CN112357095A - Aircraft system based on missile power propulsion - Google Patents
Aircraft system based on missile power propulsion Download PDFInfo
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- CN112357095A CN112357095A CN202011427484.XA CN202011427484A CN112357095A CN 112357095 A CN112357095 A CN 112357095A CN 202011427484 A CN202011427484 A CN 202011427484A CN 112357095 A CN112357095 A CN 112357095A
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- flight control
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 64
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 230000001965 increasing effect Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses an aircraft system based on missile power propulsion, wherein a missile power propulsion aircraft comprises an aircraft body, wings, an aircraft flight control system in the aircraft body, a missile power system, a missile flight control system and a switcher. When the airplane flight control network of the airplane flight control system is connected with the missile power system, the whole system works in a missile power propulsion state when the airplane flight control network of the airplane flight control system is connected to the missile power system; the aircraft flight control system controls the power of the guided missiles, the power of the guided missiles is utilized to help the aircraft to rapidly take off, and when the power of the aircraft breaks down, the power of the guided missiles can help the aircraft to maintain the flight height in an emergency mode. The invention helps the airplane to realize power backup through the reuse of the thrust of the missile, and helps the airplane to be separated from a dangerous stall state when the main engine of the airplane fails, thereby realizing the idea of the reuse of the power of the missile.
Description
Technical Field
The invention relates to the technical field of missile propulsion, in particular to an aircraft system based on missile power propulsion.
Background
The plane with striking ability is hung with a missile on the wing or the belly, and the missile is generally powered. At present, however, the power of the missile is generally started only when the missile is launched, and the power is not helpful for the takeoff and the flight of an airplane. For an aircraft, the missile influences the aerodynamic drag, and both the endurance and the speed increase of the aircraft are negatively influenced. In addition, the aircraft taking off by using the rocket boosting technology is utilized, the rocket engine is bound on the aircraft body of the aircraft, the rocket engine is started simultaneously when the aircraft takes off, and under the boosting of the rocket engine, the aircraft can accelerate at the fastest speed, so that the takeoff and running distance is shortened. However, these booster rockets are all special rockets and are discarded after the takeoff is finished. The technology of boosting the flight of an airplane by adopting the power on a missile has not been applied.
Disclosure of Invention
Based on the technical problems in the background art, the missile power propulsion-based aircraft system provided by the invention helps an aircraft to realize shorter take-off and landing distances through the reuse of the thrust of missiles. On one hand, the airplane is helped to realize power backup through the reuse of the thrust of the missile, and when the main engine of the airplane breaks down, the airplane is helped to be separated from a dangerous stall state; and on the other hand, the aircraft flight control system is used for connecting and controlling a missile power system, so that the missile power multiplexing idea is realized.
The missile power propulsion aircraft comprises an aircraft body, wings, an aircraft flight control system in the aircraft body, a missile power system, a missile flight control system and a switcher; the wings are arranged on two sides of the fuselage, and the missile is arranged on the wings or the fuselage; the missile is fixed on the wing and the multiple rotors in a mounting working mode.
Furthermore, the missile mounting work mode has two kinds, one mode is fixed wing unmanned aerial vehicle mounting work, and the missile passes through the stores pylon and the connector direct mount on the wing. Another mounting working mode of the missile is multi-rotor unmanned aerial vehicle mounting work, and the missile is installed on the multi-rotor through a hanger and a connector.
Further, the switch is connected with the aircraft flight control system through a switching network and an aircraft flight control power control network.
Furthermore, the switcher is respectively connected with an airplane flight power control network of an airplane flight control system and a missile flight power control network of a missile flight control system, and the switcher is connected with the missile power system through a missile power network; the switch selects the network-connected missile power system according to a switching network given by the airplane flight control system.
Furthermore, an airplane flight force control network of the airplane flight control system is connected with a missile power system, and when the airplane flight force control network of the airplane flight control system is connected to the missile power system, the whole system works in a missile power propulsion state; the aircraft flight control system controls the power of the missile.
Furthermore, the missile flight control system is connected with a missile power system through a switcher on one hand, and the missile flight control system is connected into the missile power system through a missile flight power control network on the other hand.
Further, the switch controls network connection of the switching network, the airplane flight power control network, the missile power network and the missile flight power control network.
Compared with the prior art, the invention has the following beneficial effects.
1. The interior of the airplane body of the invention consists of an airplane flight control system, a missile power system, a missile flight control system and a switcher, and the airplane is helped to realize shorter take-off and landing distances by multiplexing the thrust of the missiles. On one hand, the airplane is helped to realize power backup through the reuse of the thrust of the missile, and when the main engine of the airplane breaks down, the airplane is helped to be separated from a dangerous stall state; and on the other hand, the aircraft flight control system is used for connecting and controlling a missile power system, so that the missile power multiplexing idea is realized.
2. On the premise of not increasing the weight and the cost of the system, the power reserve and the redundancy of the whole aircraft are increased; the take-off and landing distance of the fixed-wing aircraft is shortened, and the emergency handling capacity of the aircraft is improved. For a rotary wing aircraft, the invention can help the rotary wing aircraft to realize larger flat flight speed and longer air-braking time. The method has small influence on the original missile system, low implementation cost, small influence on the structure of the airplane and low implementation cost.
Drawings
FIG. 1 is a schematic structural diagram of a missile power propulsion-based aircraft system provided by the invention;
FIG. 2 is a schematic illustration of missile installation of an aircraft system based on missile power propulsion according to the present invention;
FIG. 3 is a schematic view of the mounting work of a fixed-wing UAV (unmanned aerial vehicle) of an aircraft system based on missile power propulsion provided by the invention;
fig. 4 is a schematic view of the mounting work of a multi-rotor unmanned aerial vehicle of an aircraft system based on missile power propulsion provided by the invention.
Wherein: 100. fuselage, 101, wing, 101-1, multi-rotor, 102, missile, 103, pylon, 104, connector, 110, aircraft flight control system, 111, flight power control network, 112, switching network, 120, missile power system, 121, missile power network, 130, missile flight control system, 131, missile flight power control network, 140, switch.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 1, 2, 3 and 4, the invention provides a missile power propulsion-based aircraft system, which is composed of a fuselage 100, wings 101, an aircraft flight control system 110 inside the fuselage 100, a missile power system 120, a missile flight control system 130 and a switch 140; the wings 101 are arranged on two sides of the fuselage 100, and the missiles 102 are arranged on the wings 101 or the fuselage 100; the missile 102 is fixed on the wing 101 and the multi-rotor 101-1 in a mounting working mode.
Referring to fig. 3, the missile 102 is mounted in two modes, one mode is fixed-wing drone mounting, and the missile 102 is directly mounted on the wing 101 through a hanger 103 and a connector 104.
Referring to fig. 4, another mounting operation mode of the missile 102 is that of a multi-rotor unmanned aerial vehicle, and the missile 1025 is mounted on a multi-rotor 101-1 through a hanger 103 and a connector 104. The aircraft flight control system 110, the missile power system 120, the missile flight control system 130 and the switch 140 are cooperative with each other, and the switch 140 is used for controlling network input and output of the switching network 112, the aircraft flight power control network 111, the missile power network 121 and the missile flight power control network 131, so that independent work and mutual interference among the networks are realized. The aircraft flight control system 110 is a combination of flight automatic control subsystems with various functions on the aircraft, and can be used for ensuring the stability and maneuverability of the aircraft, improving the task completion capability and flight quality, enhancing the flight safety and lightening the burden of a driver; under various interference conditions, the missile power system 120 and the missile flight control system 130 stabilize the attitude of the missile 102, ensure that the deviation of the flight attitude angle of the missile 102 is within an allowable range, control the attitude angle of the missile according to a guidance instruction, adjust the flight direction of the missile 102, correct the flight path and enable the missile 102 to accurately hit a target.
The switch 140 is coupled to the aircraft flight control system 110 via the switching network 112 and the aircraft flight control network 111. The internal operation, power conversion and flight of the aircraft and control of the missile 102 are achieved by a switching network 112 and an aircraft flight power control network 111 that receive the aircraft flight control system 110.
The switch 140 is respectively connected with the airplane flight force control network 111 of the airplane flight control system 110 and the missile flight force control network 131 of the missile flight control system 120, and the switch 140 is connected with the missile power system 120 through the missile power network 121; the switch 140 selects the on-network missile power system 120 based on the switching network 112 provided by the aircraft flight control system 110. In operation, the switch 140 may respectively send the airplane flight control network 111 and the guided missile flight control network 131 sent by the airplane flight control system 110 and the guided missile flight control system 120 to the guided missile power system 120 via the guided missile power network 121.
Referring to fig. 1, the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120, and when the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120, the whole system works in the power propulsion state of the missile 102; the aircraft flight control system 110 controls the power of the guided missiles, the power of the guided missiles 102 is utilized to help the aircraft to take off quickly, and when the power of the aircraft per se fails, the power of the guided missiles 102 can help the aircraft to maintain the flying height in an emergency mode.
The missile flight control system 130 is connected with the missile power system 120 through a switch 140, when the missile flight control system 130 is connected into the missile power system 120 through a missile flight power control network 131, the whole system works in a missile autonomous flight mode, and at the moment, a missile is launched and is not connected with an airplane any more.
The switch 140 controls the network connection of the switching network 112, the airplane flight force control network 111, the missile power network 121 and the missile flight force control network 131, and the switch 140 realizes the network signal input and output of the switching network 112, the airplane flight force control network 111, the missile power network 121 and the missile flight force control network 131.
The power source of the missile 102 comprises solid fuel and liquid fuel, and also comprises power of a motor, an engine and the like. The missile 102 has wide power source distribution, on one hand, the wide and rich power source channel of the missile 102 is realized, and on the other hand, the foundation is provided for realizing the power diversification.
The invention provides a missile power propulsion-based airplane system, which consists of a fuselage 100, wings 101, an airplane flight control system 110 inside the fuselage 100, a missile power system 120, a missile flight control system 130 and a switch 140. When the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120 during operation, the whole system works in a missile power propulsion state; the aircraft flight control system 110 controls the power of the guided missiles, the power of the guided missiles 102 is utilized to help the aircraft to take off quickly, and when the power of the aircraft per se fails, the power of the guided missiles 102 can help the aircraft to maintain the flying height in an emergency mode. The invention solves the problem that the power of the missile is generally started only when the missile 102 is launched, which is not helpful for the takeoff and the flight of the airplane, and in addition, the power of the missile 102 is used, when the airplane takes off, under the boosting of the missile 102, the airplane can accelerate at the fastest speed, thereby shortening the takeoff and running distance. The missile 102 is directly installed on the wing 101 or the fuselage 100 through the pylon 103 and the connector 104, and when the missile 102 is used, the missile 102 is mounted in two modes, wherein one mode is the mounting work of a fixed-wing unmanned aerial vehicle, and the other mode is the mounting work of a multi-rotor unmanned aerial vehicle. The two mounting working modes can fully meet different working requirements.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (8)
1. The missile power propulsion-based airplane system is characterized in that the missile power propulsion-based airplane consists of a fuselage (100), wings (101), an airplane flight control system (110) inside the fuselage (100), a missile power system (120), a missile flight control system (130) and a switcher (140); the wings (101) are arranged on two sides of the fuselage (100), and the missiles (102) are arranged on the wings (101) or the fuselage (100); the missile (102) is fixed on the wing (101) and the multiple rotors (101-1) in a mounting working mode.
2. The missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile (102) is mounted in a fixed wing unmanned aerial vehicle mode, and the missile (102) is directly mounted on the wing (101) through a hanging frame (103) and a connector (104).
3. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile (102) is mounted in a mode of multi-rotor unmanned aerial vehicle mounting work, and the missile (102) is mounted on a multi-rotor (101-1) through a hanging rack (103) and a connector (104).
4. A missile-based power propulsion aircraft system as claimed in claim 1 wherein the switch (140) is connected to the aircraft flight control system (110) via a switching network (112) and an aircraft flight power control network (111).
5. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the switch (140) is connected with an aircraft flight power control network (111) of the aircraft flight control system (110) and a missile flight power control network (131) of the missile flight control system (120), respectively, and the switch (140) is connected with the missile power system (120) through a missile power network (121); the switch (140) selects the network-connected missile power system (120) according to a switching network (112) given by the aircraft flight control system (110).
6. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the aircraft flight power control network (111) of the aircraft flight control system (110) is connected with the missile power system (120), and when the aircraft flight power control network (111) of the aircraft flight control system (110) is connected with the missile power system (120), the whole system works in the missile (102) power propulsion state; an aircraft flight control system (110) controls the power of the missile.
7. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile flight control system (130) is connected to the missile power system (120) through a switch (140) on the one hand, and the missile flight control system (130) is connected to the missile power system (120) through a missile flight power control network (131) on the other hand.
8. A missile power propulsion-based aircraft system as claimed in claim 1 wherein the switch (140) controls the network connections of the switch network (112), the aircraft flight power control network (111), the missile power network (121) and the missile flight power control network (131).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011427484.XA CN112357095A (en) | 2020-12-09 | 2020-12-09 | Aircraft system based on missile power propulsion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011427484.XA CN112357095A (en) | 2020-12-09 | 2020-12-09 | Aircraft system based on missile power propulsion |
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| Publication Number | Publication Date |
|---|---|
| CN112357095A true CN112357095A (en) | 2021-02-12 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011427484.XA Pending CN112357095A (en) | 2020-12-09 | 2020-12-09 | Aircraft system based on missile power propulsion |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB760153A (en) * | 1953-04-24 | 1956-10-31 | Sncaso | Improvements in auxiliary reaction-propulsion units for aircraft |
| DE1224156B (en) * | 1964-06-23 | 1966-09-01 | Ver Flugtechnische Werke Ges M | Airplane with missiles |
| DE2428402A1 (en) * | 1974-06-12 | 1976-01-02 | Dornier Gmbh | Rocket launcher on an aircraft - has air flow stabilising deflector on firing rocket in opposite direction to flight |
| CN1281409A (en) * | 1997-12-10 | 2001-01-24 | 佛朗哥·卡潘纳 | System to transform horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane |
| US20180319486A1 (en) * | 2015-10-13 | 2018-11-08 | Newrocket Ltd. | Thrusting rockets for enhancing emergency autorotation |
| CN214029165U (en) * | 2020-12-09 | 2021-08-24 | 西安忠林世纪电子科技有限公司 | Aircraft system based on missile power propulsion |
-
2020
- 2020-12-09 CN CN202011427484.XA patent/CN112357095A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB760153A (en) * | 1953-04-24 | 1956-10-31 | Sncaso | Improvements in auxiliary reaction-propulsion units for aircraft |
| DE1224156B (en) * | 1964-06-23 | 1966-09-01 | Ver Flugtechnische Werke Ges M | Airplane with missiles |
| DE2428402A1 (en) * | 1974-06-12 | 1976-01-02 | Dornier Gmbh | Rocket launcher on an aircraft - has air flow stabilising deflector on firing rocket in opposite direction to flight |
| CN1281409A (en) * | 1997-12-10 | 2001-01-24 | 佛朗哥·卡潘纳 | System to transform horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane |
| US20180319486A1 (en) * | 2015-10-13 | 2018-11-08 | Newrocket Ltd. | Thrusting rockets for enhancing emergency autorotation |
| CN214029165U (en) * | 2020-12-09 | 2021-08-24 | 西安忠林世纪电子科技有限公司 | Aircraft system based on missile power propulsion |
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