RU2768801C1 - Device of the system for ensuring the landing of the spent stage with a reusable liquid rocket engine and a rocket stage - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: group of inventions relates to ground-based mesh-type means for ensuring the landing of spent launch vehicle (LV) stages containing reusable liquid rocket engines, as well as to the design of such stages. In the proposed device, some ends of the cables are fixed concentrically around the circumference of the annular cable, attached along the periphery to the supports in a plane parallel to the landing table, spaced from it in height. The second ends of the cables are similarly fixed to the attachment points placed on the platform in the plane of this table with the possibility of displacement by the drive around the longitudinal axis of the table and thereby forming a single-cavity cable hyperboloid with a receiving window along the longitudinal axis of symmetry of the table. The platform can move horizontally using a coordinate mechanism. At the same time, the aerodynamic stabilizers of the stage are installed above its center of mass, are made extendable and with locks of movement relative to the cables.

EFFECT: formation of a “window” close to a round one for receiving the LV stage and ensuring its movement with tracking the movement of the stage in the horizontal plane, as well as providing a pliable touch with the stage of the trapping device.

6 cl, 17 dwg

Description

The invention relates to the field of rocket and space technology, and more specifically to landing system devices, and can be used to create devices for landing systems for launch vehicles for launching commercial objects into orbit, providing the return and rescue of spent propulsion units, including fuel tanks and reusable liquid rocket engines of the first stages of the rocket, which is an urgent task when performing commercial launches.

Known systems for the return of a rocket propulsion unit using parachute systems, projects for the return of a rocket unit using an aerodynamic wing with approach and landing at the airfield (RF patent No.

The disadvantage of such a rescue system is the need to introduce aircraft systems into the design of the rocket block, supplementing the first stage of the rocket block to the version of the cruise missile block, which, although it allows the stage to land by planning on the return airfield, however, increases the weight and supplements with new control systems, which is not always advisable, especially to ensure the return of already developed launch vehicles and those widely used for launching useful commercial cargo.

A device for landing the return stage of a launch vehicle is known, containing a mesh structure of heat-resistant steel cables located on the earth's surface, made in the form of a truncated cone and mounted on hinged supports, and a mechanical manipulator, the executive bodies of which are located above the mesh structure, the base of the truncated cone, formed by a mesh structure, are located in a horizontal plane, its internal cavity is facing in the direction "to the zenith", and the diameter of the smaller base has a size larger than the size of the part of the tail section of the launch vehicle passing through it during landing, while the supports of the mesh structure are made with the possibility of adjusting the position of its longitudinal axis relative to the normal to the earth's surface, and in the plane passing through the smaller base of the cone of the mesh structure, mounting hooks are installed that hold the launch vehicle after it has landed (see RF patent No. 2740525 MPK B64G 5/00 dated May 22 2020) - prototype.

The known device of the landing support system for a spent stage with a reusable liquid rocket engine has a number of advantages compared to those previously mentioned, since it can be used to land the returned already developed and used first stages of launch vehicles that do not require significant refinement of launch vehicles and are significant in this case of material costs.

However, it does not always make it possible to compensate for the deviation of the stage aiming system at the landing point, which is associated both with the influence of many other factors associated with the operation of brake engines, with the spread of the thrust impulse of a liquid rocket engine, or even with the effect of a crosswind, which can lead to an off-design case. landing, violation of the integrity of the ground device and, no less important, the landing stage of the launch vehicle. This is due to the fact that the configuration of the landing system device does not allow changing the overall dimensions of the receiving "window" so that it provides geometric dimensions close to the dimensions of a round one for receiving the launch vehicle stage, and does not allow moving it along the landing plane with its longitudinal axis symmetry, focusing on the landing stage of the launch vehicle in any direction in the horizontal system of rectangular coordinates, thereby increasing the load on the formation of landing commands on the landing stage of the rocket, on the system for regulating the operation of the reusable liquid rocket engine, which ultimately leads to irrational use of the resource of the reusable of a liquid-propellant rocket engine in off-design modes of operation, compared to those required by its operation in the launch mode, and the associated resource depletion. In addition, the landing system configuration in the form of a mesh of cables does not have sufficient maintainability if it is damaged by a jet of combustion products from the chambers of a reusable liquid rocket engine in the braking and descent mode, since it requires complete dismantling of the entire system and replacing it with a new design. Any connected in a single rigid design of the elements of the cone inevitably has such rigidity that, in contact, it can lead to damage to the landing stage. The interaction of the mounting hooks of the device with the landing launch vehicle requires the solution of a number of problems associated with their impact on the landing stage, which requires additional experimental development and lengthens the period of use.

The objective of the invention is to form a receiving symmetrical close to a round "window" for receiving a spent stage with a reusable liquid rocket engine and ensuring the movement of the receiving "window" in accordance with the movement of the receiving stage of the carrier rocket in the horizontal plane, the compliant touch of the catching system with the body of the rocket stage - carrier by applying a new fundamental approach to the process of catching the stage of the launch vehicle using the clutch of aerodynamic stabilizers in the upper part of the stage of the launch vehicle for the catching system and fixing it in this position before moving it with the help of the evacuation system.

The objective of the invention is also to expand the range of spent stages in terms of their height and to simplify the elimination of the spent stage.

The objective of the invention is also to reduce the shock loads on the spent stage.

The objective of the invention is also to reduce the preparation time of the device with a minimum number of cables for receiving the spent stage of the launch vehicle by moving the middle part of the cable in the radial direction due to the tension force.

The objective of the invention is also to simplify the reception of a spent stage with a reusable liquid rocket engine by a landing system device through the use of aerodynamic stabilizers (hooks) in the upper part of the launch vehicle stage above the center of mass as fixing catchable hooks.

The above problem of the invention is solved by the fact that in the known device of the system for ensuring the landing of the spent stage with a reusable liquid rocket engine, containing a cable system fixed symmetrically about the longitudinal axis of symmetry of the receiving table and at a vertical distance from it with the help of supports, the cable system, and the evacuation system of the spent stage, alone the ends of the cables are fixed concentrically evenly around the circumference to the ring cable, mounted with attachment points along the periphery to the installed supports, in a plane parallel to the landing table and at a vertical distance from the table, and the second ends of the cables are fixed concentrically evenly around the circumference to the attachment points placed on the platform , in the plane of the landing table with the possibility of shifting clockwise or counterclockwise relative to the longitudinal axis of symmetry of the table with the help of a drive, with the formation of a single-sheet hyperboloid by cables with a receiving window along the longitudinal axis of symmetry one hundred la ground device.

The above task of the invention is also solved by the fact that in the device of the system for landing the spent stage with a reusable liquid rocket engine, the platform is made movable by means of a coordinate mechanism relative to two transverse axes perpendicular to the longitudinal axis of symmetry of the landing table, which in turn is equipped with drives and clamps coordinate movement.

The above objective of the invention is also solved by the fact that in the device of the system for landing a spent stage with a reusable liquid rocket engine, the attachment points located on the platform are made with the possibility of telescopic movement in height and are equipped with drums with drives for changing the length of the cables.

The above objective of the invention is also solved by the fact that in the device of the system for landing a spent stage with a reusable liquid rocket engine, the attachment points are equipped with shock absorbers, on the one hand connected to the longitudinal cables, and on the other hand, to the ring cable.

The above task of the invention is also solved by the fact that in the device of the landing support system for the spent stage with a reusable liquid rocket engine, the minimum number of cables in it is provided with additional cables connected in the middle with the help of triggers and tensioners towards the outer side of the device.

The above objective of the invention is also solved by the fact that in the device of the landing support system for a spent stage with a reusable liquid rocket engine, in a rocket stage with a reusable liquid rocket engine, containing a reusable liquid rocket engine with a body, fuel tanks of fuel components and aerodynamic stabilizers, places for attaching aerodynamic Stabilizers to the body are made in the transverse plane of the stage above the center of mass of the stage towards the upper point of the stage, and with the possibility of extension and provided with locks for movement relative to the cables of the landing system device for the spent stage with a reusable liquid rocket engine during landing.

The proposed device of the system for landing a spent stage with a reusable liquid rocket engine is shown in the drawing (Fig. 1-17), (Fig. 1 is an axonometric image of the device with all its constituent systems with a maximum number of supports 4 along the periphery (in this case, 18 pieces ) and the maximum number of cables 8 (in this case 18 pieces) of the cable system; Fig. 2 is a general side and top view of the device of the landing support system for a spent stage with a reusable liquid rocket engine, which shows a receiving “window” close to a round one, close to round minimum diameter, Fig. 3 is a general view from above on the device of the system for landing a spent stage with a reusable liquid rocket engine, which shows a receiving "window" close to a round one, close to a round maximum diameter with an offset from the center, Fig. 4 - general view from above on the device of the system for ensuring the landing of the spent stage with a reusable liquid awn rocket engine; where a receiving “window” close to a round one is shown, close to a round minimum diameter with an offset from the center; fig. 5 is a general top view of the device of the landing support system for a spent stage with a reusable liquid-propellant rocket engine; where a receiving "window" close to round is shown, close to round average between the minimum and maximum diameters, fig. 6 is a general top and side view of the spent stage landing support system device with a reusable liquid rocket engine, an axonometric image, which shows a receiving “window” close to a round one, close to a round minimum diameter, and with a minimum number of supports 4 along the periphery (in this case eight pieces) and a minimum number of cables 8 (in this case eight pieces) of the cable system), Fig. 7 is a general top and side view of the spent stage landing support system with a reusable liquid-propellant rocket engine; where the receiving “window” close to the round is shown, close to the round average between the minimum and maximum diameters, with the maximum displacement of the receiving “window” close to the round away from the center of the receiving table (along the Y coordinate and along the Z coordinate in the receiving table plane), fig. 8 - a general top and side view of the device of the system for landing a spent stage with a reusable liquid rocket engine, which shows a receiving "window" close to a round one, close to a round minimum diameter, and with a minimum number of supports 4 along the periphery (in this case, eight pieces ) and a minimum number of cables 8 (in this case, eight pieces) of the cable system) and a pre-tensioning system of adjacent cables with a trigger mechanism for organizing accelerated reception of the landing stage of the launch vehicle, the trigger mechanism in the closed and open state, Fig. 9 is an image of the stage of the launch vehicle with a plane located above the center of mass (CM), with aerodynamic stabilizers in the form of hooks mounted to the body of the launch vehicle to simplify landing and picking up the stage with a cable system, Fig. 10 is an axonometric image of the device with all its constituent systems with a maximum number of supports 4 along the periphery (in this case, eighteen pieces) and a maximum number of cables 8 (in this case, eighteen pieces) of a cable system with a grounded launch vehicle stage and aerodynamic stabilizers fixed on the cables ( hooks), Fig. 11 is a general side view of the system for landing a spent stage with a reusable liquid rocket engine with a launch vehicle stage placed in it after landing, FIG. 12 is a general side and top view of the spent stage landing support system device with a reusable liquid rocket engine with the stage of the launch vehicle placed in it after landing and the manipulator 58 of the evacuation system of the 6th stage of the launch vehicle 35, FIG. 13 is a general side and top view of the system for landing a spent stage with a reusable liquid rocket engine with the stage of the launch vehicle extracted in the vertical direction after landing with the help of the manipulator 58 of the evacuation system of the 6th stage of the launch vehicle 35, FIG. 14 is a general side and top view of the system for landing a spent stage with a reusable liquid rocket engine with the stage of the launch vehicle removed from the landing zone by turning the manipulator 58 of the evacuation system of the 6th stage of the launch vehicle 35, FIG. 15 is a schematic representation of the manipulator 58 with its constituent functional parts in axonometric projection in the initial position, FIG. 16 is a schematic representation of the manipulator 58 with its constituent functional parts in an axonometric projection in the position of lifting the stage of the launch vehicle, FIG. 17 is a schematic representation of the manipulator 58 with its constituent functional parts in an axonometric projection in the position of removing the launch vehicle stage from the device zone after turning, where the following units are shown:

1. Longitudinal axis of symmetry;

2. Receiving table;

3. Vertical distance;

4. Support;

5 Rope system;

6. Spent stage evacuation system;

7. The first end of the cable;

8. Rope;

9. Ring cable;

10. Mounting unit;

11. Periphery of the ground complex;

12. Landing table;

13. The plane of the landing table;

14. Vertical distance;

15. The second end of the cable;

16. Mounting unit;

17. Platform;

18. Plane;

19. Drive;

20. One-sheeted hyperboloid;

21. Reception "window";

22. Rope direction;

23. Sagging cable;

24. The direction of gravity of the cable;

25. Platform periphery;

26. Ring;

27. Telescopic mount;

28. The theoretical plane of the receiving "window";

29. Total height of fuel tanks;

30. Fuel tank;

31. Reusable liquid rocket engine;

32. Winch drum;

33. Winch drum drive;

34. Aiming point of the receiving "window";

35. Launch vehicle stage;

36. Hook;

37. Coordinate mechanism;

38. Transverse coordinate axis (Y);

39. Transverse coordinate axis (Z);

40. Drive;

41. Coordinate movement lock;

42. Friction brake mechanism;

43. Longitudinal axis of symmetry of the platform;

44. Shock absorber;

45. Housing of a reusable liquid rocket engine;

46. Aerodynamic stabilizer (hook);

47. Place of attachment of the aerodynamic stabilizer to the carrier rocket body;

48. Fuel tank housing;

49. Transverse plane;

50. Center of gravity of the launch vehicle stage;

51. The upper point of the launch vehicle stage;

52. Travel lock;

53. Additional cable;

54. Trigger;

55. Longitudinal axis of symmetry of the platform;

56. Longitudinal axis of symmetry of the carrier rocket;

57. Aiming point of the launch vehicle stage;

58. Manipulator of the evacuation system for the spent stage of the carrier rocket;

59. Embracing device;

60. Hook;

61. Sample;

62. Bracket;

63. Rod;

64. Rotary mechanism;

65. Telescopic lift;

66. Rotary mechanism;

67. Cantilever beam;

68. Winch drum.

The device of the landing support system for a spent stage with a reusable liquid-propellant rocket engine contains a cable system 5 fixed symmetrically about the longitudinal axis of symmetry 1 of the receiving table 2 and at a vertical distance 3 from it using supports 4, and a system for evacuating the spent stage 6. The first ends 7 of the cables 8 are fixed concentrically evenly around the circumference of the annular cable 9, mounted with the help of attachment points 10 along the periphery 11 to the supports 4, in a plane 13 parallel to the landing table 12 and at a distance 14 vertical from the table, and the second ends 15 of the cables 8 are fixed concentrically evenly around the circumference for the nodes fasteners 16 placed on the platform 17, in the plane 18 of the landing table 12 with the possibility of displacement by means of the drive 19 clockwise or counterclockwise relative to the longitudinal axis of symmetry 1 of the receiving table 2, with the formation by cables 8 of a single-cavity hyperboloid 20 with a receiving "window" 21 along the longitudinal axis of symmetry 1 landing table 12 of the ground complex. Simplification of the formation of the receiving "window" 21 is provided by separate stretched cables 8 in directions 22, close to straight lines, differing from straight lines only by the influence of the own weight of a linear meter of the cable 8, leading to some sagging 23 along the longitudinal axis of symmetry 1 of the receiving table 2 in the direction of force the gravity of the cable 24. A set of individual cables 8 ensures the maintainability of the device of the system for landing a spent stage with a reusable liquid rocket engine in the event of the release of one or more adjacent cables 8, and in some cases, even when several non-adjacent cables 8 fail, ensures the operation of the device due to the location of the cables 8 with the formation of a single-sheet hyperboloid 20. The second ends 15 of the cables 8 are fixed on the periphery 25 of the platform 17, made in the form of a ring 26, on telescopic attachment points 27, with the possibility of extension in the vertical direction. This quality makes it possible to adjust the placement of the theoretical plane 28 of the receiving “window” 23 in height, which ensures the reception of the return stages of launch vehicles with different up to the maximum total height 29 of fuel tanks 30 and a reusable liquid rocket engine 31. Placement in the upper zone of telescopic attachment points 27 drums 32 with drives 33 makes it possible to compensate for the length of the cables 8 and provide tension to the cables 8 when adjusting the size of the receiving "window" 23 and moving the receiving "window" 23 in the horizontal plane to adjust the aiming point 34 of the launch vehicle stage 35, which ensures the elasticity of the cables 8 in contact with the hooks 36 on the launch vehicle stage 35.

In the device of the landing support system for the spent stage with a reusable liquid rocket engine 31, the attachment points 16, located on the platform 17, are made with the possibility of telescopic movement in height, and are equipped with drums 32 with drives 33 for changing the length of the cables 8. Ensuring the landing stage of the launch vehicle 35 with a reusable liquid rocket engine 31 is carried out by rotating the platform 17 and moving with the help of a coordinate mechanism 37 relative to two transverse coordinate axes 38 and 39 perpendicular to the longitudinal axis of symmetry 1 of the landing table 12, which in turn is equipped with drives 40, for example, electric or pneumatic, and clamps coordinate movement 41, for example, friction electric brakes 42. Moving the platform 17 along the Y and Z axes in a rectangular coordinate system in the horizontal plane allows you to move it along the landing plane with its longitudinal axis of symmetry 43, focusing on the landing stage of the launch vehicle 35 in any direction in the horizontal system of rectangular coordinates, thereby reducing the load on the formation of landing commands on the landing stage of the launch vehicle 35, which ultimately leads to the rational use of the resource of the reusable liquid rocket engine 31 and the reduction of the creation time braking thrust in operating modes during landing, in contrast to those modes, as required by its operation in the withdrawal mode, and the associated reduction in resource development.

In the device of the landing support system for the spent stage of the launch vehicle 35 with a reusable liquid-propellant rocket engine 31, the attachment points are equipped with shock absorbers 44, on the one hand connected with cables 8, and on the other hand, with an annular cable 9.

The launch vehicle stage 35 with a reusable liquid-propellant rocket engine 31, intended for landing in the device of the landing support system for a spent stage with a reusable liquid-propellant rocket engine, contains a reusable liquid-propellant rocket engine 31 with a housing 45, fuel tanks 30 of fuel components and aerodynamic stabilizers (hooks) 46. Attachment points 47 of aerodynamic stabilizers (hooks) 46 to the body 48 of the fuel tank 30 are made in the transverse plane 49 of the stage of the launch vehicle 35 above the center of gravity 50 of the stage of the launch vehicle 35 towards the top point 51 of the stage of the launch vehicle 35, and with the possibility of extension and are equipped with movement locks 52 relative to the cables 8 of the device during landing.

The number of cables 8 can be selected from the minimum - eight pieces to the maximum (in this case, up to eighteen pieces), or more, depending on the mass of the stage of the launch vehicle 35 and the thickness of the cables 8. For the option with a minimum number of cables 8 to reduce the time preparation of the device for landing of the stage of the launch vehicle 35 in real time, each of the cables 8 can be equipped with a system of additional cables 53 for a preliminary increase in the size of the receiving "window" 23 and a trigger mechanism 54 for returning the cables 8 to a straight position with a decrease in the receiving "window" 23 in addition to the system of rotation of the platform 17 around its longitudinal axis of symmetry 54, which reduces the time of receiving the stage of the launch vehicle 35 and reduces the required operating time of the reusable liquid rocket engine 31 during landing.

The device of the landing support system for the spent stage of the launch vehicle 35 with a reusable liquid-propellant rocket engine 31 operates as follows. In the initial position (Fig. 3), the receiving "window" 23 due to the rotation of the platform 17 takes the specified maximum dimensions, close to round in shape. As the launch vehicle stage 35 approaches the device in a vertical or close to vertical position with the reusable liquid rocket engine 31 turned on, the device receives the value of the horizontal coordinate axes Y and Z of the longitudinal symmetry axis 56 of the launch vehicle stage 35 from the control system (in Fig. 1 -17 not shown) and corrects the aiming point 34 in the center of the receiving "window" 23 by moving the platform 17 in a horizontal plane along the two coordinate axes Y and Z, and as the stage of the launch vehicle 35 approaches the device, the platform 17 moves until the aiming point of the receiving "windows" 34 and aiming points 57 stages of the launch vehicle. With a minimum distance of the stage of the launch vehicle 35 to the device of the system for ensuring the landing of the spent stage of the launch vehicle 35 with a reusable liquid rocket engine 31, sufficient to adjust the size of the receiving "window" 23 from the maximum to the size of the entry of the stage of the launch vehicle 35 into the receiving "window" 23, by rotating the platform 17 in a given direction, if the number of cables 8 is maximum (for example, eighteen), or by triggering the trigger 53 and simultaneously rotating the platform 17, if the number of cables 8 is minimal (eight), the reusable liquid-propellant rocket engine 31 is turned off, further free moving the stage of the launch vehicle 35 into the receiving "window" 23 under the action of inertia and gravity in the direction 24, and fixing it with the help of aerodynamic stabilizers (hooks) 46, the number of which is selected to guarantee the adhesion of each hook 46 with the cables 8 using the clamps 52 .Because of the possibility of grounding the stage of the launch vehicle 35 with the reusable liquid rocket engine 31 turned off, the impact of high-temperature combustion products on the stage of the launch vehicle 35 from interaction with the receiving table 2 is reduced, and the impact of high-temperature combustion products on the device of the system for ensuring the landing of the spent stage of the launch vehicle 35 is reduced reusable liquid-propellant rocket engine 31. Due to the placement of autonomous cables 8, the maintainability of the ground complex is ensured. The evacuation of the stage of the launch vehicle 35 is carried out by known methods, for example, by the manipulator 58 of the system for evacuating the spent stage 6 of the launch vehicle 35. FIG. 12-14 show the sequence of removing the booster stage 35 from the device. The coupling of the manipulator 58 with the stage of the launch vehicle 35 is carried out using a cylindrical gripping device 59, in which hooks 60 are formed, formed by samples 61, equipped with brackets 62, a cable 62 and a rod 63 for rotating the cylindrical gripping device 59 using a rotary mechanism 64. Manipulator 58 lifts the stage of the launch vehicle 35 using a telescopic lift 65, which combines the functions of the rotary mechanism 66 of the cantilever beam 67 with the rotary mechanism 64 fixed on it and the winch drum 68 for lifting the cable 62.

The application of the invention will make it possible to form a receiving symmetrical close to a round "window" for receiving a spent stage with a reusable liquid rocket engine and ensuring the movement of the receiving "window" in accordance with the movement of the receiving stage of the launch vehicle in the horizontal plane, pliable touch of the device of the system for ensuring the landing of the spent stage of a launch vehicle with a reusable liquid rocket engine with the body of the landing stage of the launch vehicle by applying a new fundamental approach to the process of catching the landing stage of the launch vehicle using the clutch of aerodynamic stabilizers in the upper part of the stage of the launch vehicle for the system of catching and fixing it in this position before moving it with the help of the evacuation system. In addition, the application of the present invention is also the expansion of the range of spent stages in terms of their height and the simplification of the evacuation of the spent stage of the launch vehicle, the reduction of impact loads on the spent stage of the launch vehicle and the simplification of the reception of the spent stage of the launch vehicle with a reusable liquid rocket engine with a support system device landing through the use of retractable aerodynamic stabilizers (hooks) in the upper part of the launch vehicle stage above the center of mass.

Claims (6)

1. The device of the landing support system for a spent stage with a reusable liquid-propellant rocket engine, containing a cable system fixed symmetrically about the longitudinal axis of symmetry of the receiving table and at a vertical distance from it with the help of supports and a system for evacuating the spent stage, characterized in that one end of the cables is fixed in it concentrically evenly around the circumference of the annular cable, attached by means of attachment points along the periphery to the installed supports, in a plane parallel to the landing table and at a vertical distance from the table, and the second ends of the cables are fixed concentrically evenly around the circumference to the attachment points placed on the platform in the plane of the table landing with the possibility of displacement by means of a drive clockwise or counterclockwise relative to the longitudinal axis of symmetry of the landing table, with the formation of single-sheet hyperboloid by cables with a receiving window along the longitudinal axis of symmetry of the ground landing table devices. 2. The device according to claim 1, characterized in that the platform is made capable of moving with the help of a coordinate mechanism relative to two transverse axes perpendicular to the longitudinal axis of symmetry of the landing table, which in turn is equipped with drives and clamps for coordinate movement. 3. The device according to claim. 1, characterized in that the attachment points placed on the platform are made with the possibility of telescopic movement in height and are equipped with drums with drives to change the length of the cables. 4. The device according to claim 1, characterized in that the attachment points in it are equipped with shock absorbers, on the one hand connected to the longitudinal cables, and on the other hand, to the ring cable. 5. The device according to claim 1, characterized in that the minimum number of cables in it is equipped with additional cables connected in the middle with the help of triggers and tensioners towards the outside of the device. 6. Rocket stage with a reusable liquid-propellant rocket engine, containing a reusable liquid-propellant rocket engine with a body, fuel tanks of fuel components and aerodynamic stabilizers, characterized in that the attachment points of the aerodynamic stabilizers to the body are made in the transverse plane of the stage above the center of mass of the stage towards the upper point of the stage and with the possibility of extension and are equipped with locks for movement relative to the cables of the landing support system device for the spent stage with a reusable liquid rocket engine during landing.

Images