CN117232343A - Airborne launching rocket with wings and airborne launching system - Google Patents
Airborne launching rocket with wings and airborne launching system Download PDFInfo
- Publication number
- CN117232343A CN117232343A CN202311428002.6A CN202311428002A CN117232343A CN 117232343 A CN117232343 A CN 117232343A CN 202311428002 A CN202311428002 A CN 202311428002A CN 117232343 A CN117232343 A CN 117232343A
- Authority
- CN
- China
- Prior art keywords
- rocket
- sub
- stage
- main wing
- winged
- 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.)
- Pending
Links
- 241000276425 Xiphophorus maculatus Species 0.000 claims abstract description 3
- 210000001503 joint Anatomy 0.000 claims description 12
- 239000007787 solid Substances 0.000 claims description 12
- 210000001015 abdomen Anatomy 0.000 claims description 4
- 230000005540 biological transmission Effects 0.000 claims description 2
- 235000015842 Hesperis Nutrition 0.000 abstract description 2
- 235000012633 Iberis amara Nutrition 0.000 abstract description 2
- 238000000926 separation method Methods 0.000 description 10
- 238000010586 diagram Methods 0.000 description 2
- 208000035742 Air-borne transmission Diseases 0.000 description 1
- 230000005557 airborne transmission Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The application relates to the technical field of rockets, in particular to an airborne launching rocket with wings and an airborne launching system, which comprise the following components: the rocket comprises a rocket body, a main wing and two hooks; the main wing is in an axisymmetric platy shape, the part of the inner side surface of the main wing, which is positioned at the symmetric axis, is fixedly connected with the outer surface of the rocket body, the tail edge of the main wing is perpendicular to the axis of the rocket body, and the head edge of the main wing gradually inclines from the symmetric axis to two sides to the tail; the two hooks are fixed on the rocket body, are in a straight line with the symmetry axis of the main wing, are distributed on the front and back of the main wing, and are used for being mounted on a carrier hanger during airborne launching. The application can reduce the cost of rocket launching and improve the efficiency of rocket launching.
Description
Technical Field
The application relates to the technical field of rockets, in particular to an airborne launching rocket with wings and an airborne launching system.
Background
With the rapid development of the aerospace launching technology, the aerospace launching has the development toward the low-cost and high-efficiency launching direction. However, the conventional rocket launching is usually carried out on land or at sea, the initial speed of the rocket launching is zero, and the initial height of the launching is low, so that the conventional rocket launching has the defects of high launching cost, relatively fixed launching site, relatively low launching efficiency and the like.
Therefore, how to reduce the cost of rocket launching and improve the efficiency of rocket launching is a technical problem which needs to be solved by the technicians in the field at present.
Disclosure of Invention
The application provides an airborne launching rocket with wings and an airborne launching system, which are used for reducing the cost of rocket launching and improving the efficiency of rocket launching.
In order to solve the technical problems, the application provides the following technical scheme:
an airborne launch rocket with wings, comprising: the rocket comprises a rocket body, a main wing and two hooks; the main wing is in an axisymmetric platy shape, the part of the inner side surface of the main wing, which is positioned at the symmetric axis, is fixedly connected with the outer surface of the rocket body, the tail edge of the main wing is perpendicular to the axis of the rocket body, and the head edge of the main wing gradually inclines from the symmetric axis to two sides to the tail; the two hooks are fixed on the rocket body, are in a straight line with the symmetry axis of the main wing, are distributed on the front and back of the main wing, and are used for being mounted on a carrier hanger during airborne launching.
A winged on-board launch rocket as described above, wherein preferably the rocket body comprises: a first sub-stage, a second three-stage, a third sub-stage, a third four-stage, a fourth sub-stage and a fairing; wherein the front end of the first sub-stage is in butt joint with the rear end of the second sub-stage, the front end of the second sub-stage is in butt joint with the rear end of the second three-stage, the front end of the second-level interstage section is in butt joint with the rear end of the third sub-level, the front end of the third sub-level is in butt joint with the rear end of the third-level interstage section, the front end of the third-level interstage section is in butt joint with the rear end of the fourth sub-level, and the rear end of the fairing is in butt joint with the front end of the fourth sub-level.
A winged airborne launch rocket as described above, wherein preferably a sub-stage comprises: a sub-level body, tail wing and main wing; the part of the inner side surface of the main wing, which is positioned at the symmetrical axis, is fixedly connected with the outer surface of a sub-level body, and the tail edge of the main wing is vertical to the axis of the sub-level body; the fin is fixedly connected with the outer surface of a sub-level body, and the fin is positioned behind the main wing.
The airborne rocket with the wings, as described above, wherein preferably, the trailing edge flap is installed at the tail edge of the main wing, and the steering engine is arranged in the main wing, and the action of the trailing edge flap is controlled by the steering engine; the tail edge of the tail wing is also provided with a trailing edge flap, and a steering engine is arranged in the tail wing and used for controlling the action of the trailing edge flap.
A winged airborne launch rocket as described above, wherein preferably the four sub-stages comprise: the device comprises a shell section, a four-stage solid rocket engine, a rocket control instrument and a plurality of attitude control engines; a four-stage solid rocket engine is fixed into the shell section and is positioned at an intermediate position in the shell section; the rocket control instrument is fixed into the shell section and is positioned between the four-stage solid rocket engine and the shell section; a plurality of attitude control engines are secured to the outer surface of the housing section.
The winged on-board launch rocket as described above wherein preferably one hook is secured to one sub-stage body and the other hook is secured to the outer surface of the three sub-stages.
A winged airborne launch rocket as described above, wherein preferably the hook comprises: a transverse plate and two vertical plates; the lower edges of the two vertical plates are fixedly connected with the outer surface of the sub-level body/the outer surface of the three sub-levels, the two vertical plates are opposite, and a certain distance is reserved between the two vertical plates; the transverse plate is fixedly connected with the upper edges of the two vertical plates so as to form a hanging space with the two vertical plates.
The winged launch vehicle as described above wherein the side edges of the riser of one hanger opposite the riser of the other hanger are preferably tapered from top to bottom toward the other hanger.
An on-board transmission system comprising: a transporter, two hangers, and a winged airborne launch rocket as defined in any one of the foregoing; the upper ends of the two hanging frames are fixed to the belly of the conveyor, and the two hanging frames are right below the symmetrical axis of the conveyor; the lower hook of one hanger is hooked to one hook of the airborne launch rocket with the wing, and the lower hook of the other hanger is hooked to the other hook of the airborne launch rocket with the wing.
The onboard emission system as described above, wherein preferably the hooks of the hangers near the nose of the conveyor are directed forward and the hooks of the hangers near the tail of the conveyor are directed rearward.
Compared with the background art, the winged airborne launching rocket and the airborne launching system provided by the application can reduce the rocket launching cost and improve the rocket launching efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments described in the present application, and other drawings may be obtained according to these drawings for a person having ordinary skill in the art.
FIG. 1 is a perspective view of a winged airborne launch rocket provided in an embodiment of the present application;
FIG. 2 is an exploded view of a winged airborne launch rocket provided in an embodiment of the present application;
FIG. 3 is a perspective view of a sub-stage of a winged airborne launch rocket provided in accordance with an embodiment of the present application;
FIG. 4 is a perspective view of four sub-stages of a winged airborne launch rocket provided in an embodiment of the present application;
FIG. 5 is a perspective view of a hanger for a winged airborne launch rocket provided in an embodiment of the present application;
FIG. 6 is a schematic diagram I of an airborne transmission system provided by an embodiment of the application;
fig. 7 is a schematic diagram of an airborne transmitting system according to an embodiment of the present application.
Detailed Description
Embodiments of the present application are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. In addition, spatial relationship terms such as "upper", "lower", "left", "right", "front", "rear", and the like are used for convenience of description to explain a positional relationship between two components. The embodiments described below by referring to the drawings are illustrative only and are not to be construed as limiting the application.
As shown in fig. 1 and 2, the present application provides a winged airborne launch rocket 100, comprising: rocket body, main wing 113, and two hooks 190; the main wing 113 is in an axisymmetric plate shape, the part of the inner side surface of the main wing 113 positioned at the symmetric axis is fixedly connected with the outer surface of the rocket body, the tail edge of the main wing 113 is perpendicular to the axis of the rocket body, and the head edge of the main wing 113 gradually inclines from the symmetric axis to two sides towards the tail; two hooks 190 are fixed to the rocket body, and the two hooks 190 are aligned with the symmetry axis of the main wing 113, distributed in front of and behind the main wing, and are mounted on the carrier hanger when used for airborne launching.
On the basis, the rocket body comprises: a first sub-stage 110, a second sub-stage 120, a second sub-stage 130, a second third stage 140, a third sub-stage 150, a third fourth stage 160, a fourth sub-stage 170, and a fairing 180; the front end of the primary stage 110 is butt-fixed to the rear end of the secondary stage 120, the front end of the secondary stage 120 is butt-fixed to the rear end of the secondary stage 130, the front end of the secondary stage 130 is butt-fixed to the rear end of the secondary stage 140, the front end of the secondary stage 140 is butt-fixed to the rear end of the tertiary stage 150, the front end of the tertiary stage 150 is butt-fixed to the rear end of the tertiary-quaternary stage 160, the front end of the tertiary-quaternary stage 160 is butt-fixed to the rear end of the quaternary stage 170, and the rear end of the fairing 180 is butt-fixed to the front end of the quaternary stage 170.
As shown in fig. 3, a sub-stage 110 includes: a sub-level body 111, tail wing 112 and main wing 113; the part of the inner side surface of the main wing 113 positioned at the symmetrical axis is fixedly connected with the outer surface of the sub-level body 111, and the tail edge of the main wing 113 is perpendicular to the axis of the sub-level body 111; the tail wing 112 is fixedly connected to the outer surface of a sub-stage body 111, and the tail wing 112 is located behind the main wing 113, wherein the term "rear" refers to the direction toward the tail of the sub-stage body 111.
Optionally, a trailing edge flap is installed at the tail edge of the main wing 113, and a steering engine is arranged in the main wing 113, and the action of the trailing edge flap is controlled through the steering engine, so that the pitching attitude of the airborne rocket with wings is controlled. Still alternatively, a trailing edge flap is also mounted at the tail edge of the tail wing 112, and a steering engine is also disposed in the tail wing 112, and the steering engine controls the action of the trailing edge flap, so as to control the attitude of the airborne rocket with wings.
The primary solid rocket motor is arranged in the primary stage body 111, the secondary solid rocket motor is arranged in the secondary stage 130, the tertiary solid rocket motor is arranged in the tertiary stage 150, and the payload of the rocket is arranged in the fairing 180. As shown in fig. 4, the four sub-stages 170 include: a casing section 171, a four-stage solid rocket motor 172, rocket control instruments 173, and a plurality of attitude control motors 174; a four-stage solid rocket motor 172 is fixed into the casing section 171 and is located at an intermediate position within the casing section 171; rocket control instrument 173 is fixed in shell section 171 and is positioned between four-stage solid rocket engine 172 and shell section 171, mainly being the electrical control hardware of the rocket, mainly controlling the flight program and attitude control of the rocket, issuing of separation instructions, etc.; a plurality of attitude control engines 174 are secured to the outer surface of the casing section 171 for controlling the final orbital accuracy and satellite attitude of the rocket after separation of the first 110, second 130 and third 150 sub-stages.
Alternatively, a plurality of the pilot motors 174 are evenly distributed over the same circumference of the casing section 171. Alternatively, a plurality of control motors 174 are distributed to the housing section 171 on a circumference near the front end. Still alternatively, the four sub-stages 170 include: four attitude control engines 174.
As shown in fig. 1 and 2, one hanger 190 is fixed to one sub-stage body 111 and the other hanger 190 is fixed to the outer surface of the three sub-stages 150. Alternatively, as shown in fig. 5, the hook 190 includes: a transverse plate 191 and two vertical plates 192; the lower edges of the two vertical plates 192 are fixedly connected with the outer surface of the sub-level body 111/the third sub-level 150, the two vertical plates 192 are opposite, a certain distance is provided between the two vertical plates 192, and the transverse plate 191 is fixedly connected with the upper edges of the two vertical plates 192, so that the two vertical plates 192 and the transverse plate 191 enclose a hanging space, which is that the "upper" refers to the direction away from the sub-level body 111 and the third sub-level 150, and the "lower" refers to the direction close to the sub-level body 111 and the third sub-level 150. Still alternatively, the side edges of the riser 192 of one hanger 190 opposite the riser 192 of the other hanger 190 are gradually inclined from top to bottom toward the other hanger 190. Specifically, the two vertical plates 192 of the hooks 190 on the one sub-stage body 111 are inclined gradually from top to bottom toward the hooks 190 on the three sub-stages 150 at the opposite side edges of the hooks 190 on the three sub-stages 150; the two risers 192 of the hooks 190 on the three sub-stages 150 are inclined gradually from top to bottom toward the hooks 190 on the one sub-stage body 111 at the side edges opposite to the hooks 190 on the one sub-stage body 111.
As shown in fig. 6 and 7, the present application provides an airborne transmitting system comprising: a transporter 200, the winged onboard launch rocket 100, and two hangers (not shown); wherein, the upper ends of the two hangers are fixed to the belly of the conveyor 200, and the two hangers are right below the symmetry axis of the conveyor 200, thereby being beneficial to ensuring the flight stability of the conveyor 200; and a lower hook of one pylon is hooked to one hook 190 of the winged on-board launch rocket 100, and a lower hook of the other pylon is hooked to the other hook 190 of the winged on-board launch rocket 100. Alternatively, the hooks of the hangers near the nose of the transporter 200 are forward facing and the hooks of the hangers near the tail of the transporter 200 are rearward facing, thereby facilitating hooking onto the hooks 190 of the winged on-board launch rocket 100. Alternatively, the hooks of the hanger near the nose of the transporter 200 are hooked to the hooks 190 of the three sub-stages 150 of the winged on-board launch rocket 100, and the hooks of the hanger near the tail of the transporter 200 are hooked to the hooks 190 of the one sub-stage body 111 of the winged on-board launch rocket 100, thereby facilitating the provision of an initial launch speed for the winged on-board launch rocket 100. Still alternatively, the on-board transmitting system further includes: a hook separating mechanism; the hook separation mechanism is used to separate the hook 190 of the winged on-board launch rocket 100 from the pylon, for example: and (5) initiating explosive devices.
During rocket launching, the winged onboard launch rocket 100 is fixed on a hanger of the belly of the transporter 200 by using the hanging hook 190, the transporter 200 takes off the winged onboard launch rocket 100 carried by an airport, the winged onboard launch rocket 100 carried by the transporter 200 reaches a launching airspace, and after reaching a preset height and speed, the hanging hook 190 of the winged onboard launch rocket 100 is separated from the hanger, so that the winged onboard launch rocket 100 is separated from the transporter 200, then the winged onboard launch rocket 100 inertially flies under the control of the tail wing 112 and the main wing 113, each sub-stage of the winged onboard launch rocket 100 is successively ignited after flying to the preset height, and a payload is sent into a preset orbit, wherein 6 times of separation are carried out during the flight of the winged onboard launch rocket 100, and the method comprises the following steps: separation of winged airborne launch rocket 100 from transporter 200, separation of primary and secondary stages 110 and 130, separation of fairing 180, separation of secondary and tertiary stages 130 and 150, separation of tertiary and quaternary stages 150 and 170, and separation of a satellite and an arrow.
The winged onboard launch rocket 100 in the application reaches a certain height and speed when being ignited, so the propellant required to be carried by the winged onboard launch rocket 100 can be greatly reduced, thereby improving the quality of effective load, and the launching of the winged onboard launch rocket 100 in the application is not limited by a fixed launching field any more, and the winged onboard launch rocket can be carried by a conveyor from any airport to take off, thereby improving the launching efficiency.
It will be evident to those skilled in the art that the application is not limited to the details of the foregoing illustrative embodiments, and that the present application may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are, therefore, to be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present disclosure describes embodiments, not every embodiment is provided with a separate embodiment, and that this description is provided for clarity only, and that the disclosure is not limited to the embodiments described in detail below, and that the embodiments described in the examples may be combined as appropriate to form other embodiments that will be apparent to those skilled in the art.
Claims (10)
1. An airborne launch rocket with wings, comprising: the rocket comprises a rocket body, a main wing and two hooks;
the main wing is in an axisymmetric platy shape, the part of the inner side surface of the main wing, which is positioned at the symmetric axis, is fixedly connected with the outer surface of the rocket body, the tail edge of the main wing is perpendicular to the axis of the rocket body, and the head edge of the main wing gradually inclines from the symmetric axis to two sides to the tail;
the two hooks are fixed on the rocket body, are in a straight line with the symmetry axis of the main wing, are distributed on the front and back of the main wing, and are used for being mounted on a carrier hanger during airborne launching.
2. A winged onboard launch rocket according to claim 1, wherein the rocket body comprises: a first sub-stage, a second three-stage, a third sub-stage, a third four-stage, a fourth sub-stage and a fairing;
wherein the front end of the first sub-stage is in butt joint with the rear end of the second sub-stage, the front end of the second sub-stage is in butt joint with the rear end of the second three-stage, the front end of the second-level interstage section is in butt joint with the rear end of the third sub-level, the front end of the third sub-level is in butt joint with the rear end of the third-level interstage section, the front end of the third-level interstage section is in butt joint with the rear end of the fourth sub-level, and the rear end of the fairing is in butt joint with the front end of the fourth sub-level.
3. A winged onboard launch rocket according to claim 2, wherein a sub-stage comprises: a sub-level body, tail wing and main wing;
the part of the inner side surface of the main wing, which is positioned at the symmetrical axis, is fixedly connected with the outer surface of a sub-level body, and the tail edge of the main wing is vertical to the axis of the sub-level body;
the fin is fixedly connected with the outer surface of a sub-level body, and the fin is positioned behind the main wing.
4. A winged airborne launch rocket according to claim 3, wherein trailing edge flaps are mounted at the tail edges of the main wings, and steering engines are arranged in the main wings, and the action of the trailing edge flaps is controlled through the steering engines;
the tail edge of the tail wing is also provided with a trailing edge flap, and a steering engine is arranged in the tail wing and used for controlling the action of the trailing edge flap.
5. A winged onboard launch rocket according to any one of claims 2 to 4, wherein the four sub-stages comprise: the device comprises a shell section, a four-stage solid rocket engine, a rocket control instrument and a plurality of attitude control engines;
a four-stage solid rocket engine is fixed into the shell section and is positioned at an intermediate position in the shell section; the rocket control instrument is fixed into the shell section and is positioned between the four-stage solid rocket engine and the shell section; a plurality of attitude control engines are secured to the outer surface of the housing section.
6. A winged airborne launch rocket according to claim 3 or 4, wherein one hook is fixed to a sub-stage body and the other hook is fixed to the outer surface of the three sub-stages.
7. The winged onboard launch rocket according to claim 6, wherein the hook comprises: a transverse plate and two vertical plates;
the lower edges of the two vertical plates are fixedly connected with the outer surface of the sub-level body/the outer surface of the three sub-levels, the two vertical plates are opposite, and a certain distance is reserved between the two vertical plates;
the transverse plate is fixedly connected with the upper edges of the two vertical plates so as to form a hanging space with the two vertical plates.
8. A winged airborne rocket according to claim 7 wherein the side edges of the riser of one hanger opposite the riser of the other hanger are progressively inclined from top to bottom toward the other hanger.
9. An on-board transmission system, comprising: a transporter, two pylons and a winged on-board launch rocket according to any one of claims 1 to 8;
the upper ends of the two hanging frames are fixed to the belly of the conveyor, and the two hanging frames are right below the symmetrical axis of the conveyor;
the lower hook of one hanger is hooked to one hook of the airborne launch rocket with the wing, and the lower hook of the other hanger is hooked to the other hook of the airborne launch rocket with the wing.
10. The on-board launch system of claim 9 wherein the hooks of the hangers near the nose of the conveyor are forward facing and the hooks of the hangers near the tail of the conveyor are rearward facing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311428002.6A CN117232343A (en) | 2023-10-30 | 2023-10-30 | Airborne launching rocket with wings and airborne launching system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311428002.6A CN117232343A (en) | 2023-10-30 | 2023-10-30 | Airborne launching rocket with wings and airborne launching system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117232343A true CN117232343A (en) | 2023-12-15 |
Family
ID=89088199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311428002.6A Pending CN117232343A (en) | 2023-10-30 | 2023-10-30 | Airborne launching rocket with wings and airborne launching system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117232343A (en) |
-
2023
- 2023-10-30 CN CN202311428002.6A patent/CN117232343A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8528853B2 (en) | In-line staged horizontal takeoff and landing space plane | |
| US8925857B2 (en) | In-line staged horizontal takeoff vehicles and related methods | |
| US9079661B2 (en) | Ultra-rapid air vehicle and related method for aerial locomotion | |
| EP2738092B1 (en) | System and method for minimizing wave drag through bilaterally asymmetric design | |
| US5402965A (en) | Reusable flyback satellite | |
| US7234667B1 (en) | Modular aerospace plane | |
| US9527597B1 (en) | Unmanned aerial vehicle with twin-engine fore/AFT configuration and associated systems and methods | |
| US8403254B2 (en) | Aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles | |
| US6616092B1 (en) | Reusable flyback rocket booster and method for recovering same | |
| JPH03500038A (en) | A rocket-propelled, airborne, lift-assisted booster vehicle for orbital, superorbital, and low-orbit flight. | |
| US6817580B2 (en) | System and method for return and landing of launch vehicle booster stage | |
| JP2003512254A (en) | First stage reusable booster for rocket | |
| US7240878B2 (en) | High wing monoplane aerospace plane based fighter | |
| US20090179106A1 (en) | Non-powered, aero-assisted pre-stage for ballistic rockets and aero-assisted flight vehicles | |
| CN117232343A (en) | Airborne launching rocket with wings and airborne launching system | |
| US9522727B2 (en) | Bilaterally asymmetric design for minimizing wave drag | |
| US10815010B2 (en) | High altitude air launched rocket | |
| CN113232854B (en) | Distributed unmanned aerial vehicle platform applied to ballistic launching and launching method | |
| US20220315250A1 (en) | Space aircraft with optimised design and architecture | |
| US20220411108A1 (en) | Rocket bundled with a small flighting system | |
| Fujiwara et al. | Flight plan and flight test results of experimental SST vehicle NEXST-1 | |
| RU2812634C1 (en) | Small unmanned aerial vehicle | |
| RU2769000C1 (en) | Multi-element rocket and aviation complex | |
| RU2778159C1 (en) | Attack weapon aviation complex | |
| RU184666U1 (en) | Unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |