Abstract: A steering device includes: an upper column having a cylindrical shape that is disposed on a radially outer side of a steering shaft; a lower column having a cylindrical shape that is fitted to the upper column and is capable of relatively moving in an axial direction with respect to the upper column; an attachment portion that is attached to the upper column and provided with a column long hole; a column bracket that includes a side plate portion located on a side of the upper column and is attached to a vehicle body; a liner slot that is inserted into the column long hole of the attachment portion and restricts an axial movement; and a pin that extends along a vehicle width direction and penetrates through the side plate portion and the liner slot, in which the liner slot is provided with a through-hole through which the pin penetrates.

Abstract: A substrate processing system includes a substrate processing apparatus, an input/output apparatus, a first control apparatus installed with first software, configured to control the substrate processing apparatus based on a first signal output from the input/output apparatus, and configured to acquire a second signal output from the substrate processing apparatus, a second control apparatus installed with second software, and configured to perform same calculation processing as that of the first control apparatus, and not configured to control the substrate processing apparatus, a first distributor configured to distribute the first signal to the second control apparatus, and a second distributor configured to distribute the second signal to the second control apparatus. The second control apparatus outputs a third signal based on the first signal and the second signal.

Abstract: A multi-pulse gas generator includes a pressure vessel, first and second propellants, a barrier membrane that separates the first propellant and the second propellant, an igniter device that produces combustion gas of igniter charge, and an igniter charge combustion gas exhaust device having exhaust holes configured to exhaust the combustion gas of the igniter charge against the second propellant. The barrier membrane includes: a concavely-deformable portion; and a convexly-deformable portion. A flow rate of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the concavely-deformable portion is larger than that of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the convexly-deformable portion.

Abstract: The first solid propellant is formed to have a columnar shape so as for a combustion surface to move to a first direction, and to have an end surface exposed to a combustion space. The surface of first solid propellant except for the end surface is covered with a barrier membrane. The position of combustion surface in the first direction is detected by a position sensor device in an always-on measurement or a fixed-point measurement. Based on the detected result, the consumption amount of the first solid propellant is estimated.

Abstract: A propellant manufacturing method for manufacturing a propellant including a propellant grain having a first surface on which combustion starts upon ignition and a second surface to be coupled to a wall surface that prevents combustion. The manufacturing method includes placing a portion of first propellant having a first burning rate in a first space containing a first position on the second surface; and placing a portion of second propellant having a second burning rate higher than the first burning rate in a second space containing a second position on the first propellant. The method further includes placing a portion of third propellant having a third burning rate higher than the second burning rate in a third space containing a third position on the first propellant. The method further includes completing the propellant grain by simultaneously hardening the entireties of the first propellant, the second propellant, and the third propellant.

Abstract: A multi-pulse gas generator includes a pressure vessel, first and second propellants, a barrier membrane that separates the first propellant and the second propellant, an igniter device that produces combustion gas of igniter charge, and an igniter charge combustion gas exhaust device having exhaust holes configured to exhaust the combustion gas of the igniter charge against the second propellant. The barrier membrane includes: a concavely-deformable portion; and a convexly-deformable portion. A flow rate of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the concavely-deformable portion is larger than that of the combustion gas of the igniter charge exhausted against a portion of the second propellant located outside of the convexly-deformable portion.

Abstract: A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Abstract: A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Abstract: The first solid propellant is formed to have a columnar shape so as for a combustion surface to move to a first direction, and to have an end surface exposed to a combustion space. The surface of first solid propellant except for the end surface is covered with a barrier membrane. The position of combustion surface in the first direction is detected by a position sensor device in an always-on measurement or a fixed-point measurement. Based on the detected result, the consumption amount of the first solid propellant is estimated.

Abstract: A gas generator includes an outer propellant, an inner propellant arranged inside the outer propellant, and a barrier membrane which isolates the outer propellant from the inner propellant. A forward end surface of the inner propellant faces a combustion space. A side surface of the inner propellant is isolated from the combustion space.

Abstract: A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure.

Abstract: A pulse unit of a multi-pulse rocket motor has: a propellant in an internal-burning type shape or an internal-end-burning type shape that is loaded within a motor case; an igniter arranged at an end surface of the propellant; a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter; a forward joint arranged at a forward end of the motor case; and a rearward joint arranged at a rearward end of the motor case. The forward joint is formed so as to be connectable with the rearward joint of another pulse unit. The rearward joint is formed so as to be connectable with the forward joint of yet another pulse unit.

Abstract: A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Abstract: A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Abstract: In a two-pulse rocket motor provided with a pressure vessel, a first propellant placed within the pressure vessel that burns during a first pulse stage, a second propellant placed within the pressure vessel that burns during a second pulse stage following the first pulse stage, and a barrier membrane placed so as to cover the entire initial burning surface of the second propellant, wherein the barrier membrane is provided with an inner barrier membrane that covers the inner peripheral surface of the second propellant and an aft barrier membrane that covers the rear surface of the second propellant, and an end portion where the aft barrier membrane and the inner barrier membrane meet is joined over the entire circumference thereof. The ignition device includes an energy supply unit, an energy transfer unit connected at one end to the energy supply unit, and an ignition unit.

Abstract: A gas generator includes an outer propellant, an inner propellant arranged inside the outer propellant, and a barrier membrane which isolates the outer propellant from the inner propellant. A forward end surface of the inner propellant faces a combustion space. A side surface of the inner propellant is isolated from the combustion space.

Abstract: A combustion gas generator has: a motor case; a first propellant loaded within the motor case to burn at a first pulse; a second propellant loaded within the motor case to burn at a second pulse subsequent to the first pulse; a front motor head fixed to a front portion of the motor case and having a combustion gas exhaust hole; and a rear motor head fixed to a rear portion of the motor case and having a combustion gas exhaust hole. A combustion gas supply control device prevents combustion gas of the first propellant at the first pulse from flowing into the combustion gas exhaust hole of the front motor head and supplies combustion gas of the second propellant at the second pulse to the combustion gas exhaust hole of the front motor head.

Abstract: A multi-pulse gas generator includes a pressure vessel, an outer propellant arranged in the pressure vessel and which has a tubular shape, an intermediate propellant arranged inside the outer propellant and which has a tubular shape, an inner propellant arranged inside the intermediate propellant and which has a tubular shape, an internal structure arranged inside the inner propellant and fixed to the pressure vessel, a first barrier membrane arranged between the outer propellant and the intermediate propellant so as to isolate the outer propellant and the intermediate propellant from each other, and a second barrier membrane arranged between the intermediate propellant and the inner propellant so as to isolate the intermediate propellant and the inner propellant from each other. The outer propellant is supported on its outer surface by the pressure vessel. The inner propellant is supported on its inner surface by the internal structure.

Abstract: In a two-pulse rocket motor provided with a pressure vessel, a first propellant placed within the pressure vessel that burns during a first pulse stage, a second propellant placed within the pressure vessel that burns during a second pulse stage following the first pulse stage, and a barrier membrane placed so as to cover the entire initial burning surface of the second propellant, wherein the barrier membrane is provided with an inner barrier membrane that covers the inner peripheral surface of the second propellant and an aft barrier membrane that covers the rear surface of the second propellant, and an end portion where the aft barrier membrane and the inner barrier membrane meet is joined over the entire circumference thereof. The ignition device includes an energy supply unit, an energy transfer unit connected at one end to the energy supply unit, and an ignition unit.

Abstract: A combustion gas generator has: a motor case; a first propellant loaded within the motor case to burn at a first pulse; a second propellant loaded within the motor case to burn at a second pulse subsequent to the first pulse a front motor head fixed to a front portion of the motor case and having a combustion gas exhaust hole; and a rear motor head fixed to a rear portion of the motor case and having a combustion gas exhaust hole. A combustion gas supply control device prevents combustion gas of the first propellant at the first pulse from flowing into the combustion gas exhaust hole of the front motor head and supplies combustion gas of the second propellant at the second pulse to the combustion gas exhaust hole of the front motor head.