CN207748050U - A kind of spacecraft return capsule using extension type jet autorotating rotor system - Google Patents
A kind of spacecraft return capsule using extension type jet autorotating rotor system Download PDFInfo
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- CN207748050U CN207748050U CN201721808415.7U CN201721808415U CN207748050U CN 207748050 U CN207748050 U CN 207748050U CN 201721808415 U CN201721808415 U CN 201721808415U CN 207748050 U CN207748050 U CN 207748050U
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Abstract
The utility model discloses a kind of spacecraft return capsules using extension type jet autorotating rotor system, including：Return capsule enters during atmosphere stabilization decline, high temperature, high-speed flow, which enter through adjustable partition board formula air intake duct in high pressure gas holder, to be mixed, under the control of High-pressure air valve, high pressure gas enters blade through gas-guide tube, is sprayed at blade tip and then generates promotion blade rotation.During return capsule declines, return capsule state recognition and descending trajectory planning are carried out by central controller, driving is embedded in the multi-redundant motor-driven cylinder at rotor blade and carries out period manipulation, lift distribution by changing paddle disk realizes that return capsule flies towards desired trajectory, and the descending motion for making return capsule be optimal.The utility model uses extension type blade and wing tip gas jet technique, does not influence return capsule seal and heat-proof quality, without offsetting the anti-twisted design of rotor, and can plan return capsule descent path and landing point, greatly reduce the task amount of ground rescue worker.
Description
Technical field
The present invention relates to a kind of spacecraft return capsules using extension type jet autorotating rotor system, belong to spacecraft and return
Reboard equipment technical field.
Background technology
The step that the mankind explore space never stops, and subsequently will further carry out moon exploration Correlative plan demonstration, and
Carry out Mars sampling return, asteroid detection, Jupiter system and planet and passes through the schemes such as detection in-depth demonstration and tackling problems in key technologies.
It is contemplated that is obtained is that following space flight Exploratory behavior will be more and more, therefore design a kind of simple, safety return capsule
Recovery system is most important.Traditional spacecraft return capsule is to be slowed down by the way that multistage parachute is unfolded, but land parachuting
Process and uncontrollable is fallen, and can be influenced significantly, landing of return capsule place can usually be caused to deviate presumptive area by Atmospheric Flow,
Ground is increased to search and rescue difficulty and cause the unstability factor in more removal process.
The present invention relates to a kind of novel spacecraft return capsule designs, by installing a set of extension type on return capsule top
Jet rotation Smart Rotor system enters after atmosphere for realizing spacecraft return capsule under being slowed down with controllable flight path
Drop, and then reach the touchdown speed assigned spot recovery close to zero.The present invention collect spacecraft return capsule, Smart Rotor, trajectory planning,
The sophisticated technologies such as assigned spot recovery, search and rescue the design of Future Spacecraft return capsule, ground, control the recycling of the return capsules such as commander
System generates significant innovation.
Invention content
Goal of the invention：In order to overcome the deficiencies in the prior art, the present invention to provide a kind of using extension type jet
The spacecraft return capsule of autorotating rotor system has the characteristics that compact-sized, control intelligence, recycling are convenient, using extension type
Blade and wing tip gas jet technique, do not influence return capsule seal and heat-proof quality, without offsetting the anti-twisted design of rotor, and can plan
Return capsule descent path and landing point greatly reduce the task amount of ground rescue worker.
Technical solution：To achieve the above object, the technical solution adopted by the present invention is：
A kind of spacecraft return capsule using extension type jet autorotating rotor system, including hatchcover, return on return capsule
Cabin nacelle, extension type autorotating rotor system, high-pressure jet system；
Wherein, the extension type autorotating rotor system includes rotating disk and the extension type paddle along rotating disk circumference uniform distribution
Leaf, and extension type blade is extended to radially across the outer wall of rotating disk on the center lasso of rotating disk；The rotating disk cloth
It is placed between hatchcover on return capsule, return capsule nacelle, and center lasso is socketed on the center at the top of return capsule nacelle by bearing
On axis；
The high-pressure jet system includes adjustable partition board formula air intake duct, high pressure gas holder, High-pressure air valve, blade tip air-jet cover, and
Adjustable partition board formula air intake duct is uniformly distributed around return capsule nacelle outside top, and is connected to the high pressure gas holder at the top of return capsule nacelle,
The air inflow of high pressure gas holder is controlled by adjustable partition board formula air intake duct；The high pressure gas holder passes through top high-voltage air valve and rotating disk
Connection, and then be connected to the blade tip air-jet cover of extension type blade outer end by gas-guide tube.
In the present invention, high speed, high pressure draught when being declined using return capsule are sprayed through pipeline from wing tip, and rotor system will not
Torque is generated, therefore there is shipping-direction stability, is designed without reaction torque, entire rotor system is compact-sized；Blade use can stretch
Contracting formula designs, and entire rotor system is mounted on return capsule top, does not influence the seal and thermal insulation of return capsule nacelle, does not influence
Return capsule installation is docked with space station on the launch vehicle and in space；Return capsule nacelle surface layout adjustable partition board formula
Air intake duct can adjust air inflow by control system, control rotor rotating speed, ensure that return capsule is declined with acceptable speed.
Further, the return capsule upper-deck cabin tops are provided with orbital module interface and spacefarer goes out cabin channel, and return
Hatchcover is bolted with the central shaft at the top of return capsule nacelle using detachable on cabin.
Further, it is disposed with ring-shaped guide rail around center lasso in the rotating disk, and high pressure gas holder passes through annular groove
The High-pressure air valve of shape is connected to ring-shaped guide rail, and then is connected to the blade tip air-jet cover of extension type blade outer end by gas-guide tube,
Realize the air current sealed transmission of high pressure gas holder and gas-guide tube on extension type blade under rotation status.
Further, the extension type blade includes the first segment paddle radially to connect successively from inside to outside along rotating disk
Leaf, second segment blade, third section blade, and embedded trailing edge flap and the piezoresistive material for driving are disposed on third section blade
Expect actuator.Using automatically controlled rotor, that is, utilizes embedded-type electric actuator driving wing flap to realize rotor control, compare mechanical manipulation
System, which can effectively reduce the structure type of rotor system and be more easily implemented multi-redundant, manipulates design.
Further, central controller, height sensor, attitude transducer, speed are installed in the return capsule nacelle
Sensor, for realizing hatchcover, return capsule nacelle, extension type autorotating rotor system, the intelligence of high-pressure jet system on return capsule
It can control.
Return capsule enters high temperature, the high-speed flow that atmosphere is stablized when declining relatively upward and is changed into height after air intake duct
Temperature, low velocity gas are mixed in high-pressure gas slot, and under the control of air valve, high pressure gas enters paddle by metal elastic reed pipe
Leaf sprays at blade tip and then generates promotion blade rotation.
During return capsule declines, return capsule state recognition is carried out by central controller and descending trajectory is planned, is driven
The dynamic multi-redundant motor-driven cylinder being embedded at rotor blade carries out period manipulation, and the lift distribution realization by changing paddle disk is returned
Reboard flies towards desired trajectory, and the descending motion for making return capsule be optimal.
Advantageous effect：Spacecraft return capsule provided by the invention using extension type jet autorotating rotor system, relatively
In the prior art, has the following advantages：
1, using extension type blade and wing tip gas jet technique, return capsule seal and heat-proof quality are not influenced, without supporting
The anti-twisted design of the racemization wing, compact-sized, occupancy is small, integrated with return capsule；
2, it using Smart Rotor control system, controls rotor system air inflow and is transported using intellectual material driving blade rear
It is dynamic, it is small by recycling place atmosphere environment impact, so that return capsule is declined along programme path with acceptable decrease speed, significantly
It reduces ground and searches and rescues difficulty.
Description of the drawings
Fig. 1 is the overall schematic of the present invention；
Fig. 2 is the structure scheme of installation of the present invention；
Fig. 3 is that the present invention enters the diagrammatic cross-section for declining recycling state；
Fig. 4 is diagrammatic cross-section of the present invention in other task phases；
Fig. 5 is the structural schematic diagram of extension type blade in the present invention；
Figure includes：1, hatchcover on return capsule, 2, extension type blade, 3, return capsule nacelle, 4, adjustable partition board formula air inlet
Road, 5, rotating disk, 6, orbital module interface, 7, spacefarer go out cabin channel, 8, bearing, 9, High-pressure air valve, 10, high pressure gas holder, 11,
One section of blade, 12, second segment blade, 13, third section blade, 14, piezoelectric material actuator, 15, blade tip air-jet cover, 16, embedded
Formula trailing edge flap.
Specific implementation mode
The present invention is further described below in conjunction with the accompanying drawings.
It is a kind of spacecraft return capsule using extension type jet autorotating rotor system as shown in Figure 1, 2, including returns
Hatchcover 1, return capsule nacelle 3, extension type autorotating rotor system, high-pressure jet system on cabin；
Wherein, the extension type autorotating rotor system includes rotating disk 5 and the extension type along 5 circumference uniform distribution of rotating disk
Blade 2, and extension type blade 2 is extended to radially across the outer wall of rotating disk 5 on the center lasso of rotating disk 5；The rotation
Turntable 5 is arranged on return capsule between hatchcover 1, return capsule nacelle 3, and center lasso is socketed on return capsule nacelle 3 by bearing 8
On the central shaft at top；
The high-pressure jet system includes adjustable partition board formula air intake duct 4, high pressure gas holder 10, High-pressure air valve 9, blade tip air-jet cover
15, and adjustable partition board formula air intake duct 4 is uniformly distributed around 3 outside top of return capsule nacelle, and with the high pressure gas at 3 top of return capsule nacelle
Tank 10 is connected to, and the air inflow of high pressure gas holder 10 is controlled by adjustable partition board formula air intake duct 4；The high pressure gas holder 10 passes through top height
Pressure valve 9 is connected to rotating disk 5, and then is connected to the blade tip air-jet cover 15 of 2 outer end of extension type blade by gas-guide tube.
In the present embodiment, 1 top of hatchcover is provided with orbital module interface 6 on the return capsule and spacefarer goes out cabin channel 7, and
Hatchcover 1 and the central shaft at 3 top of return capsule nacelle are bolted using detachable on return capsule.
As shown in Figure 3,4, it is disposed with ring-shaped guide rail around center lasso in the rotating disk 5, and high pressure gas holder 10 passes through
The High-pressure air valve 9 of annular groove-shaped is connected to ring-shaped guide rail, and then passes through the blade tip jet of gas-guide tube and 2 outer end of extension type blade
15 connection of cover, realizes the air current sealed transmission of high pressure gas holder 10 and gas-guide tube on extension type blade 2 under rotation status.
As shown in figure 5, the extension type blade 2 includes along the radial first segment to connect successively from inside to outside of rotating disk 5
Blade 11, second segment blade 12, third section blade 13, and be disposed with embedded trailing edge flap 16 on third section blade 13 and be used for
The piezoelectric material actuator 14 of driving.
In the present embodiment, central controller, height sensor, attitude transducer, speed are installed in the return capsule nacelle 3
Sensor is spent, for realizing hatchcover on return capsule 1, return capsule nacelle 3, extension type autorotating rotor system, high-pressure jet system
Intelligent control.
The specific implementation mode of the present invention is as follows：
Return capsule is reentried after atmosphere enters stable decline state, open under program control nacelle periphery it is adjustable every
Board-like air intake duct 4 stores at a high speed, in high pressure gas holder 10 of the high pressure draught inside nacelle, and air-flow enters blade through gas-guide tube and receives
It receives in shell, while extension type blade 2 being pushed to be stretched out from rotating disk 5 and self-locking, air-flow is sprayed from wing tip drives rotor wing rotation,
Rotor, which generates lift, makes spacecraft return capsule slow down.
Installation posture sensor and velocity sensor measure return capsule decline attitude angle, lower reduction of speed in real time inside return capsule
The parameters such as degree calculate output signal by central controller and drive to actuator, to drive embedded trailing edge flap 16 on blade
Deflection realizes that return capsule presses planned orbit descending flight.Pass through adjustment nacelle peripheral intake road the first transaction of a day's business size and adjustment paddle
Leaf stores shell root air valve ventilatory capacity, ensures rotor invariablenes turning speed and return capsule can be made to reach predetermined decrease speed.
Air intake duct 4 is closed at 500 meters when return capsule is drop to above expected point of impact, integrating height by central controller passes
The measuring instruments such as sensor, attitude transducer, velocity sensor control air valve ventilatory capacity, when return capsule will be landed by program
Accelerate rotor wing rotation, making return capsule, finally vertically predetermined pick-up point is grounded with zero velocity, controllable type landing is realized, to subtract significantly
Search and rescue difficulty in few ground.
The above is only a preferred embodiment of the present invention, it should be pointed out that：For the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (5)
1. a kind of spacecraft return capsule using extension type jet autorotating rotor system, which is characterized in that including on return capsule
Hatchcover (1), return capsule nacelle (3), extension type autorotating rotor system, high-pressure jet system；
Wherein, the extension type autorotating rotor system includes rotating disk (5) and the extension type along rotating disk (5) circumference uniform distribution
Blade (2), and extension type blade (2) extends to the center lasso of rotating disk (5) radially across the outer wall of rotating disk (5)
On；The rotating disk (5) is arranged between hatchcover on return capsule (1), return capsule nacelle (3), and center lasso passes through bearing (8)
It is socketed on the central shaft at the top of return capsule nacelle (3)；
The high-pressure jet system includes adjustable partition board formula air intake duct (4), high pressure gas holder (10), High-pressure air valve (9), blade tip jet
It covers (15), and adjustable partition board formula air intake duct (4) is uniformly distributed around return capsule nacelle (3) outside top, and is pushed up with return capsule nacelle (3)
The high pressure gas holder (10) in portion is connected to, and the air inflow of high pressure gas holder (10) is controlled by adjustable partition board formula air intake duct (4)；The high pressure
Gas tank (10) is connected to by top high-voltage air valve (9) with rotating disk (5), and then outside by gas-guide tube and extension type blade (2)
The blade tip air-jet cover (15) at end is connected to.
2. a kind of spacecraft return capsule using extension type jet autorotating rotor system according to claim 1, special
Sign is, is provided with orbital module interface (6) at the top of hatchcover (1) on the return capsule and spacefarer goes out cabin channel (7), and return capsule
Upper hatchcover (1) is bolted with the central shaft at the top of return capsule nacelle (3) using detachable.
3. a kind of spacecraft return capsule using extension type jet autorotating rotor system according to claim 1, special
Sign is, is disposed with ring-shaped guide rail around center lasso in the rotating disk (5), and high pressure gas holder (10) passes through annular groove-shaped
High-pressure air valve (9) is connected to ring-shaped guide rail, and then passes through the blade tip air-jet cover (15) of gas-guide tube and extension type blade (2) outer end
The air current sealed transmission of high pressure gas holder (10) and gas-guide tube on extension type blade (2) under rotation status is realized in connection.
4. a kind of spacecraft return capsule using extension type jet autorotating rotor system according to claim 1, special
Sign is that the extension type blade (2) includes the first segment blade radially to connect successively from inside to outside along rotating disk (5)
(11), second segment blade (12), third section blade (13), and embedded trailing edge flap (16) is disposed on third section blade (13)
And the piezoelectric material actuator (14) for driving.
5. a kind of spacecraft return capsule using extension type jet autorotating rotor system according to claim 4, special
Sign is, central controller, height sensor, attitude transducer, velocity sensor are equipped in the return capsule nacelle (3),
For realizing hatchcover on return capsule (1), return capsule nacelle (3), extension type autorotating rotor system, the intelligence of high-pressure jet system
Control.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721808415.7U CN207748050U (en) | 2017-12-22 | 2017-12-22 | A kind of spacecraft return capsule using extension type jet autorotating rotor system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721808415.7U CN207748050U (en) | 2017-12-22 | 2017-12-22 | A kind of spacecraft return capsule using extension type jet autorotating rotor system |
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| CN207748050U true CN207748050U (en) | 2018-08-21 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109518824A (en) * | 2019-01-07 | 2019-03-26 | 北京宇航系统工程研究所 | A kind of spherical convertible structure of modularization for bearing big external pressure |
| CN109976224A (en) * | 2019-04-18 | 2019-07-05 | 福建金龙腾动力机械有限公司 | A kind of intelligent control circuit of inflatable illumination lamp post |
| CN110196134A (en) * | 2019-05-09 | 2019-09-03 | 大连普瑞森科技有限公司 | A kind of piston manometer persistently rotated based on no friction mode driving counterweight |
| CN114295014A (en) * | 2021-12-30 | 2022-04-08 | 宁波天擎航天科技有限公司 | Rocket of external rudder system |
-
2017
- 2017-12-22 CN CN201721808415.7U patent/CN207748050U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109518824A (en) * | 2019-01-07 | 2019-03-26 | 北京宇航系统工程研究所 | A kind of spherical convertible structure of modularization for bearing big external pressure |
| CN109976224A (en) * | 2019-04-18 | 2019-07-05 | 福建金龙腾动力机械有限公司 | A kind of intelligent control circuit of inflatable illumination lamp post |
| CN109976224B (en) * | 2019-04-18 | 2020-11-20 | 福建金龙腾动力机械有限公司 | Intelligent control circuit that inflatable lighting lamp pole was used |
| CN110196134A (en) * | 2019-05-09 | 2019-09-03 | 大连普瑞森科技有限公司 | A kind of piston manometer persistently rotated based on no friction mode driving counterweight |
| CN114295014A (en) * | 2021-12-30 | 2022-04-08 | 宁波天擎航天科技有限公司 | Rocket of external rudder system |
| CN114295014B (en) * | 2021-12-30 | 2024-03-19 | 宁波天擎航天科技有限公司 | Rocket of external rudder system |
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