CN110794484A - Weather rocket arrow of inversion type sonde - Google Patents
Weather rocket arrow of inversion type sonde Download PDFInfo
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- CN110794484A CN110794484A CN201911159391.0A CN201911159391A CN110794484A CN 110794484 A CN110794484 A CN 110794484A CN 201911159391 A CN201911159391 A CN 201911159391A CN 110794484 A CN110794484 A CN 110794484A
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- sonde
- seat
- fixing ring
- mounting seat
- rope
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01W—METEOROLOGY
- G01W1/00—Meteorology
- G01W1/08—Adaptations of balloons, missiles, or aircraft for meteorological purposes; Radiosondes
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- Environmental & Geological Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Atmospheric Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
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- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses a meteorological rocket arrow of an inverted sonde, belonging to the technical field of meteorological rockets and comprising: the device comprises a fairing shell, a guide seat, a sonde, a spring, a sonde mounting seat, a sonde connecting rope, an instrument seat and a parachute assembly; the parachute assembly is arranged in the instrument base, and the other end of the parachute assembly is connected with the instrument base through a connecting rope; the inner circumferential surface of the opening end of the fairing shell is sleeved outside the instrument base, and the sonde mounting seat is positioned in the fairing shell; the guide seat is arranged in the fairing shell, one end of the spring is fixedly connected with the connecting part at the end part of the guide seat, and the other end of the spring is abutted against the sonde mounting seat; the sonde is arranged in the fairing shell in an inverted mode; one ends of the two sonde connecting ropes are connected with the bottoms of the sondes, and the other ends of the two sonde connecting ropes respectively penetrate through the two wire passing holes of the sonde mounting seat in a one-to-one correspondence manner and are connected with the closed end of the instrument seat; the invention can ensure that the sonde can receive satellite navigation signals in the arrow loading and rising or parachute falling process.
Description
Technical Field
The invention belongs to the technical field of meteorological rockets, and particularly relates to a meteorological rocket arrow of an inverted sonde.
Background
The meteorological rocket is used for detecting meteorological parameters within 60km of the adjacent space, the meteorological rocket carries the sonde to be launched and lifted off through the launching device, the rocket sonde is separated from the rocket when the rocket flies to a preset height, then the parachute is unfolded, the suspended sonde descends, and the atmospheric parameters are measured through the sensor on the sonde in the descending process.
The design of sounding rocket (space agency, 1 st edition of 12 p 1993) introduces the working procedures of separating mechanism and recovering system of meteorological rocket, and introduces parachute system, control device and initiating device in more detail. Design and test of TY-4 sounding rocket separation device (annual meeting of the national institute of space navigation, China, 2002) introduced the structure and working principle of TY-4 sounding rocket separation device and the related conditions of ground test and flight test. The comprehensive assessment of the accuracy of detection data of an adjacent space meteorological rocket (physical science and report, vol.62, 19 of 2013) introduces the composition of the adjacent space meteorological rocket and the working process of a detection system.
Disclosure of Invention
In view of this, the invention provides a meteorological rocket arrow of an inverted sonde, which can ensure that the sonde can receive satellite navigation signals in the processes of rocket loading and ascending or parachute descending.
The invention is realized by the following technical scheme:
a weather rocket arrow for an inverted sonde, comprising: the device comprises a fairing shell, a guide seat, a sonde, a spring, a sonde mounting seat, a sonde connecting rope, an instrument seat and a parachute assembly;
connecting parts connected with the fairing shell are respectively arranged at two ends of the guide seat; an axial round hole for mounting a sonde is processed on the guide seat;
the sonde mounting seat is of a cylindrical structure with openings at two ends, flanges are processed at two ends of the sonde mounting seat, and two wire passing holes which are symmetrical along the axis of the cylinder are processed on the circumferential surface of the cylinder;
the instrument base is of a cylindrical structure with one open end and one closed end;
the top of the sonde is provided with a temperature sensor, and the bottom of the sonde is provided with a satellite navigation antenna; a shaft shoulder is arranged on the outer circumferential surface of the sonde;
the overall connection relationship is as follows: the parachute assembly is arranged in the instrument stand, the bottom end of the parachute assembly is connected with an external arrow body through a connecting rope, and the other end of the parachute assembly is connected with the instrument stand through the connecting rope; a canopy capable of separating arrow bodies is arranged in the parachute assembly;
the inner circumferential surface of the opening end of the fairing shell is sleeved outside the instrument stand, and the opening of the fairing shell is closed by the instrument stand; the sonde mounting seat is positioned in the fairing shell and coaxially fixed on the end face of the closed end of the sonde base;
the guide seat is arranged in the fairing shell and is fixedly connected with the fairing shell through connecting parts at two ends of the guide seat; the guide seat is coaxially opposite to the sonde mounting seat, one end of the spring is fixedly connected with the connecting part at the end part of the guide seat, the other end of the spring is abutted against the sonde mounting seat, and the spring is in a compressed state under the action of the gravity of the fairing shell and the guide seat;
the sonde is arranged in the fairing shell in an inverted mode, namely the top of the sonde is located in the sonde mounting seat and supported on the end face of the sonde mounting seat through a shaft shoulder of the sonde, and the bottom of the sonde is coaxially arranged in an axial round hole of the guide seat after the sonde penetrates through the spring; one ends of the two sonde connecting ropes are connected with the bottoms of the sondes, and the other ends of the two sonde connecting ropes respectively penetrate through the two wire passing holes of the sonde mounting seat in a one-to-one correspondence manner and are connected with the closed end of the instrument seat; the two sonde connecting ropes are symmetrically distributed along the axis of the sonde, and the length of the two sonde connecting ropes is the same.
Furthermore, the connecting parts at the two ends of the guide seat are respectively a front fixing ring and a rear fixing ring; the outer circumferential surfaces of the front fixing ring and the rear fixing ring are consistent with the inner surface profile of the fairing shell at the positions of the front fixing ring and the rear fixing ring;
step surfaces for mounting the front fixing ring and the rear fixing ring are respectively processed at two ends of the guide seat;
the front fixing ring and the rear fixing ring are fixed on the step surfaces at the two ends of the guide seat through an adhesive; and the outer circumferential surfaces of the front fixing ring and the rear fixing ring are attached to the inner surface of the fairing shell and fixed through bonding.
And one end of the connecting ring is arranged on the inner circumferential surface of the opening end of the fairing shell and fixedly connected through bonding, and the other end of the connecting ring is sleeved on the outer part of the instrument stand but not fixed.
Further, the parachute assembly comprises: the umbrella comprises an umbrella coat, a main umbrella rope, a cotton rope, an umbrella bag and an umbrella bag buffer rope; the main parachute line is arranged at one end of the canopy, the other end of the canopy is connected with the parachute bag through a cotton rope, and the outside of the parachute bag is connected with a parachute bag buffer line; the umbrella cover is folded and arranged in the umbrella bag when not in operation; the cotton rope can be broken when the tension reaches a set value;
the parachute assembly is arranged in the instrument stand, and one end of the parachute assembly is connected with an external arrow body through a parachute package buffer rope; the other end is connected with the inner bottom surface of the instrument stand through a main umbrella rope.
Furthermore, the spring is fixedly connected with the rear fixing ring in a bonding mode through an adhesive.
Has the advantages that: because the satellite navigation antenna is arranged at the bottom of the sonde, in order to enable the sonde to receive good satellite navigation signals in the process of ascending along with the rocket, the sonde adopts an inverted installation mode that the bottom is arranged above and the top is arranged below in the rocket, so that the integrity and the continuity of detection data are ensured; when the rocket flies to a designated height and is separated from the sonde, the sonde completes a posture turning action relative to the parachute assembly in high altitude, after the canopy is inflated, the sonde mounting seat, the instrument seat and the parachute assembly are integrally turned over, so that the bottom of the sonde points to the sky and the top of the sonde points to the ground in the descending process along with the canopy, a satellite navigation antenna of the sonde is guaranteed to have good signals, meanwhile, the temperature sensor can perform accurate measurement, and the detection precision of the meteorological rocket is improved.
Drawings
FIG. 1 is a structural component diagram of the present invention;
FIGS. 2-5 are flowcharts illustrating the operation of the present invention;
the parachute comprises a fairing shell, 2 parts of a front fixing ring, 3 parts of a guide seat, 4 parts of a sonde, 5 parts of a rear fixing ring, 6 parts of a spring, 7 parts of a sonde mounting seat, 8 parts of a sonde connecting rope, 9 parts of a connecting ring, 10 parts of an instrument seat, 11 parts of a parachute assembly, 12 parts of a canopy, 13 parts of a main parachute rope, 14 parts of cotton ropes, 15 parts of a parachute pack, 16 parts of a parachute pack buffer rope and 17 parts of a rocket body.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a meteorological rocket arrow of an inverted sonde, referring to fig. 1, including: the parachute assembly comprises a fairing shell 1, a front fixing ring 2, a guide seat 3, a sonde 4, a rear fixing ring 5, a spring 6, a sonde mounting seat 7, a sonde connecting rope 8, a connecting ring 9, an instrument seat 10 and a parachute assembly 11;
the outer circumferential surface of the front fixing ring 2 is consistent with the inner profile of the fairing shell 1 at the position of the front fixing ring;
the outer circumferential surface of the rear fixing ring 5 is consistent with the inner profile of the fairing shell 1 at the position of the rear fixing ring, and an annular groove for mounting a spring 6 is processed on one end face of the rear fixing ring;
the outer circumferential surface of the guide seat 3 is a conical surface, and step surfaces for mounting the front fixing ring 2 and the rear fixing ring 5 are respectively processed at two ends of the guide seat 3; an axial round hole for installing the sonde 4 is processed on the guide seat 3;
the sonde mounting seat 7 is a cylinder with openings at two ends, flanges are processed at two ends of the cylinder, and an annular groove for mounting the spring 6 is processed on the end face of one flange; two wire passing holes which are symmetrical along the axis are processed on the circumferential surface of the cylinder;
the instrument base 10 is a cylinder with an opening at one end and a closed end;
referring to fig. 2 and 3, the parachute assembly 11 comprises: a canopy 12, a main parachute line 13, a cotton line 14, a parachute pack 15 and a parachute pack buffer line 16; the main umbrella rope 13 is arranged at one end of the umbrella coat 12, the other end of the umbrella coat 12 is connected with the umbrella bag 15 through a cotton rope 14, and an umbrella bag buffer rope 16 is connected outside the umbrella bag 15; the umbrella coat 12 is folded and arranged in the umbrella bag 15 when not in work; the cotton rope 14 can be broken when the tension reaches a set value;
the top of the sonde 4 is provided with a temperature sensor, and the bottom of the sonde 4 is provided with a satellite navigation antenna; a shaft shoulder is arranged on the outer circumferential surface of the sonde 4 close to the top;
the overall connection relationship is as follows: the parachute pack 15 of the parachute assembly 11 is connected with an external arrow body 17 through a parachute pack buffer rope 16; the instrument stand 10 is sleeved outside a parachute bag 15 of the parachute assembly 11 through an opening of the instrument stand, and the parachute assembly 11 is connected with the inner bottom surface of the instrument stand 10 through a main parachute rope 13;
the inner circumferential surface of the opening end of the fairing shell 1 is sleeved outside the instrument stand 10 through a connecting ring 9, and the opening of the fairing shell 1 is closed by the instrument stand 10; one end of the connecting ring 9 is arranged in the fairing shell 1 and fixedly connected through bonding, and the other end of the connecting ring is sleeved outside the instrument stand 10 but is not fixed with the instrument stand 10;
the sonde mounting seat 7 is positioned in the fairing shell 1, and a flange of the sonde mounting seat 7 is coaxially fixed on the end face of the closed end of the instrument seat 10 through a screw;
the front fixing ring 2 and the rear fixing ring 5 are respectively fixed on the step surfaces at two ends of the guide seat 3 through adhesives; the front fixing ring 2, the guide seat 3 and the rear fixing ring 5 are integrally arranged in the fairing shell 1, and the outer circumferential surfaces of the front fixing ring 2 and the rear fixing ring 5 are attached to the inner surface of the fairing shell 1 and fixed through bonding; the rear fixing ring 5 is coaxially opposite to the sonde mounting seat 7, one end of the spring 6 is fixedly connected with the rear fixing ring 5 in a bonding mode through an adhesive, the other end of the spring 6 is abutted to the sonde mounting seat 7, and the spring 6 is in a compressed state under the action of gravity of the fairing shell 1, the front fixing ring 2, the guide seat 3 and the rear fixing ring 5 and used for providing power for separating the sonde 4 from the fairing shell 1;
the sonde 4 is arranged in the fairing shell 1 in an inverted mode, namely the top of the sonde 4 is located in the sonde mounting seat 7 and supported on the end face of the sonde mounting seat 7 through a shaft shoulder of the sonde 4, and the bottom of the sonde 4 is coaxially mounted in an axial round hole of the guide seat 3 after penetrating through the spring 6; one ends of the two sonde connecting ropes 8 are connected with the bottom of the sonde 4, and the other ends of the two sonde connecting ropes respectively penetrate through the two wire passing holes of the sonde mounting seat 7 in a one-to-one correspondence manner and are connected with the closed end of the instrument seat 10; the two sonde connecting ropes 8 are symmetrically distributed along the axis of the sonde 4, and the length of the two sonde connecting ropes 8 is the same.
The working principle is as follows: referring to the attached drawings 2-5, when the rocket flies to a set height, head separation is carried out, the rocket is positioned in a rising section at the moment, the fairing shell 1 is separated from the rocket 17, under the action of the elastic force of the spring 6, the whole formed by the fairing shell 1, the front fixing ring 2, the guide seat 3, the rear fixing ring 5 and the connecting ring 9 is separated from the whole formed by the instrument seat 10 and the sonde mounting seat 7, then the sonde 4 loses axial constraint and is separated from the fairing shell 1 in a relative motion manner, and after the sonde 4 is separated from the fairing shell 1, attitude turning is completed under the action of a connecting rope 8 of the sonde, so that the top of the sonde faces upwards and the bottom of the sonde faces downwards;
meanwhile, under the action of the sonde 4, the sonde mounting seat 7 and the instrument seat 10, a main parachute rope 13 of the parachute assembly 11 is straightened, the canopy 12 is pulled out of the canopy 15, a cotton rope 14 connected between the canopy 12 and the canopy 15 is broken to finish the unfolding action of the canopy 12, the canopy 12 is inflated in the falling process after being unfolded, and the sonde 4, the sonde mounting seat 7, the instrument seat 10 and the parachute assembly 11 are integrally turned over, so that the bottom of the sonde 4 faces upwards and the top of the sonde 4 faces downwards; the canopy 12 is suspended with the sonde 4 and descends to complete the measurement of atmospheric parameters.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A meteorological rocket arrow of an inverted sonde, comprising: the device comprises a fairing shell (1), a guide seat (3), a sonde (4), a spring (6), a sonde mounting seat (7), a sonde connecting rope (8), an instrument seat (10) and a parachute assembly (11);
connecting parts connected with the fairing shell (1) are respectively arranged at two ends of the guide seat (3); an axial round hole for mounting the sonde (4) is processed on the guide seat (3);
the sonde mounting seat (7) is of a cylindrical structure with openings at two ends, flanges are processed at two ends of the sonde mounting seat, and two wire passing holes which are symmetrical along the axis of the cylinder are processed on the circumferential surface of the cylinder;
the instrument base (10) is of a cylindrical structure with an opening at one end and a closed end;
the top of the sonde (4) is provided with a temperature sensor, and the bottom of the sonde is provided with a satellite navigation antenna; a shaft shoulder is arranged on the outer circumferential surface of the sonde (4);
the overall connection relationship is as follows: the parachute assembly (11) is installed in the instrument stand (10), the bottom end of the parachute assembly (11) is connected with an external arrow body (17) through a connecting rope, and the other end of the parachute assembly is connected with the instrument stand (10) through the connecting rope; a canopy (12) which can be separated by arrow bodies (17) is arranged in the parachute assembly (11);
the inner circumferential surface of the opening end of the fairing shell (1) is sleeved outside the instrument base (10), and the opening of the fairing shell (1) is closed by the instrument base (10); the sonde mounting seat (7) is positioned in the fairing shell (1), and the sonde mounting seat (7) is coaxially fixed on the end face of the closed end of the instrument seat (10);
the guide seat (3) is arranged in the fairing shell (1) and is fixedly connected with the fairing shell (1) through connecting parts at two ends of the guide seat; the guide seat (3) is coaxially opposite to the sonde mounting seat (7), one end of the spring (6) is fixedly connected with the connecting part at the end part of the guide seat (3), the other end of the spring is abutted against the sonde mounting seat, and the spring (6) is in a compressed state under the action of the gravity of the fairing shell (1) and the guide seat (3);
the sonde (4) is arranged in the fairing shell (1) in an inverted mode, namely the top of the sonde (4) is located in the sonde mounting seat (7) and supported on the end face of the sonde mounting seat (7) through a shaft shoulder of the sonde (4), and the bottom of the sonde (4) is coaxially mounted in an axial round hole of the guide seat (3) after penetrating through the spring (6); one ends of the two sonde connecting ropes (8) are connected with the bottom of the sonde (4), and the other ends of the two sonde connecting ropes respectively penetrate through the two wire passing holes of the sonde mounting seat (7) in a one-to-one correspondence manner and are connected with the closed end of the instrument seat (10); the two sonde connecting ropes (8) are symmetrically distributed along the axis of the sonde (4), and the length of the two sonde connecting ropes (8) is the same.
2. A weather rocket arrow for an inverted sonde according to claim 1, characterized in that the connecting parts at the two ends of the guide base (3) are a front fixed ring (2) and a rear fixed ring (5), respectively; the outer circumferential surfaces of the front fixing ring (2) and the rear fixing ring (5) are consistent with the inner surface profile of the fairing shell (1) at the positions where the front fixing ring and the rear fixing ring are located;
step surfaces for mounting the front fixing ring (2) and the rear fixing ring (5) are respectively processed at two ends of the guide seat (3);
the front fixing ring (2) and the rear fixing ring (5) are fixed on the step surfaces at two ends of the guide seat (3) through an adhesive; and the outer circumferential surfaces of the front fixing ring (2) and the rear fixing ring (5) are attached to the inner surface of the fairing shell (1) and fixed through bonding.
3. A weather rocket arrow for an inverted sonde according to claim 1, characterized by further comprising a connecting ring (9), wherein one end of the connecting ring (9) is mounted on the inner circumferential surface of the opening end of the fairing housing (1) and is fixedly connected by adhesion, and the other end is sleeved on the outside of the instrument base (10) but is not fixed.
4. A weather rocket arrow for an inverted sonde according to claim 1, characterized in that said parachute assembly (11) comprises: the umbrella comprises an umbrella coat (12), a main umbrella rope (13), a cotton rope (14), an umbrella bag (15) and an umbrella bag buffer rope (16); the main umbrella rope (13) is arranged at one end of the umbrella coat (12), the other end of the umbrella coat (12) is connected with the umbrella bag (15) through a cotton rope (14), and the outside of the umbrella bag (15) is connected with an umbrella bag buffer rope (16); the umbrella coat (12) is folded and arranged in the umbrella bag (15) when not in work; the cotton rope (14) can be broken when the tension reaches a set value;
the parachute assembly (11) is arranged in the instrument stand (10), and one end of the parachute assembly is connected with an external arrow body (17) through a parachute package buffer rope (16); the other end is connected with the inner bottom surface of the instrument stand (10) through a main umbrella rope (13).
5. A weather rocket arrow for an inverted sonde according to claim 2, characterized in that the spring (6) is adhesively attached to the rear fixing ring (5) by means of an adhesive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911159391.0A CN110794484A (en) | 2019-11-22 | 2019-11-22 | Weather rocket arrow of inversion type sonde |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911159391.0A CN110794484A (en) | 2019-11-22 | 2019-11-22 | Weather rocket arrow of inversion type sonde |
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| Publication Number | Publication Date |
|---|---|
| CN110794484A true CN110794484A (en) | 2020-02-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911159391.0A Withdrawn CN110794484A (en) | 2019-11-22 | 2019-11-22 | Weather rocket arrow of inversion type sonde |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110794484A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429278A (en) * | 2020-11-11 | 2021-03-02 | 陕西中天火箭技术股份有限公司 | Firer ejection recovery mechanism |
| KR102558099B1 (en) * | 2022-11-28 | 2023-07-26 | 대한민국 | Cover for parachute of rawinsonde |
-
2019
- 2019-11-22 CN CN201911159391.0A patent/CN110794484A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112429278A (en) * | 2020-11-11 | 2021-03-02 | 陕西中天火箭技术股份有限公司 | Firer ejection recovery mechanism |
| CN112429278B (en) * | 2020-11-11 | 2023-09-15 | 陕西中天火箭技术股份有限公司 | Initiating explosive device ejection recovery mechanism |
| KR102558099B1 (en) * | 2022-11-28 | 2023-07-26 | 대한민국 | Cover for parachute of rawinsonde |
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Application publication date: 20200214 |