CN111791788A - Rocket mobile launching vehicle - Google Patents
Rocket mobile launching vehicle Download PDFInfo
- Publication number
- CN111791788A CN111791788A CN202010684805.8A CN202010684805A CN111791788A CN 111791788 A CN111791788 A CN 111791788A CN 202010684805 A CN202010684805 A CN 202010684805A CN 111791788 A CN111791788 A CN 111791788A
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- Prior art keywords
- cabin
- rocket
- chassis
- heat preservation
- launching
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
- B60P3/40—Vehicles adapted to transport, to carry or to comprise special loads or objects for carrying long loads, e.g. with separate wheeled load supporting elements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P3/00—Vehicles adapted to transport, to carry or to comprise special loads or objects
- B60P3/42—Vehicles adapted to transport, to carry or to comprise special loads or objects convertible from one use to a different one
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60P—VEHICLES ADAPTED FOR LOAD TRANSPORTATION OR TO TRANSPORT, TO CARRY, OR TO COMPRISE SPECIAL LOADS OR OBJECTS
- B60P7/00—Securing or covering of load on vehicles
- B60P7/06—Securing of load
- B60P7/135—Securing or supporting by load bracing means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60S—SERVICING, CLEANING, REPAIRING, SUPPORTING, LIFTING, OR MANOEUVRING OF VEHICLES, NOT OTHERWISE PROVIDED FOR
- B60S9/00—Ground-engaging vehicle fittings for supporting, lifting, or manoeuvring the vehicle, wholly or in part, e.g. built-in jacks
- B60S9/02—Ground-engaging vehicle fittings for supporting, lifting, or manoeuvring the vehicle, wholly or in part, e.g. built-in jacks for only lifting or supporting
- B60S9/10—Ground-engaging vehicle fittings for supporting, lifting, or manoeuvring the vehicle, wholly or in part, e.g. built-in jacks for only lifting or supporting by fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
Abstract
The invention discloses a rocket mobile launching vehicle, which comprises a tractor, a chassis, a heat preservation cabin, a erecting system, a launching platform, a temperature regulating system, a hydraulic system, a vehicle control system and a power supply system, wherein the tractor is provided with a traction seat, the traction seat is connected with the chassis through a traction pin, the heat preservation cabin is fixedly arranged on the chassis, the erecting system is hinged at the rear end of the chassis, the launching platform is hinged at the rear end of the chassis and is coaxial with the erecting system, the temperature regulating system is arranged in front of and inside the heat preservation cabin, the hydraulic system is arranged below the chassis, the vehicle control system is arranged inside the heat preservation cabin, an operation panel is positioned outside the side wall of the heat preservation cabin, and the power supply system is arranged in the front of the chassis and inside the heat preservation cabin. The invention has the advantages of ingenious conception and reasonable structural layout, greatly shortens the long-distance transportation time, ensures the stability in the transportation process, improves the shock absorption capacity, has good sealing performance, and simultaneously meets the requirements of erection and launching by the full-open design.
Description
Technical Field
The invention relates to the field of rocket transportation and launching, in particular to a rocket mobile launching vehicle.
Background
The United states air force originally proposes a concept of space quick response, which is mainly used for military emergency, when regional wars occur, a satellite is quickly assembled, and meanwhile, a matched quick carrier rocket can be launched to lift off the satellite in an emergency, so that the time from the moment that the combat requirements are put forward to the moment that the spacecraft is deployed is ensured to be only a few days or a few weeks. In order to realize space quick response, higher requirements are put on the launching efficiency of the rocket. A set of rocket mobile launching vehicle with the characteristics of low launching cost, short preparation period, few guarantee conditions, rapid integration, rapid orbit entry and the like is indispensable.
Most of the existing rocket mobile launching vehicles are of an integrated chassis structure, and the off-road performance is emphasized, so that the performances of the existing rocket mobile launching vehicles on a common road are poor, and the high-speed performance and the endurance mileage are both weaker than those of conventional vehicles.
Through development for many years, the construction of the road network is obviously developed and perfected, and the comprehensive capacity of road transportation is obviously improved. How to develop a rocket mobile launcher which integrates the functions of storage, transportation, erection and launching and is suitable for highway driving can obviously improve the transportation and launching efficiency of the rocket and better realize space quick response.
Disclosure of Invention
The invention aims to provide a rocket mobile launching vehicle which integrates the functions of storage, transportation, erection and launching and is suitable for highway driving, and the transportation and launching efficiency of a rocket is obviously improved.
In order to solve the technical problems, the invention adopts the following technical scheme:
the invention relates to a rocket mobile launching vehicle, which comprises a tractor, a chassis, a heat preservation cabin, a erecting system, a launching platform, a temperature adjusting system, a hydraulic system, a vehicle control system and a power supply system, the tractor is provided with a traction seat which is connected with the chassis through a traction pin, the heat preservation cabin is fixedly arranged on the chassis, the erecting system is hinged at the rear end of the chassis, the launching platform is hinged at the rear end of the chassis and is coaxial with the erecting system, the temperature adjusting system is arranged in front of and inside the heat preservation cabin, the hydraulic system is arranged below the chassis, the vehicle control system is installed in the heat preservation cabin, the operation panel is located outside the side wall of the heat preservation cabin, and the power supply system is installed on the front portion of the chassis and inside the heat preservation cabin.
Further, the chassis is specifically designed to be of a half-hanging structure, the chassis comprises a frame at the top, a walking system and a plurality of hydraulic support legs, the walking system is installed below the frame, the hydraulic support legs are installed at the bottom of the frame, the hydraulic support legs comprise two front support legs and two rear support legs, the two front support legs are formed by front support leg oil cylinders, and the two rear support legs are formed by rear support leg oil cylinders.
The heat preservation cabin comprises a fixed bottom plate, a left-right symmetrical cabin side plate, a front side plate, an openable top cover and an openable rear cover, wherein the bottom plate, the left-right symmetrical cabin side plate, the front side plate, the top cover and the rear cover are combined into a hollow square cabin, and a sealing structure is arranged at the closed position of the top cover and the rear cover.
Furthermore, the top cover comprises a cabin left top cover and a cabin right top cover, the cabin left top cover and the cabin right top cover are both connected to the top of the cabin side plate through hinges, telescopic cylinders are mounted on the inner side of the top of the cabin side plate, working rods of the telescopic cylinders are hinged to opposite surfaces of the cabin left top cover and the cabin right top cover, the telescopic cylinders are arranged in a bilateral symmetry mode, and at least two telescopic cylinders are arranged on each side; the rear cover comprises a left rear cover and a right rear cover, the left rear cover and the right rear cover are connected to the bottom plate through rotary cylinders, reinforcing plates are arranged at the bottoms of the left rear cover and the right rear cover, and the reinforcing plates are connected to the outer side surfaces of the left rear cover and the right rear cover through bolts.
Still further, seal structure includes bent angle piece and a plurality of sealing strip, the planking side of lid behind the right top cap of cabin or the cabin right side is connected to the one end of bent angle piece, the sealing strip includes the sealed strip of first sealing strip, second and third sealing strip, first sealing strip is connected the other end of bent angle piece with the side of lid is closely laminated behind the left top cap of cabin or the left side of cabin, second sealing strip and third sealing strip set up respectively on L type corner face.
Still further, the erecting system comprises an erecting frame, a rocket clamp, a rocket support and a launching platform locking pin, the erecting frame is horizontally placed on a bottom plate of the heat preservation cabin, the rocket clamp is connected to a cross beam in the middle of the top surface of the erecting frame, the rocket support is connected to a cross beam at the tail of the top surface of the erecting frame, and the launching platform locking pin is arranged on a hinged support at the tail of the top surface of the erecting frame.
Still further, the supporting surfaces of the rocket clamp and the rocket support are designed to be arc-shaped, and a soft cushion for protection is arranged on the surface of the arc-shaped supporting surface, wherein the soft cushion is made of rubber or polyurethane materials.
Still further, the launching pad with erect the system and be provided with locking mechanical system, locking mechanical system includes bolt hydro-cylinder, fitting pin and proximity switch, the bolt hydro-cylinder is installed erect on the frame, the fitting pin is installed on the jar pole of round pin hydro-cylinder, the fitting pin is the toper structure, through the action of bolt hydro-cylinder realize with the compressing tightly and the separation of the corresponding toper part of launching pad locking seat.
Still further, the launching pad comprises a launching pad metal frame, a launching pad locking base, a deflector, auxiliary legs and a rocket mounting adapter ring, wherein the launching pad locking base is connected to two sides of the launching pad metal frame, the deflector is mounted at the bottom in the launching pad metal frame, the rocket mounting adapter ring is mounted at the center of the top surface of the launching pad metal frame, and the auxiliary legs are arranged at two corners on one side far away from the connecting end; the front end of the launching platform metal frame is hinged to the rear part of the chassis, and the launching platform locking seat is connected with the launching platform locking pin in a positioning mode.
Still further, the temperature adjusting system comprises an air conditioner and a heater, the air conditioner is arranged at the front part of the outer side of the heat preservation cabin, and the heater is arranged in the heat preservation cabin; the power supply system comprises a generator set and a storage battery pack, wherein the generator set provides power for the whole vehicle, the generator set is installed at the front end of the chassis, and the storage battery pack is installed inside the heat-preservation cabin.
Compared with the prior art, the invention has the beneficial technical effects that:
the invention relates to a rocket mobile launching vehicle, which comprises a towing vehicle, a chassis, a heat preservation cabin, a erecting system, a launching platform, a temperature regulation system, a hydraulic system, a vehicle control system and a power supply system, wherein the towing vehicle is provided with a towing seat, the towing seat is connected with the chassis through a towing pin, the heat preservation cabin is fixedly arranged on the chassis, the erecting system is hinged at the rear end of the chassis, and the launching platform is hinged at the rear end of the chassis; the invention uses the traction vehicle head as the walking power to pull the modified chassis, so that the rocket launching vehicle can walk at high speed on various severe road conditions, and the long-distance transportation time is greatly shortened.
The mobile launching vehicle breaks through the conventional launching vehicle, improves the running speed and the economical efficiency of the whole vehicle under the condition of ensuring the integral trafficability, braking performance, climbing capacity and certain off-road type, has good vibration damping performance in the integral transportation process due to the fact that the running system of the vehicle is provided with air balance suspension, and improves the braking performance of the whole vehicle due to the fact that the running system has an air braking function. The design of rocket clamps and rocket supports in the erecting system ensures the stability in the transportation process, and the design of the cushion improves the shock absorption capacity.
According to the heat-insulation cabin of the mobile launch vehicle, the top cover and the rear cover can be completely opened, the top cover adopts the telescopic cylinder to automatically control and realizes the opening and closing operation of the top cover through the telescopic function, the operation is convenient, fast and light, and the sealing performance is good; the rotary cylinder is reliably connected with the left rear cabin cover and the right rear cabin cover, and meanwhile, the local strength of the left rear cabin cover and the right rear cabin cover is improved, and the deformation caused by rotation stress is prevented; the design of the sealing structure in the heat-insulating cabin has good heat-insulating and rainproof performance, can effectively protect the rocket projectile body, and is not influenced by environmental climate in the transportation process, and the applicability is strong. The automatic open-close design of the top cover and the rear cover meets the requirements of sealed heat-preservation transportation and erection launching operation of the rocket projectile. The invention can be combined with a hydraulic and electric control system and an electro-hydraulic leveling erecting control system, realizes the quick leveling and erecting of the space carrier, ensures the initial pose of the projectile body, meets the requirement of technical index precision, and ensures the realization of the overall launching target.
The invention has the advantages of ingenious conception and reasonable structural layout, adopts a combination form of a tractor and a trailer, greatly shortens the long-distance transportation time, ensures the stability in the transportation process due to the design of the rocket clamp and the rocket support in the erecting system, improves the shock absorption capacity due to the design of the soft cushion, has good sealing property for the heat-insulating cabin, and simultaneously meets the requirements of erecting and launching due to the fully-open design of the top cover and the rear cover. In addition, the mobile launching vehicle of the erecting device adopts a standard interface, can be adapted to tractors of various models, integrates the functions of storage, transportation, erecting and launching, has low cost and high automation degree compared with the traditional launching vehicle, and is suitable for high-speed transportation and launching of rockets on roads.
Drawings
The invention is further illustrated in the following description with reference to the drawings.
FIG. 1 is a schematic axial view of a rocket in storage and transportation state;
FIG. 2 is a schematic view of the rocket in a raised state;
FIG. 3 is a schematic diagram of a rocket in a state ready for launching in accordance with the present invention;
FIG. 4 is a schematic axial view of the chassis of the present invention;
FIG. 5 is a schematic view showing the top cover of the thermal insulation cabin of the present invention opened;
FIG. 6 is a schematic view showing the opening of the rear cover of the thermal insulation chamber according to the present invention;
FIG. 7 is a schematic view of a sealing structure of the thermal insulation chamber of the present invention;
FIG. 8 is a schematic axial view of the erecting system of the present invention;
FIG. 9 is a schematic axial view of a launch pad of the present invention;
FIG. 10 is a schematic view of the locking structure of the erecting system and the launching pad of the present invention;
FIG. 11 is a schematic diagram showing the state of the rocket and the erecting frame after the thermal insulation cabin, the air conditioning system and the power system are hidden in the invention;
description of reference numerals: 1. a tractor; 2. a chassis; 3. a heat preservation bin; 4. a erecting system; 5. a launch pad; 6. a temperature regulating system; 7. a hydraulic system; 8. a vehicle control system; 9. a power supply system; 10. erecting the oil cylinder;
201. a frame; 202. a traveling system; 203. a front support leg oil cylinder; 204. a rear supporting leg oil cylinder;
301. a left hatch cover; 302. a cabin right top cover; 303. a telescopic cylinder; 304. a hinge; 305. a cabin side plate; 306. A left rear hatch cover; 307. a right rear hatch cover; 308. a reinforcing plate; 309. a rotating cylinder;
401. erecting a frame; 402. rocket tongs; 403. a rocket support; 404. a launch pad locking pin; 405. a hinge hole of the vertical frame;
501. a launch pad metal mount; 502. a launching platform locking seat; 503. a fluid director; 504. an auxiliary leg; 505. Installing a switching ring on the rocket; 506. the launching platform is hinged with the hole;
4041. a bolt oil cylinder; 4042. a locking pin; 4043. a proximity switch.
Detailed Description
As shown in fig. 1-11, a rocket mobile launch vehicle provides interfaces and installation space for ground measurement, launch and control equipment, positioning and orientation equipment, a gas distribution system and the like; the device comprises a tractor 1, a chassis 2, a heat preservation cabin 3, a erecting system 4, a launching platform 5, a temperature regulating system 6, a hydraulic system 7, a vehicle control system 8 and a power supply system 9, wherein a traction seat is mounted on the tractor 1 and is connected with the chassis 2 through a traction pin to provide moving power for the whole vehicle; the heat preservation cabin 3 is fixedly installed on the chassis 2, the erecting system 4 is hinged to the rear end of the chassis 2, the launching platform 5 is hinged to the rear end of the chassis 2 and located outside the heat preservation cabin 3, the launching platform 5 is coaxial with the erecting system 4, the temperature regulating systems 6 are installed in front of and inside the heat preservation cabin 3, and the hydraulic system 7 is installed below the chassis 2 and provides power for all actions of the whole vehicle; the vehicle control system 8 is arranged inside the heat preservation cabin 3 and is responsible for the action control of the whole vehicle; the operation panel is positioned outside the side wall of the heat preservation cabin 3, and the power supply system 9 is arranged in the front of the chassis 2 and inside the heat preservation cabin 3. Specifically, the temperature adjustment system 6 includes an air conditioner and a heater, the air conditioner is installed at the front part of the outer side of the thermal insulation cabin 3, and the heater is installed inside the thermal insulation cabin 3. The power supply system 9 comprises a generator set and a storage battery pack, wherein the generator set provides power for the whole vehicle, the generator set is arranged at the front end of the chassis 2, and the storage battery pack is arranged in the heat preservation cabin 3.
As shown in fig. 4, the chassis 2 is specifically designed as a semitrailer, the chassis 2 includes a frame 201 at the top, a traveling system 202 and a plurality of hydraulic legs, the traveling system 202 is installed below the frame 201, the hydraulic legs are installed at the bottom of the frame 201, the hydraulic legs include two front legs and two rear legs, the two front legs are composed of a front leg cylinder 203, and the two rear legs are composed of a rear leg cylinder 204; the frame 201 is used for bearing and installing other parts of the whole vehicle, the four supporting leg oil cylinders are used for leveling the chassis before erecting, the walking system 202 is used for supporting and walking the chassis, and the walking system 202 comprises a suspension, an axle, tires, rims and a braking system and is powered and controlled by a tractor. Specifically, still include the driving pilot lamp on the chassis, for the safety of guaranteeing the walking provides the illumination prompt facility, the illumination during other operations.
As shown in fig. 5 and 6, the thermal insulation cabin 3 includes a fixed bottom plate, a left-right symmetric cabin side plate 305, a front side plate, an openable top cover, and an openable rear cover, the bottom plate, the left-right symmetric cabin side plate 305, the front side plate, the top cover, and the rear cover are combined into a hollow square cabin, and a sealing structure is arranged at the closed position of the top cover and the rear cover. Specifically, the top cover comprises a cabin left top cover 301 and a cabin right top cover 302, the cabin left top cover 301 and the cabin right top cover 302 are both connected to the top of the cabin side plate 305 through hinges 304, telescopic cylinders 303 are mounted on the inner side of the top of the cabin side plate 305, working rods of the telescopic cylinders 303 are hinged to opposite surfaces of the cabin left top cover 301 and the cabin right top cover 302, the telescopic cylinders 303 are arranged in a bilateral symmetry manner, and at least two telescopic cylinders are arranged on each side; the rear cover comprises a left rear cover 306 and a right rear cover 307, the left rear cover 306 and the right rear cover 307 are connected to the bottom plate through a rotating cylinder 309, reinforcing plates 308 are arranged at the bottoms of the left rear cover 306 and the right rear cover 307, and the reinforcing plates 308 are connected to the outer side surfaces of the left rear cover 306 and the right rear cover 307 through bolts. Specifically, the design that the top cover and the rear cover are automatically opened and closed meets the requirements of sealed heat-preservation transportation and erection launching operation of the rocket projectile.
As shown in fig. 7, the sealing structure includes a corner piece 310 and a plurality of sealing strips, one end of the corner piece 310 is connected to the outer plate side of the right cabin roof cover 302 or the right cabin rear cover 307, the sealing strips include a first sealing strip 311, a second sealing strip 312 and a third sealing strip 313, the first sealing strip 311 is connected to the other end of the corner piece 310 and closely attached to the side of the left cabin roof cover 301 or the left cabin rear cover 306, and the second sealing strip 312 and the third sealing strip 313 are respectively disposed on the L-shaped corner surfaces. Specifically, the design of the internal sealing structure of the heat-insulating cabin has good heat-insulating and rainproof performance, and can effectively protect the rocket projectile body from being influenced by environmental climate in the transportation process, so that the applicability is strong.
As shown in fig. 8 and 11, the erecting system 4 comprises an erecting frame 401, a rocket clamp 402, a rocket support 403 and a launching platform locking pin 404, the erecting frame 401 is horizontally placed on the bottom plate of the heat preservation cabin 3, a erecting frame hinge hole 405 is formed in the lower portion of the tail end of the erecting frame 401, and the lower portion of the tail end of the erecting frame 401 is embedded into a clamping groove in the tail portion of the chassis 2 and then penetrates through the erecting frame hinge hole 405 through a hinge shaft for positioning; the rocket clamp 402 is connected to a cross beam in the middle of the top surface of the erecting frame 401, the rocket support 403 is connected to a cross beam at the tail of the top surface of the erecting frame 401, and the launching platform locking pin 404 is arranged on a hinged support at the tail of the top surface of the erecting frame 401. The supporting surfaces of the rocket clamp 402 and the rocket support 403 are designed into an arc shape, and a protective cushion is mounted on the surface of the arc shape, and the cushion is made of rubber or polyurethane. The lifting oil cylinder structure is characterized by further comprising two lifting oil cylinders 10, wherein the two lifting oil cylinders 10 are symmetrically arranged on the chassis 2, working rods of the lifting oil cylinders 10 are hinged to a lifting frame 401, and the lower end of the tail of the lifting frame 401 is connected to the tail of the bottom plate 2 through a hinged shaft.
As shown in fig. 10, the launching pad 5 and the erecting system 4 are provided with a locking mechanism, the locking mechanism includes a latch cylinder 4041, a locking pin 4042 and a proximity switch 4043, the latch cylinder 4041 is installed on the erecting frame 4, the locking pin 4042 is installed on a rod of the latch cylinder 4041, the locking pin 4042 is a tapered structure, and the tapered portion corresponding to the launching pad locking seat 502 is pressed and separated by the action of the latch cylinder 4041.
As shown in fig. 9, the launching pad 5 includes a launching pad metal frame 501, a launching pad locking base 502, a deflector 503, an auxiliary leg 504 and a rocket mounting adapter ring 505, the launching pad locking base 502 is connected to both sides of the launching pad metal frame 501, the deflector 503 is mounted at the bottom inside the launching pad metal frame 501, the rocket mounting adapter ring 505 is mounted at the center of the top surface of the launching pad metal frame 501, and the auxiliary leg 504 is disposed at two corners on one side far from the connecting end; the bottom of the front end of the launch pad metal frame 501 is provided with a launch pad hinge hole 506, the bottom of the front end of the launch pad metal frame 501 is embedded into a clamping groove at the rear part of the chassis 2 and then penetrates through the launch pad hinge hole 506 for positioning through a hinge shaft, and the launch pad locking seat 502 is matched, positioned and connected with the launch pad locking pin 404.
The working process of the invention is as follows:
firstly, as shown in fig. 1, the specific working method of rocket storage and transportation is as follows:
1) starting up a generator set in the tractor 1, and starting up the hydraulic system 7;
2) adjusting the chassis 2, starting two front support leg oil cylinders 203 and two rear support leg oil cylinders 204 at the bottom to extend to the ground, and automatically leveling the frame 201 at the top of the chassis 2 under the control of the vehicle control system 8;
3) the top cover and the rear cover of the heat preservation cabin 3 are opened; the working rod of the telescopic cylinder 303 extends out to jack up and open the cabin left top cover 301 and the cabin right top cover 302, and the rotary cylinder 309 is started to drive the cabin left rear cover 306 and the cabin right rear cover 307 to rotate and open towards two sides;
4) operation of the erecting system 4: the clamping arms of the rocket clamp 402 are driven to open by the oil cylinders; at this time, the launching pad 5 is in a non-working state, the launching pad metal frame 501 is vertically placed, and the launching pad locking seat 502 is connected with the launching pad locking pin 404 of the erecting system 4 in a positioning manner;
5) hoisting a rocket; the rocket is horizontally placed and hoisted to the erecting system 4, the rocket is horizontally placed on the arc-shaped surfaces of the rocket clamp 402 and the rocket support 403 at the moment, the head of the rocket is inwards placed in the heat preservation cabin 3, and the tail of the rocket is embedded into the rocket mounting adapter ring 505 and is clamped and fixed;
6) closing rocket clamps of the erecting system; after the rocket clamp is placed at a designated position, the clamping arm of the rocket clamp 402 is driven to close through the oil cylinder to clamp the upper part of the rocket, and the tail part of the rocket is clamped and fixed through the rocket mounting adapter ring 505;
7) closing a top cover and a rear cover on the heat preservation cabin 3; the working rod of the telescopic cylinder 303 retracts to drive the cabin left top cover 301 and the cabin right top cover 302 to descend and close, and the rotary cylinder 309 rotates reversely to drive the cabin left rear cover 306 and the cabin right rear cover 307 to close;
8) starting the temperature adjusting system 6; according to a temperature sensor in the heat preservation cabin, an air conditioner and a heater are started to adjust the temperature in the heat preservation cabin 3;
9) four supporting leg oil cylinders on the chassis 2 retract; two front support leg oil cylinders 203 and two rear support leg oil cylinders 204 at the bottom retract away from the ground;
10) the hydraulic system 7 stops working and the generator set continues working.
And finally, the storage operation of the rocket is completed, and the transportation of the rocket can be carried out after the tractor is started.
Next, as shown in fig. 2 and 3, after the rocket is transported to a designated location, the specific method for launching the rocket in the vertical direction is as follows:
1) the generator set in the tractor is in a starting state, and the hydraulic system 7 works;
2) four supporting leg oil cylinders on the chassis 2 extend out, and the chassis is automatically leveled under the control of a vehicle control system;
3) the temperature adjusting system 6 stops working, and the air conditioner and the heater are closed to stop adjusting the temperature inside the heat preservation cabin 3;
4) the top cover and the rear cover of the heat preservation cabin 3 are opened again; the working rod of the telescopic cylinder 303 extends out to jack up and open the cabin left top cover 301 and the cabin right top cover 302, and the rotary cylinder 309 is started to drive the cabin left rear cover 306 and the cabin right rear cover 307 to rotate and open towards two sides;
5) the erecting system 4 works, as shown in fig. 2 and 11, the working rod of the erecting oil cylinder 10 extends to act, and the rocket starts to erect; when the rocket erects at 90 degrees, the erection stops, as shown in FIG. 4; in the erecting process, the launching platform locking seat 502 and the launching platform locking pin 404 are connected together in a positioning manner;
6) the launching platform 5 works, when the rocket is erected for 90 degrees, the launching platform metal frame 501 is horizontally placed, and the oil cylinders on the auxiliary supporting legs 504 work and extend out to be supported on the ground;
7) resetting the erecting system 4, firstly, retracting the locking pin 404 of the launching platform, and synchronously disconnecting the launching platform 5 and the erecting frame 401; secondly, the rocket clamp 402 on the erecting frame 401 is opened; finally, the working rod of the erecting oil cylinder 10 is recovered to drive the erecting frame 401 to fall back into the heat preservation cabin 3;
8) closing a top cover and a rear cover of the heat preservation cabin 3; the working rod of the telescopic cylinder 303 retracts to drive the cabin left top cover 301 and the cabin right top cover 302 to descend and close, and the rotary cylinder 309 rotates reversely to drive the cabin left rear cover 306 and the cabin right rear cover 307 to close;
9) carrying out final preparation work before rocket launching;
10) and (5) disconnecting the rocket fixing pull rod, and launching the rocket.
Wherein the steps 2, 3, 4 and 5 can be completed by one key.
Finally, a recovery working method of the launching vehicle after the rocket is launched is finished;
1) cleaning rocket launching residues;
2) opening the rear cover on the heat preservation cabin 3, starting the rotary cylinder 309 to drive the left rear cover 306 and the right rear cover 307 of the cabin to rotate towards two sides for opening;
3) the turning oil cylinder on the launching pad 5 acts to turn the launching pad 5 back, and a shaft of the launching pad metal frame 501 hinged with the chassis 2 is taken as a rotating shaft during rotation; specifically, one end of the overturning oil cylinder is connected with the chassis, the other end of the overturning oil cylinder is connected with the launching platform, the launching platform rotates around a shaft for connecting the launching platform and the chassis, the oil cylinder follows up when the launching platform is erected, and after the rocket is launched, the overturning oil cylinder acts independently to overturn the launching platform;
4) closing a rear cover on the heat preservation cabin 3; the rotating cylinder 309 rotates reversely to drive the left rear cabin cover 306 and the right rear cabin cover 307 to close;
5) the auxiliary supporting leg 504 on the launching platform 5 is retracted, and the oil cylinder on the auxiliary supporting leg 504 is retracted to drive the auxiliary supporting leg 504 to reset;
6) the supporting leg oil cylinders on the chassis 2 are retracted, and the two front supporting leg oil cylinders 203 and the two rear supporting leg oil cylinders 204 at the bottom are retracted to be far away from the ground;
7) the hydraulic system 7 stops working;
8) shutting down the generator set;
9) the tractor 1 is started to drive the chassis 2 and the set of systems thereon to drive away from the launch site.
In summary, the rocket mobile launching vehicle integrates the functions of storage, transportation, erection and launching, has low cost and high degree of automation compared with the traditional launching vehicle, and is suitable for highway high-speed transportation and launching of rockets.
The above-mentioned embodiments are only for describing the preferred mode of the present invention, and do not limit the scope of the present invention, and various modifications and improvements made to the technical solution of the present invention by those skilled in the art without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.
Claims (10)
1. A rocket mobile launch vehicle is characterized in that: the tractor comprises a tractor (1), a chassis (2), a heat preservation cabin (3), a vertical system (4), a transmitting platform (5), a temperature regulating system (6), a hydraulic system (7), a vehicle control system (8) and a power supply system (9), wherein the tractor (1) is provided with the traction seat, the traction seat is connected with the chassis (2) through a traction pin, the heat preservation cabin (3) is fixedly arranged on the chassis (2), the vertical system (4) is hinged at the rear end of the chassis (2), the transmitting platform (5) and the vertical system (4) are coaxial, the temperature regulating system (6) is arranged in the front and inside of the heat preservation cabin (3), the hydraulic system (7) is arranged below the chassis (2), and the vehicle control system (8) is arranged inside the heat preservation cabin (3), the operation panel is positioned outside the side wall of the heat preservation cabin (3), and the power supply system (9) is arranged in the front of the chassis (2) and inside the heat preservation cabin (3).
2. A rocket-moving launch vehicle according to claim 1 and wherein: chassis (2) specific design is half hanging the structure, chassis (2) include frame (201), traveling system (202) and a plurality of hydraulic leg at top, traveling system (202) are installed the below of frame (201), hydraulic leg installs the bottom of frame (201), hydraulic leg includes two preceding landing legs and two back landing legs, two preceding landing leg is constituteed through preceding landing leg hydro-cylinder (203), two back landing leg is constituteed through back landing leg hydro-cylinder (204).
3. A rocket-moving launch vehicle according to claim 1 and wherein: the heat preservation cabin (3) comprises a fixed bottom plate, bilateral cabin side plates (305), a front side plate, an openable top cover and an openable rear cover, wherein the bottom plate, the bilateral cabin side plates (305), the front side plate, the top cover and the rear cover are combined into a hollow square cabin, and a sealing structure is arranged at the closed position of the top cover and the rear cover.
4. A rocket-moving launch vehicle according to claim 3 and wherein: the top covers comprise a cabin left top cover (301) and a cabin right top cover (302), the cabin left top cover (301) and the cabin right top cover (302) are connected to the top of the cabin side plate (305) through hinges (304), telescopic cylinders (303) are installed on the inner side of the top of the cabin side plate (305), working rods of the telescopic cylinders (303) are hinged to opposite surfaces of the cabin left top cover (301) and the cabin right top cover (302), the telescopic cylinders (303) are arranged in a left-right symmetrical mode, and at least two telescopic cylinders are arranged on each side; the rear cover comprises a left rear cover (306) and a right rear cover (307), the left rear cover (306) and the right rear cover (307) are connected to the bottom plate through a rotating cylinder (309), reinforcing plates (308) are arranged at the bottoms of the left rear cover (306) and the right rear cover (307), and the reinforcing plates (308) are connected to the outer side faces of the left rear cover (306) and the right rear cover (307) through bolts.
5. A rocket-moving launch vehicle according to claim 3 and wherein: the sealing structure comprises a corner piece (310) and a plurality of sealing strips, one end of the corner piece (310) is connected to the side face of the outer plate of the right cabin top cover (302) or the right cabin rear cover (307), the sealing strips comprise a first sealing strip (311), a second sealing strip (312) and a third sealing strip (313), the first sealing strip (311) is connected to the other end of the corner piece (310) and the side face of the left cabin top cover (301) or the left cabin rear cover (306) is tightly attached to each other, and the second sealing strip (2) and the third sealing strip (13) are respectively arranged on an L-shaped corner face.
6. A rocket-moving launch vehicle according to claim 1 and wherein: the erecting system (4) comprises an erecting frame (401), a rocket clamp (402), a rocket support (403) and a launching platform locking pin (404), the erecting frame (401) is horizontally placed on a bottom plate of the heat preservation cabin (3), the rocket clamp (402) is connected to a cross beam in the middle of the top surface of the erecting frame (401), the rocket support (403) is connected to a cross beam at the tail of the top surface of the erecting frame (401), and the launching platform locking pin (404) is arranged on a hinged support at the tail of the top surface of the erecting frame (401).
7. A rocket-moving launch vehicle according to claim 6, wherein: the supporting surfaces of the rocket clamp (402) and the rocket support (403) are designed to be arc-shaped, and a protective cushion is arranged on the surface of the arc-shaped supporting surface, wherein the cushion is made of rubber or polyurethane.
8. A rocket-moving launch vehicle according to claim 6, wherein: launch pad (5) with it is provided with locking mechanical system to erect system (4), locking mechanical system includes bolt hydro-cylinder (4041), fitting pin (4042) and proximity switch (4043), install bolt hydro-cylinder (4041) erect on frame (4), fitting pin (4042) is installed on the jar pole of pin hydro-cylinder (4041), fitting pin (4042) are the toper structure, through bolt hydro-cylinder (4041) action realize with the compressing tightly and the separation of the corresponding toper part of launch pad locking seat (502).
9. A rocket-moving launch vehicle according to claim 6, wherein: the launching platform (5) comprises a launching platform metal frame (501), a launching platform locking seat (502), a fluid director (503), auxiliary supporting legs (504) and rocket mounting adapter rings (505), wherein the launching platform locking seat (502) is connected to two sides of the launching platform metal frame (501), the fluid director (503) is mounted at the bottom in the launching platform metal frame (501), the rocket mounting adapter rings (505) are mounted at the center of the top surface of the launching platform metal frame (501), and the auxiliary supporting legs (504) are arranged at two corners far away from one side of a connecting end; the front end of the launching pad metal frame (501) is hinged to the rear part of the chassis (2), and the launching pad locking seat (502) is connected with the launching pad locking pin (404) in a positioning mode.
10. A rocket-moving launch vehicle according to claim 1 and wherein: the temperature adjusting system (6) comprises an air conditioner and a heater, the air conditioner is arranged at the front part of the outer side of the heat preservation cabin (3), and the heater is arranged in the heat preservation cabin (3); the power supply system (9) comprises a generator set and a storage battery set, wherein the generator set provides power for the whole vehicle, the generator set is installed at the front end of the chassis (2), and the storage battery set is installed inside the heat preservation cabin (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010684805.8A CN111791788A (en) | 2020-07-16 | 2020-07-16 | Rocket mobile launching vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010684805.8A CN111791788A (en) | 2020-07-16 | 2020-07-16 | Rocket mobile launching vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111791788A true CN111791788A (en) | 2020-10-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010684805.8A Pending CN111791788A (en) | 2020-07-16 | 2020-07-16 | Rocket mobile launching vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN111791788A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113043935A (en) * | 2021-03-18 | 2021-06-29 | 星河动力(北京)空间科技有限公司 | Launch preparation device for carrier rocket, launch preparation method for carrier rocket, and launch system |
| CN113928208A (en) * | 2021-10-13 | 2022-01-14 | 江苏悦达专用车有限公司 | Integrated platform truck of multipurpose rocket launching and unmanned aerial vehicle flying and transportation |
| CN113959259A (en) * | 2021-10-29 | 2022-01-21 | 重庆零壹空间科技集团有限公司 | Launch vehicle with locking mechanism and auxiliary erecting device |
| CN114440704A (en) * | 2021-12-31 | 2022-05-06 | 航天科工火箭技术有限公司 | Rocket transportation heat preservation emitter |
| CN115218722A (en) * | 2022-06-20 | 2022-10-21 | 重庆零壹空间航天科技有限公司 | Rocket launching pad assisted erecting control method, system, medium and electronic equipment |
| WO2023062646A1 (en) * | 2021-10-14 | 2023-04-20 | Agnikul Cosmos Private Limited | Mobile orbital launcher |
-
2020
- 2020-07-16 CN CN202010684805.8A patent/CN111791788A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113043935A (en) * | 2021-03-18 | 2021-06-29 | 星河动力(北京)空间科技有限公司 | Launch preparation device for carrier rocket, launch preparation method for carrier rocket, and launch system |
| CN113928208A (en) * | 2021-10-13 | 2022-01-14 | 江苏悦达专用车有限公司 | Integrated platform truck of multipurpose rocket launching and unmanned aerial vehicle flying and transportation |
| WO2023062646A1 (en) * | 2021-10-14 | 2023-04-20 | Agnikul Cosmos Private Limited | Mobile orbital launcher |
| CN113959259A (en) * | 2021-10-29 | 2022-01-21 | 重庆零壹空间科技集团有限公司 | Launch vehicle with locking mechanism and auxiliary erecting device |
| CN114440704A (en) * | 2021-12-31 | 2022-05-06 | 航天科工火箭技术有限公司 | Rocket transportation heat preservation emitter |
| CN114440704B (en) * | 2021-12-31 | 2024-03-08 | 航天科工火箭技术有限公司 | Rocket transportation heat preservation emitter |
| CN115218722A (en) * | 2022-06-20 | 2022-10-21 | 重庆零壹空间航天科技有限公司 | Rocket launching pad assisted erecting control method, system, medium and electronic equipment |
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