CN111239855B - Stratospheric meteorological detection rocket and application method - Google Patents
Stratospheric meteorological detection rocket and application method Download PDFInfo
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- CN111239855B CN111239855B CN201911142789.3A CN201911142789A CN111239855B CN 111239855 B CN111239855 B CN 111239855B CN 201911142789 A CN201911142789 A CN 201911142789A CN 111239855 B CN111239855 B CN 111239855B
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Abstract
The invention relates to a novel stratosphere meteorological detection rocket and an application method thereof. The device comprises an arrow body structure unit, an engine unit, a control system unit, a load release unit and a detection load unit, wherein more than two sets of load release units are loaded in a load cabin. A typical flight procedure is as follows: after the engine is ignited, the rocket is detected to reach a ballistic vertex, the load cabin is opened, the first group of sondes are released, and parachute opening is delayed; after the release of the former group of sondes is delayed, the next group of sondes is released, and the parachute is opened after the release is delayed; and circulating the previous steps until all the sondes are released. The technical scheme of the invention has the following beneficial effects: the detection rocket can load a plurality of sondes with different detection capabilities, and the comprehensive detection load loading capability is stronger; according to the requirements, single sondes can be released at different flying heights or a plurality of sondes can be released in groups, different detection heights and areas are covered, and the sounding efficiency is effectively improved; the method can be applied to providing parameter support under severe environmental conditions.
Description
Technical Field
The invention belongs to the technical field of meteorological detection equipment, and particularly relates to a novel stratospheric meteorological detection rocket and an application method thereof.
Background
The acquisition of meteorological parameters of the stratosphere has very important significance for researching the aspects of high-rise atmospheric circulation condition, weather analysis and forecast, important natural disaster monitoring and early warning, military application and the like, and the meteorological world at home and abroad strengthens the research on the detection of the stratosphere meteorological parameters.
The stratosphere non-contact detection mainly adopts means such as meteorological satellites and radars, wherein the conventional atmospheric detection satellite carries a satellite-borne radar, a microwave/infrared radiometer and the like, and can also utilize a ground radar and an air-based radar to obtain the power, heat, components and radiation characteristics of the atmosphere in the stratosphere and the middle layer; the satellite remote sensing detection also comprises occultation detection, wherein a bending angle of a GPS signal relative to a straight line during propagation is measured by using a low earth orbit satellite occultation method, and the atmospheric temperature and density profile of a stratosphere are inverted. Meteorological satellites and radar remote sensing detection obtain high-resolution data rich in global scale, and the method has important research value for understanding characteristics of the global scale stratospheric dynamic-physical-chemical process.
The stratosphere contact type detection mainly comprises a stratosphere detection balloon, an airplane detection platform and a rocket detection platform.
The existing stratospheric balloon detection mode mainly adopts the mode that a conventional sounding instrument or a dropsonde is carried by a balloon, the balloon detection height can reach 35 km-38 km, the atmospheric detection project of the lower layer in the stratosphere except temperature, pressure, humidity and wind field structures can be widely obtained, and the trace distribution of vertical structure substances such as ozone, water vapor, aerosol and the like of the lower layer in the stratosphere can also be observed.
The aircraft detection platform (manned, unmanned and the like) can detect various cloud systems, weather systems and typhoons passing detection or dropsondes, the aircraft detection height is basically within the height range of 25km, and atmospheric parameters in the stratosphere bottom layer area and the cross-connection area of the stratosphere and the troposphere can be obtained.
The existing meteorological detection rocket takes a drop-type sonde as a load, a single sonde is usually carried at an arrow part, the sonde is generally thrown out from the arrow part of the rocket at the vertex of a flight trajectory along the axial direction, a meteorological element profile of a target area is detected from top to bottom by utilizing a temperature sensor, a pressure sensor and a humidity sensor of the sonde and a GPS receiver, the height range of 20 km-60 km can be covered, and a plurality of sondes can be put in a certain combat area to obtain element distribution on a plurality of layers at different heights in the area.
A large amount of stratospheric remote sensing observation data are obtained by detection modes such as a satellite and a ground radar, but the correctness of the data needs to be corrected by contact detection data; the stratosphere detection balloon and the detection airplane can only obtain the stratosphere bottom meteorological parameters; the existing stratosphere detection rocket generally carries a single sonde, the acquisition of detection data samples is limited, and observation of the whole stratosphere ozone parameters of the stratosphere is basically not involved. Therefore, a sonde which can be carried by a user is developed, the sonde can be released in groups for multiple times at different positions of the top of the stratosphere, the comprehensive observation of wind, temperature, humidity and pressure and ozone parameters from the top of the stratosphere to the sea level is realized, the sonde can be launched and applied under the conditions before and after typhoon landing, and the sonde has important application value.
Disclosure of Invention
In view of the above drawbacks and needs of the prior art, the present invention provides a stratospheric sounding rocket, a rocket body structure unit, an engine unit, a control system unit, a load releasing unit, a sounding load unit, etc., and an application method and a work flow of the rocket. The rocket flies uncontrollably or controllably after being launched from the guide rail, the shell pieces of the rocket load cabin are separated after the rocket is fixed at a ballistic trajectory point, a channel is provided for the release of the sonde, the sondes are sequentially released in groups for multiple times in the descending section of the rocket, and the sondes are decelerated and descended for detection after being released. The detection rocket provided by the invention is provided with a drop-type sonde which meets the requirements of carrying quality, interfaces and the like, and can be used for detecting various meteorological parameters.
In order to achieve the above object, the present invention provides a stratospheric meteorological sounding rocket, which comprises a rocket body structure unit, an engine unit, a control system unit, a load release unit and a sounding load unit, wherein:
the rocket body structure unit comprises a nose cone cabin, a load cabin, a separation shell piece, an instrument cabin, an empennage mounting seat, an empennage, a protective cover, a front support sliding block and a rear support sliding block. The nose cone cabin is arranged at the head of the rocket and is connected with one end of the load cabin shell, the nose cone cabin is designed into a low-resistance aerodynamic shape, the resistance in the flight process is reduced, and corresponding thermal protection measures are adopted to bear the aerodynamic thermal environment in the flight process; the load cabin is mainly used for loading more than two sets of load release units, one end of the load cabin is connected with the nose cone cabin, and the other end of the load cabin is connected with the instrument cabin; the separation shell piece is mainly used for rocket dimension shape, and is separated to provide a channel for sonde release before the sonde release; one end of the instrument cabin is connected with the load cabin, and the other end of the instrument cabin is connected with the engine unit and is mainly used for installing rocket flight control related instruments; the tail wing mounting seat is connected with the tail wing and is mounted on a tail shell of the engine unit, and the rocket is provided with more than three tail wings; the protective cover is connected with the tail part of the engine unit and covers a jet pipe at the tail part of the engine to play a role in maintaining the shape; the front supporting slide block is arranged on the belly of the instrument cabin, and the rear supporting slide block is fixed on the belly of the tail end of the engine and matched with a rocket in a launching guide rail groove type, so that guiding and supporting are provided for rocket launching.
The engine unit adopts a general solid rocket engine, meets the energy required by detecting the flight trajectory of the rocket, and provides power for the on-orbit gliding and subsequent flying of the rocket.
The control system unit mainly comprises a satellite positioning signal antenna (GNSS antenna), a satellite positioning signal processor (GNSS host), a battery, a comprehensive controller, a remote measuring antenna and a remote measuring host. The GNSS antenna is arranged at the rear end of the nose cone cabin, is arranged in a bilateral symmetry mode, and receives satellite positioning signals; the GNSS host receives and positions satellite signals received by the GNSS antenna, and transmits the information of the rocket flight position and speed to the integrated controller; the battery supplies power for the rocket control single machine; the integrated controller is connected with the battery and the GNSS host, comprehensively processes the rocket acquisition input information, sends a rocket working time sequence instruction, and controls the rocket to separate the separation shell pieces and release the detection load unit; the remote sensing host receives the information of the integrated controller and transmits signals through a remote sensing transmitting antenna; the telemetering antenna is arranged on the outer wall of the instrument cabin in a bilateral symmetry layout manner, so that telemetering signal transmission is realized.
The load release unit mainly comprises a sonde installation cabin, a sonde locking mechanism, a sonde release actuator and a shell separation actuator. The sonde mounting cabin is embedded into the load cabin, and the detection load unit is loaded in the mounting cabin; the sonde locking mechanism realizes the locking of the detection load unit in the sonde installation cabin, prevents the detection load unit from changing in position in the rocket flying process, and can effectively unlock in the sonde releasing process; the sonde release actuator provides power for the release of the sonde, and the detecting load unit can be pushed out and separated from the sonde installation cabin after receiving a rocket control system unlocking instruction. The shell separation actuator pushes out the corresponding separation shell before the detection load unit is released, so that a channel is provided for the release of the detection load unit.
The detection load unit mainly comprises a lower-throwing type sonde and a sonde speed reduction system, the lower-throwing type sonde is axially butted with the sonde speed reduction system and then installed in the load release unit, the lower-throwing type sonde is mainly used for detecting related parameters of the atmosphere below the top of a stratosphere, and the sonde speed reduction system mainly realizes speed reduction of the sonde in the flight process and provides flight speed and attitude conditions meeting requirements for detection of the lower-throwing type sonde.
According to the stratospheric meteorological detection rocket, the working process of the detection rocket is adopted, the detection rocket adopts an inclined launching mode, the detection rocket slides along the guide rail after the engine is ignited, the detection rocket flies along the parabolic trajectory after the engine is out of orbit, and the detection rocket continues to fly along the parabolic trajectory after the engine is exhausted and shut down until all the dropsondes are released. A typical flight procedure is as follows:
a) igniting the engine at 0s, and detecting the rocket to slide along the launcher;
b) the rocket leaves the orbit at the time t1, and the rocket is detected to fly along the parabolic trajectory without control;
c) at the time t2, detecting the exhaustion of the rocket engine and shutting down the rocket engine;
d) at the time of t3, when the detection rocket reaches the ballistic vertex, the load cabin is opened, and a channel is provided for the release of the follow-up drop-type sonde;
e) The detection rocket continuously flies for a certain time, the first group of sondes are released at the time t4 (the first release point of the sondes), and parachute opening is carried out after the sondes are released for 1-4 s (the parachute opening point of the first sonde deceleration system);
f) and (3) the rocket continuously flies, the time delay of the first group of sondes is 5.0-15.0 s, the time (the second release point of the sondes) is t5, the second group of sondes is released, and the time delay of the second group of sondes is 1-4 s, and the parachute is opened (the parachute opening point of the second sonde deceleration system).
g) The rocket continuously flies, the time is delayed for 5-15 s after the front group of sondes are released, and then at t6, the next group of sondes are released, and the time is delayed for 1-4 s after the sondes are released to open the parachute;
h) and g), circulating the preamble step g) until all the sondes are released.
In general, the above technical solutions contemplated by the present invention can achieve the following beneficial effects:
(1) the detection rocket is loaded with more than 2 sondes, under the condition of meeting the constraints of interfaces and overall parameters, the conventional meteorological sondes with wind temperature pressure humidity detection capability, or stratospheric ozone sondes, lightning sondes and the like can be loaded, the mixed loading configuration of different types of sondes can be realized, and the comprehensive detection load loading capability is stronger;
(2) the rocket is loaded with more than 2 sondes, and the single sondes can be released at the defined flying height or more than 2 sondes can be released in groups according to requirements, so that different sondes cover different detection heights and areas, the single effective detection area for detecting the rocket and the size of the obtained data sample are increased, and the sounding efficiency can be effectively improved;
(3) The detection rocket is aimed and applied to stratospheric detection, has strong ground environment adaptability, can be applied to the conditions before and after typhoon landing to obtain meteorological parameters below the top of the stratosphere under severe environmental conditions such as typhoon and the like, and provides parameter support for researching the process of an outflow layer at the top of the typhoon.
Drawings
FIG. 1 is a perspective view of a rocket according to an embodiment of the present invention;
FIG. 2 is a schematic view of a rocket nose cone structure provided by an embodiment of the invention;
FIG. 3 is a schematic view of a load compartment configuration provided by an embodiment of the present invention;
FIG. 4 is a schematic structural view of a load release unit in the load compartment;
FIG. 5 is a schematic view of an instrument pod configuration provided by an embodiment of the present invention;
FIG. 6 is a probe rocket workflow provided by an embodiment of the present invention.
The same reference numbers will be used throughout the drawings to refer to the same or like elements or structures, wherein:
1. a nose cone cabin 2, a satellite positioning signal antenna (GNSS antenna) 3 and a separation shell sheet
4. Load cabin 5, telemetering antenna 6, front supporting slide block 7 and instrument cabin
8. Separate plug 9, engine 10, tail 11 and tail mounting seat
12. Shield 13, rear support slide 14, satellite positioning signal processor (GNSS host)
15. Shell and sheet separation actuator 16, lower-throwing type sonde 17 and sonde installation cabin
18. Sonde locking mechanism 19 and sonde release actuator 20 sonde speed reduction system
21. Integrated controller 22, battery 23 and telemetering host
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The following further describes embodiments of the present invention with reference to the drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The invention provides a stratosphere meteorological detection rocket which comprises a rocket body structure unit, an engine unit, a control system unit, a load release unit and a detection load unit.
The rocket body structure unit realizes the appearance function of the rocket and provides structural support for the rocket, and comprises a nose cone cabin 1, a load cabin 4, a separation shell piece 3, an instrument cabin 7, a tail wing mounting seat 11, a tail wing 10, a protective cover 12, a front support sliding block 6 and a rear support sliding block 13; the engine unit provides power support for rocket flight and mainly comprises an engine 9; the control system unit mainly realizes rocket flight comprehensive control, obtains rocket position and speed parameters through a satellite navigation positioning system, and carries out telemetering wireless return on the acquired parameters and flight trajectory parameters in the rocket flight process, and comprises a satellite positioning signal antenna (GNSS antenna) 2, a satellite positioning signal processor (GNSS host) 14, a battery 22, a comprehensive controller 21, a telemetering antenna 5, a telemetering host 23 and a separation release-insertion unit 8; the load release unit mainly realizes safe and reliable release of the detection load and mainly comprises a sonde installation cabin 17, a sonde locking mechanism 18, a sonde release actuator 19 and a shell separation actuator 15; the detection load unit mainly realizes atmospheric parameter detection and consists of a lower-dropping type sonde 16 and a sonde deceleration system 20.
Fig. 1 to 6 show the specific structure of a preferred embodiment of the present invention, which is described in detail below.
Wherein, FIG. 1 is a rocket outline diagram provided by the embodiment of the invention, a nose cone cabin 1 is designed into a low-resistance aerodynamic outline, the resistance in the flight process is reduced, and corresponding thermal protection measures are adopted to bear the aerodynamic heat environment in the flight process; the load cabin 4 is mainly used for loading more than two sets of load release units 2, one end of the load cabin is connected with the nose cone cabin 1, the other end of the load cabin is connected with the instrument cabin 7, and 6 (in the embodiment) separation shell pieces 3 are arranged on the load cabin 4; one end of an instrument cabin 7 is connected with the load cabin 4, the other end of the instrument cabin is connected with an engine 9 and is mainly used for installing rocket flight control related instruments, telemetering antennas 5 are installed on the outer wall of the instrument cabin and are symmetrically arranged left and right to realize telemetering signal transmission, and a front supporting slide block 6 is installed on the belly of the instrument cabin and provides support for the rocket to slide in a transmitting guide rail; the engine 9 provides power for detection to the on-orbit gliding and subsequent flying of the rocket; in the embodiment, the four tail wings 10 are arranged in an X shape and are arranged at the tail end of the engine 9 through a tail wing mounting seat 11, so that the stable flight of the rocket is guaranteed; the shield 12 is connected with the tail end of the engine 9 and plays a role in maintaining the shape during the rocket flying process. The empennage can be more than 3 pieces and is in a Y-shaped layout or an X-shaped layout or more than five, six and the like.
Fig. 2 is a structural diagram of a rocket nose cone cabin 1 according to an embodiment of the present invention, a GNSS antenna 2 is installed at the rear end of the nose cone cabin 1, and is installed in a left-right symmetrical layout to receive satellite positioning signals, and a GNSS host 14 receives the satellite signals received by the GNSS antenna 2 and realizes positioning, and transmits rocket flight position and velocity information to an integrated controller 21.
Fig. 3 is a structural diagram of a load compartment 4 provided by an example of the present invention, where the load compartment 4 mainly implements installation of load release units, the load compartment 4 has 2 layers along an axial direction, each layer has 3 load release unit installation positions distributed along the axial direction at 120 °, and two ends of each load release unit installation position are provided with 2 shell separation actuators 15 for implementing separation of the separation shell pieces 3 and providing a passage for a sonde to release.
Fig. 4 is a schematic view of a load release unit, which is mainly used to achieve safe and reliable release of a probe load unit. The sonde installation cabin 17 is embedded in the load cabin 4, and a detection load unit (namely, a lower-throwing sonde and a sonde deceleration system) is loaded in the load cabin; the sonde locking mechanism 18, the sonde release actuator 19 and the shell separation actuator 15 are arranged on the sonde installation cabin 17, the sonde locking mechanism 18 realizes the locking of the detection load unit in the sonde installation cabin 17, the position change of the detection load unit in the rocket flying process is prevented, and meanwhile, the detection load unit can be effectively unlocked in the release process; the sonde release actuator 19 provides power for the release of the probe load unit, and after receiving a rocket control system unlocking instruction, the probe load unit can be pushed out of the sonde installation cabin 17 for separation.
FIG. 5 is a schematic view of an instrument pod configuration provided by an embodiment of the present invention; a battery 22 powers the rocket control components; the integrated controller 21 is connected with the battery 22 and the GNSS host 14, comprehensively processes rocket acquisition input information, sends a rocket working time sequence instruction, realizes separation of the separation shell pieces 3 according to time sequence, and provides a channel for subsequent release of the detection load unit; the telemetry host 23 receives the information of the integrated controller 21 and transmits the signal transmission through the telemetry antenna 5.
Fig. 6 is a working flow of the detection rocket provided by the embodiment of the invention, the detection rocket adopts an oblique launching mode, the detection rocket slides along the guide rail after the ignition of the engine, flies along the parabolic trajectory after the engine leaves the rail, and the rocket continues to fly along the parabolic trajectory after the engine is exhausted and shut down until the release of 6 dropsondes is completed.
The working process comprises the following steps:
a) igniting the engine at 0s, and detecting the rocket to slide along the launcher;
b) the rocket leaves the orbit at the time t1, and the rocket is detected to fly along the parabolic trajectory without control;
c) at the time t2, detecting the exhaustion of the rocket engine and shutting down the rocket engine;
d) at the time of t3, when the detection rocket reaches the ballistic vertex, the load cabin is opened, and a channel is provided for the release of the follow-up drop-type sonde;
e) The detection rocket continuously flies for a certain time, the first group of 3 sondes is released at the moment t4 (the first release point of the sondes), and the parachute is opened after the sondes are released for 2.5 seconds (the parachute opening point of the first sonde deceleration system);
f) the rocket continues flying, the time delay of the first group of sondes is 8.0s, then the time t5 (the second release point of the sondes) is delayed to release the second group of 3 sondes, and the time delay of the sondes after release is 2.5s to open the parachute (the second parachute opening point of the sonde deceleration system).
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. A stratospheric meteorological sounding rocket comprises a rocket body structure unit, an engine unit, a control system unit, a load release unit and a sounding load unit, wherein: the rocket body structure unit comprises a nose cone cabin, a load cabin, a separation shell piece, an instrument cabin, a tail wing mounting seat, a tail wing, a protective cover, a front support sliding block and a rear support sliding block, and is characterized in that the nose cone cabin is arranged at the head of the rocket and is connected with one end of a load cabin shell; the load cabin is provided with more than two sets of load release units, the load detection units refer to a down-dropping type sonde and a sonde deceleration system which are locked in a sonde installation cabin, the load cabin is provided with 2 layers along the axial direction, each layer is provided with 3 load release units along the axial direction at 120 degrees, two ends of the installation position of each load release unit are provided with shell-piece separation actuators, and the middle part of each load release unit is provided with a sonde release actuator; one end of the load cabin is connected with the nose cone cabin, and the other end of the load cabin is connected with the instrument cabin; one end of the instrument cabin is connected with the load cabin, and the other end of the instrument cabin is connected with the engine unit; the tail wing mounting seat is connected with the tail wing and is arranged on a tail shell of the engine unit, and the rocket is provided with more than three tail wings; the protective cover is connected with the tail part of the engine unit and covers the jet pipe at the tail part of the engine.
2. The stratospheric weather detection rocket of claim 1, wherein the load bay has a probe load unit disposed therein, the probe load unit being disposed in the sonde mounting bay; the sonde locking mechanism, the sonde release actuator and the shell separation actuator are arranged on the sonde installation cabin.
3. The stratospheric meteorological sounding rocket of claim 1, wherein the control system unit comprises a satellite positioning signal antenna, a satellite positioning signal processor, a battery, an integrated controller, a telemetry antenna and a telemetry host; the satellite positioning signal antenna is arranged at the rear end of the nose cone cabin in a bilateral symmetry layout.
4. The stratospheric meteorological sounding rocket of claim 3, wherein the integrated controller, the battery and the telemetry mainframe are arranged in an instrument chamber; the telemetering antenna is arranged on the outer wall of the instrument cabin in a bilateral symmetry mode and is separated, disconnected and inserted.
5. A stratospheric weather detection rocket according to claim 3 or claim 4 wherein the integrated controller is connected to the battery and the satellite positioning signal processor.
6. The stratospheric meteorological sounding rocket of claim 1, wherein the front support block is mounted on the belly of the instrument bay, and the rear support block is fixed on the belly of the tail end of the engine and is matched with the rocket in a launching guide rail groove shape.
7. The launching application method of the stratospheric meteorological sounding rocket is followed according to claim 1, the sounding rocket adopts an inclined launching mode, the sounding rocket slides along a guide rail after the ignition of an engine, flies along a parabolic trajectory after the engine leaves the rail, and the rocket continues to fly along the parabolic trajectory after the engine is exhausted and shut down until all the dropsondes are released; the typical flight procedure is as follows:
a) igniting the engine at 0s, and detecting the rocket to slide along the launcher;
b) the rocket leaves the orbit at the time t1, and the rocket is detected to fly along the parabolic trajectory without control;
c) at the time t2, detecting the exhaustion of the rocket engine and shutting down the rocket engine;
d) at the time of t3, when the detection rocket reaches the ballistic vertex, the load cabin is opened, and a channel is provided for the release of the follow-up drop-type sonde;
e) the detection rocket continuously flies for a certain time, the first group of sondes are released at t4, and parachute opening is delayed for 1-4 s after the sondes are released, namely parachute opening points of a first-time sonde deceleration system;
f) the rocket continuously flies, the time delay is 5-15 s after the first group of sondes are released, then at t5, the second group of sondes are released, and the time delay is 1-4 s after the sondes are released, so that parachute opening is realized;
g) the rocket continuously flies, the time is delayed for 5-15 s after the front group of sondes are released, and then at t6, the next group of sondes are released, and the time is delayed for 1-4 s after the sondes are released to open the parachute;
h) And g), circulating the preamble step g) until all the sondes are released.
8. The method for launching an stratospheric meteorological sounding rocket, according to claim 7, wherein the flight procedure comprises the steps of:
a) igniting the engine at 0s, and detecting the rocket to slide along the launcher;
b) the rocket leaves the orbit at the time t1, and the rocket is detected to fly along the parabolic trajectory without control;
c) at the time t2, detecting the exhaustion of the rocket engine and shutting down the rocket engine;
d) at the time of t3, when the detection rocket reaches the ballistic vertex, the load cabin is opened, and a channel is provided for the release of the follow-up drop-type sonde;
e) the detection rocket continuously flies for a certain time till t4, the sonde releases the first group of 3 sondes for the first time, and the time delay is 2.5s after the sondes are released, so that the detection rocket is a parachute opening point of a first sonde deceleration system;
f) the rocket continuously flies, the time t5 is delayed after the first group of sondes are released for 8.0s, the second group of 3 sondes are released by the sondes, and the parachute is opened by the second sonde deceleration system after the sondes are released and delayed for 2.5 s.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201540375U (en) * | 2009-12-03 | 2010-08-04 | 陕西中天火箭技术有限责任公司 | low-altitude sounding rocket |
| CN201914463U (en) * | 2010-12-31 | 2011-08-03 | 航宇救生装备有限公司 | Time delay secondary parachute-opening device of meteorological rocket parachute |
| RO128775A2 (en) * | 2011-11-24 | 2013-08-30 | Universitatea Politehnica Din Bucureşti | Suborbital vector with hybrid gasodynamic control system |
| CN108398730A (en) * | 2018-03-01 | 2018-08-14 | 北京爱尔达电子设备有限公司 | Sounding rocket detection system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3043656B1 (en) * | 2015-11-17 | 2019-05-10 | Centre National D'etudes Spatiales (Cnes) | METHOD AND DEVICE FOR DEVIATION OF SPATIAL DEBRIS |
-
2019
- 2019-11-20 CN CN201911142789.3A patent/CN111239855B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201540375U (en) * | 2009-12-03 | 2010-08-04 | 陕西中天火箭技术有限责任公司 | low-altitude sounding rocket |
| CN201914463U (en) * | 2010-12-31 | 2011-08-03 | 航宇救生装备有限公司 | Time delay secondary parachute-opening device of meteorological rocket parachute |
| RO128775A2 (en) * | 2011-11-24 | 2013-08-30 | Universitatea Politehnica Din Bucureşti | Suborbital vector with hybrid gasodynamic control system |
| CN108398730A (en) * | 2018-03-01 | 2018-08-14 | 北京爱尔达电子设备有限公司 | Sounding rocket detection system |
Non-Patent Citations (1)
| Title |
|---|
| 火箭弹下投探测台风气象参数新技术及初步试验;雷小途 等;《科学通报》;20171026;第62卷(第32期);第3790页左栏第3段至第3792段左栏第1段，图1-2 * |
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