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1. 发明专利

JPS56154400A SEPARATOR FOR DIVISION TYPE NOSE FEARING 失效
公开(公告)号：JPS56154400A
公开(公告)日：1981-11-28
申请号：JP5477080
申请日：1980-04-24
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： B64G1/64 , F42B15/00

2. 发明专利

JPH08183499A TRAVELING VEHICLE FOR SPACE PROBE 失效
公开(公告)号：JPH08183499A
公开(公告)日：1996-07-16
申请号：JP32812794
申请日：1994-12-28
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： B60K17/16 , B60K17/28 , B64G1/16 , F16H48/08
摘要： PURPOSE: To dispense with a center-of-gravity moving motor by engaging a power transmission body, driven by both reduction main wheels, with the reduction main wheels provided at the output shafts of front and rear differential gears, and connecting a mounted body, held movably in the longitudinal direction of a vehicle body, to the power transmission body. CONSTITUTION: Differential gears 8, 9 with one differential main wheel 13 side made the input side from travel motors 5, 6 and with the other differential main wheel 15 side made the output side to wheels 3, 4 are interposed in a power transmission system reaching the wheels 3, 4 from the respective travel motors 5, 6. A transmission member 27 driven by both reduction main wheels 18 is engaged with the reduction main wheels 18 provided at the output shafts 14 of the differential gears 8, 9, and a mounted body 7 held movably in the longitudinal direction of a vehicle body is connected to the transmission member 27. A center-of-gravity moving motor can thereby be dispensed with, and the reduction in the number of part items, the simplification of structure, weight and the like can be realized.

3. 发明专利

JPH1114299A WING FOR AIRFRAME 失效
公开(公告)号：JPH1114299A
公开(公告)日：1999-01-22
申请号：JP16304697
申请日：1997-06-19
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU , MIURA TAKAHIRO
IPC分类号： F42B10/06
摘要： PROBLEM TO BE SOLVED: To ensure light weight, heat resistance and strength by forming a profile of a front edge by a crossbeam member, forming a recess opened on both side surfaces, and charging a heat resistant charging member in the recess. SOLUTION: A wing front edge 10 has a crossbeam member 11 for forming a profile of a front edge part as a basic frame. And, a plurality of rectangular recesses 12 are formed at the member 11 to arrange on both surfaces S1 , S2 in an extending direction of the wing. That is, the recesses 12 formed on one surface side are isolated via ribs 13 in its arranging direction. And, the recesses 12 formed on both side surfaces S1 , S2 are isolated by partition members 14 as a partition part. And, light weight heat resistant charging member (e.g. resin material) 20 is charged in the recess 12 of the member 1 formed in this manner. Thus, light weight, heat resistance and strength can be sufficiently ensured, and its manufacture is easily done at a low cost.

4. 发明专利

JPH08183364A WHEEL DRIVE CONTROL DEVICE 失效
公开(公告)号：JPH08183364A
公开(公告)日：1996-07-16
申请号：JP32834194
申请日：1994-12-28
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： B60K28/14 , B60K17/348
摘要： PURPOSE: To provide a wheel drive control device which can realize smooth running by driving each wheel with minimum required toque distribution in an unpaved ground. CONSTITUTION: In a wheel drive control device for a vehicle driven to run by a wheel individually provided with a drive source, the wheel driven control device comprises a tilt angle detecting means 13 of estimating a tilt angle of grounding each wheel based on a running motion condition and a torque setting means 14 of calculating torque distribution in an acceleratable limit point of each wheel based on the grounding tilt angle from the tilt angle detecting means 13, to feedback control torque of each wheel by comparing a torque value of each wheel obtained from the running motion condition with a preset value obtained from the torque setting means.

5. 发明专利

JPH03220096A AIR INTRODUCING TYPE ROCKET 失效
公开(公告)号：JPH03220096A
公开(公告)日：1991-09-27
申请号：JP1703490
申请日：1990-01-25
申请人： NISSAN MOTOR
发明人： YAMAMOTO YOICHI , ONOSHIMA NOBORU
IPC分类号： B64G1/00
摘要： PURPOSE:To permit the spin of a rocket in flying and stabilize the flying in the direction of the axis of the machine by arranging an outer cylinder forming a secondary combustion chamber on the periphery of an injection nozzle and installing a spinning means for spinning a rocket in the secondary combustion chamber. CONSTITUTION:When the propellant in a primary combustion chamber 19 is ignited, the combustion gas is jetted into a secondary combustion chamber through an injection nozzle 12 from the primary combustion chamber. At the same time, air is introduced into the secondary combustion chamber from the front edge part of an outer cylinder 13, and the air and the combustion gas are violently mixed and combusted in the secondary combustion chamber, and jetted from the secondary combustion chamber, and a prescribed propulsion force is obtained. Since, in this case, a rocket is spun by the injection nozzle 12 installed in the secondary combustion chamber, the flying in the direction of axis of the machine is stabilized, and the air and the combustion gas flow in spiral form in the outer cylinder 13, and the mixing efficiency in the secondary combustion chamber 20 is improved. Accordingly, even if the total length of the secondary combustion chamber, i.e., the total length of the outer cylinder is shortened, the mixing and combustion can be carried out satisfactorily.

6. 发明专利

JPS5989299A DEVICE FOR CHANGING MOTION AROUND AIRFRAME AXIS OF MISSILE 失效
公开(公告)号：JPS5989299A
公开(公告)日：1984-05-23
申请号：JP19665882
申请日：1982-11-09
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： B64G1/28 , B64G1/24 , B64G1/64

7. 发明专利

JPS582120B2 失效
公开(公告)号：JPS582120B2
公开(公告)日：1983-01-14
申请号：JP5477080
申请日：1980-04-24
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： B64G1/64 , F42B15/00

8. 发明专利

JPH094512A ACCELERATOR FOR FLYING OBJECT 失效
公开(公告)号：JPH094512A
公开(公告)日：1997-01-07
申请号：JP15472995
申请日：1995-06-21
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： F02K7/18
摘要： PURPOSE: To accelerate a flying body by utilizing air in the atmosphere and realize the launch of a rocket at low cost, when the flying object is the rocket. CONSTITUTION: The accelerator for flying object is provided with a fuel tank 4 connected to a rocket separatably, plural fuel supply pipes 6 installed in the diameter direction of the fuel tank 4 radially and at an equal interval and rotated around a machine axis and plural rotor blades 10 arranged in the peripheral direction of the fuel tank 4 and supported on the plural fuel supply pipes 6 respectively. In the rotor blades 10, an air intake port 11 is provided on its front edge and also a nozzle 12 is provided on its rear edge and a space between the air intake port 11 of the rotor blade 10 and the nozzle 12 is formed as a rum combustion room 13 for communicating to the fuel supply pipes 6.

9. 发明专利

JPH08177629A ROCKET ENGINE AND ITS ATTITUDE CONTROL METHOD 失效
公开(公告)号：JPH08177629A
公开(公告)日：1996-07-12
申请号：JP32823394
申请日：1994-12-28
申请人： NISSAN MOTOR
发明人： ONOSHIMA NOBORU
IPC分类号： F02K9/72 , F02K9/88
摘要： PURPOSE: To attain downsizing and reducing cost while improving control efficiency by maintaining combustion gas, injected from a subnozzle of a side plaster, at a relatively low temperature so as to eliminate necessity for adjusting a flow amount of gas by a super heat resisting valve, in the case that attitude control is unnecessary. CONSTITUTION: In a rocket engine 1, first in the inside of a main primary combustion chamber 4, a solid propellant 2 is ignited by an igniter 3 to perform combustion, and this combustion gas is respectively introduced to each subcombustion chamber 22 of both side plasters 20 through a main intermediate nozzle 7. Simultaneously with opening a start valve 10, after a liquid oxidant 5 from a tank 6 is introduced to a manifold 12, the gas is injected from a main injector 13 to inside a main combustion chamber 8, also to perform recombustion by mixing with the combustion gas. Further, the recombustion gas is injected from a main nozzle 9 to obtain main thrust. In the case that attitude control is not necessary, combustion gas injected from each subnozzle 23 of both the side plasters 20 is maintained at a relatively low temperature.

10. 发明专利

JPH0742615A ROTATING NOZZLE HOLDING STRUCTURE 失效
公开(公告)号：JPH0742615A
公开(公告)日：1995-02-10
申请号：JP19037693
申请日：1993-07-30
申请人： NISSAN MOTOR
发明人： TAKAGI YASUTADA , ONOSHIMA NOBORU
IPC分类号： B64G1/00 , F02K9/30 , F02K9/84
摘要： PURPOSE:To operate a rotating nozzle smoothly with small driving torque, and prevent problems such as a slight change in nozzle steering angle, and combustion gas leaking from parts other than the rotating nozzle. CONSTITUTION:A nozzle receiver 7 is mounted on the end part of a rocket 1, a rotating nozzle 10 is fitted into the nozzle receiver 7, the rotating nozzle 10 and the nozzle receiver 7 are pivotally-connected. The nozzle receiver is formed with a high pressure cooling gas introduction port 6A and a gas flow passage 6B which comnunicates the high pressure cooling gas introduction port 6A of the nozzle receiver 7 to a clearance S between the rotating nozzle 10 and the nozzle receiver 7.

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