CN109163622A - A kind of anti-stable wing mechanism of sounding rocket disposable - Google Patents
A kind of anti-stable wing mechanism of sounding rocket disposable Download PDFInfo
- Publication number
- CN109163622A CN109163622A CN201811013075.8A CN201811013075A CN109163622A CN 109163622 A CN109163622 A CN 109163622A CN 201811013075 A CN201811013075 A CN 201811013075A CN 109163622 A CN109163622 A CN 109163622A
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- CN
- China
- Prior art keywords
- rocket
- aerofoil
- sounding
- wing mechanism
- sounding rocket
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of disposables of sounding rocket instead to stabilize wing mechanism, belongs to sounding rocket technology field.The anti-stable wing mechanism includes promotional implement, nut, aerofoil and spring, aerofoil is fixedly mounted on the outer wall of sounding rocket rocket body using promotional implement and nut, spring is placed between aerofoil and rocket body with compressive state；Under the control of the sequence controller of sounding rocket, its pin shaft and nut are pushed outwardly by promotional implement, and aerofoil separates under the thrust of spring with rocket body.Anti- stable wing mechanism of the present invention can be effectively reduced the steady state stability of sounding rocket flight low speed segment, to greatly reduce influence of the ambient wind to the rocket initial stage；The anti-stable wing mechanism is cast aside after flight to predetermined instant, so that sounding rocket is restored Primordial Qi and moves profile state, guarantee the stability of sounding rocket flight course, to realize the accurate control of sounding rocket trajectory.
Description
Technical field
The present invention relates to a kind of disposables of sounding rocket instead to stabilize wing mechanism, belongs to sounding rocket technology field.
Background technique
Sounding rocket is mostly free rocket, the trajectory (especially burning trajectory) of rocket by ambient wind influenced compared with
Greatly, in the case where there is wind, the position vector of rocket all-burnt point and velocity vector are intended to deviate nominal value.
" sounding rocket design " (Yuhang Publishing House, December the 1st edition in 1993) describes by adjusting the rocket launching elevation angle
And azimuth firing angle, cutoff velocity direction is influenced to compensate by practical wind field." sounding rocket wind field compensation and
The conversion of equivalent ballistic wind " (National University of Defense technology's journal, the 6th phase of volume 22 in 2000) describe sounding rocket ballistic wind field compensation
The wind method weighing calculation method, and propose a kind of search of computer step iteration more accurately obtains rocket compensation in wind field
Parameter." research of sounding rocket flight attitude spinning stability " (the 26th national space exploration scientific seminar, 2013 10
Month) describe a kind of sounding rocket and revolve stabilization technique scheme slowly, after rocket leaves the right or normal track, rocket is assigned using a rotation engine is played
Rotation reduces the influence of the factors such as wind, the disturbance that leaves the right or normal track, thrust eccentric." sounding rocket S19 simple control system general situation of development " (China
Space flight, the 10th phase in 2014) describe the development of the S19 motors in boost phase penetration control system that Sa Bo-space company of Ericsson is developed in detail
Course, the impact dispersion of rocket can be effectively reduced by increasing the control system on sounding rocket.
But in above-mentioned document, be not directed to realize that sounding rocket trajectory accurately controls by increasing the anti-stable wing in
Hold.Aerodynamic characteristic and quiet can be improved under conditions of not changing existing structure layout designing the anti-stable wing on sounding rocket
Stability has been widely used on petite combination guided missile and guided bomb, such as Haier's method guided missile, brim stone guided missile, boccaccio
Stone precision-guided bomb etc., but above-mentioned anti-stable wing structure is that can not cast structure aside.And new knot is looked into according to related document
Fruit is it is found that instead stabilize the report of wing mechanism the relevant technologies currently without sounding rocket disposable.
Summary of the invention
In order to reduce influence of the ambient wind to the sounding rocket initial stage, the accurate control of sounding rocket trajectory and drop point is realized
System, the present invention provides a kind of sounding rocket disposables instead to stabilize wing mechanism, can cast the anti-stable wing aside in flight course
Mechanism restores former sounding rocket aerodynamic configuration state, guarantees the stability of sounding rocket flight course.
The purpose of the present invention is what is be achieved through the following technical solutions:
A kind of sounding rocket disposable instead stabilizes wing mechanism, the anti-stable wing mechanism include promotional implement, nut, aerofoil with
And spring；
Mounting hole and blind hole are machined on the aerofoil；
Promotional implement is mounted on the inner wall of rocket body, and the pin shaft of promotional implement is stretched out out of my cabin by the aperture on rocket body, promotional implement
It is electrically connected with the sequence controller of sounding rocket；Aerofoil is placed on the outer wall of rocket body, and the mounting hole on aerofoil passes through promotional implement
Pin shaft；Nut is mounted on the pin shaft of promotional implement, and aerofoil is fixed on the outer wall of rocket body；Spring is located at the blind hole on aerofoil
In, one end of spring and aerofoil are inconsistent, and the outer wall of the other end and rocket body is inconsistent；
In sounding rocket flight course, what the sequence controller that promotional implement receives sounding rocket issued casts instruction aside
Afterwards, the pin shaft of promotional implement and nut are pushed outwardly, aerofoil separates under the thrust of spring with rocket body.
Further, one hair sounding rocket needs 4 groups are symmetrically installed on rocket body described in instead stabilize wing mechanism.
Further, processing places a spring there are two blind hole on the aerofoil in each blind hole.
The utility model has the advantages that
4 groups of anti-stable wing mechanisms of the present invention are installed in the head position of sounding rocket, can be effectively reduced sounding fire
The steady state stability of flight low speed segment, to greatly reduce influence of the ambient wind to the rocket initial stage；And fly in sounding rocket
The anti-stable wing mechanism is separated with rocket body after row to predetermined instant, so that sounding rocket is restored Primordial Qi and moves profile state, guarantee
The stability of sounding rocket flight course, to realize the accurate control of sounding rocket trajectory.
Detailed description of the invention
Fig. 1 is the sounding rocket two dimension schematic diagram of installation anti-stable wing mechanism of the present invention.
Fig. 2 is the installation relation schematic diagram of anti-stable wing mechanism and rocket body of the present invention.
Fig. 3 casts schematic diagram aside for anti-stable wing mechanism of the present invention.
Wherein, 1- promotional implement, 2- nut, 3- aerofoil, 4- spring, 5- rocket body, 6- instead stabilize wing mechanism, 7- empennage.
Specific embodiment
The present invention will be further described with reference to the accompanying drawings and detailed description.
Embodiment 1
In order to reduce influence of the ambient wind to the sounding rocket initial stage, head (the i.e. sounding rocket matter in rocket body 5 is needed
In front of the heart) 4 groups of formulas of the present invention of casting aside are symmetrically installed on outer circumference surface instead stabilizes wing mechanism 6, as shown in Figure 1；Every group
Anti- stable wing mechanism 6 includes promotional implement 1, nut 2, aerofoil 3 and spring 4, as shown in Figure 2；
Mounting hole and two blind holes are machined on the aerofoil 3；
The anti-stable wing mechanism 6 is in the installation relation on rocket body 5: promotional implement 1 is mounted on the inner wall of rocket body 5, is promoted
The pin shaft of device 1 is stretched out out of my cabin by the aperture on rocket body 5, and the sequence controller of promotional implement 1 and sounding rocket is electrically connected；Aerofoil
3 are placed on the outer wall of rocket body 5, and the mounting hole on aerofoil 3 passes through the pin shaft of promotional implement 1；Nut 2 is mounted on the pin shaft of promotional implement 1
On, to aerofoil 3 is fixed on the outer wall of rocket body 5；Spring 4 is placed in the blind hole on aerofoil 3 with compressive state, and one blind
A spring 4 is placed in hole, one end of spring 4 and aerofoil 3 are inconsistent, and the outer wall of the other end and rocket body 5 is inconsistent, such as Fig. 2 institute
Show；
In sounding rocket flight course, what the sequence controller that promotional implement 1 receives sounding rocket issued casts instruction aside
Afterwards, the pin shaft of promotional implement 1 and nut 2 being pushed outwardly, aerofoil 3 separates under the thrust of another two spring 4 with rocket body 5,
Restore former sounding rocket aerodynamic configuration state, guarantees the stability of sounding rocket flight course, as shown in Figure 3.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (3)
1. a kind of sounding rocket disposable instead stabilizes wing mechanism, it is characterised in that: the anti-stable wing mechanism includes promotional implement
(1), nut (2), aerofoil (3) and spring (4)；
Mounting hole and blind hole are machined on the aerofoil (3)；
Promotional implement (1) is mounted on the inner wall of sounding rocket rocket body (5), and the pin shaft of promotional implement (1) passes through the aperture on rocket body (5)
It stretches out out of my cabin, the sequence controller of promotional implement (1) and sounding rocket is electrically connected；Aerofoil (3) is placed on the outer wall of rocket body (5),
Mounting hole on aerofoil (5) passes through the pin shaft of promotional implement (1)；Nut (2) is mounted on the pin shaft of promotional implement (1), by aerofoil (3)
It is fixed on the outer wall of rocket body (5)；Spring (4) is located in the blind hole on aerofoil (3), and one end and the aerofoil (3) of spring (4) offset
Touching, the other end and the outer wall of rocket body (5) are inconsistent；
In sounding rocket flight course, after what the sequence controller that promotional implement (1) receives sounding rocket issued casts instruction aside,
The pin shaft of promotional implement (1) and nut (2) are pushed outwardly, aerofoil (3) separates under the thrust of spring (4) with rocket body (5).
2. a kind of sounding rocket disposable according to claim 1 instead stabilizes wing mechanism, it is characterised in that: a hair sounding fire
Instead stabilize wing mechanism (6) described in being symmetrically installed 4 groups on the rocket body (5) of arrow.
3. a kind of sounding rocket disposable according to claim 1 instead stabilizes wing mechanism, it is characterised in that: the aerofoil
(3) processing places a spring (4) there are two blind hole in each blind hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811013075.8A CN109163622A (en) | 2018-08-31 | 2018-08-31 | A kind of anti-stable wing mechanism of sounding rocket disposable |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811013075.8A CN109163622A (en) | 2018-08-31 | 2018-08-31 | A kind of anti-stable wing mechanism of sounding rocket disposable |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109163622A true CN109163622A (en) | 2019-01-08 |
Family
ID=64893559
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811013075.8A Withdrawn CN109163622A (en) | 2018-08-31 | 2018-08-31 | A kind of anti-stable wing mechanism of sounding rocket disposable |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109163622A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111259501A (en) * | 2020-01-19 | 2020-06-09 | 北京中科宇航探索技术有限公司 | Rocket and method for determining length of annular stabilizer wing for rocket |
| CN112651078A (en) * | 2020-12-02 | 2021-04-13 | 西安航天动力技术研究所 | Rocket body structure state anomaly detection method based on symbolic dynamics |
| CN113091523A (en) * | 2021-04-13 | 2021-07-09 | 西安航天动力技术研究所 | Firer throwing-off type anti-stabilizer wing |
-
2018
- 2018-08-31 CN CN201811013075.8A patent/CN109163622A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111259501A (en) * | 2020-01-19 | 2020-06-09 | 北京中科宇航探索技术有限公司 | Rocket and method for determining length of annular stabilizer wing for rocket |
| CN112651078A (en) * | 2020-12-02 | 2021-04-13 | 西安航天动力技术研究所 | Rocket body structure state anomaly detection method based on symbolic dynamics |
| CN112651078B (en) * | 2020-12-02 | 2023-09-08 | 西安航天动力技术研究所 | Arrow body structure state abnormality detection method based on symbol dynamics |
| CN113091523A (en) * | 2021-04-13 | 2021-07-09 | 西安航天动力技术研究所 | Firer throwing-off type anti-stabilizer wing |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190108 |