CN111017193A - Carrying aircraft and load delivery method - Google Patents
Carrying aircraft and load delivery method Download PDFInfo
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- CN111017193A CN111017193A CN201911326797.3A CN201911326797A CN111017193A CN 111017193 A CN111017193 A CN 111017193A CN 201911326797 A CN201911326797 A CN 201911326797A CN 111017193 A CN111017193 A CN 111017193A
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- load
- skirt
- deceleration
- carrying compartment
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- 238000002716 delivery method Methods 0.000 title claims abstract description 13
- 230000002093 peripheral effect Effects 0.000 claims abstract description 4
- 230000001681 protective effect Effects 0.000 claims description 15
- 230000009467 reduction Effects 0.000 claims description 13
- 229910000838 Al alloy Inorganic materials 0.000 claims description 11
- 239000004964 aerogel Substances 0.000 claims description 8
- ISWSIDIOOBJBQZ-UHFFFAOYSA-N phenol group Chemical group C1(=CC=CC=C1)O ISWSIDIOOBJBQZ-UHFFFAOYSA-N 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 7
- 239000011241 protective layer Substances 0.000 claims description 6
- 230000008569 process Effects 0.000 claims description 5
- 239000002737 fuel gas Substances 0.000 claims description 4
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 230000009471 action Effects 0.000 claims description 2
- 230000008878 coupling Effects 0.000 claims 2
- 238000010168 coupling process Methods 0.000 claims 2
- 238000005859 coupling reaction Methods 0.000 claims 2
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000008859 change Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000010355 oscillation Effects 0.000 description 4
- 238000003825 pressing Methods 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 108010066057 cabin-1 Proteins 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000011253 protective coating Substances 0.000 description 2
- 230000007480 spreading Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003607 modifier Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/10—Stabilising surfaces adjustable
- B64C5/12—Stabilising surfaces adjustable for retraction against or within fuselage or nacelle
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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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
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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
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/02—Dropping, ejecting, or releasing articles
- B64D1/08—Dropping, ejecting, or releasing articles the articles being load-carrying devices
- B64D1/10—Stowage arrangements for the devices in aircraft
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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
- B64D9/00—Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention provides a carrier vehicle and a load delivery method, wherein the carrier vehicle comprises a load loading cabin and a deceleration expansion skirt arranged around the outer peripheral wall of the load loading cabin, one end of the deceleration expansion skirt is connected with the outer wall of the load loading cabin, the deceleration expansion skirt is provided with a furled position furled on the outer wall of the load loading cabin and an unfolded position outwards opened relative to the load loading cabin, and when the deceleration expansion skirt is at the unfolded position, the carrier vehicle decelerates by using pneumatic resistance generated by the deceleration expansion skirt. The carrier aircraft of the invention decelerates by utilizing the aerodynamic resistance generated by the expansion of the deceleration expansion skirt, and compared with the traditional carrier aircraft adopting the reverse thrust deceleration of a rocket engine, the invention can increase the delivery distance, improve the delivery load capacity, improve the delivery cost-effectiveness ratio of the carrier aircraft, realize a larger delivery range, reduce the complexity of a power system due to the omission of a deceleration engine, reduce the cost and realize simple and convenient use and maintenance.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a carrying aircraft and a load delivery method.
Background
The high-speed aircraft is adopted to deliver loads such as unmanned aerial vehicles, small satellites and aerostats to a long-distance area which cannot be reached in a short time, and the high-speed aircraft is a novel means for achieving the purposes of emergency monitoring, disaster prevention and relief and the like. Unlike aircraft delivery or autonomous flight to target airspace, high-speed aircraft can be boosted to very high speed by rocket engines, thereby shortening delivery time. The load throwing is usually controlled within a certain height and speed range to ensure that the pneumatic load and the thermal load are small after the load is thrown, so that the load is safely thrown, and therefore, the speed is reduced when the load is re-thrown at the tail end.
The traditional reentry deceleration mode of the carrier aircraft usually adopts the reverse thrust work of a rocket engine in the falling process to offset the higher speed in the boosting and flying processes, thereby adapting to the requirement of load throwing. Aiming at the requirement of throwing load in high altitude after reentry, the technology mainly has the following defects:
(1) under the conditions of very high speed of the aircraft, higher height during load throwing and lower speed, the energy demand on the speed reduction engine is larger, so the speed reduction engine with the same mass as that of the boosting rocket engine is often carried, the throwing distance and the throwing load capacity are obviously reduced, and the throwing cost ratio of the carrier aircraft is greatly reduced;
(2) the delivery distance change range of the delivery aircraft composed of the boosting engine and the reducing engine is small under the condition that the delivery condition is met, and the delivery distance is not convenient to adjust according to task requirements;
(3) in order to realize the adjustable requirements of the thrust and the energy of the speed reducing engine, a liquid rocket engine is often needed, the cost is high, the use and the maintenance are complex, and the requirements of simple use and strong emergency response capability of the carrier aircraft are not facilitated.
Disclosure of Invention
The invention aims to provide a carrier vehicle and a load delivery method, and aims to solve the problems of low delivery efficiency cost ratio, small delivery distance change range, high cost and complex use and maintenance in the prior art by adopting rocket engine reverse thrust.
In order to achieve the above object, the present invention provides a vehicle including a load-carrying compartment and a deceleration expansion skirt provided around an outer peripheral wall of the load-carrying compartment, one end of the deceleration expansion skirt being connected to the outer wall of the load-carrying compartment, the deceleration expansion skirt having a stowed position stowed on the outer wall of the load-carrying compartment and a deployed position outwardly expanded with respect to the load-carrying compartment, the vehicle being decelerated by aerodynamic resistance generated by the deceleration expansion skirt when the deceleration expansion skirt is in the deployed position.
The vehicle as described above, wherein the deceleration extension skirt is surrounded by a plurality of skirt panels arranged at intervals in a circumferential direction of the load-carrying compartment, one end of each of the skirt panels is rotatably connected to an outer wall of the load-carrying compartment to form a swing center, the skirt panels are abutted against the outer wall of the load-carrying compartment when the deceleration extension skirt is in the collapsed position, the skirt panels are inclined outward with respect to the load-carrying compartment when the deceleration extension skirt is in the expanded position, and the skirt panels are switched from the collapsed position to the expanded position by swinging around the swing center in a direction away from the load-carrying compartment.
The carrier vehicle as described above, wherein the carrier vehicle further includes a plurality of driving devices for driving each skirt board to swing, the plurality of driving devices are respectively provided between the plurality of skirt boards and the load compartment, each driving device includes a ram and a link, the ram is disposed along an axial direction of the load compartment and fixed to a bulkhead of the load compartment, the ram has a push rod movable along the axial direction of the load compartment, one end of the link is rotatably connected to the push rod, the other end of the link is rotatably connected to the skirt board, and the push rod drives the skirt board to swing in a direction away from the load compartment by moving toward the swing center.
The carrier aircraft as described above, wherein each of the driving devices further includes an adapter plate and a slider, the adapter plate is fixed to a bulkhead of the load loading bay, the actuator cylinder is fixed to the adapter plate, the push rod and the connecting rod are connected through the slider, the adapter plate is provided with a guide rail, the guide rail extends in an axial direction of the load loading bay, the slider is slidably connected to the guide rail, and the slider slides along the guide rail when the push rod moves.
The carrier aircraft as described above, wherein a mounting port is provided in a bulkhead of the load loading bay, the adapter plate is provided in the mounting port, the adapter plate has a bottom surface facing the inside of the load loading bay and a top surface facing the outside of the load loading bay, a protective cover is provided on the bottom surface of the adapter plate, the protective cover is located in the load loading bay, the actuator cylinder is located with the slider in a space enclosed by the adapter plate and the protective cover, the actuator cylinder is located with the guide rail on the bottom surface of the adapter plate, and an opening for the connecting rod to pass through and move is provided in the adapter plate.
The carrier vehicle as described above, wherein one end of each skirt board is rotatably connected to the outer wall of the load carrying compartment by a connecting assembly, the connecting assembly includes a support fixed to the outer wall of the load carrying compartment and a rotating shaft provided on the support, one end of each skirt board has a support leg, the support leg and the support leg are rotatably connected by the rotating shaft, the support is provided with a lock pin hole, a locking member for locking the deceleration expansion skirt in the deployed position is provided in the lock pin hole, the locking member includes a spring and a locking pin that are connected, the support leg is provided with a receptacle, when the deceleration expansion skirt is in the stowed position, the receptacle and the lock pin hole are misaligned, the locking pin is located inside the lock pin hole, and when the deceleration expansion skirt is in the deployed position, the receptacle and the lock pin hole are aligned, the locking pin extends out of the locking pin hole under the action of the elastic force of the spring and is inserted into the insertion hole.
The carrier vehicle as described above, wherein the ram is an ignition ram, the load loading bay is provided with a comprehensive controller and an electrical control box, the comprehensive controller can send a deceleration expansion skirt deployment instruction to the electrical control box, the electrical control box controls the ignition ram to ignite and generate fuel gas after receiving the deceleration expansion skirt deployment instruction, and the push rod moves under the thrust of the fuel gas.
The carrier aircraft as described above, wherein the bulkhead of the load carrying compartment is an aluminum alloy skin, the outer surface of the aluminum alloy skin is covered with a phenolic aerogel protective layer, the apron board is an aluminum alloy board, and the aluminum alloy board is covered with a phenolic aerogel protective layer.
The vehicle as described above, wherein the speed-reducing expansion skirt is provided with a plurality of through-holes through which the air flow passes when the speed-reducing expansion skirt is in the deployed position.
The invention also provides a load delivery method, which adopts the carrier aircraft to deliver the load, wherein the load is loaded in the load loading cabin, and the load delivery method comprises the following steps:
adjusting a speed reduction expansion skirt of the vehicle to the stowed position;
the carrier vehicle flies under the boosting of a rocket engine, when the carrier vehicle reaches the maximum preset speed under the boosting of the rocket engine, the carrier vehicle is separated from the rocket engine, and the carrier vehicle continues flying;
the attitude adjustment is completed when the flight of the carrier aircraft reaches a preset highest point, the deceleration expansion skirt is switched to the unfolding position, the carrier aircraft reenters and flies in the attitude that the deceleration expansion skirt is at the unfolding position, and the carrier aircraft decelerates to reach the target speed required by load throwing by utilizing the pneumatic resistance generated by the deceleration expansion skirt in the reentry flight process;
the carrier vehicle throws the load at the target speed.
The carrier aircraft and the load delivery method have the characteristics and advantages that:
1. the carrier aircraft of the invention decelerates by utilizing the aerodynamic resistance generated by the expansion of the deceleration expansion skirt, and compared with the traditional carrier aircraft adopting the reverse thrust deceleration of a rocket engine, the carrier aircraft can increase the delivery distance, improve the delivery load capacity, improve the delivery cost-effectiveness ratio of the carrier aircraft, realize a larger delivery range, save the deceleration engine, reduce the complexity of a power system, reduce the cost and is simple and convenient to use and maintain;
2. the invention relates to a reentry deceleration method of a carrier aircraft based on aerodynamic drag, which greatly improves the efficiency of carrier delivery, reduces the complexity of a system, realizes the delivery requirement without a deceleration rocket engine and is beneficial to improving the rapidity and the low cost of emergency response based on the requirement of flight delivery of decelerating to a specific speed (namely a target speed) in a specific airspace.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein:
FIG. 1 is a schematic illustration of the vehicle of the present invention with the speed reduction expansion skirt in a stowed position;
FIG. 2 is a schematic view of the vehicle of the present invention with the deceleration expansion skirt in the deployed position;
FIG. 3 is a schematic view of the skirt panel of the present invention in a stowed position;
FIG. 4 is a schematic view of the skirt panel of the present invention in a deployed position;
FIG. 5 is a left side schematic view of FIG. 4;
FIG. 6 is a schematic view of a drive arrangement according to the present invention;
FIG. 7 is a bottom view of FIG. 6;
FIG. 8 is a schematic view of the slider engaged with the guide rail of the present invention;
fig. 9 is an assembly schematic of the connecting assembly and locking member of the present invention.
Main element number description:
1. a load carrying compartment; 11. a head portion; 12. a tail portion; 13. a bulkhead;
2. a deceleration expansion skirt; 21. a through hole; 22. a skirt board; 221. a first end; 222. a second end;
223. an inner surface; 224. an outer surface; 225. supporting legs; 2251. a jack;
3. a center of oscillation;
4. a drive device; 41. an actuator cylinder; 411. a push rod; 412. an outer cylinder; 413. pressing a plate;
42. a connecting rod; 43. an adapter plate; 431. a guide rail; 432. a bottom surface; 433. a top surface; 434. an opening;
44. a slider; 441. a bump;
5. a connecting assembly; 51. a support; 52. a rotating shaft; 6. a locking pin.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Where adjective or adverbial modifiers "center," "clockwise" and "counterclockwise," "front" and "back," "left" and "right," "top" and "bottom," "inner" and "outer" are used merely to facilitate relative reference between sets of terms, and do not describe any particular directional limitation on the modified terms. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
As shown in fig. 1 and 2, the present invention provides a carrier vehicle comprising a load-carrying compartment 1 and a deceleration expansion skirt 2 provided around the outer peripheral wall of the load-carrying compartment 1, one end of the deceleration expansion skirt 2 being connected to the outer wall of the load-carrying compartment 1, the deceleration expansion skirt 2 having a stowed position stowed on the outer wall of the load-carrying compartment 1 (collapsed position) and a deployed position deployed outwardly with respect to the load-carrying compartment 1, the deceleration expansion skirt 2 abutting against the outer wall of the load-carrying compartment 1 when the deceleration expansion skirt 2 is in the stowed position (shown in fig. 1), the deceleration expansion skirt 2 being inclined outwardly with respect to the load-carrying compartment 1 (outside the load-carrying compartment 1) and facing the wind when the deceleration expansion skirt 2 is in the deployed position (shown in fig. 2), whereby the deceleration expansion skirt 2 increases the windward area of the carrier vehicle, and in use, during the launch boost phase of the carrier vehicle, the deceleration expansion skirt 2 is in the folded position, and during the reentry of the carrier vehicle, the deceleration expansion skirt 2 is in the unfolded position, so that the carrier vehicle decelerates by using the aerodynamic resistance generated by the deceleration expansion skirt 2 facing the wind during the reentry (i.e., the reentry section).
The carrier vehicle of the invention utilizes the aerodynamic resistance generated by the expansion of the deceleration expansion skirt 2 to decelerate, and compared with the traditional carrier vehicle adopting a rocket engine to reversely decelerate, the carrier vehicle at least has the following advantages:
firstly, the invention improves the delivery efficiency and the delivery cost-effectiveness ratio, because the traditional carrier aircraft needs to increase a speed reducing engine on the basis of a boosting engine, the quality of a rocket engine needs to be improved to achieve the required delivery effect, and the invention can reduce the quality of the rocket engine because the speed reducing engine does not need to be carried, thereby increasing the delivery distance, improving the delivery load capacity and improving the delivery cost-effectiveness ratio of the carrier aircraft, and tests show that the carrier aircraft adopting the invention can reduce the total mass of the rocket engine by 25 percent under the condition of the same delivery distance and the same height/speed requirement of a delivery point, improves the delivery distance by 60 percent under the condition of the same takeoff quality and obviously improves the delivery efficiency;
secondly, the adaptability of the delivery distance is improved, the change range of the delivery distance is larger, and as the final boosting speed is larger, the pneumatic resistance received by reentry is larger, and the speed difference at the specified height after the deceleration through the pneumatic resistance is not large at different final boosting speeds, the flight distance of the reentry section can be changed by adjusting the track inclination angle (namely the trajectory inclination angle), so that the larger delivery range is realized, the minimum delivery distance can reach less than 30% of the maximum delivery distance, and the flexibility and the convenience of use are improved, while the traditional carrier aircraft needs boosting and fine calculation and adjustment of the dosage of a deceleration engine if the adjustment of the delivery distance is realized;
thirdly, compared with the traditional carrier aircraft, the invention omits a deceleration engine, not only reduces the complexity of a power system, but also omits an attitude control system required by the traditional carrier aircraft at a reentry section, thereby reducing the system complexity, reducing the cost and being simple and convenient to use and maintain.
As shown in fig. 1 and 2, in one embodiment, a plurality of through holes 21 are provided in the deceleration expanding skirt 2, each through hole 21 penetrates through the deceleration expanding skirt 2, and the through holes 21 allow an airflow to pass therethrough when the deceleration expanding skirt 2 is in the deployed position (i.e., in a state of a low mach number), so that moment oscillation caused by poor airflow can be alleviated, and particularly aerodynamic moment oscillation in a transonic speed stage can be avoided, and the through holes 21 make the airflow difficult to pass therethrough when the deceleration expanding skirt 2 is in the stowed position (i.e., in a state of a high mach number), and thus by providing the through holes 21, it is advantageous to achieve both flight stability control and deceleration effect.
As shown in fig. 1 and 2, in one embodiment, the speed-reducing expansion skirt 2 is surrounded by a plurality of skirt panels 22 arranged at intervals in the circumferential direction of the load-carrying compartment 1, one end of each skirt panel 22 is rotatably connected to the outer wall of the load-carrying compartment 1 to form a swing center 3, the skirt panels 22 abut against the outer wall of the load-carrying compartment 1 when the speed-reducing expansion skirt 2 is in the collapsed position, the skirt panels 22 are inclined outward with respect to the load-carrying compartment 1 (the skirt panels 22 are in the shape of fins) when the speed-reducing expansion skirt 2 is in the expanded position, and the skirt panels 22 are swung in a direction away from the load-carrying compartment 1 about the swing center 3 to switch the speed-reducing expansion skirt 2 from the collapsed position to the expanded position.
Specifically, the load carrying compartment 1 is cylindrical, the outer wall surface of the load carrying compartment 1 is smooth, the skirt board 22 is plate-shaped, the skirt board 22 is elongated in the axial direction of the load carrying compartment 1, the cross section of the skirt board 22 in the radial direction of the load carrying compartment 1 is arc-shaped, and the concave arc surface of the skirt board 22 faces the load carrying compartment 1 so as to be adapted (attached) to the load carrying compartment 1 when the skirt board is in the folded position. For example, the number of the skirt panels 22 is six, and the six skirt panels 22 are arranged at equal intervals in the circumferential direction of the load compartment 1.
As shown in fig. 1 and 2, the load carrying compartment 1 further has a leading portion 11 and a trailing portion 12, when the carrier vehicle is flying, the leading portion 11 of the load carrying compartment 1 is forward, that is, the carrier vehicle is flying in a direction of the left side in fig. 2, the speed-reducing expansion skirt 2 is provided at the trailing portion 12 of the load carrying compartment 1, the skirt panel 22 has a first end 221 and a second end 222 which are opposite to each other, the first end 221 of the skirt panel 22 is an end close to the leading portion 11 of the load carrying compartment 1, the second end 222 of the skirt panel 22 is an end far from the leading portion 11 of the load carrying compartment 1, the first end 221 of the skirt panel 22 is rotatably connected with the outer wall of the load carrying compartment 1 to form the center of oscillation 3, and the second end 222 of the skirt panel 22.
As shown in fig. 1 and 2, a region (which may be referred to as a root region) of the skirt panel 22 near the first end 221 is provided with a plurality of through holes 21, the plurality of through holes 21 on the skirt panel 22 are arranged in a plurality of rows and a plurality of columns, for example, the through holes 21 are circular through holes 21, the number of the through holes 21 on each skirt panel 22 is eight, and the eight through holes 21 are arranged in two rows and four columns. However, the present invention is not limited to this, and the through holes 21 may be formed in the entire skirt panel 22.
Further, as shown in fig. 4, when the deceleration expansion skirt 2 is in the deployed position, the angle between the deceleration expansion skirt 2 and the central axis of the load-carrying compartment 1 is α, 0 < α ≦ 90 °, specifically, for example, the angle between the deceleration expansion skirt 2 and the tail 12 of the load-carrying compartment 1 is α, and the angle between the deceleration expansion skirt 2 and the head 11 of the load-carrying compartment 1 is (180 ° - α).
As shown in fig. 3 and 4, in one embodiment, the vehicle further includes a plurality of driving devices 4 for driving each skirt panel 22 to swing, the plurality of driving devices 4 are respectively disposed between the plurality of skirt panels 22 and the load carrying compartment 1, each driving device 4 includes a cylinder 41 and a connecting rod 42, the cylinder 41 is disposed along the axial direction of the load carrying compartment 1 and fixed on the bulkhead 13 of the load carrying compartment 1, the cylinder 41 has a push rod 411 (or referred to as a thrust rod) capable of moving along the axial direction of the load carrying compartment 1, one end of the connecting rod 42 is rotatably connected to the push rod 411, the other end of the connecting rod 42 is rotatably connected to the skirt panel 22, and the push rod 411 moves along the axial direction of the load carrying compartment 1 toward the swing center 3 to drive the skirt panel 22 to swing away from the load carrying compartment 1, so that the deceleration expansion skirt 2 is switched from the folded position to the unfolded position.
Specifically, the actuator cylinder 41 is fixed on the bulkhead 13 of the tail 12 of the load carrying compartment 1, the skirt panel 22 has an inner surface 223 and an outer surface 224 which are opposite to each other, when the deceleration extension skirt 2 is in the collapsed position, the inner surface 223 of the skirt panel 22 faces (faces) the outer wall surface of the tail 12 of the load carrying compartment 1, the outer surface 224 of the skirt panel 22 faces away from the outer wall surface of the tail 12 of the load carrying compartment 1, the other end of the connecting rod 42 is rotatably connected to the inner surface 223 of the skirt panel 22, the connecting rod 42 is in the laid-down state, the connecting rod 42 and the actuator cylinder 41 can also play a role in limiting the expansion of the deceleration extension skirt 2, when the deceleration extension skirt 2 is in the expanded position, the connecting rod 42 can play a supporting role in supporting the expanded deceleration extension skirt 2, the inclination angle of the inner surface 223 of the skirt panel 22 relative to the central axis of the load carrying compartment 1 is α.
For example, the link 42 may be pivotally connected to the panel 22 by a pin, and to prevent the pin from backing out, a hole may be formed in the end of the pin and a pin may be inserted into the hole with an opening 434.
As shown in fig. 3, 4, 6 and 7, in a specific embodiment, each driving device 4 further includes an adapter plate 43 and a slider 44, the adapter plate 43 is fixed on the bulkhead 13 of the load compartment 1, the ram 41 is fixed on the adapter plate 43, the push rod 411 and the link 42 are connected through the slider 44, the adapter plate 43 is provided with a guide rail 431, the guide rail 431 extends along the axial direction of the load compartment 1, the slider 44 is slidably connected with the guide rail 431, and the slider 44 slides along the guide rail 431 when the push rod 411 moves.
As shown in fig. 6, 7 and 8, specifically, the outer cylinder 412 of the actuator cylinder 41 is fixedly connected to the adapter plate 43, and mounting lugs are respectively disposed on two sides of the outer cylinder 412 of the actuator cylinder 41, and the mounting lugs are fixedly connected to the adapter plate 43 through bolts, so as to improve the connection strength, the outer side of the outer cylinder 412 of the actuator cylinder 41 may be covered with a pressing plate 413, and two ends of the pressing plate 413 are fixedly connected to the adapter plate 43 through screws; the two guide rails 431 are respectively positioned at two sides of the sliding block 44, the guide rails 431 are of a long strip-shaped structure extending along the axial direction of the load loading compartment 1, the section of each guide rail 431 is L-shaped, two sides of the sliding block 44 are respectively provided with a convex block 441, and the two convex blocks 441 respectively extend into the corresponding guide rails 431 and can slide along the guide rails 431; the link 42 is connected to the slider 44 by a pin, and the slider 44 is connected to the push rod 411 by a pin.
As shown in fig. 6 and 7, in one embodiment, the bulkhead 13 of the load carrying compartment 1 is provided with a mounting opening, the adapter plate 43 is provided at the mounting opening, the adapter plate 43 has a bottom surface 432 facing the inside of the load carrying compartment 1 and a top surface 433 facing the outside of the load carrying compartment 1, the bottom surface 432 of the adapter plate 43 is covered with a protective cover, the protective cover is in a hollow rectangular parallelepiped shape with an open top, the top of the protective cover is connected with the bottom surface 432 of the adapter plate 43, for example, the protective cover is connected with the adapter plate 43 through a connecting member such as a screw, the protective cover and the adapter plate 43 are located inside the load carrying compartment 1, that is, the adapter plate 43 is connected with the inner wall surface of the bulkhead 13 of the load carrying compartment 1 through a connecting member such as a screw, and the adapter plate 43 completely covers the mounting opening to prevent external hot air flow from entering the inside of the load carrying compartment 1 from the mounting opening, so that the protective cover and, the actuating cylinder 41 and the sliding block 44 are located in a space enclosed by the adapter plate 43 and the protective cover, the actuating cylinder 41 and the guide rail 431 are arranged on a bottom surface 432 of the adapter plate 43, an opening 434 for the connecting rod 42 to pass through and move is formed in the adapter plate 43, so that the connecting rod 42 can pass through the opening 434 to be connected with the skirt board 22, and when the push rod 411 of the actuating cylinder 41 pushes the connecting rod 42 to move, the opening 434 is used as a moving space of the connecting rod 42 to enable the connecting rod 42 to move smoothly.
In the embodiment, the actuating cylinder 41, the sliding block 44, the guide rail 431, the protective cover and the adapter plate 43 are arranged inside the load loading cabin 1, so that the skirt board 22 can be more tightly attached to the outer wall of the load loading cabin 1 when the speed reduction expansion skirt 2 is in the folded position, the outer diameter size of the speed reduction expansion skirt 2 in the folded position is reduced to the maximum extent, and the pneumatic resistance generated when the speed reduction expansion skirt 2 is in the folded position is reduced to the maximum extent; the present embodiment prevents the external hot air from entering the load compartment 1 through the opening 434 of the adapter plate 43 by providing a protective cover.
In one embodiment, a locking member for locking the speed-reducing expansion skirt 2 in the deployed position is provided between one end of the skirt panel 22 (i.e., the first end 221) and the outer wall of the load-carrying compartment 1.
As shown in fig. 3, 4 and 9, further, one end (first end 221) of each skirt panel 22 is rotatably connected with the outer wall of the load carrying compartment 1 through a connecting assembly 5, the connecting assembly 5 comprises a support 51 fixed on the outer wall of the load carrying compartment 1 and a rotating shaft 52 arranged on the support 51, one end (first end 221) of each skirt panel 22 is provided with a support leg 225, the support leg 225 and the support 51 are rotatably connected through the rotating shaft 52, the support 51 is provided with a lock pin hole, a locking piece is arranged in the lock pin hole, the locking piece comprises a spring (not shown) and a locking pin 6 which are connected, the support leg 225 is provided with a plug hole 2251, when the speed reduction expansion skirt 2 is in the folded position (as shown in fig. 3), the plug hole 2251 and the lock pin hole, namely, are misaligned with each other plug hole 2251, the locking pin 6 is positioned in the lock pin hole, one end of the locking pin, when the speed reduction expansion skirt 2 is in the deployed position (as shown in figure 4), the receptacles 2251 are aligned with the locking pin holes and the locking pins 6 extend out of the locking pin holes and into the receptacles 2251 under the force of the springs, thereby locking the skirt panel 22 in the deployed position.
In one embodiment, the actuator 41 is a fire actuator, and the load carrying compartment 1 is provided with a comprehensive controller and an electrical control box, the comprehensive controller can send a deceleration expansion skirt expansion command (i.e. a deceleration expansion skirt expansion signal) to the electrical control box, the electrical control box controls the fire actuator to ignite and generate gas after receiving the deceleration expansion skirt expansion command, and the push rod 411 moves under the thrust of the gas, and the fire actuator is adopted in this embodiment, so that the actuator 41 is electrically controlled.
As shown in fig. 1 and 9, in an embodiment, the bulkhead 13 of the load carrying compartment 1 is an aluminum alloy skin (as shown in fig. 9), the outer surface of the aluminum alloy skin is covered with a phenolic aerogel protective layer, the lightweight low-cost aluminum alloy skin is adopted, the cost of the carrier vehicle can be further reduced, and the lightweight high-temperature resistant phenolic aerogel protective layer can meet the requirement of high-altitude high-mach-number heat protection in the reentry stage.
In one embodiment, the skirt panels 22 are lightweight low cost aluminum alloy panels covered with a phenolic aerogel protective coating, i.e., all outer surfaces of the aluminum alloy panels are covered with a phenolic aerogel protective coating to meet the high altitude mach number thermal protection requirements of the reentry section.
The present invention also provides a load delivery method for delivering a load by using the above-described carrier vehicle, the load being loaded in the load loading bay 1, the load delivery method comprising:
adjusting the deceleration shed 2 of the vehicle to the stowed position (as shown in figure 1);
the carrier vehicle flies under the boosting of the rocket engine, when the carrier vehicle reaches the maximum preset speed under the boosting of the rocket engine, the carrier vehicle is separated from the rocket engine, and the carrier vehicle continues flying (as shown in figure 1);
finishing attitude adjustment when the carrier aircraft flies to reach a preset highest point, then switching the deceleration expansion skirt 2 to a spreading position to form a larger windward area (as shown in fig. 2), enabling the carrier aircraft to reenter and fly (enter a reentry section) in a stable attitude of the deceleration expansion skirt 2 at the spreading position, utilizing the pneumatic resistance generated by the deceleration expansion skirt 2 to decelerate in the reentry flying process of the carrier aircraft, and decelerating to a target speed required by load throwing at a specified height;
and the carrier aircraft throws the load at the target speed, so that safe throwing of the load is realized.
The attitude adjustment of the carrier aircraft before the speed reduction expansion skirt 2 is deployed refers to adjusting the speed, the attack angle, the sideslip angle and other attitude positions so as to better enter the release window.
The invention relates to a reentry deceleration method of a carrier aircraft based on aerodynamic drag, which greatly improves the efficiency of carrier delivery, reduces the complexity of a system, realizes the delivery requirement without a deceleration rocket engine and is beneficial to improving the rapidity and the low cost of emergency response based on the requirement of flight delivery of decelerating to a specific speed (namely a target speed) in a specific airspace.
The carrier aircraft and the load delivery method change the aerodynamic resistance borne by the aircraft through the folding and unfolding of the speed reduction expansion skirt, and increase the windward area through unfolding the speed reduction expansion skirt, so that the aerodynamic resistance during reentry is obviously increased, the effect of obviously reducing the speed at high altitude is realized by utilizing the aerodynamic resistance, the delivery cost effectiveness ratio of the carrier aircraft is favorably improved, the system complexity is reduced, the cost is reduced, and the flexibility and the convenience in use are improved.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent changes and modifications that can be made by one skilled in the art without departing from the spirit and principles of the invention should be considered within the scope of the invention. It should be noted that the components of the present invention are not limited to the above-mentioned whole application, and various technical features described in the present specification can be selected to be used alone or in combination according to actual needs, so that the present invention naturally covers other combinations and specific applications related to the invention.
Claims (10)
1. A vehicle comprising a load-carrying compartment and a deceleration expansion skirt provided around an outer peripheral wall of the load-carrying compartment, one end of the deceleration expansion skirt being connected to an outer wall of the load-carrying compartment, the deceleration expansion skirt having a stowed position stowed on the outer wall of the load-carrying compartment and a deployed position outwardly expanded with respect to the load-carrying compartment, the vehicle being decelerated by aerodynamic resistance generated by the deceleration expansion skirt when the deceleration expansion skirt is in the deployed position.
2. A vehicle according to claim 1, wherein the speed-reducing expansion skirt is surrounded by a plurality of skirt panels spaced circumferentially around the load-carrying compartment, each skirt panel having one end pivotally connected to the outer wall of the load-carrying compartment to define a swing center, the skirt panels abutting the outer wall of the load-carrying compartment when the speed-reducing expansion skirt is in the stowed position, the skirt panels being outwardly inclined relative to the load-carrying compartment when the speed-reducing expansion skirt is in the deployed position, the skirt panels being adapted to switch the speed-reducing expansion skirt from the stowed position to the deployed position by swinging the skirt panels about the swing center in a direction away from the load-carrying compartment.
3. A vehicle according to claim 2, further comprising a plurality of driving devices for driving each skirt panel to swing, wherein a plurality of the driving devices are provided between a plurality of the skirt panels and the load-carrying compartment, and wherein each driving device comprises a cylinder disposed in an axial direction of the load-carrying compartment and fixed to a wall of the load-carrying compartment, and a connecting rod having a push rod movable in the axial direction of the load-carrying compartment, wherein one end of the connecting rod is rotatably connected to the push rod, and wherein the other end of the connecting rod is rotatably connected to the skirt panel, and wherein the push rod drives the skirt panel to swing in a direction away from the load-carrying compartment by moving toward the swing center.
4. A vehicle according to claim 3, wherein each of said drive units further comprises an adapter plate fixed to a bulkhead of said load compartment, said ram being fixed to said adapter plate, said ram and said link being connected by said slider, said adapter plate having a guide rail extending in an axial direction of said load compartment, said slider being slidably connected to said guide rail, said slider sliding along said guide rail when said ram moves.
5. A vehicle according to claim 4, wherein a mounting opening is provided in a bulkhead of the load carrying bay, the adapter plate is provided at the mounting opening, the adapter plate has a bottom surface facing the inside of the load carrying bay and a top surface facing the outside of the load carrying bay, a protective cover is provided on the bottom surface of the adapter plate, the protective cover and the adapter plate are located inside the load carrying bay, the ram and the slider are located in a space enclosed by the adapter plate and the protective cover, the ram and the guide rail are provided on the bottom surface of the adapter plate, and an opening for the link to pass through and move is provided on the adapter plate.
6. The vehicle of claim 2, wherein one end of each skirt panel is rotatably coupled to the outer wall of the load carrying compartment by a coupling assembly, the coupling assembly including a bracket fixed to the outer wall of the load carrying compartment and a rotating shaft provided on the bracket, one end of each skirt panel having a support leg, the support leg and the bracket being rotatably coupled by the rotating shaft, the bracket having a lock pin hole, a lock member provided in the lock pin hole for locking the deceleration expansion skirt in the deployed position, the lock member including a spring and a lock pin coupled to each other, the support leg having a socket, the socket and the lock pin hole being misaligned when the deceleration expansion skirt is in the stowed position, the lock pin being positioned inside the lock pin hole, the deceleration expansion skirt being in the deployed position, the insertion hole is aligned with the lock pin hole, and the lock pin extends out of the lock pin hole and is inserted into the insertion hole under the action of the elastic force of the spring.
7. The vehicle according to claim 3, wherein the cylinder is a fire cylinder, and the load-carrying compartment is provided with a comprehensive controller and an electric control box, the comprehensive controller can send a deceleration expansion skirt unfolding command to the electric control box, the electric control box can control the fire cylinder to ignite and generate fuel gas after receiving the deceleration expansion skirt unfolding command, and the push rod moves under the thrust of the fuel gas.
8. A vehicle according to claim 2, wherein the bulkhead of the load carrying compartment is an aluminum alloy skin covered on its outer surface with a protective layer of phenolic aerogel, the skirt is an aluminum alloy panel covered on its outer surface with a protective layer of phenolic aerogel.
9. A vehicle according to any one of claims 1 to 8, characterised in that the deceleration sheds are provided with a plurality of through-holes for the passage of the air flow when the deceleration sheds are in the deployed position.
10. A load delivery method that delivers a load using the carrier vehicle according to any one of claims 1 to 9, the load being loaded in the load carrying compartment, the load delivery method comprising:
adjusting a speed reduction expansion skirt of the vehicle to the stowed position;
the carrier vehicle flies under the boosting of a rocket engine, when the carrier vehicle reaches the maximum preset speed under the boosting of the rocket engine, the carrier vehicle is separated from the rocket engine, and the carrier vehicle continues flying;
the attitude adjustment is completed when the flight of the carrier aircraft reaches a preset highest point, the deceleration expansion skirt is switched to the unfolding position, the carrier aircraft reenters and flies in the attitude that the deceleration expansion skirt is at the unfolding position, and the carrier aircraft decelerates to reach the target speed required by load throwing by utilizing the pneumatic resistance generated by the deceleration expansion skirt in the reentry flight process;
the carrier vehicle throws the load at the target speed.
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| CN201911326797.3A CN111017193A (en) | 2019-12-20 | 2019-12-20 | Carrying aircraft and load delivery method |
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| CN201911326797.3A CN111017193A (en) | 2019-12-20 | 2019-12-20 | Carrying aircraft and load delivery method |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173074A (en) * | 2020-10-22 | 2021-01-05 | 北京空天技术研究所 | Reusable high-temperature speed reducing plate mechanism |
| CN113155187A (en) * | 2021-04-14 | 2021-07-23 | 深圳市北斗云信息技术有限公司 | Throwing object self-righting method |
| CN113525715A (en) * | 2021-08-13 | 2021-10-22 | 哈尔滨工程大学 | High-speed aircraft final segment comprehensive experiment system and method based on fixed-wing unmanned aerial vehicle |
| CN115416858A (en) * | 2022-08-25 | 2022-12-02 | 中国空气动力研究与发展中心空天技术研究所 | Stability augmentation ring for taper sleeve for air refueling |
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2019
- 2019-12-20 CN CN201911326797.3A patent/CN111017193A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173074A (en) * | 2020-10-22 | 2021-01-05 | 北京空天技术研究所 | Reusable high-temperature speed reducing plate mechanism |
| CN112173074B (en) * | 2020-10-22 | 2022-05-20 | 北京空天技术研究所 | Reusable high-temperature speed reducing plate mechanism |
| CN113155187A (en) * | 2021-04-14 | 2021-07-23 | 深圳市北斗云信息技术有限公司 | Throwing object self-righting method |
| CN113525715A (en) * | 2021-08-13 | 2021-10-22 | 哈尔滨工程大学 | High-speed aircraft final segment comprehensive experiment system and method based on fixed-wing unmanned aerial vehicle |
| CN113525715B (en) * | 2021-08-13 | 2022-07-15 | 哈尔滨工程大学 | High-speed aircraft final segment comprehensive experiment system and method based on fixed-wing unmanned aerial vehicle |
| CN115416858A (en) * | 2022-08-25 | 2022-12-02 | 中国空气动力研究与发展中心空天技术研究所 | Stability augmentation ring for taper sleeve for air refueling |
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Application publication date: 20200417 |