KR100938997B1 - Spaceplane, Reentry Attitude Control of the Spaceplane using Canard and Elevon - Google Patents

Abstract

The present invention relates to a spaceplane capable of ensuring posture stability during low orbit reentry and a posture control method for low orbit reentry of the space shuttle.

Space Shuttle, elevon, canad, angle of attack, yaw, pitch, roll, freefall

Description

Spaceplane, Reentry Attitude Control of the Spaceplane using Canard and Elevon}

The present invention relates to a spaceplane capable of ensuring posture stability during low orbit reentry and a posture control method for low orbit reentry of the space shuttle.

In the US, the space shuttle controls the attitude by jet-jet method called Reaction Control System (RCS) when re-entering the atmosphere, and in particular, the Spaceship-1 in the US displaces the entire rear wing vertically to provide free fall posture stability (Shuttle Cock). Stability has been secured.

However, the space shuttle of the United States has a disadvantage in that the process is very complicated as the attitude control by the jet injection method of the reaction control system (RCS) at the time of re-entry into the atmosphere, the cost of manufacturing the space shuttle for this purpose.

The present invention is to provide a method for controlling the attitude of the space shuttle and the space shuttle when re-entry the space shuttle capable of performing posture stability and attitude control of a reentrant vehicle at a simple and low cost without additional mechanical devices.

The present invention is a fuselage; A nozzle for applying a driving force to the body; A rudder for causing yaw motion in the body; A main blade having a triangular wing shape and a trailing edge portion connected to the leading edge portion and having a first mounting groove portion penetrating the upper and lower surfaces thereof, the main blade being mounted on the fuselage; An elevon mounted on the first mounting groove so as to cause a change in the angle of attack by rotation; A tail boom formed at an outer end of the main wing trailing edge portion; It relates to a space shuttle, including; a carnad (carnad) that is mounted at a predetermined distance apart from the main wing in the front portion of the fuselage to cause a change in the angle of attack by rotation.

In the present invention, the cannad is rotatably mounted to the fuselage so that the angle of attack becomes 0 ° when ascending and the angle of attack is 90 ° when entering the low orbit due to free fall, and the elevon Silver, the angle of attack is 0 ° to rise and the angle of attack when entering the low orbit due to free fall, so that it can be rotated mounted to the elbow mounting groove portion, the canad (carnad) the angle of attack is 0 ° In the case that the can be mounted so as to be located on the upper side of the horizontal plane passing through the main wing, the rudder (rudder) can be rotatably mounted to the second mounting groove formed in the tail of the tail boom, the main blade leading edge is outside The stage can be inclined 30 ° with respect to the longitudinal axis passing through the fuselage, and the canad is 30 ° with respect to the longitudinal axis passing through the fuselage when the angle of attack is 0 °. Can be inclined and the rear outer end can be inclined 60 ° with respect to the longitudinal axis passing through the body.

On the other hand, the present invention is a posture control method for entering the low-orbit of the space shuttle, the fuselage is located so that the longitudinal direction is perpendicular to the flight direction by the free fall, the elvon (elevon) with respect to the trailing edge of the main wing The rotation angle maintains the angle of attack 90 °, the canad (carnad) relates to the attitude control method for entering the space shuttle low-orbit, characterized in that the angle of rotation to maintain the angle of rotation 90 ° relative to the body.

Space shuttle according to the present invention has the advantage that can perform the posture stability and attitude control of the aircraft at low orbit re-entry by free fall at low cost without additional mechanical device.

Hereinafter, an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

Example 1

Example 1 is an embodiment of a space shuttle according to the present invention. 1 is a rear view of the first embodiment, FIG. 2 is a plan view of the first embodiment, FIG. 3 is a right side view of the first embodiment, and FIG. 4 is a plan view of the first embodiment of the re-entry. 5 is a left side view at the time of reentry of Example 1, and FIG. 6 is a left side view at the time of reentry of Example 1. FIG.

1, the first embodiment according to the present invention is a fuselage 100, a nozzle 200, a main wing 300, an elevon 400, a tail boom 500, a rudder ( rudder 600, canad 700.

1 to 3, the body 100 is equipped with the nozzle 200, the main wing 300, the canad 700, and the like as the main part of the first embodiment according to the present invention. The body 100 has a cylindrical portion (not shown), which is formed in a cylindrical shape, the head portion (not shown) is formed in a convex cone shape, and the tail portion (not shown) has a vertex portion. It may be formed into a truncated convex shape. An engine (not shown) is housed in the body 100.

Referring to FIGS. 1 and 3, the nozzle 200 may be mounted at a tail portion (not shown) of the body 100. The nozzle 200 is used to apply a driving force to the fuselage 100 by injecting fuel combusted from an engine (not shown).

1 and 3, the main wings 300 are mounted one each on the left and right sides of the body 100. The main wing 100 is composed of the leading edge 310 and the trailing edge 320. The leading edge 310 is formed in the shape of a triangular wing, the trailing edge 320 is formed in a substantially rectangular shape is connected to the rear end of the leading edge 310. 2 and 3, the main blade 300 is mounted to the lower portion of the body 100.

Referring to Figure 1, the leading edge 310 of the main wing 300 is formed so that the outer end is inclined 30 ° with respect to the longitudinal axis passing through the body (100).

Referring to FIG. 4, a first mounting groove 322 is formed at a rear end of the main wing 300 of the trailing edge part 320. The first mounting groove 322 penetrates through the upper and lower surfaces of the trailing edge part 320, and is recessed inwardly from the rear end of the trailing edge part 320.

Referring to FIG. 1, an elevon 400 is mounted in the first mounting groove 322 of the trailing edge 320. 4 and 5 together, the elevon 400 is hingedly rotatably coupled to the first mounting groove 322 to cause a change in the angle of attack. Elevon (400) is located on the same plane as the main blade 300, the trailing edge 320 when raised, the angle of attack is 0 °, the trailing edge 320 of the main blade 300 when entering the low orbit due to free fall ) Is hinged to the first mounting groove 322 so that the angle of attack is 90 °. That is, the elevon 400 is hinged to the first mounting groove 322 to have a rotation angle of at least 90 °.

2 and 3, a tail boom 500 is erected at an outer end of the trailing edge 320 of the main blade 300. The tail boom 500 stands approximately perpendicular to the trailing edge 320.

Referring to FIG. 3, a second mounting groove (not shown) is formed at the tail of the tail boom 500. The second mounting groove portion (not shown) penetrates the left and right side surfaces of the tail boom 500 and is recessed inwardly from the tail boom 500.

Referring to FIG. 3, a rudder 600 is hingedly rotatably coupled to a second mounting groove (not shown). The rudder 600 rotates left and right with respect to the tail boom 500 so as to cause yaw movement in the body.

Referring to FIG. 1, the body portion (not shown) of the fuselage 100 is mounted with a cannad 700 spaced apart from the main wing in a forward direction. 4 and 5 together, the canad 700 is pivotally coupled to the fuselage 100 so as to cause a change in the angle of attack. When the canad 700 is located on a plane parallel to the main wing 300 when ascending, the angle of attack becomes 0 °, and the angle of attack is orthogonal to the plane parallel to the main wing 300 when entering the low orbit due to free fall. It is hinged to the fuselage 100 to be 90 °. That is, the carnad 700 is hinged to the fuselage 100 to have a rotation angle of at least 90 °.

2 and 3, the cannad 700 is mounted to be positioned above the plane where the main wing 300 is located when the angle of attack is 0 °. Thus, the vortices generated by the carnad 700 pass over the main wing 300, supply energy to the flow of the main wing 300 to stabilize the flow and increase the stability of the vehicle at high angles of attack. do.

Meanwhile, referring to FIG. 3, when the receiving angle is 0 ° when the cannad 700 is raised, the front outer end is inclined 30 ° with respect to the longitudinal axis passing through the body 100, and the rear outer end is the body 100. It is formed to incline 60 ° with respect to the longitudinal axis passing through. This is a general shape of the carnad 700, and a strong vortex is generated due to this retreat angle, which has a positive effect on the main wing 300 (with the oil well to the high angle of attack).

Hereinafter, the operation of the first embodiment described above will be described.

One embodiment according to the present invention is launched from the mother ship in the 15km altitude, the fuel is injected through the nozzle 200 to rise to an altitude of 60km, and then to the altitude of 100km defined by the universe to an inertial force, 100km altitude It is a space shuttle that lands freely from 15km altitude without any driving force and then glides and lands from 15km.

1 to 3, when the space shuttle rises to an altitude of 100 km, the length portion of the fuselage 100 will fly toward the X direction, and the main blade 300 will be close to the parallel to the X direction. Since the angle of attack of the main wings 300 is small, the elevance 400 and the canad 700 are attached to the trailing edge 320 and the fuselage 100 of the main wings 300. Since the angle of attack of each of them is rotatably connected to each other, for example, the drag angle can be reduced by keeping the displacement angles of the elevon 400 and the canad 700 within about 10 °.

4 to 6, when the space shuttle travels freely from 100km to 15km in altitude and re-enters the low orbit, the length of the fuselage 100 is to be positioned in a plane perpendicular to the -X direction, and the tail boom ( A rudder 600 mounted at the tail to the tail boom 500 pivots out of the tail boom 500 to provide roll and yaw stability.

In particular, referring to FIGS. 4 and 6, when the space shuttle falls freely and reenters the low orbit, the carnad 700 and the elevon 400 rotate to the upper side of the main wing 300 to receive an angle of attack. Maintaining 0 ° reduces the resistance of air during free fall and provides pitch and yaw stability. Furthermore, by adjusting the angle of attack of the canad 700, it is possible to actively control the pitch attitude.

Example 2

Embodiment 2 relates to a posture control method when the space shuttle enters the low orbit by the free fall according to the first embodiment.

4 to 6, the second embodiment is a position where the fuselage 100 is perpendicular to the flight direction due to free fall when the reentry into the low orbit by free fall from the altitude 100km to 15km altitude do.

The elbow 400 mounted on the trailing edge part 320 of the main wing 300 rotates upward with respect to the trailing edge part 320 of the main wing 300 and maintains a reception angle of 90 °. The cannad 700 mounted on the body 100 rotates with respect to the body 100 and maintains a reception angle of 90 °.

Therefore, when the space shuttle falls freely and reenters the low orbit, the carnad 700 and the elevon 400 rotate to the upper side of the main wing 300 so that the angle of attack remains at 0 °. This reduces air resistance in the sea and provides pitch and yaw stability.

1 is a rear view when the first embodiment is raised.

2 is a plan view of the rise of Example 1;

3 is a right side view at the time of rising of the first embodiment;

4 is a plan view of the re-entry of the first embodiment;

Fig. 5 is a left side view of re-entry of Example 1;

6 is a left side view of re-entry of Example 1;

<Description of the symbols for the main parts of the drawings>

100: fuselage 200: nozzle

300: A wing wing 310: A leading edge part

320: trailing edge portion 322: first mounting groove portion

400: elevon 500: tail boom

600: rudder 700: canad

Claims (7)

delete fuselage; A nozzle for applying a driving force to the body; A rudder for causing yaw motion in the body; A main blade having a triangular wing shape and a trailing edge portion connected to the leading edge portion and having a first mounting groove portion penetrating the upper and lower surfaces thereof, the main blade being mounted to the body; An elevon mounted on the first mounting groove so as to cause a change in the angle of attack by rotation; A tail boom formed at an outer end of the main wing trailing edge portion; A canad mounted to the front part of the body at a predetermined distance apart from the main wing so as to cause a change in the angle of attack by rotation; Including but not limited to: The canad is rotatably mounted to the fuselage so that the angle of attack becomes 0 ° when ascending and the angle of attack is 90 ° when entering the low orbit due to free fall, The elevon is a space shuttle, characterized in that the ellipse mounting groove is rotatably mounted so that the angle of attack is 0 ° when rising and the angle of attack is 90 ° when entering the low orbit due to free fall. The method of claim 2, The canad is space shuttle, characterized in that mounted to be located on the upper side of the horizontal plane passing through the main wing when the angle of attack is 0 °. The method of claim 3, The rudder is a space shuttle, characterized in that rotatably mounted to the second mounting groove formed on the tail of the tail boom. The method according to any one of claims 2 to 4 , The main wing leading edge is a space shuttle, characterized in that the outer end is inclined 30 ° with respect to the longitudinal axis passing through the fuselage. The method of claim 5, When the angle of attack is 0 ° when the carnad is raised, the front outer end is inclined 30 ° with respect to the longitudinal axis passing through the fuselage and the rear outer end is inclined at 60 ° with respect to the longitudinal axis passing through the fuselage. Shuttle. As a method of controlling the attitude when entering the low-orbit of the space shuttle of claim 2 or 3 , The fuselage is located so that its longitudinal direction is perpendicular to the direction of flight due to free fall, The elevon is rotated with respect to the trailing edge of the main blade to maintain the angle of attack 90 °, The canad is a attitude control method for entering the space shuttle low-orbit, characterized in that the angle of rotation is maintained by 90 ° with respect to the fuselage.

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