RU2816372C1 - Launch vehicle nose cone reusable flap and landing method thereof - Google Patents

Abstract

FIELD: cosmonautics.

SUBSTANCE: group of inventions relates to space engineering. Reusable flap of carrier rocket nose cone consists of rounded nose part, front cone and cylindrical part ending with rear truncated inverse cone. Transverse load-bearing plate resting on the power set of the flap is installed inside. On the transverse power plate there is a rotor attachment assembly for lowering the flap in the Earth's atmosphere "as a helicopter", wherein flap safe landing cushion made of tight fabric is secured on rear truncated inverted cone on its outer side under protective plate. Method of landing reusable flap of nose cone of carrier rocket consists of stages of flaps separation, their separation from carrier rocket and further stages of movement to the Earth. Last stage consists of separation of flap of small nose cone, release of rotor blades and their withdrawal into working position, transition to autorotation mode and oriented position of flap relative to direction of incoming air flow, maintaining constant preset rotor rpm by controlling the total pitch of the blades when passing the trajectory section with high velocity head and maintaining the rotor rpm. Safe landing cushion is changed over to the working condition.

EFFECT: higher reliability of landing.

9 cl, 1 dwg

Description

Field of technology

The invention relates to the field of rocket technology and can be used in the creation of return flaps of the head fairings of space launch vehicles.

State of the art

One of the important modern directions in the development of rocket technology is the reusability of its elements, in particular, the first and second stages of space launch vehicles. This allows you to reduce the cost of one launch and the time to prepare the next launch.

The same elements of space technology that could become reusable include the head fairing, which is designed to protect the payload of the launch vehicle being launched into orbit from large mechanical and thermal loads at the launch site and is separated from the launch vehicle at a high altitude only after passing areas with high speed pressure. The head fairing is a complex technical device, the cost of which can reach 10% of the cost of launching a launch vehicle.

There is a well-known Chinese project on the use of a parachute system for the rescue and controlled descent of the nose fairing flaps of launch vehicles (magazine “All about Space” dated July 26, 2021), accepted as an analogue, which is based on the use of a parachute system for the controlled descent of the nose fairing flaps to Earth. The fairing flaps fall to a certain height and reach the appropriate conditions suitable for parachute deployment. The parachute then opens to slow the fall of the flap. At a certain altitude, the braking parachute separates, the parafoil opens, and secondary braking and process control begin. The fairing flap then lands in a safe area in a controlled manner. The advantage of the planting method and the design that implements this method is its simplicity. At the same time, a significant drawback of the method is the low accuracy of ensuring the specified landing coordinates and the low reliability of maintaining the integrity of the sash structure during landing.

The media knows of a project to save the wings of the head fairing of the private US company SpaceX, adopted as a prototype, in which, shortly after the separation of the first stage, when the rocket exits the dense layers of the atmosphere, the head fairing is dropped in the form of two separate wings. Each fairing flap is equipped with nitrogen engines to control orientation in a vacuum and a parafoil control system, providing a smooth, controlled splashdown at a given point with an accuracy of 50 m. To avoid contact of the flap with water, SpaceX tries to catch it in a grid with an area of ~3716 m ² , stretched like a trampoline over fast ships. The disadvantage of this method is the indispensable presence of a warm sea in the country launching launch vehicles, and if it is available, the need to create special vessels and nets. In this case, the difficulty of catching the head fairing doubles, since each of the two flaps moves towards the ground independently.

Thus, none of the known technical solutions are the only possible and finally accepted in the industry and therefore require further research and development.

The reason preventing the solution of the technical problem of creating a reusable wing of the head fairing of a launch vehicle and a method for landing it is the absence to date of projects that provide the necessary reliability of solving the problem at a relatively low cost of project implementation.

Disclosure of the invention

A design is proposed for a reusable flap of the head fairing of a launch vehicle and a method for landing it, containing a main rotor and a control system that ensures descent in the Earth’s atmosphere “helicopter-style” in the autorotation mode of the main rotor when moving along the descent trajectory at variable speed in an environment with varying density and soft landing using a safe landing cushion.

a. The reusable flap of the launch vehicle's head fairing consists of a front cone, a cylindrical part ending in a rear truncated reverse cone. On the transverse force plate, resting on the internal force set of the sash, there is a main rotor attachment unit for lowering the sash in the Earth’s atmosphere “like a helicopter.” On the rear truncated reverse cone, on its outer side under the protective plate, a cushion for safe landing of the sash made of sealed fabric is fixed in the folded state.

b. The main rotor attachment unit for lowering the shutter in the Earth's atmosphere "in a helicopter" consists of a stationary power pipe in which is fixed a rotating pipe with a main rotor hub fixed on top of it, capable of rotating together with the blades fixed in the hub during the descent section in the autorotation mode. To control the overall pitch of the blades, they are inserted into the bushing with their own axial hinge. To ensure rotation of the blade relative to the hinge axis, a reversible stepper motor is used, inserted into the bushing along with a blade rotation angle sensor.

c. When the launch vehicle is launched, two main rotor blades are rotated relative to their horizontal hinges, pressed against the generatrix of the front cone of the flap and attached to it at the end using a bracket with a pyrobolt and a spring pusher. The vertical hinge of the blade is located between the axial and horizontal hinges.

d. The flap is equipped with a control system, including control of the number of rotations of the main rotor when moving along the descent trajectory at variable speed in an environment with varying density. The control system consists of an electric battery, an on-board computer, a rotor speed sensor and stepper motors with blade angle sensors to control the overall pitch of the blades.

e. The main rotor attachment point is closed on top by a small head fairing flap, which serves as protection for the conical part of the head fairing from mechanical and thermal loads in the launch vehicle launch area.

f. The small head fairing flap is fastened to the head fairing flap along the upper and lower planes of the pyrobolts installation.

g. The separation and separation of the small head fairing flap from the head fairing flap is ensured thanks to the same devices that are used to separate and separate the head fairing flaps from the launch vehicle, namely, two spring pushers on pyrobolts and an axial hinge also on pyrobolts.

h. The cushion for the safe landing of the sash is secured with a compressed air cylinder and fittings, which ensures a soft landing of the sash after the protective plate is shot off and filled with air.

i. The method of landing a reusable flap of the head fairing of a launch vehicle consists of the stages of separating the flaps, separating them from the launch vehicle and further independent movement towards the Earth and is controlled using a control system. It consists of several stages. The initial stage of separation of the small head fairing flap. The stage of releasing the main rotor blades and bringing them into working position due to the incoming air flow during chaotic rotation of the shutter at the initial stage. The stage of transition to the autorotation mode and the oriented position of the leaf relative to the direction of the oncoming air flow. The stage of maintaining constant set rotor speeds by controlling the overall pitch of the blades when passing through a section of the trajectory with a high speed pressure. The stage of maintaining rotor speed, providing maximum lifting force of the blades, after entering the trajectory section with a steady low speed pressure and a minimum vertical descent speed. The stage of transferring the safe landing airbag into a working state in the shape of a torus and landing in this state with possible breakage of the blades when the sash overturns, but maintaining the integrity of the sash.

The objective of this invention is to develop a reusable flap of the head fairing of a launch vehicle based on the use of a main rotor to implement a method for landing it “like a helicopter” and increasing the reliability of its preservation during landing.

The problem is solved by the fact that a reusable flap of the head fairing of a launch vehicle, consisting of a front cone, a cylindrical part ending with a rear truncated reverse cone, according to the invention, a transverse force plate resting on the internal force set of the flap is installed, a main rotor attachment unit is installed on the transverse force plate to lower the sash in the Earth's atmosphere "helicopter-style", while on the rear truncated reverse cone on its outer side under the protective plate, a cushion for the safe landing of the sash made of sealed fabric is fixed in the folded state.

The main rotor mounting unit for lowering the shutter in the earth's atmosphere "like a helicopter" consists of a stationary power pipe in which is fixed a rotating pipe with a main rotor hub fixed on top of it, capable of rotating together with the blades fixed in the hub during the descent section in the autorotation mode, Moreover, to control the overall pitch of the blades, they are inserted into the bushing with their axial hinge, and to ensure rotation of the blade relative to the hinge axis, a reversible stepper motor is used, inserted into the bushing along with a blade rotation angle sensor.

When the launch vehicle is launched, two main rotor blades are rotated relative to their horizontal hinges, pressed against the generatrix of the front cone of the flap and attached to it at the end using a bracket with a pyrobolt and a spring pusher, while the vertical hinge of the blade is located between the axial and horizontal hinges.

The flap is equipped with a control system, including control of the number of rotor revolutions when moving along a descent trajectory with variable speed in an environment with changing density, consisting of an electric battery, an on-board computer, a rotor speed sensor and stepper motors with blade rotation angle sensors for control common pitch of the blades.

The main rotor attachment point is closed on top by a small head fairing flap, which serves as protection for the conical part of the head fairing from mechanical and thermal loads in the launch vehicle launch area.

The small head fairing flap is fastened to the head fairing flap along the upper and lower planes of the pyrobolts installation.

The separation and separation of the small head fairing flap from the head fairing flap is ensured thanks to the same devices that are used to separate and separate the head fairing flaps from the launch vehicle, namely, two spring pushers on pyrobolts and an axial hinge also on pyrobolts.

The cushion for the safe landing of the sash is secured with a compressed air cylinder and fittings, which ensures a soft landing of the sash after the protective plate is shot off and filled with air.

A method for landing a reusable flap of the head fairing of a launch vehicle, consisting of the stages of separating the flaps, separating them from the launch vehicle and further independent movement towards the Earth, according to the invention, the stage of further movement towards the Earth is controlled using a control system, it consists of the initial stage of separating the flap small head fairing, releasing the main rotor blades and bringing them into operating position due to the incoming air flow during chaotic rotation of the shutter at the initial stage, switching to the autorotation mode and the oriented position of the shutter relative to the direction of the oncoming air flow, maintaining constant set rotor speeds by controlling the general pitch of the blades when passing a section of the trajectory with a high speed pressure and maintaining rotor speeds that provide maximum lifting force of the blades, after entering the section of the trajectory with a steady low speed pressure and a minimum speed of vertical descent, transferring the airbag to a working state in the shape of a torus and landing in this state with possible breakage of the blades when the sash is tipped over, but maintaining the integrity of the sash.

The essence of the invention is illustrated by the drawing.

Figure 1 shows a diagram of a reusable flap of the head fairing of a launch vehicle.

In this diagram:

1 - front cone;

2 - cylindrical part;

3 - rear cone;

4 - force plate;

5 - fixed pipe;

6 - rotating pipe;

7 - bushing;

8 - horizontal hinge;

9 - blade;

10 - vertical hinge;

11 - bracket;

12 - small head fairing flap; 13-pillow folded.

Carrying out the invention

An example of a possible implementation of the proposed technical solution.

The reusable flap of the head fairing of the launch vehicle consists of a front cone 1, a cylindrical part 2, a rear truncated reverse cone 3, a power plate 4 on which a main rotor attachment unit is installed, consisting of a stationary power pipe 5, a rotating pipe 6 with a rotor attached to it on top sleeve 7, into which the main rotor blades 11 are inserted with their axial hinges. The rotation of the blades in the axial hinge is ensured by reversible stepper electric motors inserted into the sleeve together with sensors for the angles of rotation of the blades (not shown in Fig. 1). When the launch vehicle is launched, the blades 11 are rotated relative to their horizontal hinges 8, pressed against the generatrix of the front cone of the flap and attached to it at the end using a bracket 11 with a pyrobolt and a spring pusher, while the vertical hinge 10 of the blade is placed between the axial hinge and the horizontal hinge 8. The flap is equipped with a control system consisting of an electric battery, an on-board computer, a rotor speed sensor and stepper motors with blade rotation angle sensors (not shown in Fig. 1). The main rotor mounting unit is closed on top by the flap of the small head fairing 12, which is attached to the head fairing flap along the upper and lower planes of installation of the pyrobolts (not shown in Fig. 1). The separation and separation of the small head fairing flap from the head fairing flap is ensured by two spring pushers on pyrobolts and an axial hinge also on pyrobolts (not shown in Fig. 1). On the rear truncated reverse cone, on its outer side under the protective plate, a cushion 13 for safe landing of the shutter made of sealed fabric, a compressed air cylinder and fittings (not shown in Fig. 1) are fixed in the folded state.

The reusable flap at the moment of separation from the launch vehicle has the following characteristics. The length of the leaf is 15 m, the diameter of its cylindrical part is 5.1 m, the mass of the leaf is 1.5 tons. The length of the main rotor blades is 6.0 m, the width is 0.3 m.

As a result of the application of the present invention, a technical solution aimed at developing a reusable flap of the head fairing of a launch vehicle and a method for landing it in order to reduce the cost of production and operation of the head fairing, as well as increasing the reliability of preserving the flaps, is implemented through the use of a main rotor that ensures the descent of the flap in the Earth’s atmosphere in the “helicopter-style” autorotation mode, and the use of a safe landing cushion for the flap, ensuring its soft landing.

Claims (9)

1. A reusable flap of the head fairing of a launch vehicle, consisting of a front cone, a cylindrical part ending with a rear truncated reverse cone, characterized in that a transverse force plate resting on the internal power set of the flap is installed, and a main rotor attachment unit for descent is installed on the transverse force plate flap in the Earth's atmosphere "in a helicopter", while on the rear truncated reverse cone on its outer side under the protective plate, a cushion for the safe landing of the flap made of sealed fabric is fixed in the folded state. 2. The flap according to claim 1, characterized in that the main rotor attachment point for lowering the flap in the Earth’s atmosphere “helicopter-style” consists of a stationary power pipe in which is fixed a rotating pipe with a main rotor hub fixed on top of it, capable of rotating together with blades fixed in the bushing in the descent section in autorotation mode, while to control the overall pitch of the blades they are inserted into the bushing with their axial hinge, and to ensure rotation of the blade relative to the hinge axis, a reversible stepper motor is used, inserted into the bushing along with a blade rotation angle sensor. 3. The flap according to claim 2, characterized in that when the launch vehicle is launched, two main rotor blades are rotated relative to their horizontal hinges, pressed against the generatrix of the front cone of the flap and attached to it at the end using a bracket with a pyrobolt and a spring pusher, in this case, the vertical hinge of the blade is located between the axial and horizontal hinges. 4. The flap according to claim 3, characterized in that it is equipped with a control system, including control of the number of revolutions of the main rotor when moving along a descent trajectory at variable speed in an environment with varying density, consisting of an electric battery, an on-board computer, and a speed sensor rotor and stepper motors with blade angle sensors to control the overall pitch of the blades. 5. The flap according to claim 2, characterized in that the main rotor attachment point is closed on top by the flap of a small head fairing, which performs the function of protecting the conical part of the head fairing from mechanical and thermal loads at the launch site. 6. The flap according to claim 5, characterized in that the fastening of the small head fairing flap to the head fairing flap is carried out along the upper and lower planes of installation of the pyrobolts. 7. The flap according to claim 6, characterized in that the separation and separation of the small head fairing flap from the head fairing flap is ensured thanks to the same devices that are used to separate and separate the head fairing flaps from the launch vehicle, namely two spring pushers on pyrobolts and the axial hinge also on pyrobolts. 8. The sash according to claim 6, characterized in that the safe landing cushion of the sash is secured with a compressed air cylinder and fittings that ensure a soft landing of the sash after the protective plate is shot off and filled with air. 9. A method of landing a reusable flap of the head fairing of a launch vehicle, consisting of the stages of separating the flaps, separating them from the launch vehicle and further independent movement towards the Earth, characterized in that the stage of further movement towards the Earth is controlled using a control system, it consists of the initial stage of separating the flap of the small head fairing, releasing the main rotor blades and bringing them into working position due to the incoming air flow with chaotic rotation of the flap at the initial stage, switching to the autorotation mode and the oriented position of the flap relative to the direction of the oncoming air flow, maintaining constant specified rotor speed propeller by controlling the overall pitch of the blades when passing through a section of the trajectory with a high speed pressure and maintaining rotor speeds that provide maximum lifting force of the blades, after reaching the section of the trajectory with a steady low speed pressure and a minimum speed of vertical descent, transferring the safe landing airbag to the working state in the shape of a torus and landing in this state with possible breakage of the blades when the sash overturns, but maintaining the integrity of the sash.

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