CN209258422U - A kind of device for adjusting posture for small-sized sounding rocket - Google Patents
A kind of device for adjusting posture for small-sized sounding rocket Download PDFInfo
- Publication number
- CN209258422U CN209258422U CN201821818089.2U CN201821818089U CN209258422U CN 209258422 U CN209258422 U CN 209258422U CN 201821818089 U CN201821818089 U CN 201821818089U CN 209258422 U CN209258422 U CN 209258422U
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- steering engine
- attitude
- rocker arm
- adjusting system
- connecting rod
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- 238000010586 diagram Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
A kind of device for adjusting posture for small-sized sounding rocket of the utility model, including rocket body and it is arranged in identical first attitude-adjusting system of the intracorporal structure of arrow and the second attitude-adjusting system, first attitude-adjusting system and the second attitude-adjusting system is symmetricly set on the left and right ends on the inside of rocket body, and first attitude-adjusting system is used to control the rotational angle of wherein two symmetrically arranged wings；The rotational angle that second attitude-adjusting system is used to control other two symmetrically arranged wings realizes the pose adjustment of sounding rocket by the mutual cooperation of the first attitude-adjusting system and the second attitude-adjusting system.The utility model have the advantages that it is compact-sized it is light, quality is small, center of gravity is located at rocket body central location；The deflection that aerofoil is controlled by the first attitude-adjusting system and the second attitude-adjusting system, to reach the pose adjustment function to rocket body；This structure it is high-efficient and stable and reliable in work；Function is easier to realize, and debugging difficulty is lower.
Description
Technical field
The utility model relates to a kind of technical field of aerospace, especially a kind of pose adjustment mould for small-sized sounding rocket
Block.
Background technique
In the experimental applications of sounding rocket, rocket body posture and heading during flight are needed to sounding rocket
It is adjusted, the pose adjustment of sounding rocket mainly utilizes servo mechanism control vector engine to pass through anti-impulse principle at present
It is adjusted, but its structure is complex huge, it is not compact enough, and the center of gravity that can make rocket body is excessively rearward, cause
Rocket body stabilized flight ability reduces, and for small-sized sounding rocket, structural volume is excessive so that this device for adjusting posture
It is difficult to realize in a limited space, and center of gravity makes rocket body need other additional counterweight rearward, can make the total constitution of rocket body in this way
Amount rises, and is unfavorable for testing and apply.
Utility model content
In view of the deficiencies of the prior art, the utility model provides a kind of device for adjusting posture for small-sized sounding rocket,
The device for adjusting posture mechanism is simple, compact, by the pose adjustment for realizing sounding rocket using pneumatic principle.
The technical solution of the utility model are as follows: a kind of device for adjusting posture for small-sized sounding rocket, including rocket body, with
And it is arranged in identical first attitude-adjusting system of the intracorporal structure of arrow and the second attitude-adjusting system, the first posture tune
Complete machine structure and the second attitude-adjusting system are symmetricly set on the left and right ends on the inside of rocket body, and first attitude-adjusting system is used
In the rotational angle for controlling wherein two symmetrically arranged wings；Second attitude-adjusting system is symmetrically arranged for controlling other two
The rotational angle of wing realizes sounding rocket by the mutual cooperation of the first attitude-adjusting system and the second attitude-adjusting system
Pose adjustment.
Further, first attitude-adjusting system includes the first steering engine, the first steering engine rocker arm, the first wing company
Bar, the first extension arm, first steering engine are connect with the first steering engine rocker arm, and the first steering engine rocker arm passes through the first rocker arm
Tabletting is connect with the first extension arm, and first extension arm is connect with the first wing connecting rod, the first wing connecting rod with
Wherein two symmetrically arranged wing connections, the first steering engine control the first steering engine by the location information and attitude data of sounding rocket
Rocker arm is swung, and drives the first wing connecting rod to rotate around wing axis by the first extension arm, so that connecting with the first wing
The certain angle of the wing beat that bar is fixedly connected, realizes the pose adjustment of rocket.
Further, second attitude-adjusting system includes the second steering engine, the second steering engine rocker arm, the second wing company
Bar, the second extension arm, second steering engine are connect with the second steering engine rocker arm, and the second steering engine rocker arm passes through the second rocker arm
Tabletting is connect with the second extension arm, and second extension arm is connect with the second wing connecting rod, the second wing connecting rod with
Other two symmetrically arranged wing connection, the second steering engine control the second steering engine by the location information and attitude data of sounding rocket
Rocker arm is swung, and drives the second wing connecting rod to rotate around wing axis by the second extension arm, so that connecting with the second wing
The certain angle of the wing beat that bar is fixedly connected, realizes the pose adjustment of rocket.
Further, the first steering engine rocker arm and the second steering engine rocker arm shape are identical, are cross, and in center
Position offers an axis hole.
Further, the structure of first extension arm and the second extension arm is identical, includes linkage section and annular
Link slot section, offer on the linkage section multiple threaded holes, first extension arm and the second extension arm pass through it is multiple
Threaded hole and bolt are connect with the first rocker arm tabletting, the second rocker arm tabletting respectively, and the first wing connecting rod and the second wing connect
Bar is respectively sleeved in corresponding annular link slot.
Further, the structure of the first rocker arm tabletting is identical with the structure of the second rocker arm tabletting, and described first
Rocking arm for pressing on piece offers one for accommodating the cross groove of the first rocker arm, and the second rocking arm for pressing on piece, which offers, to be used for
Accommodate the cross groove of the second rocker arm.
Further, the shape of the first wing connecting rod and the second wing connecting rod is identical, be it is arch-shaped, it is arch-shaped
Both ends the angle for driving the rotation of symmetrical wing mobile is connect with symmetrically arranged wing respectively, realize the posture tune of rocket body
It is whole.
The utility model has the following beneficial effects:
1, have the advantages that it is compact-sized it is light, quality is small, center of gravity is located at rocket body central location；
2, the deflection that aerofoil is controlled by the first attitude-adjusting system and the second attitude-adjusting system, to reach to rocket body
Pose adjustment function；This structure it is high-efficient and stable and reliable in work；
3, this device for adjusting posture carries out appearance relative to the vector engine of existing mainstream in terms of circuit control simultaneously
State adjustment function is easier to realize, and stability is higher, and debugging difficulty is lower；
4, servo driving is converted electrical signals to by steering engine and pushes dynamic steering engine rocker arm and extension arm, so that the wing-connecting rod turns
It is dynamic, therefore aerofoil rotates, rocket body carries out pose adjustment, can not only go on smoothly work, but also can be according to predetermined
Course bearing carry out pose adjustment.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the structural schematic diagram inside the utility model；
Fig. 3 is the structural schematic diagram of the first steering engine of the utility model rocker arm；
Fig. 4 is the structural schematic diagram of the first rocker arm of the utility model tabletting；
Fig. 5 is the structural schematic diagram that the utility model is the first extension arm；
Fig. 6 is the structural scheme of mechanism of the first wing of the utility model connecting rod
In figure, 1- rocket body, the first attitude-adjusting system of 2-, the second attitude-adjusting system of 3-, 4- wing, the first steering engine of 21-,
22- the first steering engine rocker arm, 23- the first rocker arm tabletting, the first extension arm of 24-, 25- the first wing connecting rod, 26- cross groove,
27- linkage section, 28- annular link slot section, the second steering engine of 31-, 33- the second rocker arm tabletting, the second extension arm of 34-, 35- second
Wing connecting rod.
Specific embodiment
Specific embodiment of the present utility model is described further with reference to the accompanying drawing:
As depicted in figs. 1 and 2, a kind of device for adjusting posture for small-sized sounding rocket, including rocket body 1 and setting
Identical first attitude-adjusting system 2 of structure and the second attitude-adjusting system 3 in rocket body 1, first pose adjustment
Mechanism 2 and the second attitude-adjusting system 3 are symmetricly set on the left and right ends of 1 inside of rocket body, first attitude-adjusting system 2
For controlling the rotational angle of wherein two symmetrically arranged wings 4；Second attitude-adjusting system 2 is symmetrically set for controlling other two
The rotational angle for the wing 4 set is realized and is visited by the mutual cooperation of the first attitude-adjusting system 2 and the second attitude-adjusting system 3
The pose adjustment of empty rocket.
As shown in Fig. 2, first attitude-adjusting system 2 includes the first steering engine 21, the first steering engine rocker arm 22, the first machine
Wing connecting rod 25, the first extension arm 24, first steering engine 21 are connect with the first steering engine rocker arm 22, the shape of the first steering engine rocker arm 22
Shape is cross, as shown in figure 3, and offering an axis hole for connecting with the first steering engine 21, first rudder thereon
Machine rocker arm 22 is connect by the first rocker arm tabletting 23 with the first extension arm 24, and the first rocking arm for pressing on piece accordingly offers one
Criss-cross groove 26, as shown in figure 4, criss-cross first steering engine rocker arm 22 is arranged in cross groove 26, such as Fig. 5 institute
Show, first extension arm includes linkage section 27 and annular link slot section 28, is offered on the linkage section 27 multiple
Threaded hole, first extension arm 24 are connect by multiple threaded holes and bolt with the first rocker arm tabletting 23, first machine
Wing connecting rod 25 is set in annular link slot, as shown in fig. 6, the shape of the first wing connecting rod 25 be it is arch-shaped, it is described
The both ends of the first wing connecting rod 25 connect with wherein two symmetrically arranged wings 4, the position that the first steering engine 21 passes through sounding rocket
Confidence breath and attitude data control the first steering engine rocker arm 22 swing, and by the first extension arm 24 drive the first wing connecting rod 25 around
The axis rotation of first pair of wing 4, so that the angle for driving first pair of 4 beat of wing certain, realizes the pose adjustment of rocket.
As shown in Fig. 2, second attitude-adjusting system 3 includes the second steering engine 31, the second steering engine rocker arm, the second wing
Connecting rod 35, the second extension arm 34, second steering engine 31 are connect with the second steering engine rocker arm, and the shape of the second steering engine rocker arm is also
Cross, a cross groove is offered in the second rocker arm tabletting 33, and criss-cross second steering engine rocker arm is arranged ten
In the groove of font, second extension arm 34 includes linkage section and annular link slot section, and the linkage section is by thereon
Threaded hole and bolt be arranged in the second rocker arm tabletting 33, other end annular link slot is connect with the second wing connecting rod 35, institute
The shape for the second wing connecting rod 35 stated be it is arch-shaped, both ends are connect with other two symmetrically arranged wings 4, the second steering engine 31
The second steering engine rocker arm is controlled by the location information and attitude data of sounding rocket to swing, and passes through the second extension arm 34 driving the
Two wing connecting rods 35 are rotated around the axis of the 2nd the second wing 4, so that the angle that second pair of 4 beat of wing is certain, realizes fire
The pose adjustment of arrow.
The description of the embodiments and the specification only illustrate the principle of the present utility model and most preferred embodiment, is not taking off
Under the premise of from the spirit and scope of the utility model, the utility model also has various changes and improvements, these changes and improvements
It falls within the scope of the claimed invention.
Claims (9)
1. a kind of device for adjusting posture for small-sized sounding rocket, it is characterised in that: including rocket body and be arranged in rocket body
Identical first attitude-adjusting system of structure and the second attitude-adjusting system, first attitude-adjusting system and the second appearance
State adjustment mechanism is symmetricly set on the left and right ends on the inside of rocket body, and first attitude-adjusting system is for controlling wherein two pairs
Claim the beat of the wing of setting；Second attitude-adjusting system is used to control the beat of other two symmetrically arranged wings.
2. a kind of device for adjusting posture for small-sized sounding rocket according to claim 1, it is characterised in that: described
First attitude-adjusting system include the first steering engine, the first steering engine rocker arm, the first wing connecting rod, the first extension arm, described first
Steering engine is connect with the first steering engine rocker arm, and the first steering engine rocker arm is connect by the first rocker arm tabletting with the first extension arm, institute
The first extension arm stated is connect with the first wing connecting rod, and the first wing connecting rod connects with wherein two symmetrically arranged wings
It connects.
3. a kind of device for adjusting posture for small-sized sounding rocket according to claim 1, it is characterised in that: described
Second attitude-adjusting system include the second steering engine, the second steering engine rocker arm, the second wing connecting rod, the second extension arm, described second
Steering engine is connect with the second steering engine rocker arm, and the second steering engine rocker arm is connect by the second rocker arm tabletting with the second extension arm, institute
The second extension arm stated is connect with the second wing connecting rod, and the second wing connecting rod connects with other two symmetrically arranged wings
It connects.
4. a kind of device for adjusting posture for small-sized sounding rocket according to claim 2, it is characterised in that: described
First extension arm includes linkage section and annular link slot section, offers multiple threaded holes on the linkage section, and described the
One extension arm is connect by multiple threaded holes and bolt with the first rocker arm tabletting, and the first wing connecting rod is set in annular connection
In slot.
5. a kind of device for adjusting posture for small-sized sounding rocket according to claim 3, it is characterised in that: described
Second extension arm includes linkage section and annular link slot section, offers multiple threaded holes on the linkage section, and described the
Two extension arms are connect by multiple threaded holes and bolt with the second rocker arm tabletting, and the second wing connecting rod is set in annular connection
In slot.
6. a kind of device for adjusting posture for small-sized sounding rocket according to claim 2, it is characterised in that: described
The shape of first steering engine rocker arm is cross, and offers an axis hole in central location, and the first rocking arm for pressing on piece opens up
There is the cross groove for accommodating the first steering engine rocker arm.
7. a kind of device for adjusting posture for small-sized sounding rocket according to claim 2, it is characterised in that: described
The shape of first wing connecting rod is arch-shaped.
8. a kind of device for adjusting posture for small-sized sounding rocket according to claim 3, it is characterised in that: described
The shape of second steering engine rocker arm is cross, and offers an axis hole in central location, and the second rocking arm for pressing on piece opens up
There is the cross groove for accommodating the second steering engine rocker arm.
9. a kind of device for adjusting posture for small-sized sounding rocket according to claim 3, it is characterised in that: described
Second wing connecting rod is arch-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821818089.2U CN209258422U (en) | 2018-11-06 | 2018-11-06 | A kind of device for adjusting posture for small-sized sounding rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821818089.2U CN209258422U (en) | 2018-11-06 | 2018-11-06 | A kind of device for adjusting posture for small-sized sounding rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209258422U true CN209258422U (en) | 2019-08-16 |
Family
ID=67553986
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821818089.2U Expired - Fee Related CN209258422U (en) | 2018-11-06 | 2018-11-06 | A kind of device for adjusting posture for small-sized sounding rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209258422U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207630A (en) * | 2020-01-10 | 2020-05-29 | 蓝箭航天空间科技股份有限公司 | Rocket flight attitude control method |
| CN111516909A (en) * | 2020-04-30 | 2020-08-11 | 北京星际荣耀空间科技有限公司 | Rocket attitude control system |
-
2018
- 2018-11-06 CN CN201821818089.2U patent/CN209258422U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111207630A (en) * | 2020-01-10 | 2020-05-29 | 蓝箭航天空间科技股份有限公司 | Rocket flight attitude control method |
| CN111516909A (en) * | 2020-04-30 | 2020-08-11 | 北京星际荣耀空间科技有限公司 | Rocket attitude control system |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190816 |
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| CF01 | Termination of patent right due to non-payment of annual fee |