Figure 2, Figure 5, Figure 6) thus the clamps 11, 15, simultaneously are moved out of engagement with sectors lo at that φinβ rib of the rocking lever 19 is received the switch 34 contact at the tip, the plungers of electromagnet 32 (Figure 7 and Figure 8) are received electromagnetic induction excitation. Therewith the safety oatoh 27 will slip relative to electromagnet 32 and opening 30, βf the safety catch 27 will be disposed under the striker pin 28 which is actuated by spring 29 and all into opening 30 and 26 to impact permissible explosive 25 to acquire expulsive force. Thus the crew capsule 2 (Figure 1) or ■components of flying vehiole etc, detaches and separates itself from the remainder (see Figure 9) when this occurs immediately to put into operation the landing parachute 4 and the capsule 2 with the crew on board makes a safe, soft landing.

Claims: AMENDED CLAIMS [received by the International Bureau on 18 May 1988 (18.05.88) original claims 1 and 2 amended ; remaining claims unchanged ( 1 page)] 1. A device or overcoming the problem of crew safety and escape with particular applic ation to spacecraft , manned satellites and aircraft . The devic e c omprises of a detachable compar tment which is butt j ointed to the main body of the vehicle by means of a serie s of threaded c lamps and sectors screwed together and assembled together with a thrus t ring which is incorporated on the compartment body. The tripping mechanism to activate the ej ection gear has a c ontrolled explosive charge ac tivated by an impact mechanism which forces the crew compar tment to separate from the main vehicle body either during flight or on launch pad or runway . Separation during a vertical lift off by means of the c ontrolled explosion enables the crew compar tment to maintai a vertical projectory and thus avoids collision with the main vehicle body. The guidance and operation of the escape compartment is entirely independent of the main vehicle ' s power supply and is automatically operated from within the escape compartment 2. A device as described in Claim 1 in which the clamps and sectors which couple the crew escape compar tment to the main vehicle body is provided with a module multiple thread and clamps formed with a draw hook engageable with a rigid thrust ring which is firmly secured to the escape compartmen sur ace . STATEMENTUNDERARTICLE19 Briefly, the essential differences are;- My invention consists of a detachable crew escape compartment which separates itself from the main vehicle body when the vehicle is either stationary on the ground or in vertical or near vertical flight. The two elements are separated in a manner that would avoid them coming into collision with each other. On the other hand invention No. ,702,680 is only applicable to an aeroplane in horizontal flight. It is only applicable to an aeroplane whereas my invention is applicable not only to an aircraft but also to a spacecraft or manned satellite. In my invention, the ' joint between the escape module and the main vehicle is by means of series clamps and sectors which form a rigid connection which permits the multi-person crew unfettered access to other parts of the main vehicle and thus permitting them to perform their normal intended duties and relaxation. In contrast, patent No.2,702,680 is only applicable to a single pilot who is separated -at all times from his main vehicle and whose duty is only to fly the plane. The intended function of the two inventions are quite different even though they may have the same purpose. In ray invention, the crew escape compartment is not dependent on power supply from the main vehicle. In. contrast, the escape module in patent No. ,702,680 depends on power supply for JAT0 type rocket propulsion unit. There is no similarity between patent No.2,702,680 and my invention as the escape module described therein does not and could not be adapted to serve the purpose intended by my invention in use on spacecraft and manned satellites.

Inventors: LEVIN ZINOVI, LEVIN, ZINOVI
Applicants: LEVIN ZINOVI, LEVIN, ZINOVI
Application year: 1987
Main classification: B64D25
IPC codes: B64D25, B64G1