JPH09315396A - Rocket system - Google Patents

Rocket system

Info

Publication number
JPH09315396A
JPH09315396A JP8200902A JP20090296A JPH09315396A JP H09315396 A JPH09315396 A JP H09315396A JP 8200902 A JP8200902 A JP 8200902A JP 20090296 A JP20090296 A JP 20090296A JP H09315396 A JPH09315396 A JP H09315396A
Authority
JP
Japan
Prior art keywords
center
gravity
rocket
shape
velocity
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
JP8200902A
Other languages
Japanese (ja)
Inventor
Yoshio Kiguchi
善夫 木口
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to JP8200902A priority Critical patent/JPH09315396A/en
Publication of JPH09315396A publication Critical patent/JPH09315396A/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)

Abstract

PROBLEM TO BE SOLVED: To produce the form of a rocket system which can obtain a more stable orbit, and to make it physically more efficient, and to obtain a computing method for velocity in propulsion force. SOLUTION: A computing method calculates the velocity of a rocket in its shape and propulsion force on the basis of the motion of a center of gravity; a law of conservation of momentum; an impulse; natural drop; and hydrodynamics.

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】〔産業上の利用分野〕より安定した軌道を
得ることができ、そして、より効率のよい形となり、し
たがって、より活用できる。[Industrial field of application] A more stable orbit can be obtained, and a more efficient shape can be obtained, and therefore more practical use can be achieved.

【０００２】〔従来の技術〕運動量保存の法則などによ
るものは、存在していない、そして、重心の運動（重心
廻りのモーメント）においても存在してない。[Prior Art] The law of conservation of momentum does not exist, and also does not exist in the movement of the center of gravity (moment around the center of gravity).

【０００３】〔発明が解決しようとする課題〕より安定
した軌道を得るようにすることであり、そして、より効
率のよい形状とすること。[Problems to be solved by the invention] To obtain a more stable trajectory, and to make the shape more efficient.

【０００４】〔課題を解決するための手段〕ロケットの
形状として、円筒形とし、先端部を４５°円スイ形とす
る。平面的には、重心と中心が一致するようにし、バラ
ンスの取れた形状とすること、又、全体重心を推進力部
分により近づけることである。[Means for Solving the Problem] The rocket has a cylindrical shape and a tip portion of a 45 ° circular swivel shape. In plan view, the center of gravity and the center are made to coincide with each other to form a balanced shape, and the overall center of gravity is brought closer to the propulsive force portion.

【０００５】〔作用〕ここにおいて、立面では、重心廻
りのバランスより考えることである。つまり、重心と推
進力部とをより近づけて設ける。又、先端部において
は、バランスの取れた４５°円スイ形として、デザイン
する。そして、推進力における速度についてみると、 ここで、速度（Ｖ）について、自然落下、運動量保存の
法則などより 自然落下により、Ｖｙ＝−ｇｔ、Ｗ＝ｍｇ ｍ＝質
量、運動量、
ｔ＝時間 したがって、速度（Ｖ）を算出することができる。[Operation] Here, in terms of elevation, it is to consider from the balance around the center of gravity. That is, the center of gravity and the propulsion unit are provided closer to each other. In addition, the tip is designed as a well-balanced 45 ° circular swivel shape. And if you look at the speed of propulsion, Here, with respect to the velocity (V), Vy = −gt, W = mg m = mass, momentum,
t = time Therefore, the speed (V) can be calculated.

【０００６】〔実施例〕物理学的にも、そして、自然現
象面より、明白である。[Embodiment] It is clear physically and from the viewpoint of natural phenomena.

【０００７】〔発明の効果〕以上のごとく、形作ること
により、より安定した軌道を得ることができ、かつ、よ
り安全な運転が可能なのである。[Advantages of the Invention] As described above, by forming a shape, a more stable trajectory can be obtained and safer driving is possible.

【図面の簡単な説明】[Brief description of drawings]

【図１】 ロケットの平面図、1] A plan view of a rocket,

【図２】 ロケットの立面図、FIG. 2 is an elevation view of the rocket,

【符号の説明】 ロケット 平面的重心と中心、Ｇ 円筒形 ４５°円スイ形 推進力（Ｆ） 推進力部分（エンジン他） 円筒形の円の半径（ｒ） 空気（大気） 立面的重心Ｇ[Explanation of Codes] Rocket Plane center of gravity and center, G Cylindrical 45 ° circular swivel type Propulsive force (F) Propulsive force part (engine, etc.) Radius of cylindrical circle (r) Air (atmosphere) Elevated center of gravity G

─────────────────────────────────────────────────────
─────────────────────────────────────────────────── ───

【手続補正書】[Procedure amendment]

【提出日】平成８年６月３日[Submission date] June 3, 1996

【手続補正１】[Procedure amendment 1]

【補正対象書類名】明細書[Document name to be amended] Statement

【補正対象項目名】０００５[Correction target item name] 0005

【補正方法】変更[Correction method] Change

【補正内容】[Correction contents]

【０００５】〔作用〕ここにおいて、立面では、重心廻
りのバランスより考えることである。つまり、重心と推
進力部分とをより近づけて設ける。又、先端部において
は、バランスの取れた４５°円スイ形として、デザイン
する。そして、推進力における速度についてみると ここで、速度（Ｖ）について、自然落下、運動量保存の
法則などより [Operation] Here, in terms of elevation, it is to consider from the balance around the center of gravity. That is, the center of gravity and the propulsion portion are provided closer to each other. In addition, the tip is designed as a well-balanced 45 ° circular swivel shape. And if you look at the speed of propulsion Here, regarding the velocity (V), from the laws of spontaneous fall, momentum conservation, etc.

【手続補正２】[Procedure amendment 2]

【補正対象書類名】図面[Document name to be amended] Drawing

【補正対象項目名】図２[Correction target item name] Figure 2

【補正方法】変更[Correction method] Change

【補正内容】[Correction contents]

【図２】 [Fig. 2]

【手続補正３】[Procedure 3]

【補正対象書類名】明細書[Document name to be amended] Statement

【補正対象項目名】符号の説明[Correction target item name] Explanation of sign

【補正方法】追加[Correction method] Added

【補正内容】[Correction contents]

【符号の説明】 ロケット 平面的重心と中心、Ｇ 円筒形 ４５°円スイ形 推進力（Ｆ） 推進力部分（エンジン他） 円筒形の半径（ｒ） 空気（大気） 立面的重心Ｇ ▲１０▼ 円筒形の長さ（Ｈ）[Explanation of symbols] Rocket Plane center of gravity and center, G Cylindrical 45 ° circular swiss type Propulsion (F) Propulsion part (engine, etc.) Cylindrical radius (r) Air (atmosphere) Elevated center of gravity G ▲ 10 ▼ Cylindrical length (H)

Claims (4)

【特許請求の範囲】[Claims] 【請求項１】 本案は、ロケットにおける形状であり、
平面的には、全対称であり、平面的重心と中心が一致し
ていることであり、円形とする。1. The present invention is a shape in a rocket,
In plan view, it is totally symmetric, and the center of gravity of the plane coincides with the center, which is a circle. 【請求項２】 そして、立面的には、左右対称であり、
円筒形とし、先端部においては、４５°円すい形とす
る。それから2. In elevation, it is bilaterally symmetric,
It has a cylindrical shape, and the tip has a 45 ° conical shape. then 【請求項３】 全体的重心は、ロケットの推進力部分の
位置とより近づけて設ける。3. The overall center of gravity is provided closer to the position of the propulsion portion of the rocket. 【請求項４】 又、推進力における速度の算出におい
て、自然落下、運動量保存の法則、力積、流体の力学な
どより、算出することを特徴とするものである。4. The calculation of the velocity of the propulsive force is characterized in that it is calculated from spontaneous fall, the law of conservation of momentum, impulse, fluid dynamics and the like.
JP8200902A 1996-05-31 1996-05-31 Rocket system Pending JPH09315396A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP8200902A JPH09315396A (en) 1996-05-31 1996-05-31 Rocket system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP8200902A JPH09315396A (en) 1996-05-31 1996-05-31 Rocket system

Publications (1)

Publication Number Publication Date
JPH09315396A true JPH09315396A (en) 1997-12-09

Family

ID=16432169

Family Applications (1)

Application Number Title Priority Date Filing Date
JP8200902A Pending JPH09315396A (en) 1996-05-31 1996-05-31 Rocket system

Country Status (1)

Country Link
JP (1) JPH09315396A (en)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5799498A (en) * 1980-12-15 1982-06-21 Mitsubishi Electric Corp Induced flying body

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5799498A (en) * 1980-12-15 1982-06-21 Mitsubishi Electric Corp Induced flying body

Similar Documents

Publication Publication Date Title
US4631971A (en) Apparatus for developing a propulsion force
RU95113429A (en) Control torque gyroscope
WO2020086151A3 (en) Electromagnetic gyroscopic stabilizing propulsion system method and apparatus
JPH09315396A (en) Rocket system
UA74513C2 (en) method for producing a lift and a horizontal thrust
NO20004573D0 (en) Two-axis gyroscope
Leipold et al. Solar sails for space exploration- The development and demonstration of critical technologies in partnership
JPH11107905A (en) Centrifugal force propulsion device
US20050005719A1 (en) Method for generating a non-inertial coriolis force and its application to an internal propulsion device in a closed system
JP3064014U (en) Aerospace centrifugal engine
Li et al. On Optimal Energy Consumption Control Method for Tail Fin Bionic Robotic Fish
JPS5879679A (en) Turning gear
FEARING Toward micromechanical flyers
Hao et al. Study of the influence of rigidity and inertia on electro-hydraulic load simulator.
ES2119603A1 (en) Propulsion and stabilization system for vertical-take-off aircraft
Escher et al. Propulsion technology impacts on airbreathing/rocket powered TSTO concepts
Frunzulica The influence of the propeller slipstream on the aerodynamic characteristics of the aircraft.
JP3047862U (en) Bicycle wheel and its holder
RU2020106667A (en) METHOD FOR DISPOSAL OF ENERGY STREAM CARRIED OUT BY WATER ENVIRONMENTS BY USING GYROSCOPIC EFFECTS
JP2004338040A (en) Group robot system, sensing robot included in the group robot system, base station included in the group robot system, and pheromone robot included in the group robot system
Larina et al. Influence of internal molecular degrees of freedom on the hypersonic rarefied gas flow about a conical body
JPH02275066A (en) Propulsion unit using weight
CN112977881A (en) Space vehicle
Stanciu et al. Use of approximating functions for inverting the thermodynamic function of the gas mass flow.
Halsey A study into the effects and viability of applying lateral force control to an air to ground rocket