AU2021204199B2

AU2021204199B2 - Booster System for Launch Vehicle

Info

Publication number: AU2021204199B2
Application number: AU2021204199A
Authority: AU
Inventors: Yen-Sen Chen
Original assignee: At Space Pty Ltd
Current assignee: At Space Pty Ltd
Priority date: 2021-06-22
Filing date: 2021-06-22
Publication date: 2023-02-02
Anticipated expiration: 2041-06-22
Also published as: AU2021204199A1

Abstract

OF THE DISCLOSURE A booster system for a launch vehicle includes a plurality of core boosters and a plurality of patchy boosters. The plurality of core boosters and the plurality of patchy boosters are arranged in an inner space of a rocket casing of the launch vehicle, and the plurality of patchy boosters is separatable from the launch vehicle. 12 1/3 'In m0 CN

Description

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'In m0

CN

P/00/011 Regulation 3.2 AUSTRALIA

Patents Act 1990

COMPLETE SPECIFICATION FORASTANDARDPATENT ORIGINAL TO BE COMPLETED BY APPLICANT

Invention Title: Booster System for Launch Vehicle

Name of Applicant: AT Space Pty Ltd

Address for Service: A.P.T. Patent and Trade Mark Attorneys PO Box 833, Blackwood, SA 5051

The following statement is a full description of this invention, including the best method of performing it known to me/us:

BOOSTER SYSTEM FOR LAUNCH VEHICLE BACKGROUND

Field of the Invention

[1] The present invention relates to an engine system, and more particularly to a

booster system for launch vehicles.

Description of Related Art

[2] Small launch vehicles are designed to provide space launch services with

the aim of responsive and dedicated satellite payload missions. To fulfill launch

capability requirements for heavier payloads and/or higher orbits, most launch

vehicle designers may turn to the variation of strapped-on boosters at the booster

stage. However, the strapped-on boosters has the problem of increased

complexity of the vehicle's external geometry which cause increased

aerodynamic losses during the ascend phase of the launch which is in the dense

part of the atmosphere.

SUMMARY

[3] One objective of the present invention is to provide a booster system for a

launch vehicle, and the booster system replaces such strapped-on boosters by

auxiliary boosters disposed internally so that the cross section of the booster

stage of the launch vehicle can have the same or similar shape as the cross

!0 section of the rocket casing.

[4] Another objective of the present invention is to provide a booster system for

a launch vehicle, and the booster system is capable of enhancing the structural

integrity of the booster stage as well as reducing the complexity of the vehicle's external geometry.

[5] Yet another objective of the present invention is to provide a booster system

for a launch vehicle, and the booster system is capable of reducing aerodynamic

loss during the ascend phase of the launch which is in the dense part of the

atmosphere.

[6] To achieve these or more objectives, the present invention provides a

booster system for a launch vehicle according to one embodiment, and the

booster system includes a plurality of core boosters and a plurality of auxiliary

boosters. The plurality of core boosters and the plurality of auxiliary boosters are

arranged in an inner space of a rocket casing of the launch vehicle, a part of the

plurality of auxiliary boosters surrounds a part of the plurality of core boosters,

and every adjacent two auxiliary boosters of the plurality of auxiliary boosters

are separatable from each other.

[7] In some embodiments, one auxiliary booster of the plurality of auxiliary

boosters is located between adjacent two of the plurality of core boosters.

[8] In some embodiments, one core booster of the plurality of core boosters is

located between adjacent two of the plurality of auxiliary boosters.

[9] In some embodiments, the plurality of auxiliary boosters surrounds one core

booster of the plurality of core boosters.

!0 [10]In some embodiments, the plurality of core boosters surrounds one auxiliary

booster of the plurality of auxiliary boosters.

[11]In some embodiments, an amount of the plurality of core boosters is five, an

amount of the plurality of auxiliary boosters is four, central axes of first, second and third core boosters of the five core boosters are aligned in a first axis, central axes of fourth and fifth core boosters of the five core boosters and the central axis of the first core booster are aligned in a second axis, central axes of two of the four auxiliary boosters are aligned in a third axis, central axes of the other ones of the four auxiliary boosters are aligned in a fourth axis, and the first, second, third and fourth axes intersect each other.

[12]In some embodiments, an amount of the plurality of core boosters is four, an

amount of the plurality of auxiliary boosters is five, the four core boosters

surround a first auxiliary booster of the five auxiliary boosters, central axes of

two of the four core boosters are aligned in a fifth axis, central axes of the other

ones of the four core boosters are aligned in a sixth axis, central axes of second

and third auxiliary boosters of the five auxiliary boosters and the central axis of

the first auxiliary booster are aligned in a seventh axis, central axes of the other

ones of the five auxiliary boosters and the central axis of the first auxiliary

booster are aligned in an eighth axis, and the fifth, sixth, seventh and eighth axes

intersect each other.

[13]In some embodiments, an amount of the plurality of core boosters is three,

an amount of the plurality of auxiliary boosters is three, central axes of the three

core boosters are at vertices of a first triangle, central axes of the three auxiliary

!0 boosters are at vertices of a second triangle overlapping the first triangle.

[14]In some embodiments, an amount of the plurality of core boosters is two, an

amount of the plurality of auxiliary boosters is two, central axes of the two core

boosters are aligned in a ninth axis, and central axes of the two auxiliary boosters are aligned in a tenth axis intersecting the ninth axis.

[15]In some embodiments, the rocket casing is cylindrical.

BRIEF DESCRIPTION OF THE DRAWINGS

[16]After studying the detailed description in conjunction with the following

drawings, other aspects and advantages of the present invention will be

discovered:

Fig. 1 is a schematic diagram of a booster stage of a launch vehicle at a

view point according to an embodiment of the present invention;

Fig. 2 is a schematic diagram of the booster stage at another view point

according to an embodiment of the present invention, to show five core boosters

and four auxiliary boosters in the booster system thereof;

Fig. 3 is a schematic diagram of the booster stage at another view point

according to an embodiment of the present invention, to show four core boosters

and five auxiliary boosters in the booster system thereof;

Fig. 4 is a schematic diagram of the booster stage at another view point

according to an embodiment of the present invention, to show three core

boosters and three auxiliary boosters in the booster system thereof; and

Fig. 5 is a schematic diagram of the booster stage at another view point

according to an embodiment of the present invention, to show two core boosters

!0 and two auxiliary boosters in the booster system thereof. DETAILED DESCRIPTION

[17]Please refer to Fig. 1 and 2, illustrating a booster stage of a launch vehicle

according to an embodiment of the present invention. The booster stage includes a booster system including a plurality of core boosters 2 and a plurality of auxiliary boosters 3. The respective core boosters 2 and the auxiliary boosters 3 are independent from each other and do not belong to each other. The respective auxiliary booster 3 has a smaller radial size than each core booster 2. All the core boosters 2 and the auxiliary boosters 3 are disposed in an inner space of a rocket casing 1 of the launch vehicle, resulting in a cylindrical cross section of the whole booster stage. Therefore, the overall aerodynamics characteristic is possibly maintained throughout the ascending phase of the flight in the dense part of the atmosphere from the ground through vehicle acceleration and maximum dynamic pressure regime. After that, the plurality of auxiliary boosters 3 can be separated from the launch vehicle when the launch vehicle reaches the low-density high altitude.

[18]In the embodiment shown in Fig. 2, there are five core boosters 2 and four

auxiliary boosters 3 in the inner space of the rocket casing 1, i.e., first to fifth

core boosters 2A to 2E and first to fourth auxiliary boosters 3A to 3D. The

central axes G of the first, second and third core boosters 2A to 2C are aligned in

a first axis LI, and the central axes G of the first, fourth and fifth core boosters

2A, 2D and 2E are aligned in a second axis L2. The central axes P of the first

and second auxiliary boosters 3A and 3B are aligned in a third axis L3, and the

!0 central axes P of the third and fourth auxiliary boosters 3C and 3D are aligned in

a fourth axis L4. The first to fourth axes LI to L4 intersect each other at the

central axis G of the first core booster 2A. Preferably, the first axis LI is

substantially perpendicular to the second axis L2, and the third axis L3 is substantially perpendicular to the fourth axis L4. More preferably, an angle between the first and fourth axes LI and L4 and an angle between the first and third axes Li and L3 are about 45 degrees, and an angle between the second and third axes L2 and L3 and an angle between the second and fourth axes L2 and

L4 are about 45 degrees.

[19]The first core booster 2A is surrounded by the second to fifth core boosters

2B to 2E and the first to fourth auxiliary boosters 3A to 3D, and the second to

fifth core boosters 2B to 2E and the first to fourth auxiliary boosters 3A to 3D

are alternately positioned around the first core booster 2A. The second core

booster 2B is located between the first and fourth auxiliary boosters 3A and 3D,

the third core booster 2C is located between the second and third auxiliary

boosters 3B and 3C, the fourth core booster 2D is located between the first and

third auxiliary boosters 3A and 3C, and the fifth core booster 2E is located

between the second and fourth auxiliary boosters 3B and 3D.

[20]However, the present invention is not limited to the configuration of the

core and auxiliary boosters 2 and 3 and the amount of core boosters 2 and the

number of auxiliary boosters 3 in the configuration in the foregoing embodiment

shown in Fig. 2. Other configurations of the core and auxiliary boosters 2 and 3,

different amounts of core boosters 2 and different amounts of auxiliary boosters

!0 3 may also be contemplated in other embodiments, and these other embodiments

are exemplarily explained as follows.

[21]Please refer to Fig. 3, illustrating another embodiment of the booster stage.

In the drawing, four core boosters 2 and five auxiliary boosters 3 are positioned in the inner space of the rocket casing 1, namely first to fourth core boosters 2A to 2D and first to fifth auxiliary boosters 3A to 3E. The central axes G of the first and second core boosters 2A and 2B and the central axis of the first auxiliary booster 3A are aligned in a fifth axis L5, and the central axes G of the third and fourth core boosters 2C and 2D and the central axis of the first auxiliary booster 3A are aligned in a sixth axis L6. The central axes P of the first to third auxiliary boosters 3A to 3C are aligned in a seventh axis L7, and the central axes P of the first, fourth and fifth auxiliary boosters 3A, 3D and 3E are aligned in an eighth axis L8. The fifth to eighth axes L5 to L8 intersect each other at the central axis P of the first auxiliary booster 3A. Preferably, the fifth axis L5 is substantially perpendicular to the sixth axis L6, and the seventh axis

L7 is substantially perpendicular to the eighth axis L8. More preferably, an angle

between the fifth and seventh axes L5 and L7 and an angle between the fifth and

eighth axes L5 and L8 are about 45 degrees, an angle between the sixth and

seventh axes L6 and L7 and an angle between the sixth and eighth axes L6 and

L8 are about 45 degrees.

[22]The first to fourth core boosters 2A to 2D surround the first auxiliary

booster 3A, and the second to fifth auxiliary boosters 3B to 3E also surround the

first auxiliary booster 3A. The first core booster 2A is located between the

!0 second and fourth auxiliary boosters 3B and 3D, the second core booster 2B is

located between the third and fifth auxiliary boosters 3C and 3E, the third core

booster 2C is located between the third and fourth auxiliary boosters 3C and 3D,

and the fourth core booster 2D is located between the second and auxiliary auxiliary boosters 3B and 3E.

[23]Please refer to Fig. 4, illustrating yet another embodiment of the booster

stage. Three core boosters 2 and three auxiliary boosters 3 are disposed in the

inner space of the rocket casing 1, namely first to third core boosters 2A to 2C

and first to third auxiliary boosters 3A to 3C. The central axes G of the first to

third core boosters 2A to 2C aim at the three vertices of a first triangle TI, and

the central axes P of the first to third auxiliary boosters 3A to 3C aim at the three

vertices of a second triangle T2 overlapping the first triangle TI. Preferably, the

first and second triangle TI and T2 are equilateral triangles. More preferably,

centroids of the first and second triangle TI and T2 coincide at the central axis

of the rocket casing 1.

[24]The first core booster 2A is located between the first and third auxiliary

boosters 3A and 3C, the second core booster 2B is located between the first and

second auxiliary boosters 3A and 3B, and the third core booster 2C is located

between the second and third auxiliary boosters 3B and 3C.

[25]Please refer to Fig. 5, illustrating yet another embodiment of the booster

stage. Two core boosters 2 and two auxiliary boosters 3 are located in the inner

space of the rocket casing 1, namely first and second core boosters 2A and 2B

and first and second auxiliary boosters 3A and 3B. The central axes G of the first

!0 and second core boosters 2A and 2B are aligned in a ninth axis L9, and the

central axes P of the first and second auxiliary boosters 3A and 3B are aligned in

a tenth axis Li0 intersecting the ninth axis L9. Preferably, the ninth axis L9 is

substantially perpendicular to the tenth axis L10.

[26]Although the configurations of the core and auxiliary boosters 2 and 3 and

the amount of core boosters 2 and the number of auxiliary boosters 3 in the

respective configuration are exemplarily illustrated in Figs. 2 to 5, more or less

auxiliary boosters 3 paired with the same number of core boosters 2 may also be

contemplated in some embodiments.

[27]While we have shown and described various embodiments in accordance

with the present invention, it is clear to those skilled in the art that further

embodiments may be made without departing from the scope of the present

invention.

Claims

WHAT IS CLAIMED IS:

1. A booster system for a launch vehicle, comprising:

a plurality of core boosters and a plurality of auxiliary boosters, arranged in an

inner space of a rocket casing of a booster stage of the launch vehicle, wherein a

radial size of each core booster of the plurality of core boosters is larger than a radial

size of each auxiliary booster of the plurality of auxiliary boosters, the respective

auxiliary boosters are independent of the respective core boosters, an amount of the

plurality of core boosters is five, an amount of the plurality of auxiliary boosters is

four, central axes of first, second and third core boosters of the five core boosters are

aligned in a first axis, central axes of fourth and fifth core boosters of the five core

boosters and the central axis of the first core booster are aligned in a second axis,

central axes of two of the four auxiliary boosters are aligned in a third axis, central

axes of the other ones of the four auxiliary boosters are aligned in a fourth axis, and

the first, second, third and fourth axes intersect each other.

2. The booster system according to claim 1, wherein one auxiliary booster of

the plurality of auxiliary boosters is located between two adjacent core boosters of the

plurality of core boosters.

3. The booster system according to claim 1, wherein one core booster of the

plurality of core boosters is located between two adjacent auxiliary boosters of the

plurality of auxiliary boosters.

4. The booster system according to claim 1, wherein the plurality of auxiliary

boosters surrounds one core booster of the plurality of core boosters.

5. A booster system for a launch vehicle, comprising: a plurality of core

boosters and a plurality of auxiliary boosters, arranged in an inner space of a rocket

casing of a booster stage of the launch vehicle, wherein a radial size of each core

booster of the plurality of core boosters is larger than a radial size of each auxiliary booster of the plurality of auxiliary boosters, the respective auxiliary boosters are independent of the respective core boosters, and the plurality of core boosters surrounds one auxiliary booster of the plurality of auxiliary boosters.

6. A booster system for a launch vehicle, comprising: a plurality of core

booster of the plurality of core boosters is larger than a radial size of each auxiliary

booster of the plurality of auxiliary boosters, the respective auxiliary boosters are

independent of the respective core boosters, an amount of the plurality of core

boosters is four, an amount of the plurality of auxiliary boosters is five, the four core

boosters surround a first auxiliary booster of the five auxiliary boosters, central axes

of two of the four core boosters are aligned in a fifth axis, central axes of the other

ones of the four core boosters are aligned in a sixth axis, central axes of second and

third auxiliary boosters of the five auxiliary boosters and the central axis of the first

auxiliary booster are aligned in a seventh axis, central axes of the other ones of the

five auxiliary boosters and the central axis of the first auxiliary booster are aligned in

an eighth axis, and the fifth, sixth, seventh and eighth axes intersect each other.

7. A booster system for a launch vehicle, comprising: a plurality of core

independent of the respective core boosters, an amount of the plurality of core

boosters is three, an amount of the plurality of auxiliary boosters is three, central axes

of the three core boosters are at vertices of a first triangle, central axes of the three

auxiliary boosters are at vertices of a second triangle overlapping the first triangle.

8. The booster system according to claim 1, wherein a cross section shape of

the booster stage of the launch vehicle is the same or similar to a cross section shape

of the rocket casing.

9. The booster system according to claim 5, wherein a cross section shape of

of the rocket casing.

10. The booster system according to claim 6, wherein a cross section shape of

of the rocket casing.

11. The booster system according to claim 7, wherein a cross section shape of

of the rocket casing.