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Patent Analysis of

AEROSPACE VEHICLE SYSTEM

Updated Time 15 March 2019

Patent Registration Data

Publication Number

US20090206205A1

Application Number

US12/254456

Application Date

20 October 2008

Publication Date

20 August 2009

Current Assignee

MITSUBISHI HEAVY INDUSTRIES, LTD.

Original Assignee (Applicant)

MITSUBISHI HEAVY INDUSTRIES, LTD.

International Classification

B64G1/40

Cooperative Classification

B64G1/002,B64G1/288,B64G1/641,B64G1/402,B64G1/428

Inventor

KURODA, YOSHIKATSU,ATSUMI, MASAHIRO,ABE, NAOHIKO,KATO, MASAHIRO

Patent Images

This patent contains figures and images illustrating the invention and its embodiment.

AEROSPACE VEHICLE SYSTEM AEROSPACE VEHICLE SYSTEM AEROSPACE VEHICLE SYSTEM
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Abstract

In an aerospace vehicle in which a satellite is detachably adapted to the first step rocket and the second step rocket, an electronic device 65 is installed in the satellite 60, wherein the electronic device 65 controls the first step rocket 10 and the second step rocket 20 before the satellite is detached from the first step rocket 10 and the second step rocket 20. Thereby, it is unnecessary to provide sensors, radio devices and electronic devices for exclusive use with respect to the first step rocket 10 and the second step rocket so that a manufacturing cost of the rockets 10 and 20 can be reduced and a total weight of the rockets 10 and 20 can become lighter by omitting these equipments. Thus, an aerospace vehicle system within the rockets 10 and 20 can be simplified and a launch of the aerospace vehicle can be prepared within a short period.

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Claims

1. In an aerospace vehicle in which a satellite detachably attached to an aerospace vehicle of which a rocket is one, two or more than stepped rocket, an aerospace vehicle system characterized in that said satellite comprises an electronic device for controlling said satellite after said satellite detached from said rocket and controlling said rocket before said satellite detached from said rocket.

2. An aerospace vehicle system as claimed in claim 1, wherein said satellite includes a radio device and various kinds of sensors and said aerospace vehicle system is characterized in that said electronic device is connected to said radio device and said various kinds of sensors through signal lines.

3. An aerospace vehicle system as claimed in claim 1 or claim 2, wherein said rocket has a rocket engine with respective to each step rocket and said aerospace vehicle system is characterized in that said electronic device is connected to said rocket engine in said each step rocket through signal lines.

4. An aerospace vehicle system as claimed in claim 1 or claim 2, wherein a booster is attached to said rocket and the aerospace vehicle system is characterized in that said electronic device is connected to said booster of said rocket engine through signal lines.

5. An aerospace vehicle system as claimed in claim 3, wherein a booster is attached to said rocket and the aerospace vehicle system is characterized in that said electronic device is connected to said booster of said rocket engine through signal lines.

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Claim Tree

  • 1
    1. In an aerospace vehicle in which
    • a satellite detachably attached to an aerospace vehicle of which a rocket is one, two or more than stepped rocket, an aerospace vehicle system characterized in that
    • 2. An aerospace vehicle system as claimed in claim 1, wherein
      • said satellite includes a radio device and various kinds of sensors and said aerospace vehicle system is characterized in that
    • 3. An aerospace vehicle system as claimed in claim 1 or claim 2, wherein
      • said rocket has a rocket engine with respective to each step rocket and said aerospace vehicle system is characterized in that
    • 4. An aerospace vehicle system as claimed in claim 1 or claim 2, wherein
      • a booster is attached to said rocket and the aerospace vehicle system is characterized in that
See all 1 independent claims

Description

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to an aerospace vehicle system, particularly to an aerospace vehicle system with a relatively low manufacture cost and a relatively light body weight.

2. Prior Art

FIG. 2 attached to the present application shows an outline of such a conventional aerospace vehicle system. FIG. 2 shows a two-step rocket having a first step rocket 10 and a second step rocket 20.

The second step rocket 20 is set on the first step rocket 10. A fairing 30 is set on the second step rocket 20 as a front end portion. In the first step rocket 10, a fuel tank 11 and a rocket engine 12 are provided. Further, a plurality of boosters 40 and 50 are included, wherein each booster has a rocket engine 42 (52).

In the second step rocket 20, a fuel tank 21 and a rocket engine 22 are provided. In the fairing 30 set on the second step rocket 20, a satellite 60 is detachably installed.

Accordingly, after igniting the first step rocket 10 and the boosters 40, 50, the second step rocket 20 is separated from the first step rocket 10 and then the separated second step rocket 20 is ignited. After the aerospace vehicle approaching into outer space, the satellite 60 is separated from the second step rocket 20 and the satellite 60 can be put on orbit.

In the above described conventional aerospace vehicle system, the first step rocket 10 and the second step rocket 20 has various kinds of sensors, radio devices and electronic devices (such as computers) are provided with respect to each rockets 10 and 20, respectively. By utilizing the various kinds of the sensors, the radio devices and the electronic devices, the aerospace vehicle and the rockets are controlled.

That is, the first step rocket 10 and the second step rocket 20, each rockets 10 (20) has various kinds of sensors 13 (23) such as an acceleration sensor and angular acceleration (gyro meter), respectively. Further, the each rocket 10 (20) has a radio device 14 (24) for communication with a radio base on the earth and an electronic device (such as computer) 15 (25) are included. The electronic device 15 (25) is electrically connected to the sensor 13 (23), the radio device 14 (24) and the rocket engine 12 (22) through a rocket exclusive use bus (signal lines) 70.

In addition, various kinds of sensors 43 (53), a radio device 44 (54) and an electronic device 45 (54) are provided to the respective booster 40 (50). The electronic device 45 (55) is electrically connected to the various kinds of sensors 43 (53), the radio device 44 (54) and a rocket engine 42 (52) through a rocket exclusive use bus (signal lines).

Accordingly, in accordance with signals obtained from the respective sensors 13, 23, 43 and 53 and commands received from the radio devices 14, 24, 44 and 54, the electronic devices 15, 25, 45 and 55 can control the rocket engines 12, 22, 42 and 53, respectively.

On the other hand, the satellite 60 is put on outer space by the two stepped rocket, the satellite 60 is controlled by itself by utilizing various kinds of sensors, a radio device and an electronic device (such as a computer), and those are equipped in the satellite for an exclusive use.

That is, in the satellite 60, various kinds of exclusive use satellite sensors 63, an exclusive use radio device 64 for communicating with a radio base on the earth and an exclusive use electronic device (such as computer) 65 are installed. The electronic device 65 is electrically connected to the various kinds of sensors 63 and the radio device 64 through an exclusive use satellite bus (signal lines) 80.

Accordingly, in the satellite 60 separated from the two stepped rocket, in accordance with signals obtained by the various kinds of sensors 63 and commands received from the radio device 64, the satellite can be controlled by itself.

In the above described conventional aerospace vehicle system, after the two stepped rocket carried the satellite 60 to outer space, a lot of various kinds of expensive sensors 13, 23, 43 and 53, expensive radio devices 14, 24, 44 and 45 and expensive electronic devices 15, 25, 45 and 55 are wasted al all. By including these equipments, its manufacturing cost and its total body weight of the first step rocket and the second step rocket 20 are increased. Further, aerospace vehicle systems in the first step rocket 10 and the second step rocket 20 become very complicated and a time period for preparing a launch of an aerospace vehicle becomes longer.

U.S. Patent Publication No. 2005/0150998 discloses a communication structure for an aerospace vehicle in which a satellite is not shipped.

Devries describes, “Sensors are accessible and coupled to ordnance controller 14 via addressable bus 22”, at a paragraph of

in U.S. Patent Publication No. 2005/0150998. By utilizing the addressable bus 22, the initiator and the sensors can be controlled by the single ordnance controller 14.

SUMMARY OF THE INVENTION

To resolve the above subject, in an aerospace vehicle according to the present invention in which a space tool such as an artificial satellite (herein after, it is referred as “satellite”) detachably attached to an aerospace vehicle of which a rocket is one, two or more than stepped rocket, the aerospace vehicle system is characterized in that the satellite comprises an electronic device for controlling the satellite after the satellite detached from the rocket and controlling the rocket before the satellite detached from the rocket.

To resolve the above subject, an aerospace vehicle system according to the present invention comprises a satellite including a radio device and various kinds of sensors and the aerospace vehicle system is characterized in that the electronic device is connected to the radio device and the various kinds of sensors through signal lines in the aerospace vehicle system according to the present invention.

To resolve the above subject, an aerospace vehicle system according to the present invention comprises a rocket having a rocket engine with respective to each step rocket and the aerospace vehicle system is characterized in that the electronic device is connected to the rocket engine in the each step rocket through signal lines in the aerospace vehicle system according to the present invention.

To resolve the above subject, an aerospace vehicle system according to the present invention comprises at least one booster attached to a rocket and the aerospace vehicle system is characterized in that the electronic device is connected to the booster of the rocket engine through signal lines in the aerospace vehicle system according to the present invention.

In the aerospace vehicle system according to the present invention, an aerospace vehicle comprises a satellite detachably attached from the first step rocket the second step rocket and more step rocket wherein an electronic device installed at the satellite controls not only the satellite but also the each step rocket. Therefore, it is unnecessary for each step rocket to provide exclusive use sensors, an exclusive use radio device and an exclusive use electronic device. As the result, a manufacturing cost and a total body weight of the rocket can be decreased and a communication/control system in each rocket can be simplified and a time period for launching the aerospace vehicle can be shortened.

In the aerospace vehicle system according to the present invention, after the satellite is detached from the rocket, an electronic device installed in the satellite controls the satellite through signal lines in accordance with signals obtained from various kinds of sensors and commands received from the radio device

In the aerospace vehicle system according to the present invention, before the satellite is detached from the rocket, an electronic device installed in the satellite controls a rocket engine of each step rocket.

In the aerospace vehicle system according to the present invention, before the satellite is detached from the rocket, an electronic device installed in the satellite controls a rocket engine of each booster attached to a respective step rocket through signal lines.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 shows an outline of an aerospace vehicle of the first embodiment according to the present invention.

FIG. 2 shows an outline of a conventional aerospace vehicle system.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

The present invention relates to an aerospace vehicle in which a satellite is installed, wherein the aerospace vehicle has two stepped rocket or more than two stepped rocket and an installed satellite is capable of separating from the rocket. Rocket exclusive use sensors, rocket exclusive use radio devices and rocket exclusive use electronic devices (such as computers) are not installed in the rocket. Before the satellite is separated from the rocket, the rocket is controlled by an electronic device installed in the satellite. An embodiment as described below is the best mode of the embodiment of the present invention.

Embodiment 1

FIG. 1 shows an aerospace vehicle system of the first embodiment according to the present invention. The embodiment employs a two stepped rocket consisted of the first step rocket 10 and the second step rocket 20.

That is, the second step rocket 20 is provided on the first step rocket 10 and a fairing 30 is set on the second step rocket 20 as a front end portion.

The first step rocket 10 comprises a fuel tank 11 and a rocket engine 12. Further, a plurality of boosters 40 and 50 having rocket engines 42 and 52 are attached.

The second step rocket 20 comprises a fuel tank 21 and a rocket engine 22. In the fairing 30 on the second step rocket 20, a satellite 60 is detachably installed.

Although the embodiment shows two stepped rocket as an aerospace vehicle system, the aerospace vehicle system according to the present invention may employ a first stepped rocket and exclude the boosters 40 and 50.

The first step rocket 10 and the second step rocket 20 need not to comprise various kinds of sensors such as an acceleration sensor, an angular acceleration sensor (gyro meter), a radio device for communicating with a radio base on the earth and an electronic device (such as computer), respectively.

The various kinds of sensors, the radio device and the electronic device (such as computer) are not installed in the boosters 40 and 50.

On the other hand, various kinds of sensor such as an acceleration sensor 63, a radio device for communicating with a radio base on the earth and an electronic device (such as computer) 65 are only installed in the satellite 60 in the fairing. The satellite 60 can be detached from the fairing on the second step rocket 20.

The electronic device 65 is electrically connected to the various kinds of sensors 63 and the radio device 64 through a rocket-satellite common bus (signal line) 90. Further, the rocket engine 12 of the first step rocket 10 and the rocket engine 22 of the second step rocket 20 and jet engines 42 and 52 of the boosters 40 and 50 are electrically connected within the aerospace vehicle system. As the rocket-satellite common use bus 90, a bus disclosed in the patent document 1 is applicable.

Accordingly, before the satellite 60 is separated from the second step rocket, the electronic device 65 can control the all rocket engines 12, 22, 42 and 52 in accordance with signals obtained form various kinds of sensors 63 and commands received from the radio device 64. After the satellite 60 is separated from the second stepped rocket, the satellite is controlled by itself in accordance with signals from various kinds of sensors 63 and commands received from the radio device 64.

A pressure sensor and a thermo sensor (not illustrated in the drawings) are adapted to the rocket engines 12, 22, 42 and 52. These sensors and the electronic device 65 are electrically connected through the rocket-satellite common use bus 90.

When the satellite 60 is separated from the two stepped rocket, the rocket-satellite common use bus 90 is divided into a satellite portion and a rocket portion.

As described above, in the embodiment, rocket exclusive-use sensors, an exclusive use radio device and an exclusive use electromagnetic device (computer) are not installed in the first step rocket 10 and the second step rocket 20, respectively. Before the satellite 60 is separated from the first step rocket 10 and the second step rocket 20, the electronic device 65 installed in the satellite 60 controls the first step rocket 10 and the second step rocket 20. As the result, the manufacturing cost and the total weight of the first step rocket 10 and the second step rocket can be reduced by omitting these equipments. In addition, it is obtained an effect that an aerospace vehicle system arranged within the first step rocket 10 and the second step rocket 20 can be simplified and a time period for preparing a launch of an aerospace vehicle can be shortened.

On the other words, in the conventional aerospace vehicle system, expensive electronic devices, sensors and radio devices are wasted together with a launched rocket after the satellite is separated from the rocket. Therefore, an aerospace vehicle is required high manufacturing cost, heavy total weight, complicated systems and a long launch time period. On the contrary, the present invention provides the minimum system with the minimum number of electronic devices, sensors and radio devices so that an aerospace vehicle can be manufactured with remarkably low manufacturing cost and a lighter total weight. A launch of the aerospace vehicle can be very adequately prepared.

After the satellite 60 is separated from the first step rocket 10 and the second step rocket 20, the satellite 60 is self-controlled by the electronic device 65 installed in the satellite 60.

The electronic device 65 installed in the satellite 60 has sufficient capability for controlling the first step rocket 10 and the second step rocket 20 as well as the satellite 60.

Further, in the above embodiment, although the rocket engines 12 and 22 use liquid fuel in the fuel tanks 11 and 12, solid fuel is also applicable to the present invention instead of the liquid fuel.

In the above embodiment, although the two stepped rocket is described, a three, four or more than stepped rocket is also applicable to the present invention.

The present invention is broadly applicable in an industry as an aerospace vehicle system with a simple structure, a low manufacturing cost and light weight.

Having thereby described the subject matter of the present invention, it should be apparent that many substitutions, modifications, and variations of the invention are possible in light of the above teachings. It is therefore to be understood that the invention as taught and described herein is only to be limited to the extent of the breadth and scope of the appended claims.

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Patent Valuation

11.0/100 Score

Market Attractiveness

It shows from an IP point of view how many competitors are active and innovations are made in the different technical fields of the company. On a company level, the market attractiveness is often also an indicator of how diversified a company is. Here we look into the commercial relevance of the market.

41.0/100 Score

Market Coverage

It shows the sizes of the market that is covered with the IP and in how many countries the IP guarantees protection. It reflects a market size that is potentially addressable with the invented technology/formulation with a legal protection which also includes a freedom to operate. Here we look into the size of the impacted market.

53.22/100 Score

Technology Quality

It shows the degree of innovation that can be derived from a company’s IP. Here we look into ease of detection, ability to design around and significance of the patented feature to the product/service.

90.0/100 Score

Assignee Score

It takes the R&D behavior of the company itself into account that results in IP. During the invention phase, larger companies are considered to assign a higher R&D budget on a certain technology field, these companies have a better influence on their market, on what is marketable and what might lead to a standard.

22.18/100 Score

Legal Score

It shows the legal strength of IP in terms of its degree of protecting effect. Here we look into claim scope, claim breadth, claim quality, stability and priority.

Citation

Title Current Assignee Application Date Publication Date
Space transfer vehicle and integrated guidance launch system SCOTT; DAVID R. 30 January 1990 16 February 1993
Modular mother satellite bus for subsidiary payloads PERKINS, FREDERICK W. 29 June 1990 06 October 1992
Satellite spin inversion using a single degree of freedom momentum storage device HUGHES ELECTRONICS CORPORATION 13 March 1997 02 June 1998
System for the delivery and orbital maintenance of micro satellites and small space-based instruments SPACE LAUNCH CORPORATION 27 March 2002 26 July 2005
Modular mother satellite bus for subsidiary payloads PERKINS, FREDERICK W. 01 May 1992 21 December 1993
Title Current Assignee Application Date Publication Date
模块化的双组元推进系统 上海卫星工程研究所 11 September 2014 24 August 2016
模块化的双组元推进系统 上海卫星工程研究所 11 September 2014 07 January 2015
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