KR20240017520A - Reusable solid-propellant rocket using propellers - Google Patents

Abstract

The present invention provides a lower projectile 100 capable of landing after launch, a landing leg 101 located at the lower part of the lower projectile 100 to add stability when the projectile rises and prevent damage to the projectile when landing, and the lower projectile ( A control wing 102 located in the middle of the projectile 100 to guide the projectile to fly on a desired trajectory and to a desired location, and a stage separator 103 located at the top of the lower projectile 100 to separate the upper and lower stages of the projectile. ), a lower solid propellant rocket motor 201 located at the lower center of the lower launch vehicle 100 to provide propulsion for the initial rise after takeoff, and a payload mounted at the upper center of the upper projectile 400 to reduce air resistance. a nose cone 202 that reduces A pillar 301 that functions as the rotation axis of (306), two left and right electric motors (302) located inside the coaxial inversion rotation unit (300) that provide rotational power to the propeller (306), and an upper and lower propeller mount. An upper and lower electric motor gearwheel 303 that engages and rotates the gearwheel 304, an upper and lower propeller mount gearwheel 304 that is connected to the pillar 301 and causes rotation of the propeller mount 305, and an upper and lower propeller mount gearwheel ( 304), the upper and lower propeller mounts 305 on which the propeller 306 is mounted, the upper and lower propellers 306 that rotate and provide the lift necessary for landing, and the upper part that further accelerates the payload after separating the upper and lower projectiles. The present invention is to provide a reusable solid propellant launch vehicle using a propeller, characterized in that it consists of a launch vehicle 400 and an upper solid propellant rocket motor 401 that provides propulsion for acceleration of the upper launch vehicle 400. By enabling the landing of solid propellant launches, which was previously impossible, it expands the scope of use of launch vehicle landing technology, which was limited to liquid propellant launches. In addition, it is possible to reduce the damage to the launch vehicle and reduce the complexity of the recovery process by landing at the desired location, compared to the inefficient and limited range of solid launch vehicle use technologies such as the launch using the parachute of the space shuttle's solid rocket booster that was used in the past. Enables active reuse of propellant projectiles. In addition, when taking off using a propeller to rise and then ignite in the air, it is possible to launch without the existing complex launch pad facilities, which has the effect of reducing costs such as the cost of maintaining the launch pad facilities.

Description

{Reusable solid-propellant rocket using propellers}

The present invention relates to a reusable solid propellant launch vehicle using a propeller. More specifically, it relates to a reusable solid propellant launch vehicle using a propeller that can take off by burning a solid propellant during takeoff and land at a desired location by operating a coaxially reversing propeller during landing. It's about projectiles.

As the new space era led by private companies began, launch vehicle reuse technology became a groundbreaking solution to reducing costs.

Launch vehicles of private companies that use liquid propellants, such as the existing Falcon 9 and New Shepard, utilize reignition and thrust control technologies to enable rocket reuse and subsequent cost reduction.

However, the solid propellant launch vehicle, which is simple to manufacture and relatively inexpensive, making it suitable as a launch vehicle for private companies, could not land at the desired location because it was impossible to control the above re-ignition.

For example, in the case of the space shuttle's solid rocket booster (SRB), it was slowed down using a parachute and landed in the sea, but as the complexity of the damage and recovery process reveals problems with the current solid propellant reuse technology, it cannot be placed in the desired location. The present invention is disclosed to develop a solid launch vehicle capable of landing.

Domestic Patent Publication No. 10-2019-0133120 (2019.12.02.)

Therefore, the present invention was applied to solve the above-described conventional problems,

The present invention is a solid propellant launch vehicle, which had shortcomings in reuse and cost reduction through reuse. Unlike the prior art, which rotated the propeller through friction with the air to lower the speed of the launch vehicle and then launched into the sea, the present invention uses a propeller driven by an electric motor. The goal is to reduce launch costs by combining technologies to provide a reusable solid propellant launch vehicle using a propeller that can land at a desired location.

This invention

Bottom launch vehicle (100) capable of landing after launch,

A landing leg (101) located at the bottom of the lower projectile (100) to add stability when the projectile rises and prevent damage to the projectile when landing,

A control wing 102 located in the middle of the lower projectile 100 to guide the projectile to fly on a desired trajectory and to a desired location,

A stage separator (103) located at the top of the lower projectile (100) to separate the upper and lower stages of the projectile,

A bottom solid propellant rocket motor (201) located at the bottom center of the bottom launch vehicle (100) to provide initial upward propulsion after takeoff,

A nose cone (202) located at the upper center of the upper launch vehicle (400), on which the payload is mounted and reduces air resistance,

A coaxial inversion rotation unit 300 located on one upper side of the lower projectile 100 to cause stable rotation of the upper and lower propellers,

A pillar 301 that fixes the part at the inner center of the coaxial rotation unit 300 and functions as a rotation axis of the propeller 306,

Two left and right electric motors (302) located inside the coaxial rotation unit (300) to provide rotational power to the propeller (306),

An upper and lower electric motor gearwheel (303) that engages and rotates the upper and lower propeller mount gearwheels (304),

An upper and lower propeller mount gearwheel (304) connected to the pillar (301) to rotate the propeller mount (305),

An upper and lower propeller mount (305) connected to the upper and lower propeller mount gears (304) and on which the propeller (306) is mounted,

An upper and lower propeller (306) that rotates and provides the lift necessary for landing,

After separating the upper and lower projectiles, an upper projectile (400) that further accelerates the payload,

It is characterized by being composed of an upper solid propellant rocket motor (401) that provides propulsion for acceleration of the upper launch vehicle (400).

The present invention expands the scope of use of launch vehicle landing technology, which was limited to liquid propellant launch vehicles, by enabling the landing of solid propellant launch vehicles, which was previously impossible.

In addition, the present invention reduces damage to the launch vehicle and reduces the complexity of the recovery process by landing at the desired location, rather than the inefficient and limited scope of solid launch vehicle use technology, such as the launch using the parachute of the space shuttle's solid rocket booster that was previously used. This enables active reuse of solid propellant launch vehicles.

In particular, the present invention can be launched without complex existing launch pad facilities when rising using a propeller during takeoff and then ignited in the air, thereby reducing costs such as the cost of maintaining the launch pad facility.

Figure 1 shows a perspective view showing the structure of the lower projectile.
Figure 2 is a front view showing the structure of the projectile before stage separation occurs.
Figure 3 is a front view showing the internal structure of the coaxial rotation unit.
Figure 4 shows a front view showing the structure of the upper projectile.

As described above, the configuration of the present invention will be described in detail with the accompanying drawings as follows.

Figure 1 is a diagram and representative diagram of the lower launch vehicle 100 landing after the upper launch vehicle 400 and the lower launch vehicle 100 are separated.

In FIG. 1, the lower launch vehicle 100 includes a landing leg 101 at the bottom, four control wings 102, a coaxial rotation unit 300 and four upper and lower propeller blades 306 connected thereto, and a landing leg 101 at the bottom. It consists of a stage separator (103).

Figure 2 is a view of the projectile 200 before the upper end 400 and the lower end 100 are separated.

In Figure 2, the launch vehicle is the landing leg 101 at the bottom, the bottom solid propellant rocket motor 201, the nose cone 202 on which the payload is mounted at the top, and the top launch vehicle 400 to which the nose cone 202 is attached. ), the four control blades (102) of FIG. 1, the coaxial reversal rotating part (300), the four upper and lower propellers (306) folded in the state before operation, and the upper and lower propeller mounts (305) to which the upper and lower propellers are respectively connected. It consists of

Figure 3 is a diagram of the coaxial rotation rotation unit 300 composed of parts responsible for the landing of the projectile.

In Figure 3, four upper and lower propellers (306), two upper and lower propeller mounts (305) to which the propellers are connected, two upper and lower propeller mount gear wheels (304) connected to the upper and lower propeller mounts, respectively engaged with the upper and lower propeller mounts. It consists of two upper and lower electric motor gearwheels (303), two left and right electric motors (302) each engaged with the upper and lower electric motor gearwheels, and a pillar (301) that connects and fixes the parts in the center.

Figure 4 is a diagram of the upper launch vehicle 400, which consists of a fairing 202 on which the payload is mounted, and an upper solid propellant rocket motor 401.

The lower projectile 100 is the lower end of the reusable projectile having a coaxial rotation rotation unit 300 to enable reuse through controlled landing. Inside, it has parts such as an electric battery, communication device, and control computer.

The landing leg 101 is manufactured in a wing-like shape to increase stability by lowering the center of pressure to the bottom during takeoff and ascent of the reusable projectile.

However, depending on mission requirements, foldable landing legs may be applied as landing legs.

Additionally, a shock absorber may be used to minimize the impact that may occur during landing to the launch vehicle.

Additionally, pads such as silicone or rubber may be attached to the bottom to increase traction with the landing site.

Also, rather than the eight legs shown in the drawing, more or fewer legs may be used.

The control wing 102 is used to guide the projectile to a desired trajectory at all stages of takeoff, ascent, and landing of the projectile by calculating control values obtained from a gyro sensor or the like.

However, the number of control wings 102 may be used more or less than the four in the drawing.

The stage separator 103 is used to separate the upper end 400 and the lower end 100 of the projectile. The stage separator 104 can be used in various ways using gunpowder or springs.

The bottom solid propellant rocket motor 201 provides the necessary thrust during takeoff and ascent. In addition, the accuracy of control can be improved by applying thrust deflection technology.

The nose cone 202 is separated from the upper projectile 400 in various ways before the payload is ejected. Additionally, the shape can vary depending on the volume and weight of the payload.

The coaxial rotation unit 300 can be used at both the top and bottom of the projectile.

The pillar 301 fixes the parts of the coaxial rotation unit 300 and connects the upper and lower ends of the projectile before separating them.

The two left and right electric motors (302) supply power to operate the propeller, and the two left and right electric motors (302) are all oriented in the same direction when the connection with the upper and lower gears (303) is viewed from above. It rotates and is manufactured to look at the top and bottom of the projectile, respectively. Therefore, the rotation in the actual projectile proceeds in the opposite direction.

In addition, the left and right electric motors 302 are connected to the upper and lower electric motor gear wheels 303, respectively.

In particular, when landing, the altitude and speed of the projectile are comprehensively judged and the rotation speed of the motor is adjusted to ensure a stable landing at the desired location.

The upper and lower electric motor gearwheels 303 are connected to the left and right electric motors 302, respectively, and rotate. In addition, it engages and rotates with the upper and lower propeller mount gear wheels 304, respectively.

The upper and lower propeller mount gearwheels 304 rotate around the pillar 301.

And the propeller mount gearwheel 304 has teeth attached to a bearing connected to the column 301 in the center, enabling rotation of the upper and lower propeller mounts 305 and at the same time being fixed to the column 301. Let it happen.

The upper and lower propeller mounts 305 are attached to the upper and lower propeller mount gear wheels 304. Two propeller blades 306 are mounted on the upper and lower propeller mounts. Two or more propeller blades 306 may be installed each.

The upper and lower propellers 306 rotate and provide lift, thereby providing the lift necessary for landing of the projectile, thereby enabling the launch vehicle to land.

The upper and lower propellers 306 rotate in opposite directions, thereby canceling out the angular momentum generated through each other's rotation, thereby reducing the rotation of the projectile and the resulting instability.

The upper launch vehicle 400 is equipped with a nose cone 202, a payload, etc., and has the upper solid propellant motor 401 as a propulsion engine.

The upper projectile 400 may be used in one or more projectiles. It also has internal components such as an electric battery, communication device, and control computer.

The upper solid propellant motor 401 is not limited to solid propellants, and various propellants such as liquid propellants and hybrid propellants can be used. In addition, the accuracy of control can be improved by applying thrust deflection technology.

Although the embodiments of the present invention have been described in detail as described above, the scope of the rights of the present invention is not limited thereto, and the scope of the rights of the present invention includes only those that are substantially equivalent to the embodiments of the present invention. Of course.

100: Bottom projectile
101: Landing legs
102: Control wings
103: stage separator
200: Projectile before separation occurs
201: Bottom solid propellant rocket motor
202: Nose cone
300: Coaxial reversal rotating part
301: pillar
302: Left and right electric motors
303: Electric motor gear wheel
304: 2 propeller mount gear wheels
305: 2 propeller mounts
306: 4 upper and lower propellers
400: Top projectile
401: Upper solid propellant rocket motor

Claims (1)

Bottom launch vehicle (100) capable of landing after launch,
A landing leg (101) located at the bottom of the lower projectile (100) to add stability when the projectile rises and prevent damage to the projectile when landing,
A control wing 102 located in the middle of the lower projectile 100 to guide the projectile to fly on a desired trajectory and at a desired location,
A stage separator (103) located at the top of the lower projectile (100) to separate the upper and lower stages of the projectile,
A lower solid propellant rocket motor (201) located at the lower center of the lower launch vehicle (100) to provide initial upward propulsion after takeoff,
A nose cone (202) located at the upper center of the upper launch vehicle (400), on which the payload is mounted and reduces air resistance,
A coaxial inversion rotation unit 300 located on one upper side of the lower projectile 100 to cause stable rotation of the upper and lower propellers,
A pillar 301 that fixes the part at the inner center of the coaxial rotation unit 300 and functions as a rotation axis of the propeller 306,
Two left and right electric motors (302) located inside the coaxial rotation unit (300) to provide rotational power to the propeller (306),
An upper and lower electric motor gearwheel (303) that engages and rotates the upper and lower propeller mount gearwheels (304),
An upper and lower propeller mount gearwheel (304) connected to the pillar (301) to rotate the propeller mount (305),
An upper and lower propeller mount (305) connected to the upper and lower propeller mount gears (304) and on which the propeller (306) is mounted,
An upper and lower propeller (306) that rotates and provides the lift necessary for landing,
After separating the upper and lower projectiles, an upper projectile (400) that further accelerates the payload,
A reusable solid propellant launch vehicle using a propeller, characterized in that it consists of an upper solid propellant rocket motor (401) that provides propulsion for acceleration of the upper launch vehicle (400).