CN109781063A - Relative altitude measuring device and aircraft - Google Patents
Relative altitude measuring device and aircraft Download PDFInfo
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- CN109781063A CN109781063A CN201811573020.2A CN201811573020A CN109781063A CN 109781063 A CN109781063 A CN 109781063A CN 201811573020 A CN201811573020 A CN 201811573020A CN 109781063 A CN109781063 A CN 109781063A
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Abstract
The invention discloses a kind of relative altitude measuring device and aircraft, are related to vehicle technology field, and main purpose is so that the structure and algorithm of the relative altitude measuring device of aircraft are relatively simple, and reduce cost.Main technical schemes of the invention are as follows: the device includes pulley；First weight block and multiple second weight blocks, the weight of the first weight block are greater than the sum of the weight of multiple second weight blocks；Flexible strand, one end is connect with the first weight block, the other end concatenates multiple second weight blocks around pulley, the sum of height of the total length of flexible strand, the height of the first weight block and multiple second weight blocks is the first preset value, and the sum of height of flexible strand length and any second weight block between two neighboring second weight block is the second preset value；Measuring unit, including detection module and the computing module being electrically connected with detection module, the vertical range between detection module and pulley center is third preset value.Present invention is mainly used for the relative altitudes of measurement aircraft.
Description
The present invention relates to vehicle technology fields, in particular to a kind of relative altitude measuring device and aircraft.
Background technique
Relative altitude refers to aircraft to the vertical range of specified horizontal plane, and aircraft needs to survey when taking off or landing
Its relative altitude between plane to be landed is measured, so that flight control system can formulate phase to aircraft for different relative altitudes
Answer control strategy.
Currently, the measurement for aircraft relative altitude, generallys use corresponding using sensor, the barometer at airborne end etc.
Equipment is carried out data fusion or is measured using carrier phase difference technology, to obtain the absolute altitude of aircraft, is recycled
Certain algorithm and data processing estimates the relative altitude of aircraft；Or using vision, millimeter wave, ultrasonic wave and Laser Measuring
Away from etc. modes directly measure the relative altitude of aircraft.
Relative altitude is measured in manner just described however, adopting, structure and algorithm are more complex, and higher cost.
Summary of the invention
In view of this, the embodiment of the present invention provides a kind of relative altitude measuring device and aircraft, main purpose be so that
The structure and algorithm of the relative altitude measuring device of aircraft are relatively simple, and reduce cost.
In order to achieve the above objectives, present invention generally provides following technical solutions:
On the one hand, the embodiment of the invention provides a kind of relative altitude measuring devices, comprising:
Pulley；
The weight of first weight block and multiple second weight blocks, first weight block is greater than multiple second weight blocks
The sum of weight；
Flexible strand, one end of the flexible strand are connect with first weight block, and the other end concatenates more around the pulley
A second weight block, the total length of the flexible strand, the height of first weight block and multiple second weight blocks
The sum of height be the first preset value, the flexible strand length between two neighboring second weight block and any described the
The sum of height of two weight blocks is the second preset value；
Measuring unit, the measuring unit include detection module and the computing module that is electrically connected with the detection module, institute
Stating the vertical range between detection module and the pulley center is third preset value；
Wherein, the detection module is used in the first weight block exposure level face, and second weight block is in gravity
When being moved to its position under effect, Xiang Suoshu computing module issues corresponding signal, and the computing module is described for receiving
Signal, and institute is calculated according to the radius of first preset value, second preset value, the third preset value and the pulley
State height of the pulley center relative to the horizontal plane.
Further, the relative altitude measuring device further include:
First guide cylinder, extending direction of first guide cylinder along described flexible strand one end are arranged；
One end of the flexible strand passes through first guide cylinder and connect with first weight block, first weight block
Can the length direction in first guide cylinder along first guide cylinder moved.
Further, the relative altitude measuring device further include:
Second guide cylinder, second guide cylinder are arranged along the extending direction of the flexible strand other end；
The other end of the flexible strand is around the pulley and penetrates first guide cylinder, multiple second weight blocks
It is arranged successively by the flexible strand in first guide cylinder, and can be moved along the length direction of first guide cylinder
It is dynamic.
Further, the detection module is the photoelectric door being set in second guide cylinder.
Further, the detection module is the laser door being set in second guide cylinder.
Further, each second weight block is embedded in magnetic material or each second weight block is magnetic
Property material weight block；
The detection module is the magnetic induction sensor being set in second guide cylinder.
Further, first weight block and multiple second weight blocks are sphere structure.
On the other hand, the embodiment of the invention provides a kind of aircraft, including fuselage and relative altitude above-mentioned measurement dress
It sets；
The pulley and detection module of the relative altitude measuring device are respectively arranged in the fuselage.
Further, door body is provided on the fuselage；
When the door body is opened, first weight block can be exposed to the fuselage by the door body；
When the door body is closed, first weight block can be located in the fuselage by the door body.
Further, the relative altitude measuring device further include the first guide cylinder for being respectively arranged in the fuselage and
Second guide cylinder, first guide cylinder and second guiding are arranged along the both ends extending direction of the flexible strand respectively；
One end of the flexible strand passes through first guide cylinder and connect with first weight block, first weight block
Can the length direction in first guide cylinder along first guide cylinder moved；
The other end of the flexible strand is around the pulley and penetrates second guide cylinder, multiple second weight blocks
It is arranged successively by the flexible strand in second guide cylinder, and can be moved along the length direction of second guide cylinder
It is dynamic.
By above-mentioned technical proposal, the present invention is at least had the advantages that
Technical solution provided in an embodiment of the present invention, can be applied to aircraft, by flexible strand by the first weight block and
Multiple second weight blocks are hung on the both ends of pulley, and the weight of the first weight block be greater than multiple second weight blocks weight it
It is the first preset value with, the sum of height of the total length of flexible strand, the height of the first weight block and multiple second weight blocks, it is adjacent
The sum of height of flexible strand length and any second weight block between two the second weight block centers is the second preset value, together
When, pulley and detection module can be set in aircraft, and the distance of pulley center to detection module is third preset value, realize
When aircraft is when taking off or landing, the first weight block and horizontal face contact can be made, since the weight of the first weight block is big
In the sum of multiple second weight blocks, therefore, after the first weight block and horizontal face contact, each second weight block can be made in gravity
It is successively moved down under, and the distance of its movement is consistent with the dropping distance of aircraft, when each second weight block successively divides
When being clipped to up to detection module position, detection module can send corresponding signal to computing module respectively, so that computing module can
To calculate current pulley center relative to water according to the radius of the first preset value, the second preset value, third preset value and pulley
The height of plane, that is, the relative altitude of aircraft, measurement accuracy is higher, and structure and algorithm are relatively simple, and cost is relatively low.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of relative altitude measuring device provided in an embodiment of the present invention.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, below in conjunction with the preferred embodiment of the present invention
In attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or
Similar label indicates same or similar element or element with the same or similar functions.Described embodiment is this hair
Bright a part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to
It is used to explain the present invention, and is not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.
The embodiment of the present invention is described in detail with reference to the accompanying drawing.
In the description of the present embodiment, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the present embodiment and simplifies description, rather than indication or suggestion meaning
Device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to the present embodiment
The limitation of protection scope.
As shown in Figure 1, the embodiment of the invention provides a kind of relative altitude measuring device, including pulley 1, for being mounted on
In aircraft；The weight of first weight block 21 and multiple second weight blocks 22, the first weight block 21 is greater than multiple second weight blocks
The sum of 22 weight；Flexible strand 2, one end are connect with the first weight block 21, and the other end concatenates multiple second weight around pulley 1
Block 22, the sum of height of the total length of flexible strand 2, the height of the first weight block 21 and multiple second weight blocks 22 are first default
It is worth, the sum of 2 length of flexible strand and the height of any second weight block 22 are default for second between two neighboring second weight block 22
Value；Measuring unit comprising computing module and the detection module 3 being electrically connected with computing module, the detection module 3 is for being mounted on
In aircraft, the vertical range between 1 center of the detection module 3 and pulley is third preset value；Wherein, detection module 3 is used for
In 21 exposure level face of the first weight block, when the second weight block 22 is moved to its position under the effect of gravity, to calculating mould
Block issues corresponding signal, and computing module is used to receive the signal, and according to the first preset value, the second preset value, third preset value
The height of 1 center of pulley with respect to the horizontal plane is calculated with the radius of pulley 1.
In some instances, which can be applied to aircraft, such as unmanned plane, 1 He of pulley
Detection module 3 can be separately mounted in the fuselage of aircraft, and be moved with the movement of aircraft, and computing module can be
The flight control system of aircraft；And flexible strand 2 is by biggish first weight block 21 of weight and lesser multiple second weight blocks of weight
22 are hung on the two sides of pulley 1, and the height of the total length of flexible strand 2, the first weight block 21 and multiple second weight blocks respectively
The sum of 22 height is the first preset value, 2 length of flexible strand and any second weight between two neighboring second weight block 22
The sum of height of block 22 is the second preset value, and the vertical range between 1 center of pulley and detection module 3 is third preset value,
In, the first preset value and the second preset value can be targeted according to the prepared different control strategies of flight control system of aircraft
Different relative altitudes and preset, and the distance between two neighboring second weight block 22 can be different, and third is pre-
If value can be preset according to the length of space size in fuselage and flexible strand 2；Detection module 3 is for detecting the second weight
Whether gauge block 22 reaches its position, and sends phase signals to computing module when it reaches the position, so that computing module
The height of 1 center of pulley with respect to the horizontal plane can be calculated according to corresponding data, that is, calculates aircraft relative to level
The relative altitude in face.
Below with the quantity of the second weight block 22 for two, and the relative altitude during aircraft lands need to be measured and be
Example, is specifically described the principle and the course of work of the relative altitude measuring device.It wherein, for ease of description, will be opposite
Highly, the radius of the first preset value, the second preset value, third preset value and pulley 1 is successively denoted as H, S, A, C and R respectively.
Since the weight of the first weight block 21 is greater than the sum of the weight of two the second weight blocks 22, in the first weight
For block 21 not and before ground face contact, two the second weight blocks 22 are unable to reach predeterminated position；When 21 exposure level of the first weight block
Behind face, two the second weight blocks 22 can move down under the effect of gravity, and the relative distance and the device or flight of its movement
The dropping distance of device is consistent, and when first the second weight block 22 reaches predeterminated position, detection module 3 can trigger corresponding signal,
Computing module can receive the signal, and calculate height of 1 center of current time pulley relative to ground according to S, A, C and R, tool
Body calculation formula can be with are as follows: H=S- π R-C, H are the current relative altitude of aircraft, and flight control system can be directed to the phase
To highly formulating corresponding control strategy.
In some instances, the above process can be adapted for the situation that the quantity of the second weight block 22 is only one, i.e., only
A relative altitude of measuring device measurement aircraft is needed, so that flight control system formulates corresponding control for a relative altitude
Make the situation of strategy.
According to above-described embodiment, with the decline of the second weight block 22, when second the second weight block 22 reaches detection mould
When 3 position of block, detection module 3 also triggers corresponding signal, and computing module continues to receive the signal, and counts again according to S, A and R
Height of 1 center of current time pulley relative to ground is calculated, specifically calculation formula can be with are as follows: H=S- π R-C-A, H are
For the current relative altitude of aircraft, flight control system can formulate corresponding control strategy for the relative altitude.
Relative altitude measuring device provided in an embodiment of the present invention, can be applied to aircraft, by flexible strand by first
Weight block and multiple second weight blocks are hung on the both ends of pulley, and the weight of the first weight block is greater than multiple second weight blocks
The sum of weight, the sum of height of the total length of flexible strand, the height of the first weight block and multiple second weight blocks are first default
It is worth, the sum of height of flexible strand length and any second weight block between two neighboring second weight block center is default for second
Value, meanwhile, pulley and detection module can be set in aircraft, and the distance of pulley center to detection module is default for third
Value realizes when aircraft is when taking off or landing, can make the first weight block and horizontal face contact, due to the first weight block
Weight is greater than the sum of multiple second weight blocks, and therefore, after the first weight block and horizontal face contact, each second weight block can be
It is successively moved down under gravity, and the distance of its movement is consistent with the dropping distance of aircraft, when each second weight block
When successively arriving separately at detection module position, detection module can send corresponding signal to computing module respectively, so that calculating
Module can calculate current 1 center of pulley according to the radius of the first preset value, the second preset value, third preset value and pulley 1
Height with respect to the horizontal plane, that is, the relative altitude of aircraft, measurement accuracy is higher, and structure and algorithm are relatively simple, and
Cost is relatively low.
In some instances, referring to Fig. 1, which can also include the first guide cylinder 4, this second is led
To cylinder for being mounted in aircraft；And extending direction of first guide cylinder 4 along 2 one end of flexible strand is arranged；The one of flexible strand 2
End is connect across the first guide cylinder 4 with the first weight block 21, and the first weight block 21 can be in the first guide cylinder 4 along the first guide cylinder
4 length direction is moved.
In some instances, which can be cylindrical, and its fuselage that can be vertically installed at aircraft
It is interior, and can be arranged along the length direction of 2 one end of flexible strand, so that the first weight block 21 passes through flexible strand 2 in first guiding
Movement in cylinder 4.By the setting of the first guide cylinder 4, the first guide cylinder 4 is provided for the movement of the first weight block 21 and is led
To effect, in order to the first weight block 21 can successfully with horizontal face contact.
In some instances, referring to Fig. 1, which can also include the second guide cylinder 5, this second is led
Extending direction to cylinder 5 along 2 other end of flexible strand is arranged；The other end of flexible strand 2 is around pulley 1 and penetrates the second guide cylinder 5,
Multiple second weight blocks 22 are arranged successively by flexible strand 2 in the second guide cylinder 5, and can be along the length side of the second guide cylinder 5
To being moved.
In some instances, which can be cylindrical, and its fuselage that can be vertically installed at aircraft
It is interior, and can be arranged along the length direction of 2 other end of flexible strand, will pass through multiple second weight that flexible strand 2 mutually concatenates
Block 22 can movably be located in second guide cylinder 5.By the setting of the second guide cylinder 5, so that the second guide cylinder 5 can be with
Descending motion for each second weight block 22 provides guiding role, in order to which the second weight block 22 can successfully reach detection
Position where module 3.
In some instances, detection module 3 above-mentioned can be the photoelectric door being set in the first guide cylinder 4.When second
When weight block 22 drops to photoelectric door in the first guide cylinder 4, photoelectric door i.e. meeting trigger signal is simultaneously sent to computing module, by counting
It calculates module to calculate the relative altitude of aircraft at this time, structure is simple, and using reliable, cost is relatively low.
In some instances, detection module 3 above-mentioned can also be the laser door being set in the second guide cylinder 5, that is, swash
Optical sensor.When the second weight block 22 drops to photoelectric door in the second guide cylinder 5, laser door i.e. meeting trigger signal is simultaneously sent
To computing module, calculated by relative altitude of the computing module to aircraft at this time, structure is simple, using reliable, cost compared with
It is low.
In some instances, magnetic material or each second weight block 22 can be embedded in each second weight block 22
It can be magnetic material weight block, i.e., each second weight block 22 is made of magnetic material；At this point, detection module 3 can be with
For the magnetic induction sensor being set in the second guide cylinder 5.By being embedded in magnetic material in the second mass block, or by second
Weight block 22 is made of magnetic material, then be will test module 3 and is set as magnetic induction sensor, is realized when the second weight block
22 when dropping to the position of magnetic induction sensor in the second guide cylinder 5, and magnetic induction sensor can sense that magnetic signal is existed side by side
It triggers corresponding signal and is sent to computing module, calculated by relative altitude of the computing module to aircraft at this time, structure
Simply, using reliable, cost is relatively low.
It should be noted that due to being usually mostly signal transmission connection between all parts of aircraft interior, and it is magnetic
Material to a certain extent easily interferes signal accuracy or signal transmission etc., in order to avoid the generation of this phenomenon, recommends
Select photoelectric door or laser door as detection module 3.Furthermore, it would be desirable to explanation, when being embedded in magnetism in the second weight block 22
Material, the and when magnetic material is located at the center of the second weight block 22, the first preset value above-mentioned be flexible strand 2 total length,
The sum of the height of the height of first weight block 21 and multiple second weight blocks 22, then subtract 1/2 times of second weight block 22
The obtained value of height.
In some instances, referring to Fig. 1, the first weight block 21 and multiple second weight blocks 22 all can be sphere structure,
In order to the movement in the second guide cylinder 5 and the first guide cylinder 4 respectively of the first weight block 21 and the second weight block 22.Certainly,
First weight block 21 and the second weight block 22 can also be cylindrical structure, can specifically be decided according to the actual requirements.
The embodiment of the invention also provides a kind of aircraft, including fuselage and relative altitude measuring device above-mentioned；Wherein,
The pulley 1 and detection module 3 of relative altitude measuring device are respectively arranged in fuselage.
Aircraft provided in an embodiment of the present invention, including relative altitude measuring device, the relative altitude measuring device pass through
First weight block and multiple second weight blocks are hung on the both ends of pulley by flexible strand, and the weight of the first weight block is greater than multiple
The sum of the weight of second weight block, the length of flexible strand are the first preset value, between two neighboring second weight block center away from
From for the second preset value, meanwhile, the distance of pulley center to detection module is third preset value, is realized when aircraft is taking off
Or when landing, the first weight block and horizontal face contact can be made, since the weight of the first weight block is greater than multiple second weight blocks
The sum of, therefore, after the first weight block and horizontal face contact, each second weight block can be under the effect of gravity successively to moving down
It is dynamic, and the distance of its movement is consistent with the dropping distance of aircraft, when each second weight block successively arrives separately at detection module
When position, detection module can send corresponding signal to computing module respectively, allow computing module default according to first
Value, the second preset value, third preset value and pulley radius calculate the height of current pulley center with respect to the horizontal plane, also
It is the relative altitude of aircraft, measurement accuracy is higher, and structure and algorithm are relatively simple, and cost is relatively low.
In some instances, door body can be set on the fuselage of aircraft；When the door body is opened, the first weight block
21 can be exposed to fuselage by door body；When the door body is closed, the first weight block 21 can be located in fuselage by door body.It is logical
It crosses and door body is set on the fuselage of aircraft, so that the first weight block 21 can just expose fuselage when door body is opened, in order to
It realizes the measurement of aircraft relative altitude with horizontal face contact, and when being not necessarily to measure the height of aircraft, first
Weight block 21 can be placed in fuselage by door body, avoided it outside without exposed as the flight of aircraft and brought resistance,
To ensure that the normal flight of aircraft.
In some instances, door body above-mentioned can be rotatablely connected with fuselage by shaft, and may be used also in fuselage
Be provided with for drive door body carry out open the door or shutdown movement movement mechanism, and control the movement mechanism drive door body into
Row open the door or close the door control module, in order to the control module can according to control instruction control movement mechanism drive door body into
The movement that row opens the door or closes the door, so that the first weight block 21 exposes fuselage or is placed in fuselage interior.
In some instances, movement mechanism above-mentioned may include gas source and be connect by solenoid valve with the gas source
The piston rod of cylinder, the cylinder is connect with door body, and control module above-mentioned can be the flight control system of aircraft, and flies control system
System is electrically connected with the solenoid valve, and opening or closing for solenoid valve can be controlled according to control instruction by realizing flight control system, to control
The stretching of cylinder piston rod processed or retraction, and then realize the enabling or shutdown movement of door body.Wherein, control instruction can be set to
The button being electrically connected with flight control system is triggered and the implementation that provides, and easy to use, cost is relatively low.Alternatively, can also adopt
Realize that above-mentioned function, i.e. flight control system drive door according to control instruction control flaps horn with the steering engine being electrically connected with flight control system
The movement that body is opened the door or closed the door, structure is simple, realizes reliable.
In some instances, it can refer to Fig. 1, relative altitude measuring device can also include the be respectively arranged in fuselage
One guide cylinder 4 and the second guide cylinder 5, first guide cylinder 4 and second guide cylinder 5 extend along the both ends of flexible strand 2 respectively
Direction arrangement；One end of flexible strand 2 passes through the first guide cylinder 4 and connect with the first weight block 21, and the first weight block 21 can be first
Length direction in guide cylinder 4 along the first guide cylinder 4 is moved；The other end of flexible strand 2 bypasses pulley 1 and penetrates second and leads
To cylinder 5, multiple second weight blocks 22 are arranged successively by flexible strand 2 in the second guide cylinder 5, and can be along the second guide cylinder 5
Length direction is moved.
In some instances, which can be cylindrical, and its fuselage that can be vertically installed at aircraft
It is interior, and can be arranged along the length direction of 2 one end of flexible strand, so that the first weight block 21 passes through flexible strand 2 in first guiding
Movement in cylinder 4.By the setting of the first guide cylinder 4, the first guide cylinder 4 is provided for the movement of the first weight block 21 and is led
To effect, in order to the first weight block 21 can successfully with horizontal face contact.
In some instances, which can be cylindrical, and its fuselage that can be vertically installed at aircraft
It is interior, and can be arranged along the length direction of 2 other end of flexible strand, will pass through multiple second weight that flexible strand 2 mutually concatenates
Block 22 can movably be located in second guide cylinder 5.By the setting of the second guide cylinder 5, so that the second guide cylinder 5 can be with
Descending motion for each second weight block 22 provides guiding role, in order to which the second weight block 22 can successfully reach detection
Position where module 3.
In some instances, the computing module of relative altitude measuring device can be the flight control system of aircraft, to guarantee
The precision of measurement result.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features；
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (10)
1. a kind of relative altitude measuring device characterized by comprising
Pulley (1)；
First weight block (21) and multiple second weight blocks (22), the weight of first weight block (21) are greater than multiple described the
The sum of the weight of two weight blocks (22)；
Flexible strand (2), one end of the flexible strand (2) are connect with first weight block (21), and the other end bypasses the pulley
(1) multiple second weight blocks (22) are concatenated, the total length of the flexible strand (2), the height of first weight block and more
The sum of height of a second weight block is the first preset value, described soft between two neighboring second weight block (22)
Property rope length degree and the sum of the height of any second weight block be the second preset value；
Measuring unit, the measuring unit include detection module (3) and the computing module that is electrically connected with the detection module (3),
Vertical range between the detection module (3) and the pulley (1) center is third preset value；
Wherein, the detection module (3) is used in the first weight block (21) exposure level face, second weight block (22)
When being moved to its position under the effect of gravity, Xiang Suoshu computing module issues corresponding signal, and the computing module is for connecing
The signal is received, and according to first preset value, second preset value, the third preset value and the pulley (1)
Radius calculates height of pulley (1) center relative to the horizontal plane.
2. relative altitude measuring device according to claim 1, which is characterized in that further include:
First guide cylinder (4), extending direction of first guide cylinder (4) along the flexible strand (2) one end are arranged；
One end of the flexible strand (2) passes through first guide cylinder (4) and connect with first weight block (21), and described first
Weight block (21) can be moved in the interior length direction along first guide cylinder (4) of first guide cylinder (4).
3. relative altitude measuring device according to claim 1, which is characterized in that further include:
Second guide cylinder (5), second guide cylinder (5) are arranged along the extending direction of the flexible strand (2) other end；
The other end of the flexible strand (2) is around the pulley (1) and penetrates second guide cylinder (5), and multiple described second
Weight block (22) is arranged successively in second guide cylinder (5) by the flexible strand (2), and can be along second guide cylinder
(5) length direction is moved.
4. relative altitude measuring device according to claim 3, which is characterized in that
The detection module (3) is the photoelectric door being set in second guide cylinder (5).
5. relative altitude measuring device according to claim 3, which is characterized in that
The detection module (3) is the laser door being set in second guide cylinder (5).
6. relative altitude measuring device according to claim 3, which is characterized in that
Each second weight block (22) is embedded in magnetic material or each second weight block (22) is magnetic material
Weight block；
The detection module (3) is the magnetic induction sensor being set in second guide cylinder (5).
7. relative altitude measuring device according to claim 1, which is characterized in that
First weight block (21) and multiple second weight blocks (22) are sphere structure.
8. a kind of aircraft characterized by comprising
Fuselage and the relative altitude measuring device as described in any one of claims 1 to 7；
The pulley (1) and detection module (3) of the relative altitude measuring device are respectively arranged in the fuselage.
9. aircraft according to claim 8, which is characterized in that
Door body is provided on the fuselage；
When the door body is opened, first weight block (21) can be exposed to the fuselage by the door body；
When the door body is closed, first weight block (21) can be located in the fuselage by the door body.
10. relative altitude measuring device according to claim 8, which is characterized in that
The relative altitude measuring device further includes the first guide cylinder (4) and the second guide cylinder being respectively arranged in the fuselage
(4), first guide cylinder (4) and second guide cylinder (5) are respectively along the both ends extending direction cloth of the flexible strand (2)
It sets；
One end of the flexible strand (2) passes through first guide cylinder (4) and connect with first weight block (21), and described first
Weight block (21) can be moved in the interior length direction along first guide cylinder (4) of first guide cylinder (4)；
The other end of the flexible strand (2) is around the pulley (1) and penetrates second guide cylinder (5), and multiple described second
Weight block (22) is arranged successively in second guide cylinder (5) by the flexible strand (2), and can be along second guide cylinder
(5) length direction is moved.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811573020.2A CN109781063A (en) | 2018-12-21 | 2018-12-21 | Relative altitude measuring device and aircraft |
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| CN201811573020.2A CN109781063A (en) | 2018-12-21 | 2018-12-21 | Relative altitude measuring device and aircraft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112762909A (en) * | 2021-02-01 | 2021-05-07 | 安徽科技学院 | Portable mapping equipment |
| CN116202500A (en) * | 2023-05-06 | 2023-06-02 | 石家庄科林电力设计院有限公司 | Power transmission tower pile foundation design point location device and method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2369228Y (en) * | 1999-05-05 | 2000-03-15 | 王金泉 | Automatic powder level measuring meter |
| CN2579855Y (en) * | 2002-11-04 | 2003-10-15 | 周沛凝 | Signal obtaining mechanism for tracting construction lift fixed point stop positions |
| CN206375236U (en) * | 2016-12-19 | 2017-08-04 | 中国石油天然气股份有限公司 | Oil tank level display device |
| US20180356840A1 (en) * | 2016-02-29 | 2018-12-13 | Thinkware Corporation | Method and system for controlling unmanned air vehicle |
-
2018
- 2018-12-21 CN CN201811573020.2A patent/CN109781063A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2369228Y (en) * | 1999-05-05 | 2000-03-15 | 王金泉 | Automatic powder level measuring meter |
| CN2579855Y (en) * | 2002-11-04 | 2003-10-15 | 周沛凝 | Signal obtaining mechanism for tracting construction lift fixed point stop positions |
| US20180356840A1 (en) * | 2016-02-29 | 2018-12-13 | Thinkware Corporation | Method and system for controlling unmanned air vehicle |
| CN206375236U (en) * | 2016-12-19 | 2017-08-04 | 中国石油天然气股份有限公司 | Oil tank level display device |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112762909A (en) * | 2021-02-01 | 2021-05-07 | 安徽科技学院 | Portable mapping equipment |
| CN112762909B (en) * | 2021-02-01 | 2023-07-07 | 安徽科技学院 | Portable mapping equipment |
| CN116202500A (en) * | 2023-05-06 | 2023-06-02 | 石家庄科林电力设计院有限公司 | Power transmission tower pile foundation design point location device and method |
| CN116202500B (en) * | 2023-05-06 | 2023-07-21 | 石家庄科林电力设计院有限公司 | Power transmission tower pile foundation design point location device and method |
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Application publication date: 20190521 |