CN109264029A - A kind of carrier rocket - Google Patents
A kind of carrier rocket Download PDFInfo
- Publication number
- CN109264029A CN109264029A CN201811133903.1A CN201811133903A CN109264029A CN 109264029 A CN109264029 A CN 109264029A CN 201811133903 A CN201811133903 A CN 201811133903A CN 109264029 A CN109264029 A CN 109264029A
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- Prior art keywords
- accommodating cavity
- rocket
- pushing meanss
- power device
- carrier rocket
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- 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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- 238000005183 dynamical system Methods 0.000 claims abstract description 9
- 239000004449 solid propellant Substances 0.000 claims description 17
- 239000007788 liquid Substances 0.000 claims description 11
- 239000003380 propellant Substances 0.000 claims description 10
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 230000006872 improvement Effects 0.000 description 7
- 230000008901 benefit Effects 0.000 description 6
- 238000005265 energy consumption Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/403—Solid propellant rocket engines
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Details Of Aerials (AREA)
Abstract
The present invention is suitable for space equipment technical field, provide a kind of carrier rocket, including load, radome fairing and dynamical system, radome fairing includes the first accommodating cavity of tapered shape and accommodates the second accommodating cavity that cavity is connect with first, dynamical system includes the power device being connected with radome fairing and the pushing meanss that are connected with load, pushing meanss are set in the first accommodating cavity, and pushing meanss and power device relative spacing are arranged, and load is set between pushing meanss and power device.Compared with prior art, the present invention is since pushing meanss being arranged in the first accommodating cavity of tapered shape, and it is connected with load, power device is connected with radome fairing, and power device and pushing meanss relative spacing are arranged, so pushing meanss can effectively fill the first accommodating cavity of tapered shape, so as to effectively reduce the volume and weight of carrier rocket, carrier rocket space utilization rate and carrying capacity are improved, production cost is reduced.
Description
Technical field
The invention belongs to space equipment technical field more particularly to a kind of carrier rockets.
Background technique
Small-sized or microminiature carrier rocket is to be positioned to provide the delivery vehicle of Launch Services for Foreign for small or micro-nano satellite, existing
There is both domestic and external small-sized or microminiature carrier rocket to inherit the mature technology of medium-and-large-sized liquid launch vehicle in overall structure,
I.e. small-sized or microminiature carrier rocket in overall structure generally by the way of 2-5 grades of series arrangements, carrier rocket most before
End is radome fairing, and being connected with radome fairing is multiple engines being sequentially connected in series, and the tail end of carrier rocket is equipped with boost motor.Delivery
After rocket firing transmitting, boost motor works to carrier rocket with upward motive force, then multiple engines successively work and after
Continue and provide power for carrier rocket, then each engine shuts down separation, and satellite is finally sent into preset track.
Currently, in order to obtain preferable aerodynamic configuration, often the front end of radome fairing is arranged into a cone shape, separately for carrier rocket
One end is designed to post shapes, to reduce the air drag of radome fairing.The loads such as the satellite of carrier rocket delivery are mainly concentrated
In the post shapes space of radome fairing, and the cone-shaped space of radome fairing is idle or contains few object, causes to rectify with regard to this
There is greatly waste in the cone-shaped space of cover, also increase the volume and weight of carrier rocket, to increase the dynamic of engine
Power output, production cost are higher.
Summary of the invention
The present invention provides a kind of carrier rocket, it is intended to leave unused and lead to carrier rocket in the cone-shaped space for solving radome fairing
The problem of volume and weight is big, and carrying capacity is poor, high production cost.
The invention is realized in this way provide a kind of carrier rocket, including load, the radome fairing with chamber resettling and
The dynamical system connecting with the radome fairing, the radome fairing include the first accommodating cavity of tapered shape and hold with described first
Set cavity connection second accommodating cavity, the dynamical system include the power device being connected with the radome fairing and with the fortune
The connected pushing meanss of loading, the pushing meanss are set in the first accommodating cavity, and the load is set to the promotion
Between device and the power device.
Further, it is described second accommodating cavity be in cylinder configuration, it is described second accommodating cavity one end with it is described
First accommodating cavity is connected, and the other end of the second accommodating cavity is connected with the power device.
Further, the load is set in the second accommodating cavity.
Further, the power device include it is multiple be sequentially connected in series start.
Further, each engine is liquid-propellant rocket engine or solid propellant rocket.
Further, the carrier rocket further includes multiple boost motors in the power device.
Further, each boost motor is liquid rocket boost motor or solid-propellant booster rocket.
The beneficial effect of carrier rocket provided by the invention is: compared with prior art, the present invention will be due to that will push dress
It installs in the first accommodating cavity of tapered shape, and is connected with load, power device is connected with radome fairing, load
It is arranged between power device and pushing meanss, therefore pushing meanss and power device form relative spacing setting；Power device
Carrier rocket is pushed to rise, after radome fairing separation, pushing meanss drive load to can be rotated 180 ° and turn around, and pushing meanss can be after
Continue and provides power for load until reaching predetermined trajectory.So pushing meanss are set in the first accommodating cavity, it can be by first
Accommodating cavity is effectively filled, so as to effectively reduce the volume and weight of carrier rocket, improve carrier rocket space utilization rate and
Carrying capacity reduces production cost.
Detailed description of the invention
Fig. 1 is the structural schematic diagram for the carrier rocket that the prior art provides.
Fig. 2 is the structural schematic diagram of carrier rocket provided by the invention.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
It should be noted that it can be directly another when element is referred to as " being fixed on " or " being set to " another element
On one element or indirectly on another element.When an element is known as " being connected to " another element, it can
To be directly to another element or be indirectly connected on another element.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
In the description of the present invention, it is to be understood that, term " center ", " length ", " width ", " thickness ", "upper",
The orientation or position of the instructions such as "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside"
Relationship is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of description of the present invention and simplification of the description, without referring to
Show or imply that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore cannot manage
Solution is limitation of the present invention.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
The interaction relationship of connection or two elements inside two elements.It for the ordinary skill in the art, can be with
The concrete meaning of above-mentioned term in the present invention is understood as the case may be.
As shown in Figure 1, in the prior art, the power device 21 and pushing meanss 22 of dynamical system 2 are arranged in series,
It is followed successively by load 3, pushing meanss 22 and power device 21 from top to bottom, the first accommodating cavity 11 of radome fairing 1 is in idle
State.As shown in Fig. 2, pushing meanss 22 are set in the first accommodating cavity 11 of the tapered shape of radome fairing 1 by the present invention, from upper
Pushing meanss 22, load 3 and power device 21 are followed successively by under, pushing meanss 22 and power device 21 are oppositely arranged.
Embodiment one
Referring to Figure 2 together, the carrier rocket now provided the embodiment of the present invention one is illustrated.The carrier rocket includes
Load 3, the radome fairing 1 with chamber resettling and the dynamical system 2 being connect with the radome fairing 1.The radome fairing 1 includes tapered
First accommodating cavity 11 of shape and the second accommodating cavity 12 being connect with the first accommodating cavity 11, the first accommodating cavity 11 and second
Accommodating cavity 12 is hollow structure, and the first hollow accommodating cavity 11 and the second hollow accommodating cavity 12 are encircled into accommodating cavity
Room.Dynamical system 2 includes power device 21 and pushing meanss 22, and the first accommodating cavity 11 is set to the one of the second accommodating cavity 12
Side, power device 21 are set to the other side of the second accommodating cavity 12；Pushing meanss 22 be set to first accommodating cavity 11 in, and with fortune
Loading 3 is connected, and load 3 is set between pushing meanss 22 and power device 21, and pushing meanss 22 and power device 21 are phase
Interval is arranged.
Load 3 in the application can be satellite, or other equipment do not limit uniquely herein.
After carrier rocket igniting, power device 21 works first and provides upward motive force, thus by carrier rocket
Lift-off is pushed, after carrier rocket reaches preset height and speed, power device 21 and radome fairing 1 separate in succession, in the earth
Under the action of gravitation, into coast period, pushing meanss 22 and load 3 can be realized by included position control
180 ° are turned around；When tangent with the preset track of load 3,22 ignition operation of pushing meanss enters the final stage of acceleration, until
After reaching preset speed, pushing meanss 22 are shut down and are separated with load 3, and load 3 is successfully entered preset running track.
The present invention due to by pushing meanss 22 be arranged in tapered shape first accommodating cavity 11 in, and with 3 phase of load
Even, power device 21 is connected with radome fairing 1, and power device 21 and the setting of 22 relative spacing of pushing meanss；Power device 21
Carrier rocket is pushed to rise, after radome fairing 1 separates, pushing meanss 22 can be rotated 180 ° with load 3 and turn around, pushing meanss 22
Work continues as load 3 and provides power until reaching predetermined trajectory.So pushing meanss 22 are set to the first accommodating cavity 11
In, the first accommodating cavity 11 can effectively be filled, so as to effectively reduce the volume and weight of carrier rocket, improve carrier rocket
Space utilization rate and carrying capacity reduce production cost.
Embodiment two
Referring to Figure 2 together, the present embodiment be based on the improvement carried out on the basis of embodiment one, the present embodiment with it is above-mentioned
The difference of embodiment one is: the second accommodating cavity 12 is in cylinder configuration, and one end of the second accommodating cavity 12 holds with first
It sets cavity 11 to be connected, the other end is connected with power device 21.Specifically, the second accommodating cavity 12 has an open end, and with the
One accommodating cavity 11 is connected to；The other end of second accommodating cavity 12 is sealed end, and is connected with power device 21.This structure, will
Second accommodating cavity 12 is arranged to cylinder configuration, can cooperate with the first accommodating cavity 11 of tapered shape, to reduce air resistance
Power meets Engineering Dynamics design, reduces energy consumption, reduce cost.
In other embodiments, other configurations also can be set into the second accommodating cavity 12, do not limit uniquely herein.Such as
The main view of second accommodating cavity 12 is in isosceles trapezoid, and the bottom surface of the second accommodating cavity 12 is connected with the first accommodating cavity 11,
The upper bottom surface of second accommodating cavity 12 is connected with power device 21.This structure, the second accommodating cavity 12, which stands upside down, to be arranged, the first accommodating
The tapered surface of cavity 11 can be matched with the side of the second accommodating cavity 12, and then can reduce the resistance of carrier rocket flight, be subtracted
Few energy consumption, reduces cost.
Embodiment three
Referring to Figure 2 together, the present embodiment be based on the improvement carried out on the basis of embodiment one, the present embodiment with it is above-mentioned
The difference of embodiment one is: load 3 is set in the second accommodating cavity 12.This structure, when power device 21 shut down and with it is whole
After 1 separation of stream cover, the load 3 being arranged in the second accommodating cavity 12 of radome fairing 1 can be unaffected, stores security performance
It is high.
Optionally, load 3 also can be set at other positions.When pushing meanss 22 are simultaneously by the first of radome fairing 1
Accommodating cavity 11 and the second accommodating cavity 12 take, at this point, load 3 can only be just arranged at the other positions of carrier rocket,
But remain that pushing meanss 22 are located at one end of load 3, power device 21 is located at the other end of load 3, and pushes dress
It is relative spacing setting that 22, which are set, with power device 21, and load 3 is arranged between pushing meanss 22 and power device 21.
Example IV
Referring to Figure 2 together, the present embodiment be based on the improvement carried out on the basis of embodiment one, the present embodiment with it is above-mentioned
The difference of embodiment one is: power device 21 includes multiple engines being sequentially connected in series.For convenience of description, by multiple engines
Sequence from the bottom to top be referred to as thruster, second-stage rocket motor ..., n-th grade of rocket engine,
Middle n refers to the quantity of engine.This structure can be separated with subsequent engine after previous engine cutoff.Pass through multiple engines
The operation height and speed of adjustable carrier rocket, and then may make load 3 that can enter precisely into preset track, it can be improved
The orbit injection accuracy of load 3.
Similarly, pushing meanss 22 also may include multiple pushers being sequentially connected in series.After power device 21 is successively detached from,
Pushing meanss 22 can drive load 3 to continue to run, and each pusher of pushing meanss 22 successively shuts down disengaging, and by load 3
It is sent into preset track.
Embodiment five
The present embodiment is based on the improvement carried out on the basis of example IV, the difference of the present embodiment and above-described embodiment four
Be: each engine is liquid-propellant rocket engine or solid propellant rocket.
Liquid-propellant rocket engine is that liquid chemical substance is used to start as the rocket propulsion equipment of the energy with solid-rocket
Machine is compared, and has the advantage that 1, speed is fast, load-carrying is big；2, engine arbitrarily can start and shut down；3, thrust chamber can cool down,
Propellant mass score is high.
Solid propellant rocket is the chemical rocket engine using solid propellant.Solid propellant is burning after lighting
It burns in room, chemical energy is converted into thermal energy, and the combustion product for producing high temperature and pressure accelerates through nozzle expansion, and thermal energy is
Can, with high speed is discharged from jet pipe and generates thrust.Compared with liquid-propellant rocket engine, have the advantage that 1, working time is short；
2, acceleration is big.
Each engine of power device 21 in the application can select according to actual needs liquid-propellant rocket engine or
Solid propellant rocket；Similarly, the pushing meanss 22 in the application can also select liquid-propellant rocket engine according to actual needs
Or solid propellant rocket, it does not limit uniquely herein.
Embodiment six
The present embodiment is based on the improvement carried out on the basis of embodiment one, the difference of the present embodiment and above-described embodiment one
Be: carrier rocket further includes multiple boost motors in power device 21 (attached drawing is not shown).This structure, carrier rocket point
After fire, multiple boost motors work at first, and provide motive force, to provide enough motive forces for carrier rocket.
Embodiment seven
The present embodiment is based on the improvement carried out on the basis of embodiment six, the difference of the present embodiment and above-described embodiment six
Be: each boost motor is liquid rocket boost motor or solid-propellant booster rocket.
Liquid rocket boost motor and solid-propellant booster rocket are all that one kind is bundled in the rocket core grade first order, improve rocket
The liquid fuel minitype motivation equipment of power.Compared with solid-propellant booster rocket, liquid rocket boost motor can be cut off if necessary
The supply of propellant is to realize emergency brake.Compared with liquid rocket boost motor, the motive force of solid-propellant booster rocket is bigger, and
Refrigeration heat insulation device is not needed.
Boost motor in the application can select liquid rocket boost motor or solid-propellant booster rocket according to actual needs,
It does not limit uniquely herein.
Carrier rocket provided by the present application has the beneficial effect that:
1, pushing meanss 22 are arranged in the first accommodating cavity 11 of tapered shape, the space benefit of carrier rocket can be improved
With rate, reduce the volume and weight of carrier rocket, so as to reduce cost；
2, can cooperate with the first accommodating cavity 11 of tapered shape in the second accommodating cavity 12 of cylinder configuration, to reduce
Air drag reduces energy consumption；
3, the storage security performance that the load 3 in the second accommodating cavity 12 is arranged in is high；
4, multiple engines are controllable and adjust the height and speed of carrier rocket, and control and adjustment capability are strong；
5, liquid-propellant rocket engine or solid propellant rocket have the advantages that protrusion, service performance are good；
6, multiple boost motors can provide sufficient motive force for carrier rocket；
7, liquid rocket boost motor or solid-propellant booster rocket have the advantages that protrusion, service performance are good.
Pushing meanss 22 by being arranged in the first accommodating cavity of the tapered shape of radome fairing 1 by carrier rocket provided by the present application
In body 11, the space waste rate of radome fairing 1 can be effectively reduced, and then improve the carrying capacity of carrier rocket.Specifically, it can be improved
The carrying capacity of small-sized/10% or more microminiature carrier rocket.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (7)
1. a kind of carrier rocket, including load, the radome fairing with chamber resettling and the dynamical system being connect with the radome fairing
System, the radome fairing include the first accommodating cavity of tapered shape and accommodate the second accommodating cavity that cavity is connect with described first
Body, which is characterized in that the dynamical system includes the power device being connected with the radome fairing and is connected with the load
Pushing meanss, the pushing meanss be set to it is described first accommodating cavity in, the load be set to the pushing meanss with it is described
Between power device.
2. a kind of carrier rocket as described in claim 1, which is characterized in that the second accommodating cavity is in cylinder configuration,
One end of the second accommodating cavity is connected with the first accommodating cavity, and the other end of the second accommodating cavity is moved with described
Power device is connected.
3. a kind of carrier rocket as described in claim 1, which is characterized in that the load is set to the second accommodating cavity
In.
4. a kind of carrier rocket as described in claim 1, which is characterized in that the power device includes multiple is sequentially connected in series
Engine.
5. a kind of carrier rocket as claimed in claim 4, which is characterized in that each engine be liquid-propellant rocket engine or
Person's solid propellant rocket.
6. a kind of carrier rocket as described in claim 1, which is characterized in that the carrier rocket further includes being set to the power
Multiple boost motors on device.
7. a kind of carrier rocket as claimed in claim 6, which is characterized in that each boost motor be liquid rocket boost motor or
Person's solid-propellant booster rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811133903.1A CN109264029A (en) | 2018-09-27 | 2018-09-27 | A kind of carrier rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811133903.1A CN109264029A (en) | 2018-09-27 | 2018-09-27 | A kind of carrier rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109264029A true CN109264029A (en) | 2019-01-25 |
Family
ID=65198489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811133903.1A Pending CN109264029A (en) | 2018-09-27 | 2018-09-27 | A kind of carrier rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109264029A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112325708A (en) * | 2020-11-02 | 2021-02-05 | 中国运载火箭技术研究院 | Multi-stage carrier rocket |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0699898A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Nose fairing device for rocket |
| US6244541B1 (en) * | 1997-01-29 | 2001-06-12 | Centre National D'etudes Spatiales | Device for suspension of a payload in a space launch |
| CN1405527A (en) * | 2001-08-14 | 2003-03-26 | 王雪松 | Jet propelling aircraft |
| RU2238226C2 (en) * | 2000-07-19 | 2004-10-20 | Карпов Анатолий Степанович | Multi-stage module-type launch vehicle |
| US20070068138A1 (en) * | 2005-05-17 | 2007-03-29 | Sheerin Geoffrey T | Rocket vehicle and engine |
| WO2013039426A1 (en) * | 2011-08-25 | 2013-03-21 | Ryabukha Nikolay Nikolayevich | Gliding spacecraft with folding nose fairing (variants) and method for controlling the return thereof to the landing field |
| CN209008891U (en) * | 2018-09-27 | 2019-06-21 | 宁波天擎航天科技有限公司 | A kind of carrier rocket |
-
2018
- 2018-09-27 CN CN201811133903.1A patent/CN109264029A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0699898A (en) * | 1992-09-17 | 1994-04-12 | Nissan Motor Co Ltd | Nose fairing device for rocket |
| US6244541B1 (en) * | 1997-01-29 | 2001-06-12 | Centre National D'etudes Spatiales | Device for suspension of a payload in a space launch |
| RU2238226C2 (en) * | 2000-07-19 | 2004-10-20 | Карпов Анатолий Степанович | Multi-stage module-type launch vehicle |
| CN1405527A (en) * | 2001-08-14 | 2003-03-26 | 王雪松 | Jet propelling aircraft |
| US20070068138A1 (en) * | 2005-05-17 | 2007-03-29 | Sheerin Geoffrey T | Rocket vehicle and engine |
| WO2013039426A1 (en) * | 2011-08-25 | 2013-03-21 | Ryabukha Nikolay Nikolayevich | Gliding spacecraft with folding nose fairing (variants) and method for controlling the return thereof to the landing field |
| CN209008891U (en) * | 2018-09-27 | 2019-06-21 | 宁波天擎航天科技有限公司 | A kind of carrier rocket |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112325708A (en) * | 2020-11-02 | 2021-02-05 | 中国运载火箭技术研究院 | Multi-stage carrier rocket |
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