SUBSTANCE: invention relates to retainers used to fasten cargoes delivered aboard the cargo rocket to the international space station. The proposed retainer comprises rings with hooks and adapters linked up with the said hooks. Aforesaid adapters have larger diameter collars arranged nearby the said hooks as well as smaller diameter collars. The retainer incorporates a bearing spring, its end being wound up on the adapters ends, and an arimide fabric boot fitted on the spring whereon an arimide thread is wound up very tightly, from hooks to adapter larger diameter collars.
EFFECT: higher reliability in prolonged operating in space at abnormal temperatures, longer life.
The invention relates to discharge devices of the type latch, for example, used for fastening objects (cargo) when delivering them as part of the transport cargo vehicle (THC) "Progress" on Board the International space station (ISS) and the use of crew members when performing operations on Board the ISS during extravehicular activity. This device can also be used in all sectors of the economy for fixing cargoes, including in the conditions of the aquatic environment.
The famous design of the locking mechanism intended to ensure the fixing of items (goods) on the two rails of a space object, including its supporting structure in the form of a rigid platform is rigidly mounted on the clamps number greater than or equal to three (application No. 2002101982 class B64G1/66).
As the closest analogue is selected design clips on to patent No. 2132006, MPK7: F16B 2/26, B60R 11/00 containing base, made in the form of a plate elongated in shape, provided with at least one means of attaching the base to a supporting surface, and means mounting tape, made of elastic material and arranged along the large side of the base.
The main disadvantage of existing designs of clamp is that the wiring and cables clamps in the environment of outer space (when animal is low and abnormally high temperatures in the range from -200°C to +200°C) may be susceptible to the damaging effects of the environment. In addition, existing designs retainer suggest the presence of and the fixing of the base of the clamp to a supporting surface, in space on the spacecraft to carry out much more complicated, in addition, these devices are more complex and more energy-intensive to manufacture.
The objective of the invention is to improve the reliability of the device during long-term operation in space when the abnormal temperature increase of the resource.
This task is solved in that the proposed device lock, do not use hard-coded fixed base, contains rings with hooks connected to the hooks adapter, and the adapter are coming to the hooks flange of larger diameter, and the flange of smaller diameter, the retainer also includes a bearing spring, their ends wound on the ends of the adapters, as well as the case of armenoi fabric, worn over the spring, which is tight from hooks up to the shoulder of the larger diameter of the adapter is screwed arimina thread.
Kimenyi case not only protects the latch from dust and other foreign particles into the space between the joints of coils stretched the suspension spring, but also serves as a retainer extremely stretched the suspension spring.
Use arimidex h the HLA and thread allows the latch to operate reliably, not only at high temperatures (-200°C to +200°C), but in other environments, for example in the aquatic environment, which improves the reliability and durability of the device.
Figure 1 shows an external view of the device,
where 1, 2 - hooks;
5, 6 - adapters;
7, 8 - flange of larger diameter adapters;
9, 10 - the shoulder of smaller diameter adapters;
11 - suspension spring;
12 - the case of armenoi tissue;
13 - arimina thread.
Figure 2 on an enlarged scale shows an external view of the device with the left hook 1.
The hooks 1, 2 devices are mounted, for example welded argon-arc welding, the ring 3, and 4, for example, oval. One ends of the hooks 1, 2 is placed in the cylindrical hole of the adapter 5, 6 and fixed therein, for example welded by welding. A cylindrical adapter 5,6 made in the form of two cylinders of different diameters with two pairs of ribs 7, 8 and 9, 10, thus coming to the hooks 1,2 flange 7, 8 of the adapter 5, 6 have larger diameters than the other flange 9, 10. The cylindrical adapter 5, 6 to the junction with hooks 1, 2 wound suspension spring 11, and the diameter of the small cylinder of the adapter 5, 6 coincides with the diameter of the bearing spring 11. On top of the supporting springs 11 to the junction of hooks 1, 2 with the adapter 5, 6 put the cover 12 from armenoi tissue (e.g., round). On top of the cover 12 from armenoi fabric tight clockwise from the hooks 1, 2 to Boo the ticks larger diameter adapters 5,6 wound arimina thread 13 to prevent retraction of the cover 12 when the tension of the elastic retainer. The length of the retainer may be of any desired size.
When using this device the operator (astronaut) takes the device in the glove thumb over the ring 3 or 4 and fixes the hook 1 or 2 for the constructive elements of the cargo or the handrail, then 1 thumb over the ring 4 of the hook 2 stretches the latch using the standard for astronaut efforts (300-500 grams), fixes a load supporting spring 11 release and fixes the hook 2 of the latch for the handle or hook 1 release by providing secure mooring cargo to the rail.
The proposed device is easy to manufacture, is composed of a minimum number of parts and reliably (with a five-fold margin of safety) in the long run. Conducted full-scale tests showed the ease of use and reliability in operation when the temperature in the space.
All parts of the device (rings, hooks, adapters) can be made from a different view stainless steel, the spring may be made of a different view of the spring steel, the device can be processed by the method of elektrohimpribor to make the product marketable and also removing the oxide tint in places of welding connections.
All this makes the device more durable anticorrosion the grave and increases reliability for long term use.
The latch containing rings with hooks connected to the hooks adapter, wherein the adapter are coming to the hooks flange of larger diameter, and the flange of smaller diameter, the retainer also includes a bearing spring, their ends wound on the ends of the adapters, as well as the case of armenoi fabric, worn over the spring, which is tight from hooks up to the shoulder of the larger diameter of the adapter is screwed arimina thread.
FIELD: space engineering.
SUBSTANCE: invention relates to space engineering, particularly to space vehicle docking assemblies designed to ensure a rigid electromechanical coupling between two space vehicles to dock in space allowing a tight transfer chamber. The proposed passive docking assembly comprises the main housing to be mounted and mechanically fastened on the space module mounting place aligned with its lengthwise axis, the joint tightening mechanism, docking cone and transfer hatch cover, electrical and hydraulic connectors, automatics mechanical components. Additionally the proposed assembly incorporates a transfer docking assembly representing a ring-like casing with two jointing planes furnished with electrical and hydraulic connectors, automatics electromechanical devices and the joint tightening mechanism. The said electrical and hydraulic connectors make the assemblies of interaction with the matching electrical and hydraulic connectors and automatics electromechanical devices of the main casing. Note that of the jointing planes is jointed coaxially with the main casing with the help of appropriate joint tightening mechanism so as to allow detaching.
EFFECT: expanded performances of assembly.
FIELD: space engineering.
SUBSTANCE: invention relates to space engineering and can be incorporated with the separation systems intended for jointing and separating space vehicles stages, for example for separating jettisonable stages of multi-stage carrier rockets. The proposed thrust-pneumatic pusher to separate space vehicle stages comprises a housing representing a tight hydraulic cylinder accommodating a rod, coupling units hinged to various parts of space vehicles and pyrotechnical lock. The latter has a bush furnished with a shoulder and a seat for rod end and a sleeve coupled with the pyrotechnical lock casing so as to allow the said shoulder to rest upon the cylinder end face. There are a shell interacting with the bush outer surface, a flexible split ring arranged between the bush shoulder, sleeve and nut fitted on the cylinder. The shell, in initial position, seats in side the said flexible split ring and is locked by easily deformable damper representing a sleeve arranged between the pyrotechnical lock casing and the shell. The said pyrotechnical casing is provided with seat intended for pyrocartridges furnished with channels to feed pyrogases to under the sleeve, and with union seat and channels to feed operating gas into the cylinder inner space.
EFFECT: expanded performances.
SUBSTANCE: invention refers to space engineering and may be used for installation on carrier-rocket and for separation from it of spacecraft (SC). Device includes transition frame mounted on carrier-rocket, device separating SC and carrier-rocket, and drive. This mechanism is made in form of movable rods installed in guides rectilinearly along SC periphery. Rods are kinematically connected with each other and drive by s forming kinematic circuit containing length-adjustable links. Levers are interacting with said rods essentially by ball-ends. Rods have transverse oval orifices for mating ball-ends.
EFFECT: increase of device reliability with possible significant centering dispersion of separated articles and power characteristics of drive and decrease of SC preparation time for flight.
2 cl, 5 dwg
SUBSTANCE: invention refers to space engineering and may be used for separation of essentially on-board plug-type connections connecting airborne vehicle with launching site. Mechanism contains on-board and detachable boards held by lock installed at detachable board side in hermetic cavity in that board. Lock includes collet and rod with bar hold made with ability to fix blades of collet by its ends, and also ball-end link. Mechanism is also supplied with support cartridge, sleeve, piston, spring, and stop. One ball-end link is placed in slot made in rod with bar hold interacting with sealing element installed at bottom of support cartridge. Support cartridge is secured on detachable board in said hermetic cavity. Sleeve is installed on support cartridge and it has lid. Piston is hollow, it is placed inside sleeve and it may slide inside. Inside piston there is spring interacting with inner surface and sleeve bottom. Stop is installed in through orifice made in sleeve side wall, it is supplied with fixing arm and contacts with outer surface of piston bottom. Other end of link has spherical support element interacting with piston bottom outer surface. Link has adjustable axial position. Piston bottom has through orifices. Distance between outer surface of piston bottom and sleeve lid is greater than fixing clearance of blades of collet by rod's end. Spring power is greater than collet clamp unlocking effort.
EFFECT: improvement of reliability of unit separation in operation.
FIELD: mechanics, transport.
SUBSTANCE: attachment device incorporated with spacecraft being detached from carrier rocket in orbit incorporates a hollow bolt with groove and locking blocks with external sleeve displaced with the help of drive. Note that aforesaid bolt is furnished with fast-action heater arranged in the bolt bore and connected to power supply.
EFFECT: higher reliability of spacecraft detachment, reduced impact loads on spacecraft.
2 cl, 1 dwg
SUBSTANCE: unit of joining contains the first and the second parts of connector, which are installed accordingly in detachable and board units of plug connection, bracket installed in detachable unit, and spring. Unit is additionally equipped with jacket and bracket installed in board unit. The first and the second parts of connector are tightly installed in vessels located inside jacket arranged in the form of cartridge. Jacket is equipped with supports that are tightly fixed in openings arranged on its side surface between the first and the second parts of connector and having axes that are evenly located in plane that is perpendicular to longitudinal axis of mentioned jacket. Jacket and vessel of the second connector part are equipped with shanks installed in brackets by means of adapters with external spherical surface that interacts with internal spherical surface of mentioned brackets. Spring is installed inside jacket between its bottom and vessel of the first connector part. Vessels of the first and second connector parts are sealed in relation to jacket.
EFFECT: higher reliability of joining unit operation.
FIELD: space engineering.
SUBSTANCE: device incorporates two turn units forming a geometrical axis of rotation. Every turn unit consists of a movable and fixed parts, the turn unit design allows its self-opening at the preset turn angle. Instructions for the last cutting in the engine of the rocket boost module, cutting of the independent power plant and its separation are generated in sequence providing for, in combination with the turn angle unit design, an impact less separation of the aforesaid power plant with the boost module elements.
EFFECT: impact less separation of the independent power plant in a wide range of turn angles.
2 cl, 8 dwg
FIELD: rocketry; small-caliber rockets and rocket parts.
SUBSTANCE: proposed unit includes two telescopically connected bushes and locking member made in form of split spring-loaded ring of round section. Diameter of ring section is dictated by uncoupling force. Outer bush is provided with trapezoidal groove at bevel angle of 25-30 deg.; inner bush is provided with rectangular groove for placing the split spring-loaded ring in sunken state.
EFFECT: enhanced reliability of coupling without access to joint; automatic uncoupling under action of pressure at preset load during preset period of time; low cost of manufacture of unit.
FIELD: coupling and uncoupling of space object parts.
SUBSTANCE: proposed device has body 1 with part 24 of lesser diameter and part 25 of larger diameter. Sleeve 2 consisting of hollow rod 3 and piston 4 is mounted in this body. Additional piston 6 with rod 20 is arranged inside piston 4. Attachment piece 17 mounted on rod 3 has the same diameter as part 24 of body. In initial state, frame 16 of object parts connected by means of attachment piece 17 and part 24 are clamped in between body butt 23 and nut 18. Piston 4 of sleeve has passages 5. Operation of charge 13 causes sets additional piston 6 together with rod 20 in motion and breaks neck 15 of rod 3. Motion of piston 6 gives access for gaseous products formed during operation of charge 13 to passages 5, thus throttling the gas. After break of neck 15, sleeve 2 moving as a unit till rest against nut 32 disengages its rod from attachment piece 17 and coupling between separable parts of object is removed. As a result, "smooth" joint is formed ensuring impactless separation of object parts.
EFFECT: reduction of impact pulse transmitted to structure of object in taking-up lateral loads till separation of object parts, avoidance of spurious twist of parts.
3 cl, 4 dwg
FIELD: electrical connectors used for coupling and uncoupling the electrical connectors of flying vehicles.
SUBSTANCE: proposed electrical connector unit has first and second parts, dowels, pins with spherical tips and springs. Bushes are mounted on first part. Dowels are secured on second part of connector. Each dowel is provided with tie-rod fitted coaxially relative to its axis. One end of tie-rod is connected with dowel by means of articulated bearing whose longitudinal plane is oriented to flying vehicle axis. Tie-rod is provided with locking and bearing bushes which are mounted at spaced relation. Locking bush is mounted movably for locking it on tie-rod. Bearing bush is engageable with butt surface of inner race of articulated bearing whose outer race is secured in bracket of second compartment. Spring is mounted on tie-rod and is engageable with locking and bearing bushes. Free end of tie-rod is received by hole of inner race of articulated bearing mounted in bracket of second compartment for limitation of axial motion. Spherical tips of pins are located at the same distance from dowel axis; they may be engageable with second part of connector in longitudinal plane of articulated bearing connecting the dowel with tie-rod.
EFFECT: enhanced reliability of unit at separation of compartments under action of operating loads.
FIELD: automotive industry.
SUBSTANCE: invention relates to truck tools boxes. Proposed box has polymer housing and cover with lock mechanism consisting of belt crank whose ends are hinge-coupled with rod locks engaging with stops secured on housing. Rods are fitted to pass through holes of guide plates made for connection with device designed for holding cover wide open. Housing consists of two parts interconnected by flanges forming rigidity rib. Planes of flange surfaces pointed to each other are square to plane of open end face of housing.
EFFECT: increased rigidity, strength and manufacturability of box, simple design and strong lock mechanism.
8 cl, 8 dwg