Patent ID: 11932424
Assignee: ROMAN NAWOJCZYK
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 5:
6. The system according to claim 1,
wherein the dividable sectional load cover comprises:
four cog beams that are rectangular in a cut-view;
two sections of load cover each comprising;
two rectangular tubes;
two hoisting gears each comprising;
one servomotor with a reduction gear; and
one cog wheel fitted with all cogs on the cog beam;

two rotating heads each comprising;
one servomotor with a reduction gear; and
one rotating axle;

wherein all cog beams are rectangular in the cut-view and are placed slidingly inside the rectangular tubes;
wherein inside the sectional load cover each cog beam is held up by means of one hoisting gear;
wherein each hoisting gear is mounted adjacent the rectangular tubes and inside the sectional load cover;
wherein all cog beams protrude suitably up over the hoisting gears inside the sectional load cover to enable its initial lifting;
wherein each hoisting gear is driven by one servomotor with one reduction gear which rotates the cog wheel that is fitted with all cogs on the cog beam;
wherein each cog beam is revolvingly installed to the space rocket fuselage by means of the rotating head;
wherein each rotating head is mounted inside the space rocket;
wherein each rotating head is driven by one servomotor with one reduction gear which rotates the rotating axle;
wherein to each rotating axle is permanently fastened one cog beam;
wherein each one section of the sectional load cover is held up and inclined by two cog beams;
wherein all cog beams are situated outside of the space rocket and outside of a second stage rocket;
wherein two cog beams are situated on one side of the space rocket and two other cog beams are situated on the opposite side of the space rocket;
wherein the entire dividable sectional load cover is configured to be revolvingly installed on the space rocket upper part and being situated over the second stage rocket;
wherein the dividable sectional load cover is configured to open by parting into two sections by folding outward, and is configured to close by folding up both sections, and is configured to cover a payload when closed, thereby creating thermal protection during the space rocket ascent and descent in the atmosphere;
wherein the dividable sectional load cover is adapted to be suitably lifted over the second stage rocket before folding out on two opposite sides; and
wherein the dividable sectional load cover is adapted to be thoroughly lowered to the space rocket upper part when the second stage rocket is not used.