RU2624895C1 - System of astronaut fixation while moving along the external surface of space object (versions) and the method of its operation (versions) - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: group of inventions refers to means of ensuring safe activity at the external surface of space object (SO), for example, an orbital station (OS). The system of astronaut fixation while moving along the external surface of the SO includes handrails, rigidly fixed on the external surface of SO body, a safety wrench fixed to the astronaut's suit with a slidewire, a free end of which is fixed on the external surface of the SO. The system incorporates brackets with flat spirals, each of which is made of conjugated concentric loops, or with rigid plates, each of which has a central hole that passes into the annular section in the form of a through slot with a slit of plate outer contour. In the method of operating the system, the slidewire is introduced, as it unwinds, between the loops of spiral or through the slot of plate outer contour with pulling the slidewire in the direction of motion of the astronaut.

EFFECT: increasing the safety, reliability and speed of astronaut fixation.

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Description

The invention relates to space technology, in particular, to means for ensuring the activities and safety of an astronaut in open space, including on the outer surface of a space object, for example, an orbital station (OS), and can also be used in various types of installation works in other environments for laying flexible long products: cables, hoses, etc.

Fixation under zero gravity refers to the artificial limitation of the number of degrees of freedom of one object in relation to another - the base, by imposing bonds of different rigidity. (OS Tsygankov. Labor activity in unsupported space. // Flight. No. 2. 2002, p. 6).

Reliable communication of the astronaut with the OS during operations on its outer surface, eliminating the possibility of unauthorized separation of the astronaut from the station is the dominant task in organizing and providing technical support for extra-ship activity (VCA). To this end, the surface of the OS is equipped with handrails mounted on racks located along the highway based on design considerations.

Famous Russian spacesuit for VKD "Orlan-D" (1977-1984), equipped with a safety rope with a carbine (IP Abramov and other space suits of Russia. // JSC "Scientific and Production Enterprise" Star ". Moscow. 2005. P. 339, Fig. 8.1-1). The astronaut moves along the handrails with the help of hands, while sliding the carabiner of the safety rope, fixed by the handrail, from rack to rack, providing communication with the OS, this fixation method requires a large number of carabiner hitching in racks, which causes excessive muscle fatigue -bending flexors of the astronaut’s hands and fingers in inflated gloves.

The structure of the Orlan-DMA spacesuit (1988-1997), with the transition to autonomous power supply and wireless communications, introduced a second safety rope for parallel use (IP Abramov et al. Space spacesuits of Russia. // OJSC " Scientific and Production Enterprise Zvezda, Moscow, 2005, p. 341) This increased the reliability of fixing the astronaut to the OS, but increased the load on the astronaut’s hands even more, since it was required to retrieve two carbines for each step during movement .

In the Orlan-M spacesuit (for the Mir orbital station and the ISS since 1998), one of the 2 safety files was made of variable length (IP Abramov et al. Space spacesuits of Russia. // JSC Scientific Zvezda manufacturing enterprise. Moscow. 2005, p. 342, Fig. 8. 2-1; Patent RU 2528504, published on 09/20/2014, IPC: B64G 1/66 (2006.01)). Such a solution reduced the number of transfers in a working zone with a radius of 2.5-3 m, but when moving on handrails, the need to carry out the transfers of 2 carbines remained, which does little to reduce the astronaut’s energy consumption in the VCF process.

Known means of fixing the astronaut on the spacecraft body (patent RU 2053942, publ. 02/10/1996, IPC: B64G 1/66 (2006.01)), containing handrails, rigidly fixed to the outer surface of the spacecraft’s body, and equipped with halyards and elastic elements located along the track of the handrail, one end of each halyard is rigidly fixed on one of the handrails, and the second end is provided with a ring and is mounted with the possibility of sliding on the corresponding elastic element rigidly connected with the handrail. The proposed tool could slightly reduce the number of transfers of the carabiner safety harness, however, the halyard, which is part of this tool, along its length can cover no more than 2-3 intervals between the racks. The need for exchanges remains, while hooking a carbine to the ring at the end of the soft halyard with one hand is not possible, while the astronaut's second hand should be held by the handrail. In addition, the entire structure as a whole clutters the space along the rail of the handrail and unnecessarily increases the total mass of the object.

(IAC-02-IAA.10.1.02. Russian-American Cooperation in EVA Area (from Russian Perspective). OS Tsygankov // 53 ^rd International Astronautical Congress. The Word Space Congress-2002 10-19 Oct 2002 / Houston, Texas, p. 4). A well-known system for fixing an astronaut when moving along the outer surface of a space object includes handrails rigidly fixed to the outer surface of the space object’s body, a safety winch with a safety cable fixed on the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element located on the outer surface of the space object. When the astronaut moves, as he moves away from the fastening point of the carabiner, the cable is etched, and on return, it is wound on a drum.

As a prototype of the method of operating this system, O.S. Tsygankov was chosen. Beginning of cooperation between Russia and the United States in the field of extra-ship activity. // Manned space flights. Scientific and technical journal No. 1, 2014, FSBI SRI named after Yu.A. Gagarin ", p. 111). A known method of operating this astronaut fixation system when moving along the outer surface of a space object involves attaching a safety winch with a safety rope to the astronaut's spacesuit, the free end of which is fixed to a fixed structural element on the outer surface of the space object (Fig. 5).

This system and the method of its operation excludes the transfer of the carbine along the track of the handrail. However, the surface of the OS contains many protruding elements: targets, sensors, antennas, solar panels, drain valves, cable routes, scientific equipment, and many others. etc. It is impossible to exclude winding, engagement of the etched cable for the protruding elements when the astronaut moves, when the direction of movement changes to angles up to 90 °, when moving along an arc of cylindrical surfaces, when moving from one module to another, it is connected perpendicular to the x axis of the OS and t .P. Cable engagement is a danger to both the astronaut and external equipment, especially when returning to the airlock. In addition, if the astronaut accidentally separates from the station, there is a danger of his removal along the entire length of the etched cable with an inevitable jerk at the point of fastening of the cable, which is categorically unacceptable.

The objective of the proposed inventions is to ensure the reliability and speed of fixation of astronauts, freeing from the need to carry out retransfer of safety rope carabiners while moving, eliminating unauthorized separation of the astronaut from the space object, saving time in VCS sessions for target operations, preventing uncontrolled migration of the safety rope over the surface of the space object.

The technical result of the inventions is to increase the safety, reliability, ergonomics and speed of fixation of the astronaut when moving on the outer surface of a space object, as well as preventing uncontrolled migration of the safety rope over the surface of the space object.

The technical result is achieved by the fact that in the astronaut’s fixation system when moving along the outer surface of the space object (option 1), including handrails rigidly attached to the outer surface of the space object’s body, a safety winch with a safety cable fixed to the astronaut’s spacesuit, the free end of which is fixed on a fixed structural element located on the outer surface of the space object, introduced brackets with flat spirals, each of which is made of interconnected concentric turns according to the scheme: 0.75 of the internal turn +0.75 of the external turn and is rigidly fixed to the handrails through the bracket (Fig. 2, 3, 4), while taking into account the following conditions:

L is the distance between the turns of the spiral, mm;

D is the inner diameter of the spiral, mm;

d is the diameter of the safety cable, mm,

moreover, the spirals are installed at the beginning and end of the straight sections, at the turns and kinks of the rail of the handrail with a step comparable to the functional reach of the cosmonaut's outstretched arm (Fig. 6).

The technical result is also achieved by the fact that in the method of operating the astronaut’s fixation system when moving along the outer surface of a space object (option 1), which includes attaching a safety winch with a safety rope to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element on the outer surface of the space object , as the safety cable is unwound, it is inserted between the turns of the spiral, tucked into the spiral and the safety cable is pulled in to a systematic way of movement of the astronaut.

The technical result is achieved by the fact that the astronaut’s fixation system when moving along the outer surface of the space object (option 2), including handrails rigidly attached to the outer surface of the space object’s body, a safety winch with a safety cable fixed to the astronaut’s spacesuit, the free end of which is fixed on a fixed a structural element located on the outer surface of the space object, brackets with rigid plates are introduced, in each of which a central a hole opening into the annular portion in the form of a through groove extending 270 ° around the circumference and having a cutout of the outer contour of the rigid plate with a width equal to the width of the through groove made concentrically with the central hole (Figs. 7, 8, 9), taking into account the following conditions:

L is the width of the through groove or slot of the outer contour of the rigid plate, mm;

D is the diameter of the Central hole, mm;

d is the diameter of the safety cable, mm,

moreover, the plates are rigidly fixed to the handrails through the brackets and installed at the beginning and end of the straight sections, at the turns and kinks of the handrail path, in increments comparable to the functional reach of the astronaut’s outstretched arm (Fig. 6).

The technical result is also achieved by the fact that in the method of operating the astronaut’s fixation system when moving along the outer surface of a space object (option 2), which includes attaching a safety winch with a safety cable to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element on the outer surface of the space object , as the safety cable is unwound, it is inserted through the slot of the outer contour of the plate into the through groove, then the safety cable is guided through the through th slot, it is charged into the central hole and produce broach tether in the direction of movement of the astronaut.

Formulas (1) - (4) are justified as follows.

The dependences (1.2 ÷ 1.4) d and (1.4 ÷ 1.6) d determine the gaps that ensure the free introduction of the cable between the turns or into the through grooves and the cable wiring inside the spiral or groove, which is confirmed experimentally under conditions of weightlessness modeling when flying on an airplane.

From the position of ergonomics of extra-ship activity, the distance between the turns of the spiral and the width of the groove L should be within the resolution of the astronaut in the spacesuit to work with small objects, that is, at least 12 mm.

The internal diameter of the spiral and the central hole in the rigid plate D must comply with "Industry standard OST 134-1004-95. Means of fixation for extra-ship activity. General technical requirements", clause 4.1.6.9: "The holes (round or other shape) must be transverse size not less than 30 mm. " This requirement is presented in order to avoid pinching in the hole of the finger, the diameter of which in the inflated glove is 30 mm, and also to ensure that the astronaut can perform manual manipulations in inflated gloves.

The definition of L (mm) and D (mm) was carried out according to the proposed formulas (1), (2) or (3), (4) for some points in the range d = 3 ÷ 50 mm (table).

From the table it follows that in some situations, with small cable diameters, for example, in the range d = 3 ÷ 8 mm, the distance L determined by formula (1) is not sufficient for the astronaut to work in a spacesuit, therefore, L = 12 mm .

Similarly, with a cable diameter in the range d = 3 ÷ 18 mm, the diameter D obtained by formula (2) is ergonomically unacceptable, therefore, D = 30 mm is performed.

With a cable diameter d> 8 mm for determining L and d> 10 mm for determining D, the proposed formulas are valid taking into account the right-hand sides of the inequalities indicating the minimum allowable sizes L and D.

The invention is illustrated by graphic materials: table and FIG. 1-9.

The table shows the results of determining L and D according to the proposed formulas (1), (2) or (3), (4) for some points in the range d = 3 ÷ 50 mm.

In FIG. Figure 1 shows a diagram of an astronaut’s fixation system when moving along the outer surface of a space object (options).

In FIG. 2 is an example of mounting a bracket with a flat spiral to a handrail (front view).

In FIG. 3 is an example of fixing a bracket with a flat spiral to a handrail (side view).

In FIG. 4 - a flat spiral.

In FIG. 5 - fastening the safety winch on the spacesuit and the free end of the safety cable to a fixed structural member on the outer surface of the space object.

In FIG. 6 is an example of a possible arrangement of brackets with flat spirals or rigid plates with grooves on the outer surface of a space object.

In FIG. 7 is an example of mounting a bracket and a rigid plate with a groove to a handrail (front view).

In FIG. 8 is an example of mounting a bracket and a rigid plate with a groove to a handrail (side view).

In FIG. 9 - a rigid plate with a groove.

The following notation is introduced in the figures:

1 - safety winch;

2 - safety cable;

3 - fixed structural element on the outer surface of a space object;

4 - bracket;

5 - a flat spiral;

6 - fastening element (lock) of the bracket to the handrail;

7 - handrail;

8 - rack;

9 - inner loop;

10 - external coil;

11 - through groove;

12 is a rigid plate.

There are two options for the fixation system: with flat spirals from bar material (option 1); with rigid plates with through grooves and central holes (option 2).

The astronaut’s fixation system when moving along the outer surface of the space object according to the first embodiment (Fig. 1) includes handrails 7 that are rigidly fixed on racks 8 of the outer surface of the space object’s body, a safety winch 1 with a safety cable 2, the free end of which is fixed to a fixed structural member 3 located on the outer surface of the space object, brackets 4 with flat spirals 5 are introduced into it, each of which is made of oboj concentric coils according to the scheme: the inner coil 9 0.75 0.75 + 10 and the outer coil is rigidly attached to the railing bracket 4 through 7, such as lock 6, while taking into account the following conditions:

L is the distance between the turns of the spiral, mm;

D is the inner diameter of the spiral, mm;

d is the diameter of the safety cable, mm,

moreover, the spirals are installed at the beginning and end of the straight sections, at the turns and kinks of the rail of the handrail, with a step comparable to the functional reach of the astronaut’s outstretched arm (Fig. 7).

The method of operating the astronaut’s fixation system when moving along the outer surface of a space object according to the first embodiment involves attaching a safety winch 1 with a safety rope 2 to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural member 3 on the outer surface of the space object (Fig. 6), as unwinding the safety cable 2 introduce it between the turns 9 and 10 of the spiral 5, tuck it into the spiral 5 and pull the safety cable 2 in the direction of movement of the cosmos navta.

According to the second option, the astronaut’s fixation system when moving along the outer surface of the space object (Fig. 1), including handrails 7, rigidly mounted on the racks 8 of the outer surface of the space object’s body, a safety winch 1 with a safety cable 2, the free end of which is fixed on the astronaut’s spacesuit on a fixed structural member 3 located on the outer surface of the space object, brackets 4 with rigid plates 12 are inserted into it, in each of which a central hole is made A hole that passes into the annular portion in the form of a through groove 11 extending 270 ° around the circumference and having a cut of the outer contour of the rigid plate 12 with a width equal to the width of the through groove 11 made concentrically with the central hole, taking into account the following conditions:

L is the width of the through groove and the slots of the outer contour of the rigid plate, mm;

D is the diameter of the Central hole, mm;

d is the diameter of the safety cable, mm,

moreover, the plates 12 are rigidly fixed to the handrails 7 through brackets 4, for example, by a lock 6, and are installed at the beginning and end of straight sections, at the turns and kinks of the handrail 7, with a step comparable to the functional reach of the cosmonaut's outstretched arm (Fig. 7).

The method of operating the astronaut’s fixation system when moving along the outer surface of a space object according to the second embodiment involves attaching a safety winch 1 with a safety cable 2 to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural member 3 on the outer surface of the space object (Fig. 5), as unwinding the safety cable 2 introduce it through the slot of the outer contour of the plate 12 into the through groove 11, then hold the safety cable 2 through the groove 11, tuck it into the center ral hole and pull the safety cable 2 in the direction of movement of the astronaut.

The invention can be used for laying various flexible, lengthwise products of different diameters: cables, cables, hoses, etc.

The choice of materials and manufacturing technologies is provided: according to the first option - winding from bar and tubular blanks; according to the second option - machining, stamping, casting.

Claims (16)

1. The astronaut’s fixation system when moving along the outer surface of a space object, including handrails rigidly fixed on the outer surface of the space object’s body, a safety winch with a safety cable fixed to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element located on the outer surface of the space object characterized in that brackets with flat spirals are introduced into it, each of which is made of concentric mating with each other It can be used as follows: 0.75 internal turns + 0.75 external turns and is rigidly fixed to the handrails through the bracket, while taking into account the following conditions: L = [(1.2 ÷ 1.4) d] ≥ (12 ± 2) mm; D = [(1.4 ÷ 1.6) d] ≥ (30 ± 2) mm, where L is the distance between the turns of the spiral, mm; D is the inner diameter of the spiral, mm; d is the diameter of the safety cable, mm, moreover, flat spirals are installed at the beginning and end of straight sections, at turns and kinks of the rail of the handrail, with a step comparable to the functional reach of the cosmonaut's outstretched arm. 2. A method of operating the astronaut’s fixation system when moving along the outer surface of a space object, including attaching a safety winch with a safety rope to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element on the outer surface of the space object, characterized in that, as the safety rope is unwound, they are introduced it between the turns of the spiral, tuck it into the spiral and pull the safety cable in the direction of the astronaut's movement. 3. The astronaut’s fixation system when moving along the outer surface of the space object, including handrails rigidly fixed to the outer surface of the space object’s body, a safety winch with a safety cable fixed to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element located on the outer surface of the space object characterized in that brackets with rigid plates are introduced into it, in each of which a central hole is made, passing into the annular section in the form of a through groove with a length of 270 ° around the circumference and having a cut of the outer contour of the rigid plate with a width equal to the width of the through groove made concentrically with the central hole, taking into account the following conditions: L = [(1.2 ÷ 1.4) d] ≥ (12 ± 2) mm; D = [(1.4 ÷ 1.6) d] ≥ (30 ± 2) mm, where L is the width of the through groove or slot of the outer contour of the hard platinum, mm; D is the diameter of the Central hole, mm; d is the diameter of the safety cable, mm, moreover, the plates are rigidly fixed to the handrails through the brackets and installed at the beginning and end of the straight sections, at the turns and kinks of the handrail, with a step comparable to the functional reach of the astronaut’s outstretched arm. 4. A method of operating the astronaut’s fixation system when moving along the outer surface of a space object, including attaching a safety winch with a safety rope to the astronaut’s spacesuit, the free end of which is fixed to a fixed structural element on the outer surface of the space object, characterized in that, as the safety rope is unwound, they are introduced it through the slot of the outer contour of the plate into the through groove, then hold the safety cable through the through groove, tuck it into the central Erste and produce broach tether in the direction of movement of the astronaut.

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