JPH05480Y2 - - Google Patents

Description

[Detailed explanation of the idea] [Purpose of invention]

(Field of Industrial Application) This invention relates to a spin combustion performance measuring device for a rocket motor, which is used to measure the combustion performance (combustion thrust, etc.) of a rocket motor in a spin state. (Prior art) Devices for measuring the combustion performance (combustion thrust, motor internal pressure, etc.) of a rocket motor on the ground include, for example, the device disclosed in Japanese Patent Application Laid-Open No. 72035/1983, and devices with various other structures. However, in order to be able to more accurately grasp the combustion performance of a rocket motor during actual navigation in outer space, the rocket motor is put into a spinning state on the ground and its combustion performance is measured. Combustion performance measurement devices have also been developed. In this way, you can control the combustion performance (combustion thrust, motor internal pressure, etc.) by putting the rocket motor in a spinning state.
For example, there is a spin combustion performance measuring device for measuring the spin combustion performance, which has a structure as shown in FIG. The spin combustion performance measuring device 51 shown in FIG. Bearing units 57a and 57b for rotatably supporting a rotary shaft 56 are fixed on a base portion 55a, and a mounting portion 56a for a rocket motor 58 is provided at the left end portion of the rotary shaft 56 in FIG. A pressure sensor 59 is also provided, and an air turbine blade 60 for making the rocket motor 58 spin is provided at the middle portion of the rotating shaft 56. The right end portion of the rotating shaft 56 in FIG.
A load cell 64 for measuring thrust is connected to a slip ring 62 fixed on the top via a support 61, and is arranged between the vertical wall portion 55b of the rocking table 55 and a thrust receiver 63 fixed to the foundation 53. It has a similar structure. Such a rocket motor combustion performance measuring device 5
1 to measure the combustion performance of the rocket motor 58 in a spinning state, the air turbine blades 6 are
The rotary shaft 56 is rotated by supplying nitrogen or air to the rotary shaft 56, and a predetermined spin is applied to the rocket motor 58 attached to the rotary shaft 56. Next, the rocket motor 58 in this spinning state is ignited to start combustion. During this combustion, the thrust generated by the rocket motor 58 is transmitted to the rotating shaft 56, the bearing units 57a, 5
7b and the rocking table 55, it is transmitted to the thrust measuring load cell 64 and measured. Further, the internal pressure of the rocket motor 58 is measured by inputting the output signal from the pressure sensor 59 to the slip ring 62. (Problems to be Solved by the Invention) However, although such a spin combustion performance measuring device 51 can measure the rocket in a spinning state, it is difficult to measure the rotating shaft 56 on which the rocket motor 58 is attached and the rotating shaft 56. Bearing unit 57 that supports rotatably
a, 57b, etc. are elastic supports 54 made of leaf springs.
Since the rocking system was installed on a rocking table 55 supported by a and 54b, the natural frequency of the rocking system was low, so the spin of the rocket motor 58 was reduced. In the process of spin-up to gradually increase the number of vibrations, the rocking table 55 etc. tend to generate resonance near the natural frequency, making it impossible to perform the spin-up smoothly, and at the same time, the thrust measurement system such as the load cell 64 for thrust measurement There was a problem that vibration was also added to the sensor, reducing measurement accuracy. Also,
Rocking table 5 supported by elastic supports 54a and 54b
Because the situation of 5th grade changes slightly with each combustion test,
There was a problem that the reproducibility was sometimes poor. (Purpose of the invention) This invention was made in view of the above-mentioned conventional problems, and it is possible to improve the motion system by supporting the rotating shaft and rotating shaft support body on which the rocket motor is attached in a highly rigid state. The natural frequency of the thrust force measurement system is made high, and it is possible to smoothly perform spin-up that increases the spin number during the measurement process, and it is possible to reduce the addition of vibration to the thrust force measurement system, allowing highly accurate thrust measurement, etc. The purpose of this invention is to provide a spin combustion performance measuring device that is capable of measuring spin combustion performance.

[Structure of the idea]

(Means for Solving the Problem) This invention relates to a spin combustion performance measurement device used to measure the combustion performance (combustion thrust, internal pressure, etc.) of a rocket motor in a spin state. a rotary shaft support that rotatably supports a rotary shaft having an attachment portion for the rocket motor; a shaft support holding means that slidably holds the rotary shaft support in the axial direction of the rotary shaft; spin imparting means for rotating a rotary shaft to bring the rocket motor into a spinning state; and combustion thrust measurement for measuring the combustion thrust of the rocket motor in a spinning state by being disposed between the shaft support and the thrust receiver. The present invention is characterized in that it comprises a means for measuring internal pressure of the rocket motor, and, if necessary, a means for measuring internal pressure of the rocket motor. (Example 1) FIG. 1 shows a spin combustion performance measuring device according to an embodiment of this invention. The spin combustion performance measuring device 1 shown in the figure has shaft support holding means at two locations on the ground 2. Shaft support holding blocks 3 and 4 are installed, and a cylindrical rotating shaft support 5 is held in the shaft support holding blocks 3 and 4. In this case, the shaft support holding block 3,
4 are roller bearings 3a, 3b, 4, respectively.
a, 4b, each roller bearing 3
a, 3b, 4a, and 4b, the rotary shaft support 5 is connected to the rotary shaft support 5 in the axial direction of the rotary shaft support 5 (the axial direction of the rotary shaft 9, which will be described later, and the left-right direction in FIG. 1).
It is held so that it can slide freely. Further, the shaft support holding blocks 3 and 4 are respectively provided with roller height fine adjustment mechanisms 3c and 4c. The rotary shaft support 5 rotatably supports the rotary shaft 9 through bearings 6, 7, and 8 inside thereof. This rotating shaft 9
has a mounting portion 9a for flange-coupling the rocket motor 10 on the left end portion in FIG. 1, and is also equipped with a pressure sensor 11, and the right end portion in FIG. A slip ring 1 fixed to the inner peripheral side of the rotating shaft support 5 using a base 12 is attached to the end of the small diameter portion 9b.
3 are connected via a coupling 14. This slip ring 13 serves as a motor internal pressure measuring means for receiving the output signal from the pressure sensor 11 and measuring the internal pressure of the rocket motor 10. In this case, both large-diameter ends of the rotating shaft 9 are rotatably installed inside the rotating shaft support 5 via bearings 6 and 7, and the small-diameter portion 9b of the rotating shaft 9 is rotatably installed via bearings 8. It is rotatably provided inside the shaft support 5. Furthermore, hanging hooks 16 and 17 are provided on the upper surface of the rotary shaft support 5, and an electric motor 21 is mounted on the lower surface via a mounting base 19. A V-belt 24 is stretched between a pulley 22 fixed to the output shaft 21a of the electric motor 21 and a pulley 23 fixed to the intermediate portion of the rotary shaft 9. The rotary shaft 9 is rotated by the rotary shaft 9, and a rocket motor 10 attached to the rotary shaft 9 can be given spin. That is, the electric motor 21, the pulleys 22, 23, the V-belt 24, etc. constitute a spin imparting means, and by changing the rotational speed of the electric motor 21, the spin-up gradually increases the number of spins. It has been made possible to do so. Furthermore, one end of a thrust measuring load cell 26 as a thrust measuring means for measuring the combustion thrust of the rocket motor 10 is fixed to the right end surface of the rotary shaft support 5 in FIG. 1 with a nut 27. The other end of the thrust measurement load cell 26 is connected to the vertical wall portion 2 of a thrust receiver 29 fixedly installed on the ground 2.
It is fixed at 9a. When measuring the combustion performance of the rocket motor 10 in a spin state using the rocket motor combustion performance measuring device 1 having such a structure, the electric motor 21 constituting the spin imparting means is operated,
By rotating the rotary shaft 9 via the pulley 22, V-belt 24, and pulley 23 and simultaneously rotating the rocket motor 10 to increase the rotational speed of the electric motor 21, the rocket motor 10 is given a specified number of spins. Gradually spin up until At this time, the vibration during spin-up is transmitted through the rotating shaft support 5 to the roller bearings 3a, 3.
The roller bearings 3a, 3b, 4a, 4b move in the direction perpendicular to the axis of the rotating shaft support 5 (in the vertical and horizontal directions when viewed from the thrust receiver 29 side). The rotary shaft support 5 is held by the shaft support holding blocks 3 and 4 so that it can slide only in its axial direction (the direction of the thrust of the rocket motor 10). Since it is possible to prevent vibrations from having an adverse effect on the subsequent thrust measurement as much as possible, it is possible to improve the accuracy of thrust measurement. Next, the rocket motor 10 is ignited and burned while a prescribed spin is being applied to the rocket motor 10. The thrust generated by the combustion of the rocket motor 10 is applied to each bearing 6,
7, 8 and the rotating shaft support 5, it is transmitted to the load cell 26, and the thrust is measured.
Further, the internal pressure of the rocket motor 10 is measured by inputting an output signal from the pressure sensor 11 to the slip ring 13. Therefore, in the spin combustion performance measuring device 1 according to the first embodiment, the rotating shaft 9 to which the rocket motor 10 is attached, the rotating shaft support 5 that rotatably supports the rotating shaft 9, etc.
By means of shaft support holding means (shaft support holding blocks 3, 4), conventional elastic supports made of leaf springs (elastic supports 54a, 54b in FIG. 3)
Since it is supported in a state with high rigidity compared to when it is supported by
Therefore, since it is possible to prevent resonance from occurring during the spin-up process, it is possible to smoothly spin up the rocket motor, and at the same time, it is possible to prevent vibrations from being added to the thrust measurement load cell 26. The rotary shaft support 5 is made of an integral cylindrical casing structure. Because of this, it is possible to significantly improve maintainability, and it can contribute to significant improvements in reliability and reproducibility. (Example 2) FIG. 2 shows a spin combustion performance measuring device according to another embodiment of this invention, and the spin combustion performance measuring device 31 shown in the figure is a shaft support holding means on the ground 32. A shaft support holding frame 33 is installed, and the shaft support holding frame 33 holds a rotating shaft support 35 having a cylindrical shape. In this case, the shaft support holding frame 33
are roller bearings 33a, 33b, respectively.
Rotating shaft support 35 via 33c, 33d
The axial direction of the rotary shaft support 35 (the axial direction of the rotary shaft 39 described later, the vertical direction in FIG. 2)
It is held so that it can slide freely. Further, the shaft support holding frame 33 is provided with roller position fine adjustment mechanisms 34a, 34b, 34c, and 34d, respectively. The rotary shaft support 35 rotatably supports the rotary shaft 39 through bearings 36, 37, and 38 inside thereof. This rotating shaft 39 has a mounting portion 39 for flange-coupling the rocket motor 40 to the upper end portion in FIG.
a and is also equipped with a pressure sensor 41, and the lower end side portion in FIG. A slip ring 43 fixed to the side using a base 42 is connected via a coupling ring 44. This slip ring 43 is
This constitutes a motor internal pressure measuring means for receiving an output signal from the pressure sensor 41 and measuring the internal pressure of the rocket motor 40. In this case, both ends of the rotating shaft 39 on the large diameter side are mounted on bearings 36 and 37, respectively.
The small diameter portion 39b of the rotary shaft 39 is rotatably installed inside the rotary shaft support 35 via a bearing 38. Further, in the middle part of the rotary shaft 39, the box is fixed to the rotary shaft 39 by the flow of air (other nitrogen, etc.) supplied from the air supply pipe 44 into the box 45 and then discharged from the exhaust pipe 46. The rotary shaft 39 is rotated via an air turbine in the rotary shaft 39, and a rocket motor 40 attached to the rotary shaft 39 can be given spin. That is, the air supply pipe 44, the box 45, the exhaust pipe 46
and the rotating shaft 3 within the box 45.
The spin imparting means of the air turbine unit structure is composed of an air turbine etc. fixed to the
By increasing the airflow, it is possible to perform spin-up, which gradually increases the number of spins. Furthermore, one end of a thrust measuring load cell 48 as a thrust measuring means for measuring the combustion thrust of the rocket motor 40 is fixed to the lower end surface of the rotating shaft support 35 in FIG. 2 with a nut 49. The other end of this thrust measuring load cell 48 is fixed to the ground 32 which also serves as a thrust receiver together with the shaft support holding frame 33. When measuring the combustion performance of the rocket motor 40 in a spin state using the rocket motor combustion performance measuring device 31 having such a structure, air is supplied from the air supply pipe 44 by the spin imparting means. By forming an air flow that exhausts air from the exhaust pipe 46 through the air turbine 45, the rocket motor 40 is rotated at the same time as the rotary shaft 39 is rotated together with the air turbine, thereby increasing the air flow. The motor 40 is gradually spun up to a specified number of spins. At this time, the vibration during spin-up is transmitted to the roller bearing 33 through the rotating shaft support 35.
a, 33b, 33c, 33d, but the roller bearings 33a, 33b, 33c, 3
3d restrains the movement of the rotary shaft support 35 in the direction perpendicular to the axis (vertical and horizontal directions when viewed from the rocket motor 40 side); This is because it is held by the shaft support holding frame 33 so that it can slide only in the thrust direction), so that vibrations during spin-up can be prevented as much as possible from adversely affecting subsequent thrust measurement. , it is possible to increase the accuracy of thrust measurement. Next, while a prescribed spin is applied to the rocket motor 40, the rocket motor 40 is ignited to cause combustion. The thrust generated by the combustion of the rocket motor 40 is applied to each bearing 3.
6, 37, 38 and the rotating shaft support 35, the thrust is transmitted to the load cell 48, and the thrust is measured. Further, the internal pressure of the rocket motor 40 is measured by inputting an output signal from the pressure sensor 41 to the slip ring 43. Therefore, also in the spin combustion performance measuring device 31 according to the second embodiment, the rocket motor 40
The rotary shaft 39 to which the rotary shaft 39 is attached, the rotary shaft support 35 that rotatably supports the rotary shaft 39, etc. are supported by a conventional elastic support made of a leaf spring by a shaft support holding means (shaft support holding frame 33). body (elastic support 54 in FIG.
a, 54b),
Since it is supported in a highly rigid state, it is possible to increase the natural frequency of the motion system, and as in the case of Example 1, the spin-up of the rocket motor is smoothed. , and higher measurement accuracy, and since the thrust of the rocket motor 40 is in the vertical direction, the roller bearings 33a, 33b,
Example 1: Radial load applied to 33c and 33d
It can be made considerably smaller than in the case of 1, and the structure does not apply the weight of the rocket motor 40 to the roller bearings 33a, 33b, 33c, and 33d, making it suitable for high-speed spin. In addition, since an air turbine system in which an air turbine is directly connected to the rotating shaft 39 is used as the spin imparting means, it is possible to perform spin-up even more smoothly, and furthermore, since the air turbine is directly connected to the rotary shaft 39, it is possible to perform spin-up even more smoothly. Since the ground 32 also serves as a thrust receiver, there is an advantage that there is no need to separately install a thrust receiver 29 as in the first embodiment.

[Effect of the idea]

As explained above, according to this invention,
In a spin combustion performance measuring device for measuring the combustion performance of a rocket motor in a spin state, the device comprises a shaft support for rotatably supporting a shaft having a mounting portion of the rocket motor, a shaft support holding means for holding the shaft support so as to be slidable in the axial direction of the shaft, a spin imparting means for rotating the shaft to put the rocket motor in a spin state, and a thrust measuring means disposed between the shaft support and the thrust receiver for measuring the combustion thrust of the rocket motor in the spin state. This makes it possible to smoothly perform a spin-up to increase the spin number during the measurement process by increasing the natural frequency of the motion system including the shaft and the shaft support to which the rocket motor is attached, and by reducing the vibration added to the thrust measuring system, it becomes possible to perform a highly accurate performance measurement, and it is possible to realize a performance evaluation with high reliability and excellent reproducibility, which is a remarkable effect.

[Brief explanation of drawings]

FIG. 1 is a partial longitudinal sectional view of a horizontal spin combustion performance measuring device according to an embodiment of this invention, FIG. 2 is a partial vertical sectional view of a vertical spin combustion performance measuring device according to another embodiment of this invention, and FIG. The figure is an explanatory side view of a conventional spin combustion performance measuring device. 1, 31...Spin combustion performance measuring device, 3, 4
...Shaft support holding block (shaft support holding means), 5, 35... Rotating shaft support, 3a, 3b, 4a, 4b... Roller bearing, 6, 7, 8... Bearing, 9, 39 ... Rotating shaft, 9a, 39a ... Rocket motor mounting part, 10, 40 ... Rocket motor, 11, 41
... Pressure sensor, 21 ... Electric motor (spin imparting means), 26, 48 ... Thrust measurement load cell (thrust force measurement means), 29 ... Thrust receiver, 32 ... Thrust receiver, 33 ... Shaft support holding frame (shaft support holding means), 33a, 33b, 33
c, 33d...Roller bearing, 36, 37,
38... Bearing, 44... Air supply pipe (spin imparting means).

Claims (1)

[Scope of utility model registration request] A spin combustion performance measuring device for measuring the combustion performance of a rocket motor in a spin state, comprising: a rotating shaft support that rotatably supports a rotating shaft having a mounting portion for the rocket motor;
a shaft support holding means for slidably holding the rotary shaft support in the axial direction of the rotary shaft; and a spin imparting means for rotating the rotary shaft to put the rocket motor into a spin state;
A spin combustion performance measuring device comprising: thrust measuring means disposed between the shaft support and the thrust receiver to measure the combustion thrust of the rocket motor in the spinning state.